Unless otherwise noted all installation guidance, requirements, and instructions apply to one-display, two-display, and three-display G3X ...
G3X
Installation Manual
190-01115-01
July, 2013
Revision K
© Copyright 2013 Garmin Ltd. or its subsidiaries
All Rights Reserved
Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored in any storage medium, for any purpose without the express prior written consent of Garmin. Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revision hereto, provided that such electronic or printed copy of this manual or revision must contain the complete text of this copyright notice and provided further that any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited.
Revision
A B C D E
F
G H J K
Garmin International, Inc. 1200 E. 151st Street
Olathe, KS 66062 USA Telephone: 913-397-8200 Aviation Products Support Line (US Toll Free): (866) 739-5687
www.garmin.com
Garmin (Europe) Ltd Liberty House
Bulls Copse Road Hounsdown Business Park Southampton, SO40 9RB, UK Telephone: +44 (0) 8708501241
Revision Date
08/26/09 01/05/10 02/25/10 04/07/10 10/11/10
09/09/11
07/09/12 04/19/13 05/15/13 07/23/13
RECORD OF REVISIONS
Description
Initial Release Added Appdx C and made various changes/corrections Added Section 8 and Appendices G, H, and I Updated Section 7 and Appendices E, G, H, & I Added GSU 73 Datalogging info, various updates Added GTX 23, GTN 6XX/7XX, and airborne determination information Reorganized document and added various updates Added new LRUs and various updates Updated for current software, various updates Added angle of attack info, various updates
G3X Installation Manual Page A
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INFORMATION SUBJECT TO EXPORT CONTROL LAWS
This document may contain information which is subject to the Export Administration Regulations ("EAR") issued by the United States Department of Commerce (15 CFR, Chapter VII Subchapter C) and which may not be exported, released or disclosed to foreign nationals inside or outside the United States without first obtaining an export license. The preceding statement is required to be included on any and all reproductions in whole or in part of this manual.
CURRENT REVISION DESCRIPTION
Revision Page Number(s) Section Number
Description of Change
2-2
2.1.1
Updated G3X Interconnect Example Figure 2-1
2-9
2.4.1
Updated GSU 25 and GSU 73 info in Table 2-4
8-5
8.4.3
Added Figure 8-2 recommended minimum clearance
9-7
9.5.2.4
Added CWS/Disconnect note
15-115-52
15
Removed references to connector "P" plug throughout section
19-2619-36
19.4
Added AOA calibration info
C-7
K
C-8
Appdx C Appdx C
Made corrections to Figure C-2.2 Updated Figure C-2.3
D-4
Appdx D
Added Figure D-1.4 GDU 37X/GMC 305/GSA 28 Interconnect Drawing for GSU 73
E-5
Appdx E
Made corrections to Figure E-2.2
F-1F-3, F-6
Appdx F
Made updates and corrections to Figures F-1.1F-2.1, F-3.1
G-1G-5
Appdx G
Made updates to Figures G-1.1G-3.2
H-1H-5
Appdx H
Made updates to Figures H-1.1H-3.1
I-2
Appdx I
Corrected AOA info in Table I-1
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DEFINITIONS OF WARNINGS, CAUTIONS, AND NOTES
WARNING
Warnings are used to bring to the installer's immediate attention that not only damage to the equipment but personal injury may occur if the instruction is disregarded.
CAUTION
Cautions are used to alert the individual that damage to equipment may result if the procedural step is not followed to the letter.
NOTE
Notes are used to expand and explain the preceding step and provide further understanding of the reason for the particular operation.
WARNING
This product, its packaging, and its components contain chemicals known to the State of California to cause cancer, birth defects, or reproductive harm. This Notice is being provided in accordance with California's Proposition 65. If you have any questions or would like additional information, please refer to our web site at www.garmin.com/prop65.
NOTE
The Garmin G3X system includes non-TSO certified products that have received no FAA approval or endorsement. Consequently the G3X system is not type-certificated and is not suitable for installation in type-certificated aircraft.
NOTE
Unless otherwise noted all installation guidance, requirements, and instructions apply to one-display, two-display, and three-display G3X systems.
NOTE
References to the GDU 37X throughout this manual apply equally to the GDU 370 and GDU 375 except where specifically noted.
NOTE
The term LRU, as used throughout this manual is an abbreviation for Line Replaceable Unit. LRU is used generically in aviation for a product (such as a GDU 37X or GTP 59) that can be readily "swapped out" (usually as a single component) for troubleshooting/ repair.
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NOTE
All GMU 22 information in this Installation Manual also applies to the GMU 44. The GMU 44 had previously been used as the G3X magnetometer but has been replaced by the GMU 22.
NOTE
Connector references JXXX(X) and PXXX(X) are used throughout this document. The letter "J" or "P" designates the connector (whether on the LRU or wiring harness). "J" (Jack) refers to the connector on the LRU, and "P" (Plug) refers to the connector on the wiring harness. "J" or "P" designate the connector only, regardless of contact type (pin or socket).
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DOCUMENT PAGINATION
Section Number
Section Title
TOC Section 1 Section 2 Section 3 Section 4 Section 5 Section 6 Section 7 Section 8 Section 9 Section 10 Section 11 Section 12 Section 13 Section 14 Section 15 Section 16 Section 17 Section 18 Section 19 Section 20 Section 21 Appendix A Appendix B Appendix C Appendix D Appendix E Appendix F Appendix G Appendix H Appendix I
Table of Contents Inventory of Materials Installation Preparation GAD 29 Installation (Optional LRU) GAP 26 Installation (Optional LRU) GDU 37X Installation (Core G3X LRU) GEA 24 Installation (Optional LRU) GMC 305 Installation (Optional LRU) GMU 22 Installation (Core G3X LRU) GSA 28 Installation/Configuration (Optional LRU) GSU 25 Installation (Core G3X LRU) GSU 73 Installation (Core G3X LRU) GTP 59 Installation (CORE G3X LRU) GPS/XM Antenna Installation (Core G3X LRU) Engine/Airframe Sensor Installation (Optional) LRU Pinouts Connector Installation Instructions Configuration, Software, Databases, and XM Activation Engine/Airframe Sensor Configuration Post-Installation Checkout and Calibration Procedures Troubleshooting Return to Service Information Airframe Specific Installation Guidance Outline & Installation Drawings G3X w/GSU 25 and/or GAD 29 Interconnect Drawings G3X w/GSU 73 Interconnect Drawings Sensor Wiring Examples Lycoming/Continental Sensor Wiring Examples Rotax Sensor Wiring Examples Jabiru Sensor Wiring Examples RS-232 Text Output Format
Page Range
ixiv 1-11-10 2-12-10 3-13-4 4-14-4 5-15-6 6-16-4 7-17-4 8-18-6 9-19-74 10-110-8 11-111-8 12-112-4 13-113-30 14-114-22 15-115-52 16-116-16 17-117-32 18-118-20 19-119-30 20-120-10 21-121-2 A-1A-18 B-1B-26 C-1C-20 D-1D-14 E-1E-12 F-1F-8 G-1G-6 H-1H-6
I-1I-6
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GSU 73 HARDWARE MOD LEVEL HISTORY
The following table identifies hardware modification (Mod) Levels for the GSU 73 LRU. Mod Levels are listed with the associated service bulletin number, service bulletin date, and the purpose of the modification. The table is current at the time of publication of this manual (see date on front cover) and is subject to change without notice.
MOD LEVEL
1
2
SERVICE BULLETIN NUMBER
N/A
N/A
SERVICE BULLETIN
DATE N/A
N/A
PURPOSE OF MODIFICATION
Improved HSCM accuracy when using +28 V supply Improved backup capacitor circuit to increase backup time in certain under-voltage conditions
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Limited Warranty for G3X Products
Garmin G3X LRUs GAP 26, GDU 37X, GEA 24, GMC 305, GMU22, GMU 44, GSA 28, GSU 25, GSU 73, & GTP 59 are warranted to be free from defects in materials or workmanship for two years from the date of purchase. Within the applicable period, Garmin will, at its sole option, repair or replace any components that fail in normal use. Such repairs or replacement will be made at no charge to the customer for parts or labor, provided that the customer shall be responsible for any transportation cost. This warranty does not apply to: (i) cosmetic damage, such as scratches, nicks and dents; (ii) consumable parts, such as batteries, unless product damage has occurred due to a defect in materials or workmanship; (iii) damage caused by accident, abuse, misuse, water, flood, fire, or other acts of nature or external causes; (iv) damage caused by service performed by anyone who is not an authorized service provider of Garmin; or (v) damage to a product that has been modified or altered without the written permission of Garmin. In addition, Garmin reserves the right to refuse warranty claims against products or services that are obtained and/or used in contravention of the laws of any country.
THE WARRANTIES AND REMEDIES CONTAINED HEREIN ARE EXCLUSIVE AND IN LIEU OF ALL OTHER WARRANTIES, WHETHER EXPRESS, IMPLIED OR STATUTORY, INCLUDING ANY LIABILITY ARISING UNDER ANY WARRANTY OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE, STATUTORY OR OTHERWISE. THIS WARRANTY GIVES YOU SPECIFIC LEGAL RIGHTS, WHICH MAY VARY FROM STATE TO STATE.
IN NO EVENT SHALL GARMIN BE LIABLE FOR ANY INCIDENTAL, SPECIAL, INDIRECT OR CONSEQUENTIAL DAMAGES, WHETHER RESULTING FROM THE USE, MISUSE OR INABILITY TO USE THE PRODUCT OR FROM DEFECTS IN THE PRODUCT. SOME STATES DO NOT ALLOW THE EXCLUSION OF INCIDENTAL OR CONSEQUENTIAL DAMAGES, SO THE ABOVE LIMITATIONS MAY NOT APPLY TO YOU.
Garmin retains the exclusive right to repair or replace (with a new or newly-overhauled replacement product) the product or software or offer a full refund of the purchase price at its sole discretion. SUCH REMEDY SHALL BE YOUR SOLE AND EXCLUSIVE REMEDY FOR ANY BREACH OF WARRANTY.
Online Auction Purchases: Products purchased through online auctions are not eligible for warranty coverage. Online auction confirmations are not accepted for warranty verification. To obtain warranty service, an original or copy of the sales receipt from the original retailer is required. Garmin will not replace missing components from any package purchased through an online auction.
International Purchases: A separate warranty may be provided by international distributors for devices purchased outside the United States depending on the country. If applicable, this warranty is provided by the local in-country distributor and this distributor provides local service for your device. Distributor warranties are only valid in the area of intended distribution. Devices purchased in the United States or Canada must be returned to the Garmin service center in the United Kingdom, the United States, Canada, or Taiwan for service.
Garmin International, Inc. 1200 East 151st Street Olathe, Kansas 66062, U.S.A. Phone: 913/397.8200 FAX: 913/397.8282
Garmin (Europe) Ltd. Liberty House, Bulls Copse Road Hounsdown Business Park Southampton, SO40 9RB, U.K. Phone: +44/0870.851241 FAX: +44/0870.851251
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TABLE OF CONTENTS
PARAGRAPH
PAGE
Section 1 Inventory of Materials .....................................................................1-1
1.1 Unpacking Unit................................................................................................................ 1-1 1.2 Required Garmin Equipment ........................................................................................... 1-1 1.3 Optional Garmin LRUs.................................................................................................... 1-6 1.4 Required non-Garmin Equipment.................................................................................... 1-7 1.5 Optional Garmin Equipment (non-LRU)......................................................................... 1-9 1.6 Optional non-Garmin Equipment .................................................................................... 1-9 1.7 Optional 3rd Party Sensors/LRUs.................................................................................... 1-9 1.8 Garmin Software and Documents.................................................................................... 1-9
Section 2 Installation Preparation ..................................................................2-1
2.1 System Overview ............................................................................................................. 2-1 2.2 Electrical Considerations ................................................................................................. 2-3 2.3 Wiring/Cabling Considerations ....................................................................................... 2-4 2.4 Mechanical Considerations.............................................................................................. 2-8 2.5 LRU/Sensor Installation Information ............................................................................ 2-10
Section 3 GAD 29 Installation (Optional LRU) .............................................3-1
3.1 Equipment Description .................................................................................................... 3-1 3.2 Equipment Available ....................................................................................................... 3-2 3.3 General Specifications ..................................................................................................... 3-2 3.4 Unit Installation ............................................................................................................... 3-3 3.5 Mounting Requirements .................................................................................................. 3-3 3.6 Environmental Specifications .......................................................................................... 3-3 3.7 Continued Airworthiness ................................................................................................. 3-3
Section 4 GAP 26 Installation (Optional LRU) .............................................4-1
4.1 Equipment Description .................................................................................................... 4-1 4.2 Equipment Available ....................................................................................................... 4-2 4.3 Required Equipment ........................................................................................................ 4-2 4.4 General Specifications ..................................................................................................... 4-2 4.5 Unit Installation ............................................................................................................... 4-2 4.6 Environmental Specifications .......................................................................................... 4-4 4.7 Continued Airworthiness ................................................................................................. 4-4
Section 5 GDU 37X Installation (Core G3X LRU)........................................5-1
5.1 Equipment Description .................................................................................................... 5-1 5.2 General Specifications ..................................................................................................... 5-2 5.3 Installation Information ................................................................................................... 5-2 5.4 Unit Installation ............................................................................................................... 5-4
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5.5 Mounting Requirements .................................................................................................. 5-4 5.6 GPS Specifications .......................................................................................................... 5-6 5.7 Environmental Specifications .......................................................................................... 5-6 5.8 Antennas .......................................................................................................................... 5-6 5.9 Continued Airworthiness ................................................................................................. 5-6
Section 6 GEA 24 Installation (Optional LRU) .............................................6-1
6.1 Equipment Description .................................................................................................... 6-1 6.2 Equipment Available ....................................................................................................... 6-2 6.3 General Specifications ..................................................................................................... 6-3 6.4 Unit Installation ............................................................................................................... 6-3 6.5 Mounting Requirements .................................................................................................. 6-3 6.6 Environmental Specifications .......................................................................................... 6-3 6.7 Continued Airworthiness ................................................................................................. 6-3
Section 7 GMC 305 Installation (Optional LRU) ..........................................7-1
7.1 Equipment Description .................................................................................................... 7-1 7.2 Equipment Available ....................................................................................................... 7-1 7.3 General Specifications ..................................................................................................... 7-2 7.4 Mounting and Wiring Requirements ............................................................................... 7-2 7.5 Environmental Specifications ......................................................................................... 7-4 7.6 Continued Airworthiness ................................................................................................. 7-4
Section 8 GMU 22 Installation (Core G3X LRU)..........................................8-1
8.1 Equipment Description .................................................................................................... 8-1 8.2 General Specifications ..................................................................................................... 8-1 8.3 Equipment Available ....................................................................................................... 8-2 8.4 Unit Installation ............................................................................................................... 8-2 8.5 Environmental Specifications .......................................................................................... 8-6
Section 9 GSA 28 Installation/Configuration (Optional LRU) ....................9-1
9.1 Equipment Description .................................................................................................... 9-1 9.2 Equipment Available ....................................................................................................... 9-2 9.3 General Specifications .................................................................................................... 9-2 9.4 Required Equipment ........................................................................................................ 9-3 9.5 Unit Installation ............................................................................................................... 9-4 9.6 Unit Wiring .................................................................................................................... 9-13 9.7 Environmental Specifications ........................................................................................ 9-13 9.8 Maintenance................................................................................................................... 9-13 9.9 Outline and Installation Drawings ................................................................................. 9-13 9.10 Post Installation Checkout ........................................................................................... 9-37 9.11 General Autopilot Description (for configuration) ...................................................... 9-38 9.12 Step by Step On-Ground Setup.................................................................................... 9-40 9.13 Autopilot Setup ............................................................................................................ 9-48
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9.14 Yaw Damper Setup ...................................................................................................... 9-53 9.15 Step By Step In-Air Autopilot Setup ........................................................................... 9-55 9.16 Step by Step Trim System Setup ................................................................................. 9-61 9.17 Detailed Autopilot Configuration Options .................................................................. 9-64
Section 10 GSU 25 Installation (Core G3X LRU) .........................................10-1
10.1 Equipment Description ................................................................................................ 10-1 10.2 General Specifications ................................................................................................ 10-2 10.3 Required Equipment .................................................................................................... 10-2 10.4 Unit Installation ........................................................................................................... 10-3 10.5 Environmental Specifications ...................................................................................... 10-6 10.6 Features Summary ....................................................................................................... 10-6 10.7 Performance Information ............................................................................................. 10-7 10.8 Maintenance................................................................................................................. 10-7
Section 11 GSU 73 Installation (Core G3X LRU) .........................................11-1
11.1 Equipment Description ................................................................................................ 11-1 11.2 General Specifications ................................................................................................ 11-1 11.3 Required Equipment .................................................................................................... 11-2 11.4 Unit Installation ........................................................................................................... 11-3 11.5 Environmental Specifications ...................................................................................... 11-6 11.6 Features Summary ....................................................................................................... 11-7 11.7 Performance Information ............................................................................................. 11-7 11.8 Maintenance................................................................................................................. 11-8
Section 12 GTP 59 Installation (CORE G3X LRU) ......................................12-1
12.1 Equipment Description ................................................................................................ 12-1 12.2 General Specifications ................................................................................................. 12-2 12.3 Unit Installation ........................................................................................................... 12-2 12.4 TSO/ETSO Compliance .............................................................................................. 12-4 12.5 Maintenance................................................................................................................. 12-4
Section 13 GPS/XM Antenna Installation (Core G3X LRU) .......................13-1
13.1 Non-Garmin Antennas ................................................................................................. 13-1 13.2 Garmin Antennas ......................................................................................................... 13-2 13.3 Antenna Mounting Considerations .............................................................................. 13-3 13.4 Teardrop Footprint Antenna Installation (GA 55 and GA 56) .................................... 13-8 13.5 ARINC 743 Footprint Antenna Installation (GA 55A, GA 57X).............................. 13-15 13.6 Non-Structural Mount Installation............................................................................. 13-24
Section 14 Engine/Airframe Sensor Installation (Optional).........................14-1
14.1 Engine/Airframe Sensor Options................................................................................. 14-1 14.2 Garmin G3X Sensor Kits ............................................................................................. 14-4 14.3 Engine Sensor Installation ........................................................................................... 14-5
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Section 15 LRU Pinouts ...................................................................................15-1
15.1 GAD 29........................................................................................................................ 15-1 15.2 GDU 37X ..................................................................................................................... 15-5 15.3 GEA 24 ...................................................................................................................... 15-10 15.4 GMC 305 ................................................................................................................... 15-24 15.5 GMU 22 ..................................................................................................................... 15-26 15.6 GSA 28 ...................................................................................................................... 15-27 15.7 GSU 25 ...................................................................................................................... 15-30 15.8 GSU 73 ...................................................................................................................... 15-34 15.9 GTX 23 ...................................................................................................................... 15-47 15.10 Discrete Functions ................................................................................................... 15-49 15.11 Serial Data Electrical Characteristics ...................................................................... 15-50 15.12 RS-232 Input/Output, Software Update Connections.............................................. 15-51
Section 16 Connector Installation Instructions .............................................16-1
16.1 Thermocouple Installation into a Backshell ................................................................ 16-1 16.2 Jackscrew Configuration Module Installation into a Jackscrew Backshell ................. 16-3 16.3 Jackscrew Backshell Installation Instructions ............................................................. 16-6
Section 17 Configuration, Software, Databases, and XM Activation ........17-1
17.1 Configuration Mode..................................................................................................... 17-1 17.2 Software Loading Procedure ....................................................................................... 17-1 17.3 Configuration Pages..................................................................................................... 17-4 17.4 Garmin Database Updates ......................................................................................... 17-28 17.5 XM Activation Instructions (GDU 375 only)............................................................ 17-32 17.6 GDU Splash Screen .................................................................................................. 17-32 17.7 Checklist Editor ......................................................................................................... 17-32
Section 18 Engine/Airframe Sensor Configuration.......................................18-1
18.1 Engine/Airframe Sensors ............................................................................................. 18-1 18.2 Engine Sensor Installation ........................................................................................... 18-1 18.3 Engine/Airframe Input Configuration ......................................................................... 18-2
Section 19 Post-Installation Checkout and Calibration Procedures ...........19-1
19.1 Recommended Test Equipment ................................................................................... 19-2 19.2 GDU 37X Test Procedure............................................................................................ 19-2 19.3 GSU 25/GSU 73/GMU 22 Post-Installation Calibration Procedures .......................... 19-5 19.4 AOA (Angle of Attack) Calibration (Performed In-flight)........................................ 19-26 19.5 External Interface Configuration (Garmin units only) .............................................. 19-37
Section 20 Troubleshooting ............................................................................20-1
20.1 General Troubleshooting ............................................................................................. 20-1 20.2 GDU 37X ..................................................................................................................... 20-2 20.3 Air Data Troubleshooting ............................................................................................ 20-3
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20.4 Engine Indication Troubleshooting ............................................................................. 20-4 20.5 AHRS Troubleshooting ............................................................................................... 20-5 20.6 Post Installation Calibration Procedures ..................................................................... 20-7 20.7 GSU 73 Data Logging ................................................................................................. 20-8
Section 21 Return to Service Information......................................................21-1
21.1 GDU 37X ..................................................................................................................... 21-1 21.2 GSU 73 ........................................................................................................................ 21-1 21.3 GSU 25 ........................................................................................................................ 21-2 21.4 GMU 22 ....................................................................................................................... 21-2 21.5 GEA 24 ........................................................................................................................ 21-2 21.6 GSA 28 ........................................................................................................................ 21-2 21.7 GAD 29........................................................................................................................ 21-2 21.8 GMC 305 ..................................................................................................................... 21-2
Appendix A Airframe Specific Installation Guidance ...................................A-1
A.1 Introduction.................................................................................................................... A-1 A.2 Van's Aircraft ................................................................................................................ A-2 A.3 Lancair Aircraft.............................................................................................................. A-4
Appendix B Outline & Installation Drawings.................................................B-1
Figure B-1.1 GA 55/55A Installation Drawing ..................................................................B-1 Figure B-1.2 GA 56 Installation Drawing ..........................................................................B-2 Figure B-1.3 GA 57X Installation Drawing .......................................................................B-3 Figure B-2.1 GAD 29 Outline Drawing .............................................................................B-4 Figure B-2.2 GAD 29 Installation Drawing (no CAN terminator).....................................B-5 Figure B-2.3 GAD 29 Installation Drawing (with CAN terminator) .................................B-6 Figure B-3.1 GAP 26 Outline Drawing ..............................................................................B-7 Figure B-4.1 GDU 37X Outline Drawing ..........................................................................B-8 Figure B-4.2 GDU 37X Outline Drawing ..........................................................................B-9 Figure B-5.1 GEA 24 Outline Drawing............................................................................B-10 Figure B-5.2 GEA 24 Assembly Drawing (no CAN terminator) .....................................B-11 Figure B-5.3 GEA 24 Assembly Drawing (with CAN terminator) ..................................B-12 Figure B-6.1 GMC 305 Outline Drawing .........................................................................B-13 Figure B-6.2 GMC 305 Installation Drawing...................................................................B-14 Figure B-6.3 GMC 305 Cutout Drawing (Not to Scale)...................................................B-15 Figure B-7.1 GMU 22 Mounting Rack.............................................................................B-16 Figure B-7.2 GMU 22 Top Mounted Installation.............................................................B-17 Figure B-7.3 GMU 22 Bottom Mounted Installation .......................................................B-18 Figure B-7.4 GMU 22 Wiring Details ..............................................................................B-19 Figure B-8.1 GSU 25 Outline Drawing ............................................................................B-20 Figure B-8.2 GSU 25 Installation Drawing ......................................................................B-21 Figure B-8.3 GSU 25 Orientation Drawings (page 1 of 2)...............................................B-22 Figure B-8.4 GSU 25 Orientation Drawings (page 2 of 2)...............................................B-23 Figure B-9.1 GSU 73 Outline Drawing ............................................................................B-24
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Figure B-9.2 GSU 73 Orientation Drawings ....................................................................B-25 Figure B-10.1 GTP 59 O.A. T. Probe Installation Drawing .............................................B-26
Appendix C G3X w/GSU 25 and/or GAD 29 Interconnect Drawings ..........C-1
C.1 Core Interconnect Drawings w/GSU 25 and/or GAD 29................................................C-1 Figure C-1.1 Core Interconnect Notes and 2 Display CAN Bus Interconnect Drawing ....C-1 Figure C-1.2 GDU 37X/GMU 22/GSU 25 Interconnect Drawing .....................................C-2 Figure C-1.3 Power, Backup Power, and Antennas Interconnect Drawing........................C-3 Figure C-1.4 GMU 22/GSU 25/GTP 59 Interconnect Drawing.........................................C-4 Figure C-1.5 GMC 305/GSA 28 Interconnect Drawing.....................................................C-5 Figure C-1.6 GSA 28 - Trim Switch Interconnect Drawing...............................................C-6
C.2 External Interconnect Drawings w/GSU 25....................................................................C-7 Figure C-2.1 External Interconnect Drawing Notes ...........................................................C-7 Figure C-2.2 GDU 37X - External LRU Interconnect Examples.......................................C-8 Figure C-2.3 GSU 25 - GTX 23ES Transponder Interconnect/Configuration Example....C-9 Figure C-2.4 GSU 25 - Transponder Interconnect/Configuration Example.....................C-10 Figure C-2.5 GTN 6XX/7XX Transponder Interconnect/Configuration Example ..........C-11 Figure C-2.6 Single GNS 430(W)/530(W) Interconnect/Configuration Example ...........C-12 Figure C-2.7 Dual GNS 430(W)/530(W) Interconnect/Configuration Example..............C-13 Figure C-2.8 Single GTN 6XX/7XX Interconnect/Configuration Example ....................C-14 Figure C-2.9 Dual GTN 6XX/7XX Interconnect/Configuration Example.......................C-15 Figure C-2.10 GNS 480 Interconnect/Configuration Example ........................................C-16 Figure C-2.11 Non-Garmin Auto Pilot Interconnect/Configuration Example .................C-17 Figure C-2.12 Non-Garmin Auto Pilot Interconnect/Configuration Example w/GMC 305 ......................................................................................................................C-18 Figure C-2.13 GTS 8XX Interconnect/Configuration Example .......................................C-19 Figure C-2.14 GDL 39/GDL 39R Interconnect/Configuration Example .........................C-20
Appendix D G3X w/GSU 73 Interconnect Drawings .....................................D-1
D.1 Core Interconnect Drawings .......................................................................................... D-1 Figure D-1.1 Core (w/GSU 73) Interconnect Notes and 2 Display CAN Bus Interconnect ...
DrawingD-1 Figure D-1.2 GDU 37X/GMU 22/GSU 73 Interconnect Drawing.................................... D-2 Figure D-1.3 Power, Backup Power, and Antennas Interconnect Drawing w/GSU 73 .... D-3 Figure D-1.4 GMC 305/GSA 28 Interconnect Drawing w/GSU 73.................................. D-4
D.2 External Interconnect Drawings w/GSU 73 .................................................................. D-5 Figure D-2.1 External Interconnect w/GSU 73 Drawing Notes ........................................ D-5 Figure D-2.2 G3X w/GSU 73 - Transponders Interconnect/Configuration Example ....... D-6 Figure D-2.3 GTN 6XX/7XX - Transponder Interconnect/Configuration Example w/GSU 73 .......................................................................................................................... D-7 Figure D-2.4 Single GNS 430(W)/530(W) Interconnect/Configuration Example w/GSU 73 .......................................................................................................................... D-8 Figure D-2.5 Dual GNS 430(W)/530(W) Interconnect/Configuration Example w/GSU 73 .......................................................................................................................... D-9 Figure D-2.6 Single GTN 6XX/7XX Interconnect/Configuration Example w/GSU 73 . D-10
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Figure D-2.7 Dual GTN 6XX/7XX Interconnect/Configuration Example w/GSU 73 ... D-11 Figure D-2.8 GNS 480 Interconnect/Configuration Example w/GSU 73 ....................... D-12 Figure D-2.9 Non-Garmin Auto Pilot Interconnect/Configuration Example w/GSU 73 D-13 Figure D-2.10 G3X w/GSU 73 - GTS 8XX Interconnect/Configuration Example......... D-14
Appendix E Sensor Wiring Examples .............................................................E-1
Figure E-1.1 Notes for Sensor Wiring Example Drawings (for all Appdx E drawings) ....E-1 E.1 Sensor Wiring Examples w/GEA 24...............................................................................E-2
Figure E-2.1 Page 1 of 2 Fuel Quantity and Fuel Flow Examples (w/GEA 24) ................E-2 Figure E-2.1 Page 2 of 2 Fuel Quantity and Fuel Flow Examples (w/GEA 24) ................E-3 Figure E-2.2 Page 1 of 2 Electrical and Discrete Input/Output Examples (w/GEA 24) ....E-4 Figure E-2.2 Page 2 of 2 Electrical and Discrete Input/Output Examples (w/GEA 24) ....E-5 Figure E-2.3 Flaps/Trim and UMA Pressure Transducer Examples (w/GEA 24) .............E-6 E.2 Sensor Wiring Examples w/GSU 73 ...............................................................................E-7 Figure E-3.1 Page 1 of 2 Fuel Quantity and Fuel Flow Examples (w/GSU 73) ................E-7 Figure E-3.1 Page 2 of 2 Fuel Quantity and Fuel Flow Examples (w/GSU 73) ................E-8 Figure E-3.2 Page 1 of 2 Electrical and Discrete Input/Output Examples (w/GSU 73).....E-9 Figure E-3.2 Page 2 of 2 Electrical and Discrete Input/Output Examples (w/GSU 73)...E-10 Figure E-3.3 Flaps/Trim and UMA Pressure Transducer Examples (w/GSU 73) ...........E-11
Appendix F Lycoming/Continental Sensor Wiring Examples...................... F-1
Figure F-1.1 Notes for Lycoming/Continental Sensor Drawings (for all Appdx F drawings) ................................................................................................. F-1 F.1 GEA 24 - Lycoming/Continental Sensor Drawings ........................................................ F-2 Figure F-2.1 GEA 24 - 4/6 Cylinder Lycoming/Continental Sensor Wiring Examples, Page 1 of 3 .......................................................................................................................... F-2 Figure F-2.1 GEA 24 - 4/6 Cylinder Lycoming/Continental Sensor Wiring Examples, Page 2 of 3 .......................................................................................................................... F-3 Figure F-2.1 GEA 24 - 4/6 Cylinder Lycoming/Continental Sensor Wiring Examples, Page 3 of 3 .......................................................................................................................... F-4 F.2 GSU 73 - Lycoming/Continental Sensor Drawings ........................................................ F-5 Figure F-3.1 GSU 73 - 4/6 Cylinder Lycoming/Continental Sensor Wiring Examples, Page 1 of 3 .......................................................................................................................... F-5 Figure F-3.1 GSU 73 - 4/6 Cylinder Lycoming/Continental Sensor Wiring Examples, Page 2 of 3 .......................................................................................................................... F-6 Figure F-3.1 GSU 73 - 4/6 Cylinder Lycoming/Continental Sensor Wiring Examples, Page 3 of 3 .......................................................................................................................... F-7
Appendix G Rotax Sensor Wiring Examples ................................................. G-1
Figure G-1.1 Notes for Rotax 912/914 Sensor Drawings (for all Appdx G drawings) ..... G-1 G.1 GEA 24 - Rotax Sensor Drawings ................................................................................. G-2
Figure G-2.1 GEA 24 - Rotax 912/914 Sensor Wiring Examples, Page 1 of 2 ................ G-2 Figure G-2.2 GEA 24 - Rotax 912/914 Sensor Wiring Examples, Page 2 of 2 ................ G-3 G.2 GSU 73 - Rotax Sensor Drawings ................................................................................. G-4 Figure G-3.1 GSU 73 - Rotax 912/914 Sensor Wiring Examples, Page 1 of 2................. G-4
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Figure G-3.2 GSU 73 - Rotax 912/914 Sensor Wiring Examples, Page 2 of 2................. G-5
Appendix H Jabiru Sensor Wiring Examples ................................................ H-1
Figure H-1.1 Notes for Jabiru Sensor Drawings (for all Appdx H drawings)................... H-1 H.1 GEA 24 - Jabiru Sensor Drawings................................................................................. H-2
Figure H-2.1 GEA 24 - Jabiru Sensor Wiring Examples, Page 1 of 2 .............................. H-2 Figure H-2.1 GEA 24 - Jabiru Sensor Wiring Examples, Page 2 of 2 .............................. H-3 H.2 GSU 73 - Jabiru Sensor Drawings ................................................................................. H-4 Figure H-3.1 GSU 73 - Jabiru Sensor Wiring Examples, Page 1 of 2............................... H-4 Figure H-3.1 GSU 73 - Jabiru Sensor Wiring Examples, Page 2 of 2............................... H-5
Appendix I RS-232 Text Output Format ........................................................ I-1
I.1 Electrical Interface............................................................................................................. I-1 I.2 Message Output Selection ................................................................................................. I-1 I.3 General Message Output Format....................................................................................... I-1 I.4 Attitude/Air Data Message Format ................................................................................... I-2 I.5 Engine Data Message Format............................................................................................ I-3 I.6 GPS Data Message Format................................................................................................ I-5
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1 INVENTORY OF MATERIALS
This manual provides all of the mechanical and electrical information required for the installation of the G3X system. This manual is intended to be a step-by-step guide to the installation, therefore it is important that the steps in all sections be performed in order. All materials that are required/optional for the installation of the G3X are listed in this section (as such, some of the information in this section is repeated in following sections).
Before beginning the G3X installation, it is recommended that the installer perform a complete inventory of all materials listed in this section (some materials are optional and may not be applicable to the installation). Section 1 should be used to verify that all components ordered from Garmin have been delivered correctly, and to identify any required materials that are not provided by Garmin.
1.1 Unpacking Unit
Carefully unpack the equipment and make a visual inspection of all contents for evidence of damage incurred during shipment. If any component of the G3X is damaged, notify the carrier and file a claim. To justify a claim, save the original shipping container and all packing materials. Do not return any equipment to Garmin until the carrier has authorized the claim.
Retain the original shipping containers for storage. If the original containers are not available, a separate cardboard container should be prepared that is large enough to accommodate sufficient packing material to prevent movement.
1.2 Required Garmin Equipment
1.2.1 Garmin LRU (Line Replaceable Unit) List
Table 1-1 through Table 1-8 list the available core G3X LRUs. The G3X LRU Kit (Table 1-1) is for G3X installations using the GSU 73, the kits in Table 1-2 through Table 1-8 are for G3X installations using the GSU 25. Each GDU 37X (010-00667-XX) comes with all equipment needed for installation (Table 1-9).
Table 1-1 Contents of G3X w/GSU 73 LRU Kit (K10-00016-00)
LRU
GMU 44 Magnetometer, Unit Only GSU 73 ADAHRS/EIS, Unit Only GTP 59 OAT Probe Kit
Assembly Part Number
010-01196-00
010-00691-00
011-00978-00
Quantity
1 1 1
Unit Only Part Number
011-03269-00
011-01817-00
011-00978-00
Table 1-2 Contents of GDU 370 Single Display Kit, no EIS (K10-00016-05)
LRU
GDU 370 Display, Unit Only GMU 22 Magnetometer, Unit Only GSU 25 ADAHRS, Unit Only GTP 59 OAT Probe Kit Config Module w/Sockets, Jackscrew (for PFD1)
Assembly Part Number
010-00667-15 010-01196-00 010-01071-00 011-00978-00 011-00979-22
Quantity
1 1 1 1 1
Unit Only Part Number
011-01747-15 011-03269-00 011-02929-00 011-00978-00 011-00979-22
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G3X Installation Manual - Inventory of Materials Page 1-1
Table 1-3 Contents of GDU 370 Single Display Kit w/EIS (K10-00016-10)
LRU
GDU 370 Display, Unit Only GEA 24 EIS, Unit Only GMU 22 Magnetometer, Unit Only GSU 25 ADAHRS, Unit Only GTP 59 OAT Probe Kit Config Module w/Sockets, Jackscrew (for PFD1)
Assembly Part Number
010-00667-15 010-01042-00 010-01196-00 010-01071-00 011-00978-00 011-00979-22
Quantity
1 1 1 1 1 1
Unit Only Part Number
011-01747-15 011-02848-00 011-03269-00 011-02929-00 011-00978-00 011-00979-22
Table 1-4 Contents of GDU 370 Dual Display Kit (K10-00016-20)
LRU
GDU 370 Display, Unit Only GEA 24 EIS, Unit Only GMU 22 Magnetometer, Unit Only GSU 25 ADAHRS, Unit Only GTP 59 OAT Probe Kit Config Module w/Sockets, Jackscrew (for PFD1)
Assembly Part Number
010-00667-15 010-01042-00 010-01196-00 010-01071-00 011-00978-00 011-00979-22
Quantity
2 1 1 1 1 1
Unit Only Part Number
011-01747-15 011-02848-00 011-03269-00 011-02929-00 011-00978-00 011-00979-22
Table 1-5 Contents of GDU 370 Triple Display Kit (K10-00016-30)
LRU
GDU 370 Display, Unit Only GEA 24 EIS, Unit Only GMU 22 Magnetometer, Unit Only GSU 25 ADAHRS, Unit Only GTP 59 OAT Probe Kit Config Module w/Sockets, Jackscrew (for PFD1)
Assembly Part Number
010-00667-15 010-01042-00 010-01196-00 010-01071-00 011-00978-00 011-00979-22
Quantity
3 1 1 1 1 1
Unit Only Part Number
011-01747-15 011-02848-00 011-03269-00 011-02929-00 011-00978-00 011-00979-22
G3X Installation Manual - Inventory of Materials Page 1-2
190-01115-01 Rev. K
Table 1-6 Contents of GDU 375 w/XM Single Display Kit (K10-00016-15)
LRU
GDU 375 Display, Unit Only GEA 24 EIS, Unit Only GMU 22 Magnetometer, Unit Only GSU 25 ADAHRS, Unit Only GTP 59 OAT Probe Kit Config Module w/Sockets, Jackscrew (for PFD1)
Assembly Part Number
010-00667-25 010-01042-00 010-01196-00 010-01071-00 011-00978-00 011-00979-22
Quantity
1 1 1 1 1 1
Unit Only Part Number
011-01747-30 011-02848-00 011-03269-00 011-02929-00 011-00978-00 011-00979-22
Table 1-7 Contents of GDU 370/375 w/XM Dual Display Kit (K10-00016-25)
LRU
GDU 370 Display, Unit Only GDU 375 Display, Unit Only GEA 24 EIS, Unit Only GMU 22 Magnetometer, Unit Only GSU 25 ADAHRS, Unit Only GTP 59 OAT Probe Kit Config Module w/Sockets, Jackscrew (for PFD1)
Assembly Part Number
010-00667-15 010-00667-25 010-01042-00 010-01196-00 010-01071-00 011-00978-00 011-00979-22
Quantity
1 1 1 1 1 1 1
Unit Only Part Number
011-01747-15 011-01747-30 011-02848-00 011-03269-00 011-02929-00 011-00978-00 011-00979-22
Table 1-8 Contents of GDU 370/370/375 w/XM Triple Display Kit (K10-00016-35)
LRU
GDU 370 Display, Unit Only GDU 375 Display, Unit Only GEA 24 EIS, Unit Only GMU 22 Magnetometer, Unit Only GSU 25 ADAHRS, Unit Only GTP 59 OAT Probe Kit Config Module w/Sockets, Jackscrew (for PFD1)
Assembly Part Number
010-00667-15 010-00667-25 010-01042-00 010-01196-00 010-01071-00 011-00978-00 011-00979-22
Quantity
2 1 1 1 1 1 1
Unit Only Part Number
011-01747-15 011-01747-30 011-02848-00 011-03269-00 011-02929-00 011-00978-00 011-00979-22
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G3X Installation Manual - Inventory of Materials Page 1-3
Each GDU 37X Assembly (010-00667-XX) listed in Table 1-2 through Table 1-8 includes the GDU and
the items listed in Table 1-9.
Table 1-9 Contents of GDU 37X Assembly (010-00667-XX)
Item GDU 37X GDU 37X Connector Kit GDU 37X Nutplate SD Card, Dummy Important Safety and Product Information GDU 37X Quick Reference Guide Jeppesen Free Single Update
Part Number 011-01747-XX 011-01921-00 115-01054-00 145-00561-00 190-00720-50 190-01055-00 190-10003-03
Quantity 1 1 1 1 1 1 1
1.2.2 Garmin LRU Installation Kits
The G3X w/GSU 73 Installation Kit contains the items listed in Table 1-10 which are required for the installation of the G3X.
NOTE
The GDU 37X is not included in either the G3X w/GSU 73 Installation Kit (K10-00017-00) or the G3X w/GSU 73 LRU Kit (K10-00016-00).
NOTE
Each item listed in Table 1-10 contains its own parts list to verify that all parts are included.
Table 1-10 Contents of G3X w/GSU 73 Installation Kit (K10-00017-00)
Item
GMU 22, Connector Kit Config Module w/EEPROM, Jackscrew (for GSU) Config Module w/Sockets, Jackscrew (for PFD1) Thermocouple Kit GSU 73, Connector Kit, P9731 GSU 73, Connector Kit, P9732 G3X, Supplemental Parts GMU 22, Install Rack, Modified
Part Number
011-00871-00 011-00979-20 011-00979-22 011-00981-00 011-01818-00 011-01818-01 011-02347-00 115-00481-10
Quantity
1 1 1 1 1 1 1 1
G3X Installation Manual - Inventory of Materials Page 1-4
190-01115-01 Rev. K
Table 1-11 LRU Installation Kits
LRU
Installation Kit Part Number
GAD 29 ARINC 429 Adapter GAP 26 Air Data Probe GDU 37X Display GEA 24 EIS GMC 305 Mode Controller GMU 22 Magnetometer GSA 28 Servo Actuator GSU 25 ADAHRS GSU 73 ADAHRS/EIS GTP 59 Temperature Probe Garmin GPS and/or XM Antennas
011-03271-00 (Table 3-3) N/A
011-01921-00 (Table 1-9) 011-02886-00 (Table 6-3) 010-01234-00 (Table 7-2) 011-00871-10, Conn Kit (Table 8-3) 011-02950-00, Conn Kit (Table 9-7) K10-00181-00, Conn Kit (Table 10-2 ) K10-00017-00 (Table 1-10) 011-00978-00 (Table 12-2)
NA
Installation Kit Included with LRU?
N N Y N N N N N Y Y N
1.2.3 GPS/XM Antenna(s)
A Garmin or non-Garmin GPS antenna is required for a G3X installation. A Garmin or non-Garmin XM antenna is required for G3X installations using XM weather. See Section 13 for required materials for antenna installation including mounting brackets, doubler plates, rivets, hardware, cables, connectors, and sealant.
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1.3 Optional Garmin LRUs
Table 1-12 lists optional Garmin LRUs that can be installed with the G3X system. If any of these LRUs are to be used in this installation, verify that all required installation materials such as connector kits have been acquired. Installation information for LRUs not documented in this manual can be found in the Installation Manual for each respective LRU.
Table 1-12 Optional Garmin LRUs
LRU
All Install Info Included In This Manual?
GAD 29 ARINC 429 Adapter
Yes
GAP 26 Air Data Probe
Yes
GDL 39/GDL 39R Data Link
No
GDU 37X Display (if installing more than one)
Yes
GEA 24 EIS
Yes
GMC 305 Mode Controller
Yes
GNS 400/500 Series Units
No
GNS 480 GPS/Comm Navigator
No
GSA 28 Servo Actuator
Yes
GSU 25* ADAHRS
Yes
GSU 73* ADAHRS/EIS
Yes
GTN 600/700 Series Units
No
GTX 23/327/330 Transponder
No
SL30 Nav/Comm Transceiver
No
SL40 Comm Transceiver
No
*One GSU 25 and/or GSU 73 is required
Section
Section 3 Section 4
NA
Section 5
Section 6 Section 7
NA NA Section 9 Section 10 Section 11 NA NA NA NA
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1.4 Required non-Garmin Equipment
1.4.1 Wiring/Cabling Considerations The installer will provide all wiring and cabling unless otherwise noted. Use MIL-W-22759/16 (or other approved wire) AWG #22 or larger wire for all connections unless otherwise specified. The supplied standard pin contacts are compatible with up to AWG #22 wire. RG400 or RG142 coaxial cable with 50 nominal impedance and meeting applicable aviation regulations should be used for the installation.
1.4.2 Contact and Crimp Tools Table 1-13 lists recommended crimp tools used to build the wiring harnesses for the G3X LRUs, other equivalent tooling may also be used.
Table 1-13 Pin Contact and Crimp Tools Part Numbers
LRU
Contact Type
GDU 37X
GMC 305 GSU 73 GTP 59 011-00979-20 (Config module w/ EEPROM kit) 011-00981-00 (thermocouple
kit)
Socket, Size 20 Pin, Size 22D
GMU 22
Socket, Size 20
011-00979-22 (Config
module w/ Sockets & Jackscrew kit) GAD 29 GEA 24 (J241, J243,
J244) GSA 28 GSU 25 GAD 29 GEA 24 (J242 only)
Socket, Size 20, 26-30 AWG
Socket, Size 20, 20-24 AWG Pin, Size 20
Garmin Contact Part
Number 336-00094-00
336-00021-00 (MIL P/N M39029/58-360)
336-00022-00 (MIL P/N M39029/63-368)
336-00022-01
336-00022-02
336-00024-00 (MIL P/N M39029/64-369)
Recommended Positioner
M22520/2-08, Daniels K13-1
Recommended Insertion/
Extraction Tool
Recommended Hand
Crimping Tool
M22520/2-09 Positronic P/N
9502-4, Daniels P/N K42
M22520/2-08, Daniels K13-1
Positronic P/N 9502-5
M81969/1-04 for size 22D
pins and M81969/1-02 for size 20 pins
M22520/2-01
M22520/2-08, Daniels K13-1
NOTE
Non-Garmin part numbers shown are not maintained by Garmin and consequently are subject to change without notice.
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G3X Installation Manual - Inventory of Materials Page 1-7
1.4.3 BNC/TNC Connectors
Either BNC or TNC connectors may be required to terminate the antenna cable, depending upon which antenna is used. Check the antenna installation instructions for detailed information.
1.4.4 Hex Driver
A 3/32" hex drive tool is required to secure the GDU 37X to the panel as described in Section 5.5.1 Unit Installation.
1.4.5 SD Card
An SD Card is required to be used as a DataCard. Garmin recommends a 2 GB SanDisk® brand SD card. See Section 17.4.1 and Section 20.2.1 for detailed information.
1.4.6 Non-Magnetic Tools
Use of non-magnetic tools (e.g. beryllium copper or titanium) is recommended when installing or servicing the GMU 22. Do not use a screwdriver that contains a magnet when installing or servicing the GMU 22.
1.4.7 Pneumatic Hoses and Connectors.
Air hoses and fittings are required to connect pitot and static air to the ADAHRS (GSU 25/73). The ADAHRS (GSU 25/73) has a female 1/8-27 ANPT fitting for each pitot and static port. Use appropriate aircraft fittings to connect to pitot, static, and Angle of Attack (AOA on GSU 25 only) system lines.
1.4.8 Hardware for GAD 29/GEA 24/GSU 25
If the installer does not use supplied hardware, an example of alternate mounting hardware is: (4 ea.) AN3 Bolt and (4 ea.) AN960 Cad Plate #10 Washer.
1.4.9 Hardware for GSU 73
An example of GSU 73 mounting hardware is: #10-32 pan or hex head screw (4 ea.) and #10-32 selflocking nut (4 ea). (see Section 11.4.4)
G3X Installation Manual - Inventory of Materials Page 1-8
190-01115-01 Rev. K
1.5 Optional Garmin Equipment (non-LRU)
1.5.1 Optional GMU 22 Mounting Racks
The Universal Mounting Rack is an optional mounting rack for the GMU 22, refer to the AHRS Magnetometer Installation Considerations (190-01051-00) document available from www.garmin.com.
Refer to Appendix A for airframe specific GMU 22 mounting racks and related mounting hardware.
1.5.2 Antenna Brackets/Doubler Plates
See Section 13 for detailed information.
1.5.3 Silicon Fusion Tape
Garmin Part Number 249-00114-00 or similar, used to wrap the wiring/cable bundles.
1.6 Optional non-Garmin Equipment
1.6.1 Engine/Airframe Sensors
See Section 14.1 for a list of compatible sensors, and Section 14.3 for a list of available sensor kits.
1.6.2 Mounting Hardware
Some sensors may require a torque screwdriver, copper crush gasket, #10 screws, or #8 ring terminals for installation.
1.7 Optional 3rd Party Sensors/LRUs
Refer to Appendix E, Appendix F, Appendix G, and Appendix H for wiring/configuration guidance of supported third party equipment.
1.8 Garmin Software and Documents
The below are available for free download from www.garmin.com.
· AHRS Magnetometer Installation Considerations · Aviation Checklist Editor (ACE) software · Flightlog Conversion Software · GDU 37X Cockpit Display Unit Software · GMU 22 Location Survey Tool · GSU 73 Data Logger Software · GSU 73 Field Calibration Tool · Panel Cut-out DXF File
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2 INSTALLATION PREPARATION
This section provides electrical and mechanical information needed for planning the physical layout of the G3X system installation. This information is applicable to all items comprising the G3X installation. Each LRU/Sensor has unique installation requirements. These requirement are detailed in the Installation portion of Section 4 through Section 14.
Use all of Section 2 to become familiar with all aspects of the installation before actually beginning the physical installation of any equipment into the aircraft. Some information from this section is repeated in following sections of this document.
Garmin recommends that the installer become familiar with all sections of this document before beginning the installation. The sections of this document are (as much as possible) in the order that should be followed for most installations. In general terms, the below steps are recommended to be followed in order.
1. Inventory of all needed parts
2. Planning/layout of the installation
3. Installation of LRUs, antennas, and sensors
4. Construction of wiring harness, cables, and connectors
5. Software installation/configuration
6. Post-installation checkout procedure and calibration
2.1 System Overview
The G3X is an advanced technology avionics suite designed to integrate pilot/aircraft interaction into one central system. The system combines primary flight instrumentation, aircraft systems instrumentation, and navigational information, all displayed on one, two, or three color screens. The G3X system is composed of several sub-units or Line Replaceable Units (LRUs). LRUs have a modular design and can be installed directly behind the instrument panel (or mounted to the panel in the case of the GDU 37X) or in a separate avionics bay if desired. This design greatly eases troubleshooting and maintenance of the G3X system. A failure or problem can be isolated to a particular LRU, which can be replaced quickly and easily. Each LRU has a particular function, or set of functions, that contributes to the system's operation. For additional information on LRU functions, see the applicable section (3-13) of this manual.
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G3X Installation Manual - Installation Preparation Page 2-1
2.1.1 System Architecture
Figure 2-1 illustrates an example block diagram of a G3X installation. The flexibility of the system allows the installer to determine the architecture that best fits each installation. Only one GDU 37X display is required, but up to three may be used.
Refer to Figure 2-1 to determine which of the optional LRUs will be used in the installation and to determine the required interface connections.
GAP 26 Pitot/AOA
Static Source
Static
GDU 370 PFD1
AOA
Pitot RS-232 (Optional)
RS-232 RS-232/ RS-485
GSU 25 ADAHRS 1
GMU 22 Magnetometer
GTP 59 Temp Probe
GMC 305 A/P Controller
(optional)
GSU 25 ADAHRS 2 (optional)
GSA 28 Pitch Servo
RS-232
GSA 28 Roll Servo
RS-232
RS-232
RS-232
CAN BUS
GAD 29 Data
Concentrator
GTX 23 ES Transponder
(Optional)
RS-232 A429 (NAV) A429 (GPS)
A429 (Air Data)
GDU 375 PFD2
RS-232 (ADS-B)
RS-232
A429 (NAV)
A429 (GPS)
GDU 370 MFD
No. 1 GPS/Com (Optional*)
GEA 24 Engine Analyzer
Engine/Airframe Sensors
No. 2 GPS/Com (Optional*)
Stereo/ Mono
RS-232
Third-party Autopilot (Optional)
A429 RS-232
GMA 240 (Optional)
GARMIN COM OR NAV/COM (Optional**)
Figure 2-1. G3X Interconnect Example
Notes: *Maximum of two (2) COM/NAV units installed.
**Same as (*) plus GDU to COM radio is TX-only.
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2.2 Electrical Considerations
This section presents information required for planning the electrical layout of the G3X installation.
2.2.1 Power Specifications
All G3X LRUs are capable of operating at either 14 or 28 VDC (except the GAP 26, 010-01074-10). Table 2-1, Table 2-2, and Table 2-3 list supply voltage and current draw for the G3X LRUs, use this information when determining power supply requirements. All installed electrical appliances must be considered when determining total power requirements.
2.2.1.1 GAP 26
The 010-01074-00 version of the GAP 26 does not require power as it does not have a heater. The initial current vs temperature requirements for the 010-01074-10 are listed in Table 2-1. Supply voltage for the GAP 26 is 14 Vdc, Connect aircraft power directly to GAP 26 heater wires by any preferred means for the given current draw. See Table 4-2 for acceptable wire gauge and run length for given configurations. Use of 14 AWG wire and a 20 Amp circuit breaker are recommended for most installations.
CAUTION
Do not connect the GAP 26 to 28 VDC.
Table 2-1 GAP 26 Initial Current Draw vs Temperature (-10 unit only)
Temperature Amps
-40°C 12 A
0°C 9.25 A
50°C 7.3 A
100°C 5.85 A
175°C 4.36 A
2.2.1.2 GDU 37X
NOTE
GDU 37X current draw must be multiplied by the number of installed GDU 37X units.
Table 2-2 GDU 37X Power Requirements
LRU GDU 370 GDU 375
14 V (Maximum) 15 W, 1.10 Amp 15 W, 1.10 Amp
14 V (Typical) 8.5 W, 0.600 Amp 9.5 W, 0.675 Amp
28 V (Maximum) 15 W, 0.540 Amp 15 W, 0.540 Amp
28 V (Typical) 8.50 W, 0.300 Amp 9.25 W, 0.330 Amp
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G3X Installation Manual - Installation Preparation Page 2-3
2.2.1.3 Other LRU Power Requirements
Table 2-3 G3X LRU Power Requirements
LRU
Supply Voltage
Current Draw
GAD 29
14 Vdc 28 Vdc
0.2 A 0.1A
GEA 24
14 Vdc 28 Vdc
0.43 A max (typical external sensor loading) 0.21 A max (typical external sensor loadiing)
GMC 305
14 Vdc 28 Vdc
0.50 mA 0.28 mA
GMU 22
12 Vdc (from GSU 25/GSU 73)
Inc. in GSU 25/GSU 73 Current Draw
GSA 28
14 Vdc 28 Vdc
0.36 Amp (typical) 1.80 Amp (max) 2.80 Amp (max with 1 Amp trim motor at full load)
0.20 Amp (typical) 0.90 Amp (max) 1.40 Amp (max with 1 Amp trim motor at full load)
GSU 25
14 Vdc 28 Vdc
0.2 Amp (includes GMU 22 load) 0.11 Amp (includes GMU 22 load)
GSU 73*
14 Vdc 28 Vdc
1.75 Amp (max) 0.80 Amp (max)
*Garmin recommends using Mod 1 level GSU 73 in aircraft that use a +28 V supply voltage and intend to monitor current on high voltage devices such as the aircraft alternator.
2.3 Wiring/Cabling Considerations
Section 15 lists the pin information for all LRU connectors. Section 15 lists the connector (including configuration modules) installation information. Appendices C-H contain interconnect drawings for all required/optional LRUs and sensors. These appendices, along with the following sections 314 contain all the information needed to construct the wiring harnesses/cables. It is recommended that LRUs/sensors be installed prior to constructing the wiring harnesses and cables.
Use MIL-W-22759/16 (or other approved wire) AWG #22 or larger wire for all connections unless otherwise specified. The supplied standard pin contacts are compatible with up to AWG #22 wire. In cases where some installations have more than one LRU sharing a common circuit breaker, sizing and wire gauge is based on aircraft circuit breaker layout, length of wiring, current draw on units, and internal unit protection characteristics. Do not attempt to combine more than one unit on the same circuit breaker.
RG400 or RG142 coaxial cable with 50 nominal impedance and meeting applicable aviation regulations should be used for the installation.
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2.3.1 Wiring Harness Installation
Use cable meeting the applicable aviation regulation for the interconnect wiring. Any cable meeting specifications is acceptable for the installation. When routing cables, observe the following precautions:
· All cable routing should be kept as short and as direct as possible. · Check that there is ample space for the cabling and mating connectors. · Avoid sharp bends in cabling. · Avoid routing near aircraft control cables. · Avoid routing cables near heat sources, RF sources, EMI interference sources, power sources (e.g.,
400 Hz generators, trim motors, etc.) or near power for fluorescent lighting. · Route the GPS antenna cable as far as possible away from all COM transceivers and antenna
cables. · Analog Input wires routed too close to spark plugs, plug wires, or magnetos may result in erratic
readings.
The installer shall supply and fabricate all of the cables. Required connectors, etc. are provided with the G3X w/GSU 73 Installation Kit (K10-00017-00). Electrical connections for the GMU 22 are made through a round 9-pin connector, and are made through D subminiature connectors for all other LRUs. Section 15 defines the electrical characteristics of all input and output signals. Required connectors and associated hardware are supplied with the connector kit.
Contacts for the connectors must be crimped onto the individual wires of the aircraft wiring harness. Table 1-13 lists contact part numbers (for reference) and recommended crimp tools.
CAUTION
Check wiring connections for errors before connecting any wiring harnesses. Incorrect wiring could cause internal component damage.
2.3.1.1 Backshell Assemblies
Connector kits include backshell assemblies. The backshell assembly houses the configuration module and a thermocouple reference junction. Garmin's backshell connectors give the installer the ability to quickly and easily terminate shield grounds at the backshell housing. The instructions needed to install the Jackscrew Backshell, Configuration Module, and Thermocouple are located in Section 16.
NOTE
The GDU 37X rear connector (J3701) is electrically isolated. For installations using shielded cables, a ground pin must be tied to the connector shell.
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2.3.1.2 Configuration Module
The G3X system is designed to store configuration and calibration data in multiple locations to retain the configuration of the system during maintenance. Figure 2-2 shows the configuration module that installs on both the GDU 37X (PFD 1) and the GSU 73 connector backshell. In systems using a GSU 25, only the GDU 37X (PFD 1) will use a configuration module. See Section 16 for installation instructions.
Figure 2-2. Configuration Module
2.3.1.3 CAN Bus Considerations
The CAN (controller area network) bus (Figure 2-3) is an interface format used to establish communication between several LRUs in the G3X system. Each end of the CAN Bus "backbone" must be terminated by a 120 resistor. Each node length (distance from CAN bus backbone to each LRU) must be 1 meter or less in length (keeping the node lengths as short as practicable is recommended). There is no minimum node length.
LRUs that can connect to the CAN Bus are: GAD 29, GDU 37X, GEA 24, GSA 28, GSU 25, GSU 73. The GEA 24 and GSU 25 installation kits provide a DB-9 CAN Bus terminator that contains a 120 resistor connected between pin 1 and 2 (Figure 2-4). The GDU 37X and GSU 73 units are terminated by connecting the CAN Bus Lo pin to the CAN Bus Termination pin (Figure 2-5). The GDU 37X, GSU 73, and GSA 28 units all contain a 120 resistor inside the unit that provides the termination when connected externally (as shown in Figure 2-5, Figure 2-6). The GSA 28 servos are terminated by connecting pin 3 to pin 4 (Figure 2-6).
NOTE
Use only two CAN Bus terminations per installation (even if provided more than two from associated G3X installation kits). Using less than or more than two terminations (one at each end of the backbone) will make the CAN Bus unusable or unreliable.
(Node #1)
(Node #2)
(Node #3)
(Node #n)
LRU
LRU
LRU
LRU
Node Length 1 meter max.
RL
CAN HI CAN LOW
CAN Bus Backbone Figure 2-3. CAN Bus Configuration
G3X Installation Manual - Installation Preparation Page 2-6
RL
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The following items should be considered when installing/removing/replacing LRU's on the CAN bus: 1. CAN bus node connections must be made on the connector of each LRU that connects to the CAN bus, do not tie CAN bus nodes from individual LRUs together into a single connection point. 2. Keep all node lengths as short as practicable, and allow only one `lengthy' node if possible. 3. If a GAD 29, GEA 24, and/or GSU 25 unit (that was used as a CAN bus termination) is removed, the CAN bus will remain terminated as long as the CAN bus terminator (Figure 2-4) is left connected. 4. If a GDU 37X and/or GSU 73 unit (that was used as a CAN bus termination) is removed, the CAN bus will be unusable until the CAN bus is properly terminated at both ends of the `backbone' (Figure 2-3). 5. A removal adapter (GPN 011-03158-00) is provided (with each GSA 28 connector kit) that can be used when a GSA 28 is removed. The adapter keeps that node on the CAN bus in the same state as when the servo was connected (either terminated or un-terminated). The adapter also allows trim signals to pass through when the servo is removed. 6. Based on preceding points 2-4, it is recommended that CAN bus terminations are placed at a GAD 29, GEA 24, GSA 28, GSU 25 unit, if possible.
NOTE
The 120 termination resistors described in the preceding paragraphs are "built-in" to the termination methods shown in the following figures. Do not install a separate "discrete" 120 resistor to terminate the CAN bus in addition to the termination methods shown in Figure 2-4, Figure 2-5, and Figure 2-6.
GARMIN CAN TERMINATOR
Figure 2-4. CAN Bus Termination (011-02887-00) for GAD 29, GEA 24, and GSU 25
Figure 2-5. CAN Bus Termination for GDU 37X and GSU 73
GSA 28 PITCH SERVO
CAN_TERM_1 3 CAN_TERM_2 4
NOTE: JUMPER (BETWEEN PINS 3 & 4) REQUIRED WHEN GSA 28 IS LOCATED AT END OF CAN BUS
Figure 2-6. CAN Bus Termination for GSA 28
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2.3.1.4 Cable Connector Installation
Coaxial cables are required for antenna connections for GPS, XM, transponder, comm, VHF Nav, and ADS-B functions.
1. Route the coaxial cable to the unit location. Secure the cable in accordance with good aviation practices.
2. Trim the coaxial cable to the desired length and install the BNC or TNC (per Figure 2-7) connector. If provided, follow the connector manufacturer's instructions for cable preparation.
Figure 2-7. TNC Connector Installation
2.4 Mechanical Considerations
This section presents all information required for planning the physical layout of the G3X installation.
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2.4.1 Physical Specifications
Use Table 2-4 to determine panel requirements. All width, height, and depth measurements are taken with unit rack (if applicable) and connectors, dimensions are also listed in Appendix B. Figure 5-4 and Figure 7-2 are panel cutout templates for the GDU 37X and GMC 305 respectively.
Table 2-4 G3X LRU Physical Specifications
LRU
Width
Height
Depth
GAD 29
(ARINC 429 Adapter)
6.10 inches [154.9 mm]
1.48 inches [37.6 mm]
3.23 inches [82.0 mm] no connector
5.10 inches [129.4 mm] w/connector
5.54 inches 140.7 mm] w/connector and CAN terminator
GAP 26
(Air Data Probe)
.821 inches [20.9 mm]
16 inches [406.4 mm]
6.12 inches [157.7 mm]
GDU 370
(Display)
GDU 375
(Display)
6.04 inches (153.4 mm)
6.04 inches (153.4 mm)
GEA 24
(EIS)
6.5 inches (165.1 mm)
GMC 305
(Mode Controller)
6.25 inches (158.8 mm)
GMU 22 (Magnetom- N/A
eter)
GSA 28
(Servo Actuator)
2.5 inches (63.5 mm)
GSU 25 4.0 inches (ADAHRS) (101.6 mm)
GSU 73
(ADAHRS/ EIS)
5.50 inches (139.7 mm)
7.83 inches (198.8 mm) 7.83 inches (198.8 mm)
1.9 inches (48.3 mm)
1.85 inches (47.0 mm)
2.10 inches (53.3 mm)
4.0 inches (101.6 mm)
2.12 inches (53.8 mm) 2.61 inches (66.2 mm) w/conn
3.96 inches (100.6 mm)
3.41 inches (86.6 mm)
3.41 inches (86.6 mm) 3.0 inches (76.2 mm) 5.0 inches (127.0 mm) w/connectors
3.30 inches (83.8 mm)
3.37 inches (85.6 mm) Diameter
2.8 inches (71.1 mm)
2.5 inches (63.5 mm)
5.50 inches (139.8 mm) 7.33 inches (186.2 mm) w/connectors
Unit Weight
Unit Weight w/ Nutplate & Connector Weight
.38 lb (0.172 kg)
NA
-00 unit: 0.33 lb (0.149 kg) -10 unit: 0.39 lb (0.176 kg) 1.6 lbs (0.713 kg) 1.7 lbs (0.771 kg)
0.71 lbs (0.322 kg)
0.5 lbs. (0.226 kg)
0.35 lbs. (0.158 kg)
1.40 lbs (0.635 kg)
0.48 lbs (0.217 kg)
3.1 lbs (1.406 kg)
NA
1.8 lbs (0.803 kg) 1.9 lbs (0.862 kg) 1.6 lbs (0.725 kg)
0.6 lbs. (0.272 kg)
0.50 lbs. (0.226 kg)
NA
0.684 lbs (0.310 kg)
3.5 lbs (1.587 kg)
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G3X Installation Manual - Installation Preparation Page 2-9
2.4.2 Cooling Requirements
While no forced cooling air is required for the G3X system, it is highly recommended that the air behind the panel be kept moving (by ventilation or a fan).
· No cooling air is required for the GAD 29 · No cooling air is required for the GDU 37X · No cooling air is required for the GEA 24 · No cooling air is required for the GMC 305 · No cooling air is required for the GMU 22 · No cooling air is required for the GSA 28 · No cooling air is required for the GSU 25 · No cooling air is required for the GSU 73, however the GSU 73 should be mounted in a location
that provides adequate airflow to comply with the maximum outer case temperature listed in Section 11.
NOTE
Avoid installing the G3X LRUs near heat sources. If this is not possible, ensure that additional cooling is provided. Allow adequate space for installation of cables and connectors. The installer will supply and fabricate all of the cables. All wiring should be in accordance with FAA AC 43.13-1B and AC 43.13-2B.
2.5 LRU/Sensor Installation Information
Each LRU/sensor has unique considerations that the installer should be familiar with before beginning the physical installation. Become familiar with all installation information by studying sections 3-13 of this document before actually beginning the installation of the LRUs/sensors.
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3 GAD 29 INSTALLATION (OPTIONAL LRU)
This section contains general information as well as installation information for the GAD 29. Use this section to mount the GAD 29 unit.
NOTE
A GAD 29 cannot be installed in a system that also includes a GSU 73. For ARINC 429 I/O, use the appropriate pins on the GSU 73 instead.
Figure 3-1 GAD 29 Unit View
3.1 Equipment Description
The GAD 29 allows the G3X system to interface to IFR navigators such as the GNS and GTN series. The GAD 29 has a 25 pin D-sub connector and a 9 pin D-sub connector. These connectors will provide the following functionality:
· 2 Low Speed ARINC 429 Transmitters · 4 Low Speed ARINC 429 Receivers · 1 CAN Network Port
NOTE
A GAD 29 cannot be installed in a system that also includes a GSU 73, use the GSU 73 for ARINC 429 I/O connections in these (GSU 73) installations.
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G3X Installation Manual - GAD 29 Installation Page 3-1
3.1.1 Status LED The GAD 29 has an LED on its outer case that indicates its current status. The status indications are:
Table 3-1 Status LED Indications
LED Indication No Light Steady Green Flashing Green Red
Alternating Red/Green
Status No Power On, but not communicating via CAN Bus On and communicating via CAN Bus Hardware Fault CAN bus network error two similar devices are configured with the same unit ID
3.2 Equipment Available
3.2.1 Required Equipment
Table 3-2 GAD 29 Part Numbers
Model GAD 29
Assembly Part Number
010-01172-00
Unit Only Part Number
011-03236-00
3.2.2 Additional Equipment Required The connector kit in Table 3-3 is required to install the unit, it is not provided with the GAD 29 unit.
Table 3-3 Contents of GAD 29 Connector Kit (011-03271-00)
Item Backshell w/Hdw, Jackscrew, 9 Pin Backshell w/Hdw, Jackscrew, 25 Pin Conn, Plug,D-Sub, Crimp Pin, Commercial, 25 CKT Conn, Rcpt, D-Sub, Crimp Socket, Commercial, 09 CKT Contact, Socket, Military Crimp, Size 20 Contact ,Pin, Military Crimp, Size 20
Garmin P/N 011-01855-00 011-01855-02 330-00624-25 330-00625-09 336-00022-02 336-00024-00
Quantity 1 1 1 1 11 27
3.3 General Specifications
See Section 2.2 for power/current specifications, and Section 2.4.1 for dimension/weight specifications.
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3.4 Unit Installation
1. Mount the unit to a suitable mounting location using (4) #10-32 pan or hex head screws. 2. Assemble the connector backshells and wiring harness. 3. Connect CAN terminator to unit if required (Section 2.3.1.3). 4. Connect backshell connectors.
3.5 Mounting Requirements
The GAD 29 will mount remotely. The GAD 29 will be secured to the airframe using four #10-32 pan or hex head screws supplied by the installer.
3.6 Environmental Specifications
Table 3-4 lists general environmental specifications.
Table 3-4 GAD 29 Environmental Specifications
Characteristic Unit Operating Temperature Range
Specification -45°C to +70°C
3.7 Continued Airworthiness
The GAD 29 requires no maintenance.
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4 GAP 26 INSTALLATION (OPTIONAL LRU)
This section contains general information as well as installation information for the GAP 26 Pitot/AOA (Angle of Attack) probe. Use this section to mount the GAP 26.
4.1 Equipment Description
The GAP 26 Pitot/AOA (Angle of Attack) probe is an air data probe intended for use in non FAA certified aircraft, including light sport and home-built aircraft. This air data probe is intended to be used as part of the G3X system.
The function of the GAP 26 is to provide pitot and AOA pressures to the GSU 25 for the purpose of displaying airspeed and AOA to the pilot as part of the G3X system. The GAP 26 does not provide a static pressure source to the GSU 25. There are two different versions of the GAP 26, the -00 (unheated) and the -10 (heated, for ice protection). All versions of the GAP 26 have identical aerodynamic performance including identical internal water separation/baffling chambers, drain holes, pressure port locations and pneumatic tubing.
4.1.1 Moisture Protections
Both pitot and AOA pressure chambers have internal baffling and dedicated drain holes to provide moisture protection.
4.1.2 Ice Protection
The heated version of the GAP 26 (010-01074-10) has dual internal electro-thermal heating elements to provide ice protection to the areas of the probe where surface impingement of icing elements is expected to occur.
NOTE
The pneumatic tubing for pitot pressure is the longer of the two tubes extending out of the probe (Figure 4-1).
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Figure 4-1 GAP 26 Unit View (-10 version shown)
G3X Installation Manual - GAP 26 Installation Page 4-1
4.2 Equipment Available
Table 4-1 GAP 26 Part Numbers
Model
GAP 26 Probe Only GAP 26 Probe Only, Heated
Assembly Part Number
010-01074-00
010-01074-10
Unit Only Part Number
011-02964-00
011-02964-10
Heater Control Box Part Number N/A
N/A
4.3 Required Equipment
· GAP 26 Pitot/AOA Probe (010-01074-00 or 010-01074-10) · Electrical and pneumatic connectors per installer preference. Length of aluminum pneumatic
tubing may be utilized without damage to materials from the probe heater cutting tubing to a shorter length is not recommended. · Mount: Standard AN5812 pitot tube mounting kit. · #6-32 screws (4 pcs), required length (.218" min - .312" max), recommend screws with nylon patch on threads for thread locking.
4.4 General Specifications
See Section 2.2 for power/current specifications, and Section 2.4.1 for dimension/weight specifications.
4.5 Unit Installation
Fabrication of a wiring harness is required. Sound mechanical and electrical methods and practices are recommended for installation of the GAP 26. Refer to Section 2.3 for wiring considerations (-10 unit only).
4.5.1 Mounting Location
· The GAP 26 is an under-wing mounted pitot/AOA probe, it is not intended for fuselage mount applications. For proper functionality, the GAP 26 should be mounted in a location where airflow over the probe is relatively undisturbed (typically mid-wing span).
· The tip of the GAP 26 should be located at least 4" from, but not more than 10" below the bottom surface of the wing. The tip should be located 2" to 18" behind the leading edge of the wing.
· Use the designer/manufacturer's recommended pitot mounting location (if specified). · The 3/16" diameter aluminum pneumatic tubing is intended to be hand bendable to suit various
mounting configurations. Minimum allowable bend radius is 1.5". It is recommended to bend any given section only once to prevent work hardening and cracking of the aluminum tubing. · Garmin recommends that the GAP 26 not be used on aircraft where the ship static pressure port is located under the wing (due to the likelihood that the AOA measurement will be significantly impacted). If the static port is located under the wing, it is recommended that the port be moved to an alternate location as part of the GAP 26 installation. If port relocation is required, obtain guidance from the aircraft designer regarding acceptable alternate static port locations. · Route all GAP 26 power and ground wires away from any audio wires. · To avoid magnetic interference, do not use the airframe to ground the GAP 26 or any other highcurrent device. See Section 8.4 for further magnetometer installation considerations.
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4.5.2 Heater Wiring Configuration
The GAP 26 uses two internal heaters that may only be powered by 14 Volt systems. Each of the heaters has two wires, one of these two wires is "banded" (Figure 4-2) to help identify individual heaters. These heaters can be connected to a power source as shown in Figure 4-3. Table 4-2 lists the wiring gauge and wiring lengths for the different configurations. For most installations, the use of 14 AWG wire with a 20 Amp circuit breaker is recommended.
CAUTION
Do not connect the heaters to 28 Volts.
"Banded" Wire
Figure 4-2 GAP 26 Banded Wire
15 A
PLAIN WIRES
+ 14 V -
HEATERS
GAP 26
BANDED WIRES
GAP 26 HEATERS WIRED TO AIRCRAFT POWER SOURCE. CONNECTORS MUST BE RATED TO 15A MINIMUM.
Figure 4-3 GAP 26 Installation Configuration
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G3X Installation Manual - GAP 26 Installation Page 4-3
Table 4-2 GAP 26 Wiring Specifications
Power Source Wiring
Wire Length
Wire Gauge
0 - 12 Feet
14 AWG
13 - 20 Feet
12 AWG
21 - 33 Feet
10 AWG
4.6 Environmental Specifications
· Operating Temperature Range: -55°C to 240°C
4.7 Continued Airworthiness
· Leak Checks in accordance with CFR Part 43, Appendix E, Altimeter System Test and Inspection. · Visual Inspection of pressure ports and drain holes for debris/blockage once a year.
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5 GDU 37X INSTALLATION (CORE G3X LRU)
This section contains general information as well as installation information for the GDU 37X. Use this section to mount the GDU 37X unit(s).
Figure 5-1 GDU 37X Unit View
5.1 Equipment Description
NOTE
There is no TSO/ETSO applicable to the GDU 37X.
NOTE
A minimum of one GPS antenna is required for installations using more than one GDU 37X unit, as the GDU 37X will "share" the GPS information with all GDU 37X units. Additional GPS antennas may be used for redundany, but are not required.
The GDU 37X provides a central display and user interface for the G3X system. The display is mounted flush to the aircraft instrument panel using four #6 captured screws with a 3/32" hex head. The GDU 37X is available in two models, GDU 370 and GDU 375. The GDU 370 is a Garmin Display Unit with a VFR WAAS-GPS receiver. The GDU 375 provides these same features plus an XM receiver.
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G3X Installation Manual - GDU 37X Installation Page 5-1
5.1.1 Navigation Functions
· Display of position and ground speed · Display of stored navigation and map databases · Area navigation functions using the determined position/velocity and stored navigation data · Advisory approach navigation functions and associated databases · Display of flight plan and navigation from an external GPS navigator · Display of navigation data from an external VOR/ILS NAV radio
5.1.2 Interface Summary
The GDU 37X uses CAN and RS-232 communications interfaces. The GDU 37X can be configured to communicate directly with the following Garmin LRUs:
· GAD 29 · Other GDU 37X · GDL 39/GDL 39R · GEA 24 · GNS 400/500 Series Units · GNS 480 · GSA 28 · GSU 25 · GSU 73 · GTN 600/700 Series Units · GTX 330 Transponder (TIS-A info only) · SL30 Nav/Comm Transceiver · SL40 Comm Transceiver · GTR/GNC series units
5.2 General Specifications
See Section 2.2 for power/current specifications, and Section 2.4.1 for dimension/weight specifications.
5.3 Installation Information
5.3.1 Required Equipment
Each of the following accessories is provided with the GDU 37X unit (Table 1-8). The connector kit is required to install the unit (Figure 5-2). The GDU 37X Nutplate (Figure 5-2) is available to reinforce the panel cutout in thin panel installations.
The contents of the GDU 37X Connector Kit are listed in Table 5-1. One kit is required for each GDU 37X installed.
Table 5-1 Contents of GDU 37X Connector Kit (011-01921-00)*
Item
Garmin P/N
Sub-Assy, bkshl w/Hdw, Jackscrew
011-01855-04
Conn, Rcpt, D-Sub, Crimp Socket
330-00625-50
Contact, Sckt, D-Sub, Crimp, Size 20
336-00094-00
Quantity
1 1 20
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5.3.1.1 GDU 37X PFD Configuration Module
The GDU 37X PFD 1 display uses a configuration module designated as the master system configuration module. The master system configuration module stores configuration data identical to the PFD configuration data stored in the PFD memory. The PFD cross-checks the configuration module data against internal PFD memory and self-configures to match the master system configuration module. The PFD also maintains control of other LRUs' configuration and calibration settings except for GSU 73 AHRS calibration settings which are stored in the GSU 73 configuration module. This allows critical data to be retained with the airframe even if the PFD 1 display is replaced.
5.3.2 Additional Equipment Required
A 3/32" hex drive tool is required to secure the GDU 37X to the panel as described in Section 5.5.1 Unit Installation.
Figure 5-2 GDU 37X Mounting Accessories
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G3X Installation Manual - GDU 37X Installation Page 5-3
5.4 Unit Installation
Fabrication of a wiring harness is required. Sound mechanical and electrical methods and practices are recommended for installation of the GDU 37X. Refer to Section 2.3 for wiring considerations, and to Section 15.2 for pinouts. Connector kits include backshell assemblies. Garmin's backshell connectors give the installer the ability to quickly and easily terminate shield grounds at the backshell housing. The instructions needed to assemble the backshell connector w/Shield Block grounding system are located in Section 16.
NOTE
The GDU 37X rear connector (J3701) is electrically isolated. For installations using shielded cables, a ground pin must be tied to the connector shell (Figure 5-3).
X
SIGNAL GROUND
Figure 5-3 Grounded Connector Shell
5.5 Mounting Requirements
Refer to Appendix B for outline and installation drawings. 5.5.1 Unit Installation The GDU 37X is installed by holding the unit flush with the instrument panel and fastening the four captured 3/32" hex socket head screws to the panel as shown in Figure B-4.1. 5.5.2 Panel Cutout Template Figure 5-4 can be used as a template when marking the panel for cutout. Dimensions on the figure are to verify accuracy of printout only, see Figure B-4.2 for complete cutout dimensions. A .dxf version of the drawing is also available for download at www.garmin.com.
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GDU 37X PANEL CUTOUT TEMPLATE
IMPORTANT! Ensure the Page Scaling setting is set to NONE when printing this page. Verify dimensions of printed template are accurate before cutting panel.
Cut out panel to inside line
7.33 in [186.2 mm]
5.57 in [141.4 mm]
For corner holes, center punch and drill (#36) / tap (6/32) to create threaded holes
OR drill out with 25 drill bit and use Garmin
nut-plate P/N 115-01054-00
190-01115-01 Rev. K
Figure 5-4 GDU 37X Panel Cutout Template
G3X Installation Manual - GDU 37X Installation Page 5-5
5.6 GPS Specifications
The GDU 37X uses a high-sensitivity GPS receiver that continuously tracks and uses up to 12 satellites to compute and update its position. In an installation with multiple GDU 37X units, each GDU can be configured to use its own internal GPS receiver, or to receive GPS data transmitted by another GDU. At least one GDU must be equipped with a GPS antenna. See Section 17.3.13 for further information.
Table 5-2 GDU 37X GPS Specifications
Characteristics
Acquisition Time
Update Rate Positional Accuracy Antenna Power Supply
Specifications
a) Warm Start (position known to 10 nm, time known to 10 minutes, with valid almanac and ephemeris): Less than 5 seconds
b) Cold Start (position known to 300 nm, time known to 10 minutes, with valid almanac): Less than 45 seconds
c) AutoLocateTM (with almanac, without initial position or time): Less than 60 seconds
5/second, continuous
<10 meters
Voltage (4.5 to 5.0), current (50 mA max)
5.7 Environmental Specifications
The GDU 37X has an Operating Temperature Range of -20°C to +60°C.
5.8 Antennas
Refer to Section 13 for antenna information
5.9 Continued Airworthiness
Maintenance of the GDU 37X is "on condition" only. Periodic maintenance of the GDU 37X is not required. Instructions for Continued Airworthiness (ICA) are not required for this product under 14 CFR Part 21 since the GDU 37X has received no FAA approval or endorsement.
G3X Installation Manual - GDU 37X Installation Page 5-6
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6 GEA 24 INSTALLATION (OPTIONAL LRU)
This section contains general information as well as installation information for the GEA 24. Use this section to mount the GEA 24 unit.
GEA 24 UNIT 011-02848-00
Figure 6-1 GEA 24 Unit View
6.1 Equipment Description
The GEA 24 is an input/output system used to monitor and power engine and airframe sensors for the Experimental Amateur Built (E-AB) and Light Sport Aircraft (LSA) markets.
· 9 pin network-power connector · 50 pin miscellaneous connector for airframe sensors · 25 pin thermocouple input connector · 37 pin miscellaneous connector (for airframe sensors) will provide for the following input/output
functionality: Configure analog, digital, and discrete I/O capability Output digital measurement of analog input resistive sensors Output digital measurement of analog input voltages Output digital state of discrete input sources Output frequency measurement of digital input sources Control of discrete annunciator outputs
NOTE
If a GEA 24 is installed in a system that also includes a GSU 73, the GEA 24 must be configured as EIS #2 as described in Section 15.3.15.
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G3X Installation Manual - GEA 24 Installation Page 6-1
6.1.1 Status LED The GEA 24 has an LED on its outer case that indicates its current status. The status indications are:
Table 6-1 Status LED Indications
LED Indication No Light Steady Green Flashing Green Red
Alternating Red/Green
Status No Power On, but not communicating via CAN Bus On and communicating via CAN Bus Hardware Fault CAN bus network error two similar devices are configured with the same unit ID
6.2 Equipment Available
6.2.1 Required Equipment
Table 6-2 GEA 24 Part Numbers
Model GEA 24
Assembly Part Number
010-01042-00
Unit Only Part Number
011-02848-00
6.2.2 Additional Equipment Required
Table 6-3 lists the content of the GEA 24 Connector Kit, which is required to install the unit. Use of the CAN Termination Kit is detailed in Section 2.3.1.3.
Table 6-3 Contents of GEA 24 Connector Kit (011-02886-00)
Item Backshell w/Hdw, Jackscrew, 9/15 Pin Backshell w/Hdw, Jackscrew, 25/44 Pin Backshell w/Hdw, Jackscrew, 37/62 Pin Backshell w/Hdw, Jackscrew, 50/78 Pin CAN termination kit Conn, Plug,D-Sub, Crimp Pin, Commercial, 25 CKT Conn, Rcpt, D-Sub, Crimp Socket, Commercial, 09 CKT Conn, Rcpt, D-Sub, Crimp Socket, Commercial, 37 CKT Conn, Rcpt, D-Sub, Crimp Socket, Commercial, 50 CKT Contact, Socket, Military Crimp, Size 20 Contact ,Pin, Military Crimp, Size 20
Garmin P/N 011-01855-00 011-01855-02 011-01855-03 011-01855-04 011-02887-00 330-00624-25 330-00625-09 330-00625-37 330-00625-50 336-00022-02 336-00024-00
Quantity 1 1 1 1 1 1 1 1 1
100 30
G3X Installation Manual - GEA 24 Installation Page 6-2
190-01115-01 Rev. K
6.3 General Specifications
See Section 2.2 for power/current specifications, and Section 2.4.1 for dimension/weight specifications.
6.4 Unit Installation
1. Mount the unit to a suitable mounting location using (4) #10-32 pan or hex head screws. 2. Assemble the connector backshells and wiring harness. 3. Connect CAN terminator to unit if required (Section 2.3.1.3). 4. Connect backshell connectors.
CAUTION
Do not mount the GEA 24 on the `hot' side (engine side) of the firewall.
6.5 Mounting Requirements
The GEA 24 will mount remotely. The GEA 24 will be secured to the airframe using four #10-32 pan or hex head screws supplied by the installer.
6.6 Environmental Specifications
Table 6-4 lists general environmental specifications.
Table 6-4 GEA 24 Environmental Specifications
Characteristic Unit Operating Temperature Range
Specification -45°C to +70°C
6.7 Continued Airworthiness
The GEA 24 requires no maintenance.
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G3X Installation Manual - GEA 24 Installation Page 6-3
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G3X Installation Manual - GEA 24 Installation Page 6-4
190-01115-01 Rev. K
7 GMC 305 INSTALLATION (OPTIONAL LRU)
This section contains general information as well as installation information for the GMC 305. Use this section to mount the GMC 305 unit.
Figure 7-1 GMC 305 Unit View (-20 version shown, -00 version has no YD button)
7.1 Equipment Description
The GMC 305 is a Garmin Automatic Flight Control System (AFCS) Mode Controller that can be used in a G3X installation. The GMC 305 provides user interface for the autopilot function of the G3X system. The GMC 305 mounts flush to the aircraft instrument panel using four threaded cap screws.
7.2 Equipment Available
7.2.1 Required Equipment
Table 7-1 GMC 305 Part Numbers
Model
GMC 305 GMC 305 w/Yaw Damper
Assembly Part Number
010-01169-00
010-01169-20
Unit Only Part Number
011-03226-00
011-03226-20
7.2.2 Additional Equipment Required
The following accessories are not provided with the GMC 305 unit. The Installation Kit (Table 7-2) is required to install the unit. The Installation Kit includes the Connector Kit (Table 7-3) and the Mounting Kit (Table 7-4).
Table 7-2 Contents of GMC 305 Installation Kit (010-12034-00)
Item Connector Kit, 15 Pin, Hi Density Male w/Jackscrews Mounting Kit, GMC 305
Garmin P/N 011-01824-00 011-03242-00
Quantity 1 1
Table 7-3 Contents of Connector Kit (011-01824-00)
Item Backshell w/Hdw, Jackscrew, 9/15 Pin Connector, Male, High Density D-Sub,15 CKT Contact, Pin, Military Crimp, Size 22D
Garmin P/N 011-01855-00 330-00366-15 336-00021-00
Quantity 1 1 12
190-01115-01 Rev. K
G3X Installation Manual - GMC 305 Installation Page 7-1
Table 7-4 Contents of Mounting Kit (011-03242-00)
Item Nut, Self-Locking, Plate, One Lug, 6-32 Screw, Machine, Panel Mounting, 0.550", Black
Garmin P/N 210-00104-04 211-00169-01
Quantity 4 4
7.3 General Specifications
See Section 2.2 for power/current specifications, and Section 2.4.1 for dimension/weight specifications.
7.4 Mounting and Wiring Requirements
7.4.1 Fasteners
The GMC 305 is installed using the four #6-32 threaded cap screws supplied in the GMC 305 installation kit using a 3/32" hex wrench. The instrument panel may be drilled and tapped for the #6-32 screws, or the four anchor nuts supplied in the installation kit may be installed using flush-mount rivets.
7.4.2 Panel Cutout Template
Figure 7-2 can be used as a template when marking the panel for cutout. Dimensions on the figure are to verify accuracy of printout only, see Figure B-6.3 for complete cutout dimensions.
7.4.3 Unit Installation
1. Drill holes in panel to locate nut plates and LRU (see Figure 7-2, Figure B-6.2, and Figure B-6.3).
2. Install nut plates using flush-mount rivets. 3. Hold the unit flush with the instrument panel. 4. Install the four mounting screws (Installation Kit 010-12034-00) through the four mounting holes
in the GMC 305. 5. Use a 3/32" hex drive tool to turn each of the four mounting screws clockwise until tight
(10 in-lbs).
7.4.4 Wiring
The 15 pin connector, pins, and backshell supplied in the GMC 305 installation kit are used to add wiring for the GMC 305.
It is recommended that a 2 Amp fuse or circuit breaker be used to supply power to the GMC 305 (Figure C-1.5). Backup power is optional.
The GMC 305 is connected via RS-232 to any GDU 37X display (Figure C-1.5). The selected GDU RS-232 channel must be configured for "Garmin Instrument Data".
If the installation includes a Garmin integrated autopilot using GSA 28 servos, the GMC 305 installation also includes an RS-232 connection to the GSA 28 roll servo (Figure C-1.5). GMC 305 RS-232 channel 1 must be connected to any one of the 3 available RS-232 channels on one of the GDU 37X units. The GMC 305 RS-232 channel 2 must be connected to the GSA 28 roll servo RS-232 channel 1 if this roll servo is installed.
For installations using a non-Garmin autopilot with a GMC 305 controller, refer to Figure C-2.12.
G3X Installation Manual - GMC 305 Installation Page 7-2
190-01115-01 Rev. K
GMC 305 PANEL CUTOUT
5.380 136.65
IMPORTANT! Ensure the Page Scaling setting is set to NONE when printing this page. Verify dimensions of printed template are accurate before cutting panel.
CUT OUT PANEL TO INSIDE LINE
1.730 43.94
NOTES: 1. DIMENSIONS: INCHES[mm]. METRIC VALUES ARE FOR REFERENCE ONLY. 2. DIMENSIONS ARE NOMINAL AND TOLERANCES ARE NOT IMPLIED UNLESS
SPECIFICALLY STATED.
Figure 7-2 GMC 305 Panel Cutout Template
190-01115-01 Rev. K
G3X Installation Manual - GMC 305 Installation Page 7-3
7.5 Environmental Specifications
Table 7-5 GMC 305 Environmental Specification
Characteristics Operating Temperature Range Humidity Altitude Range
Specifications -45°C to +70°C 95% non-condensing -1,500 ft to 55,000 ft
7.6 Continued Airworthiness
Maintenance of the GMC 305 is "on condition" only. For regulatory periodic functional checks, refer to approved aircraft maintenance manuals or manual supplements for actual aircraft maintenance requirements.
G3X Installation Manual - GMC 305 Installation Page 7-4
190-01115-01 Rev. K
8 GMU 22 INSTALLATION (CORE G3X LRU)
NOTE
All GMU 22 information in this Installation Manual also applies to the GMU 44, which had previously been the G3X magnetometer but has been replaced by the GMU 22.
This section contains general information as well as installation information for the GMU 22. Use this section to mount the GMU 22 unit. Installers may also benenfit from studying Appendix A, which provides guidance for installing the GMU 22 into specific experimental airframes.
Figure 8-1 GMU 22 Unit View
8.1 Equipment Description
The Garmin GMU 22 Magnetometer is a remote mounted device that interfaces with a Garmin ADAHRS (GSU 25/73) to provide flight attitude and heading data for flight instrumentation.
An Attitude and Heading Reference System combines the functions of a Vertical Gyro and a Directional Gyro to provide measurement of Roll, Pitch, and Heading angles. The Garmin ADAHRS and magnetometer replace traditional rotating mass instruments.
Using long-life solid-state sensing technology, the GMU 22 Magnetometer uses magnetic field measurements to create an electronically stabilized AHRS.
The GMU 22 magnetometer provides magnetic information to support the function of the ADAHRS (GSU 25/73). The ADAHRS (GSU 25/73) provides operating voltage to the GMU 22 Magnetometer.
8.1.1 Interface Summary
The following is an interface summary for the GMU 22:
· GMU 22 to ADAHRS (GSU 25/73) Interface: Power, RS-232, RS-485 (19,200 baud)
8.2 General Specifications
See Section 2.2 for power/current specifications, and Section 2.4.1 for dimension/weight specifications.
190-01115-01 Rev. K
G3X Installation Manual - GMU 22 Installation Page 8-1
8.3 Equipment Available
Table 8-1 GMU 22 Part Numbers
Model GMU 22
Assembly Part Number
010-01196-00
Unit Only Part Number
011-03269-00
Installation Rack No
Table 8-2 GMU 22 Accessories
Item
Garmin P/N
Quantity
GMU 22, Connector Kit
011-00871-10
1
GMU 22 Universal Mount*
011-01779-01
1 (optional)
Installation Rack, GMU 22
115-00481-10
1
*Refer to AHRS Magnetometer Installation Considerations (190-01051-00) from www.garmin.com
Table 8-3 Contents of GMU 22 Connector Kit (011-00871-10)
Item Modified Install Rack Screw, 6-32x .250, Pan Head Phillips, Brass, w/Nylon Circular Connector, Female, 9 Ckt Circular non-Magnetic Backshell Socket Contact Mil Crp, Size 20
Garmin P/N 115-00481-10 211-60037-08 330-00360-00 330-90005-01 336-00022-00
Quantity 1 3 1 1 10
8.4 Unit Installation
The following guidelines describe proper mechanical installation of the Garmin GMU 22 Magnetometer. The guidelines include requirements for proper location selection in the aircraft, requirements for supporting structure and mechanical alignment and restriction on nearby equipment.
Fabrication of a wiring harness is required. Sound mechanical and electrical methods and practices are required for installation of the GMU 22. Refer to Section 2.3 for wiring considerations and to Section 15 for pinouts.
The GMU 22 is an extremely sensitive three-axis magnetic sensor. It is more sensitive to nearby magnetic disturbances than a flux gate magnetometer. For this reason, when choosing a mounting location for the GMU 22, observe the following distances from objects or devices that can disturb the magnetic field. Table 8-4 specifies required distances from magnetic disturbances for GMU 22 location.
NOTE
If the requirements listed in Table 8-4 cannot be met, a magnetometer interference test must be performed to ensure proper operation of the G3X system. Refer to the AHRS/ Magnetometer Installation Considerations document (190-01051-00) available from the Garmin website (www.garmin.com).
G3X Installation Manual - GMU 22 Installation Page 8-2
190-01115-01 Rev. K
Table 8-4 Required Distance from Magnetic Disturbances
Disturbance Source
Electric motors and relays, including servo motors Ferromagnetic structure greater than 1 kg total (iron, steel, or cobalt materials, especially landing gear structure) Ferromagnetic materials less than 1 kg total, such as control cables Any electrical device drawing more than 100 mA current Electrical conductors passing more than 100 mA current [(must be twisted shielded pair if within 10 feet (3.0 meters)] Electrical devices drawing less than 100 mA current Magnetic measuring device (e.g. installed flux gates, even if unpowered) Electrical conductors passing less than 100 mA current [(must be twisted shielded pair if within 10 feet (3.0 meters)]
Minimum Distance from GMU 22
10 feet (3.0 meters)
8.2 feet (2.5 meters)
3 feet (1.0 meter) 3 feet (1.0 meter)
3 feet (1.0 meter)
2 feet (0.6 meter) 2 feet (0.6 meter)
1.3 feet (0.4 meter)
Ensure that any electrical conductor that comes within 10 feet (3.0 meters) of the GMU 22 is installed as a twisted shielded pair, not a single-wire conductor. (If possible, the shield should be grounded at both ends.)
Use nonmagnetic materials to mount the GMU 22, and replace any magnetic fasteners within 0.5 meter with nonmagnetic equivalents (e.g. replace zinc-plated steel screws used to mount wing covers or wing tips with nonmagnetic stainless steel screws).
In general, wing mounting of the GMU 22 magnetometer is preferred (unless as noted in Appendix A). Fuselage mounting is less desirable because of numerous potential disturbances that interfere with accurate operation.
Mechanical mounting fixtures for the GMU 22 must be rigidly connected to the aircraft structure. Use of typical aircraft-grade materials and methods for rigid mounting of components is acceptable, so long as adequate measures are taken to ensure a stiffened mounting structure.
Level the GMU 22 mounting rack to within 3.0° of the in-flight level cruise attitude.
Align the GMU 22 mounting rack's forward direction to within 0.5° of the longitudinal axis of the aircraft.
In a system with more than one ADAHRS (GSU 25/73), ADAHRS 1 must be connected to a GMU22, but installing additional GMU 22 units for other GSU 25 ADAHRS units is optional. An ADAHRS without a GMU 22connected will use magnetometer data supplied by other ADAHRS as long as they are both communicating via CAN.
190-01115-01 Rev. K
G3X Installation Manual - GMU 22 Installation Page 8-3
8.4.1 Consideration for Wing Grounded Lighting Fixtures
The following installation practices are recommended if the required GMU 22 mounting bracket is located in the wing.
The wing tip lights should not have a power ground referenced to the chassis of the light assembly that would then be referenced back to the airframe ground via the light assembly mounting.
A dedicated power ground should be used and returned as a twisted pair with the power source back into the fuselage for a wing mounted GMU 22.
These installation practices will prevent magnetically interfering currents from flowing in the wing skin that encloses the GMU 22. Electrically isolating the light assembly should not be used as an alternative to item 1 above, unless the isolated light assembly has been analyzed for adequate protection against direct attachment of lightning.
Refer to Figure B-7.1 for outline and installation drawings.
8.4.2 ADAHRS (GSU 25/73) to GMU 22 Interconnect Harness Fabrication Instructions
Table 8-5 lists parts needed for the GMU 22 interconnect harness. Some of the parts for installation are included in the GMU 22 Connector Installation Kit. Other parts are provided by the installer. Reference numbers refer to item bubble numbers shown in Figure B-7.4.
Table 8-5 Parts Needed for GMU 22 Installation
Figure D-2.4 Ref
Description
Qty. Included
1
Shield Termination (method optional)
0
2
Shield Extension Wire
0
3, 4, 9
GMU 22 Connector Kit*
1
5
3-Conductor Cable
0
6
2-Conductor Cable
0
*Included in G3X w/GSU 73 Installation Kit (K10-00017-00)
GPN or MIL Spec
Parts used depend on method chosen
M22759/16-22 011-00871-00 M27500-22TE3T14 M27500-22TE2T14
Table 8-6 lists material in the GMU 22 connector kit and the associated reference number, as shown in Figure B-7.4. The GMU 22 magnetometer has an attached pigtail with male polarity. The harness connector for the GMU 22 has female polarity.
Table 8-6 GMU 22 Connector Kit (011-00871-00)** Contents, Reference Figure B-7.4
Item
Garmin P/N
Quantity
Screw,6-32x.250,PHP,BR,w/Nyl
211-60037-08
3
Conn,Circular,Female,9 Ckt
330-00360-00
1
Backshell,Circular,Kit,SS
330-90005-01
1
Cont,Sckt,Mil Crp,Size 20
336-00022-00
10
**Included in G3X w/GSU 73 Installation Kit (K10-00017-00)
Figure B-2.4 Ref 9 4 4 3
G3X Installation Manual - GMU 22 Installation Page 8-4
190-01115-01 Rev. K
8.4.3 Mounting Instructions After evaluation of the mounting location has been completed and ensuring that requirements are met, assemble the GMU 22 mounting plate kits according to the dimensions given in Figure B-7.1. Install the unit assemblies. Mount the GMU 22 to its mounting plate, taking care to tighten the mounting screws firmly. Use of nonmagnetic tools (e.g. beryllium copper or titanium) is recommended when installing or servicing the GMU 22. Do not use a screwdriver that contains a magnet when installing or servicing the GMU 22. The metal components in the GMU 22 connector may slightly affect the magnetic field sensed by the GMU 22. Place the connector at least 2 inches from the body of the GMU 22 to minimize this effect. After attaching the GMU 22's connector to its mate in the aircraft wiring, secure the connector in place using good installation practices. This will ensure that any remaining magnetic effect can be compensated for using Calibration Procedure D: Magnetometer Calibration (Section 19.3.4). See Figure 8-2 for minimum recommended clearance for bend radius of the GMU 22 cable.
NOTE
If the GMU 22 is ever removed, the anti-rotation properties of the mounting screws must be restored. This may be done by replacing the screws with new Garmin part number 211-60037-08. If original screws must be re-used, coat screw threads with Loctite 242 (blue) thread-locking compound, Garmin part number 291-00023-02, or equivalent. Important: Mounting screws must be brass.
MINIMUM RECOMMENDED CLEARANCE FOR MINIMUM BEND RADIUS OF THE GMU 22 CABLE IS 1.57[40] FROM THE GMU 22 SURFACE
1.57 40
Figure 8-2 GMU 22 Minimum Recommended Clearance
190-01115-01 Rev. K
G3X Installation Manual - GMU 22 Installation Page 8-5
8.5 Environmental Specifications
Table 8-7 lists general environmental specifications.
Table 8-7 GMU 22 Environmental Specifications
Specification Regulatory Compliance Operating Temperature Range Altitude
Characteristic RTCA/DO-160D Environmental Conditions and EUROCAE/ED-14D
-55° C to +70° C 55,000 Feet
Maintenance of the GMU 22 is `on condition' only. Periodic maintenance of the GMU 22 is not required.
G3X Installation Manual - GMU 22 Installation Page 8-6
190-01115-01 Rev. K
9 GSA 28 INSTALLATION/CONFIGURATION (OPTIONAL LRU)
This section contains general information as well as installation information for the GSA 28 Servo Actuator. Use this section to mount the GSA 28 unit.
9.1 Equipment Description
NOTE
There is no TSO/ETSO applicable to the GSA 28.
The GSA 28 servo is an autopilot servo intended for use in non FAA certified aircraft, including light sport and home-built aircraft. The servo is intended to be used as part of the G3X system.
The function of the GSA 28 is to drive a flight-control axis (pitch, roll) of the aircraft. The servo can also be installed in the rudder control system to provide yaw damping. Trim servo drive support is available for any axis. All configurations can be used with or without auto-trim in each axis.
· Roll autopilot only · Pitch/roll autopilot · Pitch/roll autopilot with yaw damper
The GSA 28 servo features an advanced brushless DC motor and gearbox, with an engagement clutch to allow for very low-friction operation of the aircraft flight controls with clutch disengaged. The GSA 28 performs continuous internal monitoring and fault detection, and can also safely be back-driven by the pilot in the event of an engagement clutch fault condition. An advanced electronic slip clutch provides the ability for the pilot to overpower the servo at a configurable torque threshold without requiring use of a consumable shear pin or additional moving parts.
NOTE
The GSA 28 engagement clutch is actuated by an internal solenoid. An audible clicking sound when the servo is engaged or disengaged is normal and expected.
Under normal conditions, the GSA 28 servo operates based on flight director commands from the G3X display units (GDU 370/375). When used with the optional GMC 305 mode controller, the GSA 28 maintains a reversionary capability to engage and fly the aircraft in basic wings-level and altitude-hold modes even if all GDU displays in the aircraft are unavailable.
190-01115-01 Rev. K
Figure 9-1 GSA 28 Unit View
G3X Installation Manual - GSA 28 Installation Page 9-1
9.1.1 Status LED The GSA 28 has an LED on its outer case that indicates its current status. The status indications are:
Table 9-1 Status LED Indications
LED Indication No Light Steady Green Flashing Green Red
Alternating Red/Green
Status No Power On, but not communicating via CAN Bus On and communicating via CAN Bus Hardware Fault CAN bus network error two similar devices are configured with the same unit ID
9.2 Equipment Available
Table 9-2 GSA 28 Part Numbers
Model GSA 28 Servo Actuator, Unit Only
Assembly Part Number 010-01068-00
Unit Only Part Number 011-02927-00
9.3 General Specifications
Table 9-3 General Specifications
Characteristic Height Width Depth Weight
*Harness connector not included **Accessories not included
Specification 4.0 inches (10.16 cm) 2.5 inches (6.35 cm) 2.8* inches (7.11 cm) 1.40** lbs, (0.635 kg)
9.3.1 Power Specifications
The trim outputs are capable of sourcing a maximum of 1 Amp of current to drive a brushed DC motor. The trim outputs drive a maximum output voltage of 12 Vdc.
The GSA is compatible with 14 Vdc trim systems only. Do not connect the GSA 28 to a 28 Vdc trim system.
Table 9-4 GSA 28 Power Specifications
Supply Voltage 14 Vdc without Auto-trim 28 Vdc without Auto-trim
14 Vdc with Auto-trim
Current Draw 0.36 Amp (typical), 1.80 Amp (max) 0.20 Amp (typical), 1.00 Amp (max) 0.36 Amp (typical), 2.80 Amp (max)
G3X Installation Manual - GSA 28 Installation Page 9-2
190-01115-01 Rev. K
9.3.2 Torque Specifications Table 9-5 GSA 28 Torque Specifications
Characteristic Maximum Rated Torque
Specification 60 in-lbs
9.4 Required Equipment
Table 9-6 lists the kits available for the GSA 28. Table 9-6 GSA 28 Available Equipment
Item GSA 28 Connector Kit GSA 28 Stop Bracket Kit GSA 28 Mounting Kit, Generic, Push-Pull GSA 28 Mounting Kit, Generic, W/Bracket GSA 28 Mounting Kit, Generic, Capstan GSA 28 Mounting Kit, RV-6 Roll GSA 28 Mounting Kit, RV-4/8 Pitch GSA 28 Mounting Kit, RV-7/8/10 Roll GSA 28 Mounting Kit, RV-9 Roll GSA 28 Mounting Kit, RV-6/7/9 Pitch GSA 28 Mounting Kit, RV-10 Pitch GSA 28 Removal Adapter
Garmin P/N 011-02950-00 011-02951-00 011-02952-00 011-02952-01 011-02952-02 011-02952-10 011-02952-11 011-02952-12 011-02952-13 011-02952-14 011-02952-15 011-03158-00
Table 9-7 Contents of Connector Kit (011-02950-00)
Item Sub-Assy, Bkshl w/Hdw, Jackscrew, 15/26 Pin Connector, Rcpt, D-SUB, Crimp Socket,Commercial,15 Ckt Cont,Sckt,Mil Crp,Size 20,20-24 AWG,RoHS
Garmin P/N 011-01855-01 330-00625-15 336-00022-02
9.4.1 Additional Equipment Required
· Cables: The installer will fabricate and supply all system cables. · Mounting hardware is included in the available mounting kits.
Quantity 1 1 16
190-01115-01 Rev. K
G3X Installation Manual - GSA 28 Installation Page 9-3
9.5 Unit Installation
Fabrication of a wiring harness is required. Sound mechanical and electrical methods and practices should be used for installation of the GSA 28. Refer to Section 2.3 for wiring considerations, and to Section 15 for pinouts.
Connector kits include backshell assemblies. Garmin's backshell connectors give the installer the ability to quickly and easily terminate shield grounds at the backshell housing. The instructions needed to install the Jackscrew Backshell, Configuration Module, and Thermocouple are located in Section 16.
9.5.1 Pinouts
See Section 15.6 for pinout information.
9.5.2 Mounting Requirements
WARNING
It is vital to ensure the autopilot servo and aircraft control linkage is free to move throughout its entire range of travel without binding or interference. Failure to ensure adequate clearance between the moving parts of the control system linkage and nearby structure could result in serious injury or death. If any control system binding or interference is detected during installation or preflight inspection, it must be corrected before flight.
9.5.2.1 Optional attachments
The GSA 28 is supplied from the factory with a standard crank arm attachment (Figure 9-2, Figure 9-6.1, Figure 9-6.2, and Figure 9-6.3). Also available are a long crank arm supplied in the 011-02952-10 RV-6 roll kit and a capstan attachment available in the 011-02952-02 Capstan Kit. If one of these optional attachments will be used, it is up to the installer to remove the standard crank arm and replace it with the optional attachment. When removing the standard arm, keep the castle nut, lock washer, and flat washer as these items will need to be re-used with the optional attachment. Discard cotter pin that was removed from the GSA 28 and replace with pin provided with optional attachment. Refer to Figure 9-6.3 and Figure 96.4 for more details and instructions for tightening the castle nut.
WARNING
Cotter pins supplied with GSA 28 are only intended for one time use. If removed from GSA 28 discard and use new cotter pin.
G3X Installation Manual - GSA 28 Installation Page 9-4
190-01115-01 Rev. K
CRANK ARM
Figure 9-2 Crank Arm Assembly
9.5.2.2 Stop Bracket Kit
Every GSA 28 is supplied with a 011-02951-00 stop bracket kit. The intention of this stop bracket is to create redundant stops for the servo control arm that prevents the servo's arm from going over-center relative to the push rod connected to the servo's arm. It is highly recommended this part gets installed with every push-pull application. The stops created by installing this bracket are redundant in the sense that the aircraft's built-in stops should always be used as the primary means of limiting travel of the servo's control arm. This stop bracket limits the motion of the standard control arm to 100° total travel. This bracket should be positioned such that the stop bracket flanges are as close as practical to being equal distance from the servo's control arm while at the center of travel. Also, to prevent an over-center condition, the servo's push rod should be as close as practical to perpendicular with the servo's control arm while positioned at the center of travel. The position of this bracket can be adjusted in increments of 15°. If necessary, further adjustments can be made by changing the length of the push rod connected to the servo. See Figure 9-6.2, and Figure 9-6.3 for more details.
After installation of the servo is complete, verify that the stop bracket does NOT impede the full movement of the associated control.
WARNING
An over-center position of the servo control arm relative to the attached push rod can cause the flight controls to jam. This could result in serious injury or death. Please be sure this is well understood prior to flying with the GSA 28 servo.
190-01115-01 Rev. K
G3X Installation Manual - GSA 28 Installation Page 9-5
The 011-02951-00 stop bracket kit is supplied with four #4-40 screws used to attach the bracket to the front face of the servo. The screws provided are 0.25" long. This length of screw is appropriate if there is no bracket or spacers in-between the stop bracket and servo. If a mounting bracket or spacers of thickness .040" or greater will be place in-between the stop bracket and servo, longer screws should be used to mount the stop bracket. It is recommended the thread engagement into the GSA 28, as measured from the front face of the servo shall be 0.112" 0.25". If screws other than what is provided will be used, be sure to use thread locking compound or a proper thread locking patch combined with the lock washers provided. Also be sure to follow the recommended tightening torque specified in Figure 9-6.2.
CAUTION
If screws are being used to mount the stop bracket to the front face of the GSA 28 are different than the screws provided with the stop bracket kit, care must be taken to ensure these screws are not long enough to contact moving parts inside the GSA 28. Maximum screw insertion, as measured from the front of the GSA 28, must be less than 0.25" to avoid contact with parts inside the GSA 28.
CAUTION
To avoid the possibility of contaminating the internal rotating mechanisms of the GSA 28, do not apply thread locking compound directly to the stop bracket attachment holes in the front face of the servo. Instead, apply a small amount of thread locking compound to the threads of the stop bracket screws before the screws are inserted. Thread locking compound is not required upon initial installation of the included stop bracket screws, which are supplied with thread locking compound already applied.
9.5.2.3 Trim Motor Interface
The GSA 28 provides an optional interface between the pilot's electric trim switch and a 14 Vdc trim motor. When the GSA 28 servo is engaged (i.e. autopilot on), it automatically drives the connected trim motor as required to relieve control forces for the associated pitch, roll, or yaw axis. When the GSA 28 servo is not engaged (i.e. autopilot off), it provides manual electric trim (MET) functionality by running the trim motor in response to pilot input. The GSA 28 can be configured to automatically reduce the speed of the trim motor at higher airspeeds, in order to provide finer control of trim tab position. In the event that power to the GSA 28 is removed, a fail-safe system connects the trim input switch directly to the trim motor. In this condition, the trim switch powers the trim motor directly and the motor runs at its full speed when the switch is pressed. The same condition also occurs if a trim switch and motor are connected to the GSA 28, but the trim control function is disabled.
NOTE
The GSA 28 supports a single trim switch input only. For use with multiple trim switches (e.g. pilot and co-pilot), a third-party trim interface unit or relay board is required. See Figure C-1.6 for additional details.
G3X Installation Manual - GSA 28 Installation Page 9-6
190-01115-01 Rev. K
9.5.2.4 CWS/DISCONNECT
The CWS/DISCONNECT button is used to disengage the autopilot system. It can also optionally be used for autopilot engagement and control wheel steering (see section 9.14.1). The CWS/DISCONNECT input to all servos should be tied together and connected to a normally open momentary push button that connects to ground when pressed (see Figure C-1.5).
NOTE
The CWS/DISCONNECT button must be mounted where it is easily accessible to the pilot during all phases of flight. The pilot must have ability to quickly disconnect the autopilot under all circumstances.
9.5.2.5 GSA 28 Removal Adapter
The GSA 28 connector kit is shipped with a GSA 28 removal adapter (011-03158-00). This part is not intended to be installed with the GSA 28, but is used to replace the GSA 28 when the harness connector is un-plugged. The removal adapter contains an internal 120 Ohm resistor between pins 2 and 3 for CAN termination. It also contains shorts between pins 11 & 13 and 12 & 14 to pass through power for trim motors. The intention of this component is to allow operation of the CAN bus and trim motors when the servos are not plugged into the harness. It is recommended that a removal adapter is kept with each servo installation, in case the GSA 28 needs to be removed without losing functionality of the CAN bus and trim motors.
190-01115-01 Rev. K
Figure 9-3 Wiring Diagram For GSA 28 Removal Adapter G3X Installation Manual - GSA 28 Installation Page 9-7
9.5.2.6 GSA 28 Mounting Kits Garmin currently provides the mounting kits listed in Table 9-8 for the GSA 28 Servo:
Table 9-8 Mounting Kits
Garmin P/N
011-02952-00 011-02952-01 011-02952-02 011-02952-10
Description
Sub-Assy, GSA 28 Mounting Kit, Generic, Push-Pull Sub-Assy, GSA 28 Mounting Kit, Generic, W/Bracket Sub-Assy, GSA 28 Mounting Kit, Generic, Capstan Sub-Assy, GSA 28 Mounting Kit, RV-6 Roll
Mounting Bracket Included
No
Yes
No
Yes
011-02952-11 Sub-Assy, GSA 28 Mounting Kit, RV-4/8 Pitch
Yes
011-02952-12 Sub-Assy, GSA 28 Mounting Kit, RV-7/8/10 Roll
Yes
011-02952-13 Sub-Assy, GSA 28 Mounting Kit, RV-9 Roll
Yes
011-02952-14 Sub-Assy, GSA 28 Mounting Kit, RV-6/7/9 Pitch
Yes
011-02952-15 Sub-Assy, GSA 28 Mounting Kit, RV-10 Pitch
Yes
Install Manual Figures
9-6.7 9-6.8 9-6.4 9-7.1, 9-7.2, 9-7.3 9-8.1, 9-8.2, 9-8.3, 9-8.4 9-9.1, 9-9.2 9-10.1, 9-10.2 9-11.1, 9-11.2 9-12.1, 9-12.2
The "generic" kits listed in Table 9-8 (011-02952-00, -01, & -02) are not specific to any airframe. The airframe specific kits (GPN 011-02952-10 through -15) are for use with the specified experimental aircraft. The contents of each kit as well as specific instructions for their use are detailed in the figures listed in Table 9-8.
G3X Installation Manual - GSA 28 Installation Page 9-8
190-01115-01 Rev. K
9.5.2.7 Generic Push/Pull Kits
The 011-02952-00 and -01 kits are generic kits for push/pull applications. This kit is supplied with a 3/8" diameter x 8" long solid rod (Figure 9-4). This rod is intended to be used as the attachment link between the GSA 28 and the flight control system. It is the installer's responsibility to cut this rod to the correct length and tap the ends for the male rod end bearings. It is recommended these push rods are tapped to a depth of at least 0.61" to accommodate the entire thread of the rod end bearing (minus the jam nut). The length of the push rod is adjustable by changing the thread engagement between the male rod end bearings and push rod. The acceptable range of thread engagement is 0.492" +/-0.117". It is highly recommended the AN315-3R jam nuts are used and properly tightened. A push rod without a tightened jam nut will create backlash that can diminish autopilot performance.
WARNING
Thread engagement between the male rod end bearings supplied with GSA 28 mounting kits and push rod must not be less than 0.375". This minimum engagement length is recommended to prevent push rod from coming apart.
1.25
.75 USABLE THREAD
.141
.492±.117 THREAD ENGAMENT
10-32 UNF-3A
AN315-3R JAM NUT
Figure 9-4 General Dimensions For Servo Push Rod And Rod End Bearings
190-01115-01 Rev. K
G3X Installation Manual - GSA 28 Installation Page 9-9
9.5.2.8 Capstan Kit
The 011-02952-02 is the capstan kit. This kit contains a capstan, a cable guard, and fasteners used to attach these items. The capstan was designed to accept a MS20663C2 double shank ball with a 1/16" diameter cable. This kit does not currently include a bridle cable or cable clamps necessary to link the capstan to the flight control cables. Contact Garmin if these items are needed for your application.
The 011-02952-02 capstan kit is provided with four #4-40 screws and lock washers for attaching the cable guard. The screws provided are 0.25" long. This length of screw is appropriate if there is no bracket or spacers in-between the cable guard and servo. If a mounting bracket or spacers of thickness .056" or greater will be place in-between the stop bracket and servo, longer screws should be used to attach the cable guard. It is recommended the thread engagement into the GSA 28, as measured from the front face of the servo shall be 0.112" 0.25". If screws other than what is provided will be used, be sure to use thread locking compound or a proper thread locking patch combined with the lock washers provided. Also be sure to follow the recommended tightening torque specified in Figure 9-6.4.
CAUTION
If screws are being used to mount the cable guard to the front face of the GSA 28 are different than the screws provided with the stop bracket kit, care must be taken to ensure these screws are not long enough to contact moving parts inside the GSA 28. Maximum screw insertion, as measured from the front of the GSA 28, must be less than 0.25" to avoid contact with parts inside the GSA 28.
9.5.2.9 Aircraft Specific Mounting Kits
GSA 28 mounting kits are available for several experimental airframes. These mounting kits are listed in Table 9-8. All of these kits contain sheet metal mounting brackets and push rods that have been designed for the specific application. The push rods are supplied cut to the appropriate length and tapped for the male rod end bearings provided. Overall push rod length as well as rod end bearing thread engagement length is provided on the drawings for each kit. The lengths specified are considered nominal. This length should be adjusted to fit the specific application. Ideal push rod length results in the push rod being perpendicular to the servo arm when it is at the center of travel.
It is recommended the stop bracket is installed with all push/pull applications. The drawings for each of these mounting kits shows the recommended orientation of this bracket. It is acceptable to deviate from these drawings if a better orientation has been determined by the installer. The best orientation results in the stop bracket flanges being equal distance from the servo arm when at the center of travel. See Section 9.5.2.2 on stop bracket kit for more details on mounting the stop bracket.
G3X Installation Manual - GSA 28 Installation Page 9-10
190-01115-01 Rev. K
9.5.2.10 GSA 28 Installation Into a Non-Garmin Bracket
For installers who intend to fabricate their own brackets or use an existing bracket designed for a nonGarmin servo, consider the following:
The geometry of the GSA 28 varies from other popular servo models.
While the GSA 28 has the same 2.5" x 4.0" footprint, the same mounting hole locations, and uses the same mounting bolts as several other popular brands of autopilot servo, it does not fit into all mounting brackets designed for other servos. Some of the key differences to consider are:
· The GSA 28 servo has a larger bushing protrusion on the front plane of the servo. · The harness connector is larger and in a different location relative to the output shaft. · The GSA 28 does not contain tapped holes for mounting, instead it uses through holes and a
thinner mounting flange.
Brackets fabricated for other manufacturer's servos may or may not have enough clearance for the large bushing protrusion. Modification to the bracket may be necessary to avoid interference with bushing protrusion. See Figure 9-5 for details.
CAUTION
Damage may occur to the GSA 28 if the mounting bracket overlaps the bushing protrusion when tightening down the mounting bolts. The damage can occur when the bushing is displaced into the unit. To prevent damage, ensure there is clearance for the bushing protrusion and be sure the GSA 28 mounting plate is flush with the bracket when the mounting bolts are being tightened.
For RV-7/8/9/10 roll installations, the rear support bracket used with other popular servos is not compatible with the GSA 28. This is because of the difference in thickness of the GSA 28 mounting flange relative the other servos.
Refer to Figure 9-6.1 for GSA 28 outline dimensions. See Figure 9-6.5 for recommended bracket cutout dimensions.
NOTE
Garmin cannot validate the structural integrity of non-Garmin brackets.
Mounting brackets provided in the Garmin GSA 28 mounting kits have been designed to withstand (and have been tested to) repetitive stress cycles endured during loads generated by the GSA 28 and aircraft vibrations. If using a non-Garmin mounting bracket, it is the installer's responsibility to ensure the bracket is structurally adequate for the application. It is important to consider the detrimental effects of bracket displacement and potential for fatigue failures due to reaction forces created by the GSA 28 loading and aircraft vibration.
WARNING
If using a non-Garmin mounting bracket, it is the installer's responsibility to ensure the bracket is structurally adequate for the application.
190-01115-01 Rev. K
G3X Installation Manual - GSA 28 Installation Page 9-11
Figure 9-5 Non-Garmin GSA 28 Bracket
G3X Installation Manual - GSA 28 Installation Page 9-12
190-01115-01 Rev. K
9.5.3 Unit Mounting
For final installation and assembly, refer to the outline and installation drawings Figure 9-6.1 through Figure 9-12.2.
9.6 Unit Wiring
Refer to the Appendix C-1.5 interconnect drawing for connecting GSA 28 wiring.
9.7 Environmental Specifications
Table 9-9 lists general environmental specifications.
Table 9-9 GSA 28 Environmental Specifications
Characteristic Aircraft Pressure Altitude Range Unit Operating Temperature Range
Specification -1,400 feet to 30,000 Feet
-45°C to +70°C
9.8 Maintenance
The GSA 28 requires no maintenance.
9.9 Outline and Installation Drawings
Refer to the following figures for GSA 28 installation guidance.
190-01115-01 Rev. K
G3X Installation Manual - GSA 28 Installation Page 9-13
LED STATUS LIGHT
P281
GSA28 STANDARD CENTER OF SEE NOTE 5
MOUNTING FLANGE
THICKNESS
CENTER OF SEE NOTE 5
DETAIL A
CENTER OF SEE NOTE 5 A
Figure 9-6.1 GSA 28 Outline/Installation Drawing 011-02927-00
G3X Installation Manual - GSA 28 Installation Page 9-14
190-01115-01 Rev. K
190-01115-01 Rev. K
GSA28 STANDARD ACESSORIES
GSA28 UNIT
BACKSHELL D-SUB CONNECTOR
GSA28 CONNECTOR KIT 011-02950-00
Figure 9-6.2 GSA 28 Accessory Installation Drawing
G3X Installation Manual - GSA 28 Installation Page 9-15
GSA28 STOP BRACKET KIT 011-02951-00 SEE NOTE 1
STOP BRACKET
011-01855-01
ITEMS INCLUDED IN 011-02950-00 DESCRIPTION
1 1
50
Figure 9-6.3 GSA 28 Crank Arm Attachments Drawing
G3X Installation Manual - GSA 28 Installation Page 9-16
CRANK ARM
STANDARD CRANK ARM
A B C
GSA28 CRANK ARM ATTACHMENTS
PUSH ROD SEE NOTE 2
SEE NOTE 1
LONG CRANK ARM
SEE NOTE 9 SEE NOTE 8
SEE NOTE 1
BEARING ON OPPOSITE SIDE OF CRANK ARM AND AIRCRAFT ATTACHMENT
A
B
RECOMMENDED ANGLE BETWEEN PUSH ROD AND CRANK ARM IS 90 AT
C
MINIMUM THREAD ENGAGMENT BETWEEN ROD END BEARINGS AND
STOP BRACKET CAN BE RE-POSITIONED IN INCREMENTS OF 15
190-01115-01 Rev. K
STOP BRACKET
190-01115-01 Rev. K
Figure 9-6.4 GSA 28 with Capstan Kit and Cable Instructions (011-02952-02)
CABLE EXITING IN OPPOSITE DIRECTION SHOULD BE IN CENTER OF CABLE WRAP WHEN
IN EITHER
BALL
GSA28 WITH CAPSTAN KIT 011-02952-02
BOTH CABLES EXITING CAPSTAN IN SAME DIRECTION ROTATE A MAXIMUM OF 150 EITHER DIRECTION FROM
2 BALL
1 5
SEE NOTE 2
ACCEPTABLE RANG
NOMINAL
FRONT OF FLANGE TO CENTER OF BALL
2
ITEM 1 2
5
ITEMS INCLUDED IN 011-02952-02 DESCRIPTION
1
1 GSA28 CABLE GUARD 1
PITCH
ACCEPTABLE RANGE
NOMINAL
G3X Installation Manual - GSA 28 Installation Page 9-17
CABLE GUARD CAN BE ROTATED TO ALLOW FOR ALTERNATE
FRONT PANEL MOUNTING
RECOMMENDED BRACKET CUTOUT DIMENSIONS
M AM M AL
A
BACK PANEL MOUNTING
Figure 9-6.5 GSA 28 Recommended Bracket Cutout Dimensions
G3X Installation Manual - GSA 28 Installation Page 9-18
190-01115-01 Rev. K
190-01115-01 Rev. K
RECOMMENDED GSA28 MOUNTING HARDWARE
SEE NOTE 2
Figure 9-6.6 GSA 28 Recommended Mounting Hardware
G3X Installation Manual - GSA 28 Installation Page 9-19
EXAMPLE MOUNTING BRACKET
BOLT AND WASHER ARRANGMENT SHOWN CAN BE USED WITH BRACKET
PARTS INCLUDED IN 011-02951-00 E
(FIG. 8-5.2 & FIG. 8-5.3) FOR MORE DETAILS
Figure 9-6.7 GSA 28 Generic, Push-Pull Mounting Kit (No Bracket) 011-02952-00
G3X Installation Manual - GSA 28 Installation Page 9-20
SEE NOTE 1
011-02952-00
GSA28 MOUNTING KIT, GENERIC, PUSH-PULL
2
(MOUNTING BRACKET NOT INCLUDED)
3 5
1 4
SEE NOTE 4
SEE NOTE 2
SEE NOTE 4
2 1 8
3
9
5 7
8
SEE NOTE 3
SEE NOTE 3
5
6
ITEM 1 2 3 4 5 6 7 8 9 10
GARMIN P/N 212-00080-03 382-00019-02 210-00116-03 117-00542-07 212-00035-10 211-00090-01 212-00043-10 210-00117-03 211-00090-05 231-00034-04
QTY DESCRIPTION 2 AN970-3 WASHER 2 MALE ROD END BEARING 2 AN315-3R JAM JUT 1 PUSH ROD, 8.0" UNTAPPED 9 AN960-10 WASHER 4 AN3-5A BOLT 1 AN960-10L (THIN) WASHER 5 AN365-1032A LOCK NUT 1 AN3-7A BOLT 1 COTTER PIN, MS24665-208
5
5
NOTES: 1. PUSH ROD (ITEM 4) IS SUPPLIED 8" LONG AND UNTAPPED. CUT TO DESIRED LENGTH
AND TAP #10-32 THREADS X .61" MIN DEEP IN EACH END. ALLOW ENOUGH LENGTH FOR THREAD ENGAMENT BETWEEN PUSH ROD (ITEM 4) AND ROD END (ITEM 2). ACCEPTABLE THREAD ENGAGMENT BETWEEN ITEM 2 AND 4 IS 0.492" .117". 2. IF COTTER PIN IS REMOVE FROM GSA28 CASTLE NUT, DISCARD COTTER PIN AND REPLACE WITH NEW COTTER PIN (ITEM 10) INCLUDED. 3. TIGHTEN AN365-1032A NUTS (ITEM 8) TO 34 - 46 IN-LBS (40 IN-LBS 15%). 4. TIGHTEN AN315-3R JAM NUTS (ITEM 3) TO 14 - 20 IN-LBS (17 3 IN-LBS).
190-01115-01 Rev. K
Figure 9-6.8 GSA 28 Generic, Push-Pull Mounting Kit w/Bracket 011-02952-01
190-01115-01 Rev. K
011-02952-01 GSA28 MOUNTING KIT, GENERIC, PUSH-PULL, W/BRACKET
1
2
5 10
3
7
SEE NOTE 4
4
SEE NOTE 4
5
3
5
2 1 5
8
SEE NOTE 3
5
8
SEE NOTE 3
G3X Installation Manual - GSA 28 Installation Page 9-21
6
ITEM GARMIN P/N QTY DESCRIPTION 1 212-00080-03 2 AN970-3 WASHER 2 382-00019-02 2 MALE ROD END BEARING 3 210-00116-03 2 AN315-3R JAM JUT 4 117-00542-07 1 PUSH ROD, 8.0" UNTAPPED 5 212-00035-10 9 AN960-10 WASHER 6 211-00090-01 4 AN3-5A BOLT 7 212-00043-10 1 AN960-10L (THIN) WASHER 8 210-00117-03 5 AN365-1032A LOCK NUT 9 115-01854-00 1 GSA28 MOUNTING BRAKCET, GENERIC 10 211-00090-05 1 AN3-7A BOLT 11 231-00034-04 1 COTTER PIN, MS24665-208
9
5
NOTES: 1. PUSH ROD (ITEM 4) IS SUPPLIED 8" LONG AND UNTAPPED. CUT TO DESIRED LENGTH
AND TAP #10-32 THREADS X .61" MIN DEEP IN EACH END. ALLOW ENOUGH LENGTH FOR THREAD ENGAMENT BETWEEN PUSH ROD (ITEM 4) AND ROD END (ITEM 2). ACCEPTABLE THREAD ENGAGMENT BETWEEN ITEM 2 AND 4 IS 0.492" .117". 2. IF COTTER PIN IS REMOVE FROM GSA28 CASTLE NUT, DISCARD COTTER PIN AND REPLACE WITH NEW COTTER PIN (ITEM 11) INCLUDED. 3. TIGHTEN AN365-1032A NUTS (ITEM 8) TO 34 - 46 IN-LBS (40 IN-LBS 15%). 4. TIGHTEN AN315-3R JAM NUTS (ITEM 3) TO 14 - 20 IN-LBS (17 3 IN-LBS).
Figure 9-7.1 GSA 28 RV-6 Roll Mounting Kit 011-02952-10 (page 1 of 3)
G3X Installation Manual - GSA 28 Installation Page 9-22
ITEM GARMIN P/N QTY DESCRIPTION 1 231-00037-04 1 COTTER PIN, MS24665-208
NOTES: 1. DIMENSIONS: INCHES
2 115-01738-01 1 GSA28 CRANK ARM, LONG
2. DIMENSIONS ARE NOMINAL AND TOLERANCES ARE NOT IMPLIED UNLESS SPECIFICALLY STATED.
3 211-00090-05 1 AN3-7A BOLT
3. GSA28 IS PROVIDED WITH STANDARD CRANK ARM. FOR THE RV-6 ROLL INSTALLATION, THIS PART
4 211-00090-16 1 AN3-21A BOLT 5 212-00080-03 2 AN970-3 WASHER 6 212-00035-10 10 AN960-10 WASHER 7 211-00090-01 4 AN3-5A BOLT
MUST BE REMOVED AND REPLACED WITH THE LONGER ARM (ITEM 2). 4. CASTLE NUT, 5/16 LOCK WASHER, AND AN960 516L WASHER ARE NOT INCLUDED IN SERVO MOUNTING
KIT. THESE PARTS ARE INCLUDED WITH GSA28 AND MUST BE RE-USED. 5. TO INSTALL LONG CRANK ARM: REMOVE COTTER PIN, CASTLE NUT, 5/16 LOCK WASHER, AN960-516L
WASHER, AND STANDARD CRANK ARM. INSTALL LONG ARM SUCH THAT HOLE AND SLOT MATE WITH
8 115-01854-01 1 RV-6 ROLL BRACKET
ALIGNMENT PINS ON GSA28 OUPUT HUB. REPLACE CASTLE NUT, LOCK WASHER, AND AN960-516L
9 213-00093-02 1 SPACER, .192' x .375" x .600" LNG 10 115-01854-02 1 RV-6 ROLL SUPPORT PLATE
WASHER. TIGHTEN CASTLE NUT UNTIL LOCK WASHER IS FULLY COMPRESSED, BUT DO NOT TIGHTEN TO MORE THAN 20 IN-LBS. THEN LOOSEN UNTIL ADJACENT CASTELLATION LINES UP WITH HOLE IN OUTPUT
15
11 211-A0102-02 4 NAS517-2-2 FLAT HEAD SCREW
SHAFT. INSTALL NEW COTTER PIN (SUPPLIED IN MOUNTING KIT).
12 212-00035-08 13 212-00043-10 14 210-00117-03 15 210-00117-02
4 AN960-8 WASHER 1 AN960-10L (THIN) WASHER 6 AN365-1032A LOCK NUT 4 AN365-832A LOCK NUT
6. UNLESS OTHERWISE SPECIFIED, TIGHTEN ALL AN365-1032A NUTS (ITEM 6) TO 34 - 46 IN-LBS (40 IN-LBS 15%). 7. TIGHTEN ALL AN315-3R JAM NUTS (ITEM 17) TO 14 - 20 IN-LBS (17 3 IN-LBS). 8. TIGHTEN #4-40 SCREWS USED TO ATTACH STOP BRACKET TO 8 1 IN-LBS. 9. TIGHTEN AN365-832A (ITEM 15) LOCK NUTS TO 20 3 IN-LBS. 10. STOP BRACKET SHOULD NOT BE USED AS THE PRIMARY MEANS OF LIMITING MOTION. THE AIRFRAME'S
16 382-00019-12 2 MALE ROD END BEARING
STOPS SHOULD LIMIT MOTION BEFORE THE SERVO CRANK ARM CONTACTS THE STOP BRACKET.
17 210-00116-03 2 AN315-3R JAM NUT
11. THREAD ENGAMENT BETWEEN ROD END BEARINGS (ITEM 16) AND ALUMINUM PUSH ROD (ITEM 18) MUST
18 117-00542-06
1 PUSH ROD, 3/8" DIA, 7.50" LNG, TAPPED
NOT BE LESS THAN 0.375". 12. AN3-21A BOLT (ITEM 4) ATTACHES PUSH ROD TO CONTROL STICK. SEE SHEET 2 FOR DETAILS.
13. PUSH ROD DIMENSIONS SHOWN IS APPROXIMATE.
12
SEE NOTES 3 & 5
1
2
5/16 SPLIT LOCK WASHER GPN: 212-00018-08 SEE NOTE 4
AN310-5 CASTLE NUT GPN: 210-00050-01 SEE NOTE 4
AN960-516L WASHER GPN: 212-00043-31 SEE NOTE 4
16
17 18
8
6 7
6 5
3
7
6
SEE DETAIL A
9
011-02951-00 STOP BRACKET KIT (INCLUDED WITH GSA28) SEE NOTES 8 & 10
4
10
SEE NOTE 12
17
16
13 5
6
11
6 12
13 14
13
13 6
190-01115-01 Rev. K
DETAIL A
SCALE 1:1
(.523)
(.523)
SEE NOTE 11
SEE NOTE 11
11
8.95 SEE NOTE 13
190-01115-01 Rev. K
Figure 9-7.2 GSA 28 RV-6 Roll Mounting Kit 011-02952-10 (page 2 of 3)
NOTES: 1. PUSH ROD CONNECTS DIRECTLY TO CONTROL STICK. REPLACE EXISING BOLT WITH
AN3-21A BOLT PROVIDED. TIGHTEN PER AIRFRAME MANUFACTURER'S SPECIFICATION.
B
G3X Installation Manual - GSA 28 Installation Page 9-23
DETAIL B SCALE 1 : 1
9 6
AN3-21A BOLT (ITEM 4) SEE NOTE 1
14 5
Figure 9-7.3 GSA 28 RV-6 Roll Mounting Kit 011-02952-10 (page 3 of 3)
G3X Installation Manual - GSA 28 Installation Page 9-24
15 4
12 4
8
NOTES: 1. ATTACH MOUNTING BRACKET TO FLOOR AS SHOWN USING SUPPORT PLATE WITH #8 FLAT HEAD
SCREWS, WASHERS, AND NUTS PROVIDED OR USE MS21055 CORNER NUT PLATES (NOT INCLUDED). 2. MATCH DRILL THROUGH FLOOR FOR #8 SCREWS ONCE BRACKET LOCATION HAS BEEN DETERMINED. 3. DIMENSION SHOWN IS APPROXIMATE. IT IS HIGHLY RECOMMENDED SERVO WITH BRACKET AND
PUSH ROD ARE PLACED THEN INTERFERENCE AND FREEDOM OF MOTION ARE VERIFIED PRIOR TO DRILLING MOUNTING HOLES THROUGH FLOOR. 4. PUSH TUBE CLEARANCE HOLES IN FLOOR RIBS MAY NEED TO BE TRIMMED TO CREATE MORE CLEARANCE FOR SERVO PUSH ROD.
10 11 4
C
C
CONTROL STICK SHOWN IN NEUTRAL POSITION
3.30 SEE NOTE 3
SECTION C-C
190-01115-01 Rev. K
190-01115-01 Rev. K
Figure 9-8.1 GSA 28 RV-4/8 Pitch Mounting Kit 011-02952-11 (page 1 of 4)
ITEM GARMIN P/N 1 210-00117-03 2 212-00035-10 3 211-00090-05 4 115-01854-03 5 211-00090-07 213-00093-03 6 213-00093-04 211-00090-01 7 211-00090-06 8 212-00080-03 9 115-01854-04 211-00090-08 10 211-00090-09 11 211-00090-13 12 382-00019-02 13 210-00116-03 14 117-00542-00 15 212-00043-10
QTY DESCRIPTION
RV-4 & PRE-SEPT 2006 RV-8 POST-SEPT 2006 RV-8
4 AN365-1032A LOCK NUT
X
X
10 AN960-10 WASHER
X
X
1 AN3-7A BOLT
X
X
1 RV-4/8 PITCH BRACKET, LEFT
X
X
1 AN3-11A BOLT
X
X
1 SPACER, .192x.375x.75 LNG
X
1 SPACER, .192X.375X.875 LNG
X
1 AN3-5A BOLT
X
1 AN3-6A BOLT
X
2 AN970-3 WASHER
X
X
1 RV-4/8 PITCH BRACKET, RIGHT
X
X
1 AN3-14A
X
1 AN3-15A BOLT
X
1 AN4-15A
SEE NOTE 5
X
2 MALE ROD END BEARING
X
X
2 AN315-3R JAM JUT
X
X
1 PUSH ROD, 3/8 DIA, 2.25" LNG, TAPPED
X
X
1 AN960-10L (THIN) WASHER
X
X
NOTES: 1. DIMENSIONS: INCHES. 2. DIMENSIONS ARE NOMINAL AND TOLERANCES ARE NOT IMPLIED UNLESS
SPECIFICALLY STATED. 3. HOLE MUST BE DRILLED THROUGH BELL CRANK TO ATTACH PUSH ROD.
SEE SHEET 2 FOR HOLE SIZE AND LOCATION. 4. SINGLE AN960-10 WASHER (ITEM 2) MUST BE PLACED IN-BETWEEN BELL
CRANK HALVES CONCENTRIC WITH DRILLED HOLES. 5. AN4-15A BOLT PROVIDED IS TO BE USED WITH POST-SEPT 2006 RV-8
ONLY. FOR RV-4 AND PRE-SEPT 2006 RV-8, USE BOLT PROVIDED WITH AIRFRAME KIT. 6. NUT AND WASHERS FOR AN4 BOLT ARE NOT PROVIDED IN GSA28 MOUNTING KIT. USE PARTS PROVIDED WITH AIRFRAME KIT. TIGHTEN PER AIRFRAME MANUFACTURER'S SPECIFICATION. 7. TIGHTEN ALL AN365-1032A NUTS (ITEM 1) TO 34 - 46 IN-LBS (40 IN-LBS 15%). 8. TIGHTEN ALL AN315-3R JAM NUTS (ITEM 13) TO 14 - 20 IN-LBS (17 3 IN-LBS). 9. THREAD ENGAGMENT BETWEEN ROD END BEARINGS (ITEM 12) AND ALUMINUM PUSH ROD (ITEM 14) MUST NOT BE LESS THAN 0.375".
3 15
1 2
SEE NOTE 6 2
2 5
SEE NOTE 3 SEE NOTE 4 2 SEE DETAIL A
2
12 13
4
14
13
12
DETAIL A 3.80
2 7
6
9
2
8 2 1
SEE NOTE 6
11 10
G3X Installation Manual - GSA 28 Installation Page 9-25
(.475) SEE NOTE 9
(.475) SEE NOTE 9
190-01115-01 Rev. K
G3X Installation Manual - GSA 28 Installation Page 9-26
Figure 9-8.2 GSA 28 RV-4/8 Pitch Mounting Kit 011-02952-11 (page 2 of 4)
GSA28 STOP BRACKET POSITION, RV-4/8 (ALL VERSIONS)
GSA28 STOP BRACKET KIT GPN: 011-02951-00 SUPPLIED WITH GSA28
POSITON STOP BRACKET AS SHOWN INSTALL STAR WASHERS (QTY 4) AND #4-40 SCREWS (QTY 4). TIGHTEN SCREWS TO 8 1 IN-LB.
BELL CRANK MODIFICATION, RV-4/8 (ALL VERSIONS)
.40
.192±.003
CLWARANCE HOLE
FOR AN3 BOLT
(#10 OR #11 DRILL SIZE)
2.00
RV-4 AND PRE-SEPTEMBER 2006 RV-8 INSTALLATION FORWARD
Figure 9-8.3 GSA 28 RV-4/8 Pitch Mounting Kit 011-02952-11 (page 3 of 4)
190-01115-01 Rev. K
G3X Installation Manual - GSA 28 Installation Page 9-27
Figure 9-8.4 GSA 28 RV-4/8 Pitch Mounting Kit 011-02952-11 (page 4 of 4)
G3X Installation Manual - GSA 28 Installation Page 9-28
POST-SEPTEMBER 2006 RV-8 INSTALLATION
A
DETAIL A SCALE 2 : 1
SEE NOTE 1
SEE NOTE 2
NOTES: 1. MATERIAL REMOVAL FROM BULKHEAD MAY BE NECESSARY
TO ALLOW BRACKETS TO SIT FLUSH AGAINST FLOOR RIBS. 2. ATTACH EACH MOUNTING BRACKETS (ITEMS 4 AND 9) TO FLOOR RIBS
USING (5) AN470 4-X RIVETS SPACES APPROX 1". RIVETS ARE NOT INCLUDED IN MOUNTING KIT.
190-01115-01 Rev. K
190-01115-01 Rev. K
Figure 9-9.1 GSA 28 RV-7/8/10 Roll Mounting Kit 011-02952-12 (page 1 of 2)
RV-7/8/10 RIGHT WING ROLL MOUNTING KIT FOR GSA28 GARMIN PART NUMBER 011-02952-12
1
2
PUSH ROD ASSEMBLY SEE DETAIL A
2
7
6
4 2
2 4 3
5 2
4 2
8 5 5 1
9
RIGHT WING AILERON BELL CRANK SEE SHEET 2 FOR REQUIRED MODIFICATION
G3X Installation Manual - GSA 28 Installation Page 9-29
13
2
1
1 2
1
11
011-02951-00 STOP BRACKET KIT (INCLUDED WITH GSA28 UNIT) SEE NOTE 5
10
ITEM GARMIN P/N QTY DESCRIPTION
1 210-00117-03 2 212-00035-10 3 115-01854-05 4 211-00090-01 5 212-00080-03 6 211-00090-05 7 115-01854-06 8 213-00093-02 9 211-00090-08 10 382-00019-02
5 AN365-1032A LOCK NUT 8 AN960-10 WASHER 1 ROLL BRACKET, RV-7, 8, 9, &10 3 AN3-5A BOLT 3 AN970-3 WASHER 1 AN3-7A BOLT 1 ROLL SUPPORT, RV-7, 8, 9, &10 1 SPACER, .192" x .375" x. 600" LNG 1 AN3-14A BOLT 2 MALE ROD END BEARING
11 210-00116-03 2 AN315-3R JAM NUT
12 117-00542-09 1 PUSH ROD, 3/8" DIA, 3.50" LNG, TAPPED
13 212-00043-10 1 AN960-10L (THIN) WASHER
NOTES: 1. DIMENSIONS: INCHES 2. DIMENSIONS ARE NOMINAL AND TOLERANCES ARE NOT IMPLIED
UNLESS SPECIFICALLY STATED. 3. TIGHTEN ALL AN365-1032A LOCK NUTS (ITEM 1) TO 34 - 46 IN-LBS
(40 IN-LBS 15%). 4. TIGHTEN AN315R JAM NUTS (ITEM 11) TO 14 - 20 IN-LBS
(17 3 IN-LBS). 5. TIGHTEN #4-40 SCREWS FOR STOP BRACKET TO 8 1 IN-LBS. 6. THREAD ENGAGMENT BETWEEN ROD END (ITEM 10) AND
ALUMINUM PUSH ROD (ITEM 12) MUST NOT BE LESS THAN .375".
12
DETAIL A 4.89
(.555) SEE NOTE 6
(.555) SEE NOTE 6
11
10
DETAIL B RECOMMENDED STOP BRACKET ORIENTATION
AILERON BELL CRANK MODIFICATION
BRACKET B
INBOARD
Figure 9-9.2 GSA 28 RV-7/8/10 Roll Mounting Kit 011-02952-12 (page 2 of 2)
G3X Installation Manual - GSA 28 Installation Page 9-30
190-01115-01 Rev. K
G3X Installation Manual - GSA 28 Installation Page 9-31
190-01115-01 Rev. K
Figure 9-10.1 GSA 28 RV-9 Roll Mounting Kit 011-02952-13 (page 1 of 2)
SEE DETAIL A
2 4
15
3
1
2 1
RV-9 RIGHT WING ROLL MOUNTING KIT GARMIN PART NUMBER 011-02952-13
2 5
1 7
6
4
2
2
4
8
9 2
2 4 8
6
1
11 2
10 2
2 1
12
011-02951-00 STOP BRACKET KIT (INCLUDED WITH GSA28) SEE NOTE 5
ITEM GARMIN P/N 1 210-00117-03 2 212-00035-10 3 115-01854-05 4 211-00090-01 5 115-01854-06 6 212-00080-03 7 211-00090-05 8 213-00093-01 9 115-01854-07 10 211-00090-15
11 211-00090-12 12 382-00019-02 13 210-00116-03 14 117-00542-09
15 212-00043-10
QTY DESCRIPTION 5 AN365-1032A LOCK NUT 10 AN960-10 WASHER 1 ROLL BRACKET, RV-7, 8, 9, &10 3 AN3-5A BOLT 1 ROLL SUPPORT, RV-7, 8, 9, &10 3 AN970-3 WASHER 1 AN3-7A BOLT 2 SPACER, .192" x .375" X .485" LNG 1 ROLL ATTACH PLATE, RV-9 1 AN3-13A BOLT
1 AN3-25A BOLT 2 MALE ROD END BEARING 2 AN315-3R JAM NUT 1 PUSH ROD, 3/8" DIA, 3.50" LNG, TAPPED
1 AN960-10L (THIN) WASHER
13
14
13
(.500) SEE NOTE 5
DETAIL A 5.00
(.500) SEE NOTE 5
12
NOTES: 1. DIMENSIONS: INCHES 2. DIMENSIONS ARE NOMINAL AND TOLERANCES ARE NOT IMPLIED
UNLESS SPECIFICALLY STATED. 3. TIGHTEN ALL AN365-1032A LOCK NUTS (ITEM 1) TO 34 - 46 IN-LBS
(40 IN-LBS 15%). 4. TIGHTEN AN315R JAM NUTS (ITEM 12) TO 14 - 20 IN-LBS
(17 3 IN-LBS). 5. TIGHTEN #4-40 SCREWS FOR STOP BRACKET TO 8 1 IN-LBS. 6. THREAD ENGAGMENT BETWEEN ROD END (ITEM 12) AND
ALUMINUM PUSH ROD (ITEM 14) MUST NOT BE LESS THAN .375".
RECOMMENDED STOP BRACKET ORIENTATION
INBOARD
Figure 9-10.2 GSA 28 RV-9 Roll Mounting Kit 011-02952-13 (page 2 of 2)
G3X Installation Manual - GSA 28 Installation Page 9-32
190-01115-01 Rev. K
FORWARD
Figure 9-11.1 GSA 28 RV-6/7/9 Mounting Kit 011-02952-14 (page 1 of 2)
190-01115-01 Rev. K
G3X Installation Manual - GSA 28 Installation Page 9-33
RECOMMDNED STOP BRACKET ORIENTATION
Figure 9-11.2 GSA 28 RV-6/7/9 Pitch Mounting Kit 011-02952-14 (page 2 of 2)
G3X Installation Manual - GSA 28 Installation Page 9-34
190-01115-01 Rev. K
190-01115-01 Rev. K
Figure 9-12.1 GSA 28 RV-10 Pitch Mounting Kit 011-02952-15 (page 1 of 2)
ITEM
1 2 3 4 5 6 7 8 9 10
11
GARMIN P/N
211-00090-01 212-00035-10 212-00080-03 115-01854-09 211-00090-05 210-00117-03 211-00090-07 382-00019-02 210-00116-03 117-00542-08
212-00043-10
QTY DESCRIPTION
4 AN3-5A BOLT 14 AN960-10 WASHER 2 AN970-3 WASHER 1 RV-10/14 PITCH BRACKET 1 AN3-7A BOLT 6 AN365-1032A LOCK NUT 1 AN3-11A BOLT 2 MALE ROD END BEARING 2 AN315-3R JAM NUT 1 PUSH ROD, 3/8 DIA, 3.25" LNG, TAPPED
1 AN960-10L (THIN) WASHER
5 11
2
3 2
1 4
FASTEN SERVO BRACKET
TO AIRFRAME PRIOR TO
2
INSTALLING SERVO.
SEE SHEET 2.
1
011-02951-00 STOP BRACKET KIT (INCLUDED WITH GSA28) SEE NOTES 7 & 8
8
9
10
9
8
2
6
2
6
2
3 6
2
SEE NOTE 4
G3X Installation Manual - GSA 28 Installation Page 9-35
4.69
7
(.531)
(.531)
SEE NOTE 9
SEE NOTE 9
2
NOTES: 1. DIMENSIONS: INCHES 2. DIMENSIONS ARE NOMINAL AND TOLERANCES ARE NOT IMPLIED UNLESS SPECIFICALLY STATED. 3. HOLE MUST BE DRILLED THORUGH BELL CRANK TO ATTACH PUSH ROD. SEE SHEET 2 FOR HOLE SIZE AND LOCATION. 4. SINGLE AN960-10 WASHER (ITEM 2) MUST BE PLACED IN-BETWEEN BELL CRANK HALVES CONCENTRIC WITH DRILLED HOLES. 5. TIGHTEN ALL AN365-1032A NUTS (ITEM 6) TO 34 - 46 IN-LBS (40 IN-LBS 15%). 6. TIGHTEN ALL AN315-3R JAM NUTS (ITEM 9) TO 14 - 20 IN-LBS (17 3 IN-LBS). 7. TIGHTEN #4-40 SCREWS TO 8 1 IN-LBS. 8. STOP BRACKET SHOULD NOT BE USED AS THE PRIMARY MEANS OF LIMITING MOTION. THE AIRFRAME'S STOPS SHOULD LIMIT MOTION
BEFORE THE SERVO CRANK ARM CONTACTS THE STOP BRACKET. 9. THREAD ENGAMENT BETWEEN ROD END BEARINGS (ITEM 8) AND ALUMINUM PUSH ROD (ITEM 10) MUST NOT BE LESS THAN 0.375".
Figure 9-12.2 GSA 28 RV-10 Pitch Mounting Kit 011-02952-15 (page 2 of 2)
G3X Installation Manual - GSA 28 Installation Page 9-36
.192±.003 CLEARANCE HOLE
FOR AN3 BOLT (#10 OR #11 DRILL SIZE)
2.50
SEE NOTES 1 & 2
NOTE: 1. MOUNTING BRACKET SHOUDL BE FASTENED TO AIRFRAME PRIOR TO INSTALLING SERVO. 2. HOLES IN SERVO MOUTING BRACKET ALIGN WITH EXISTING HOLES IN AIRFRAME. REMOVE
FASTENERS FROM THESE HOLES TO MOUNT BRACKET TO AIRFRAME. RE-USE THESE FASTENERS TO ATTACH SERVO BRACKET. TIGHTEN PER AIRFRAME MANUFACTURER'S SPECIFICATION.
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9.10 Post Installation Checkout
9.10.1 On Ground Initial Checkout
NOTE
The following post installation checkout must be followed after every completed installation. These steps should be followed when using a Garmin mounting kit or nonGarmin mounting parts to install the GSA 28.
After mounting the GSA 28, please complete the following steps prior to completing the first flight with the GSA 28.
1. Verify that the flight controls can move from stop to stop without binding or interference. Check that the GSA 28 output mechanism and added linkage do not come in contact with any part of the airframe while traveling though its full range of motion.
2. Verify that the travel of the flight controls is being limited by the airplane's primary stops and not the secondary stops provided by the GSA 28 stop bracket.
3. Ensure the structural integrity of the mounting bracket is adequate for the application and well secured to the airframe. Bracket deflection caused by normal servo loading and aircraft acceleration/vibration should be minimal. Also verify there are no cracks or sharp inside corners that could lead to fatigue failures.
4. Verify the fasteners used to mount the servo to the airframe are installed and have been tightened. 5. Make sure the AP DISC wire is correctly wired and tested. 6. If powering the servo through a "pullable" circuit breaker (recommended), ensure the circuit
breaker is both accessible and easily identifiable to the pilot. 7. Repeat steps 1-7 for all GSA 28 servos in the aircraft.
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G3X Installation Manual - GSA 28 Installation Page 9-37
9.11 General Autopilot Description (for configuration)
The GSA 28 based autopilot system is a fully integrated, high performance autopilot that can control up to three axes of an aircraft. Each GSA 28 servo is also capable of managing the trim control for its axis. The following four subsections (roll, pitch, yaw, and trim) are provided to aid the pilot/installer in understanding/configuring the Garmin GSA 28 autopilot system.
9.11.1 Roll Servo
All GSA 28 autopilot systems require a servo to control the roll axis of an aircraft. A single axis GSA 28 installation that controls only the roll axis is sometimes referred to as a "wing-leveler".
The roll servo follows roll steering commands from the G3X display so the airplane will hold a desired roll angle, follow a desired heading, or follow the lateral component of a flight plan.
During the flight test phase of the autopilot checkout, the roll servo aggressiveness will be adjusted to get the desired in-fight performance. The "Roll Servo Gain" setting is used to set the aggressiveness of the roll servo. A larger number will cause the roll servo to more aggressively control the aircraft, and a smaller number will cause the roll servo to less aggressively control the aircraft.
9.11.2 Pitch Servo
Most GSA 28 autopilot systems consist of both a roll and pitch servo allowing for full 2-axis control of the aircraft.
The pitch servo follows vertical guidance commands from the G3X display so the airplane will hold a desired pitch angle, vertical speed, airspeed, or altitude, and also follow the vertical component of a flight plan.
Vertical control of the aircraft is all based on controlling the pitch angle with two additional sub-modes for vertical speed and airspeed. What this means is that the basic pitch mode performance must be properly adjusted before changing settings that adjust the vertical speed and airspeed based modes.
NOTE
Ensure pitch mode functionality is properly adjusted before attempting to adjust vertical speed or airspeed mode performance
During the flight test phase of the autopilot checkout, the pitch servo aggressiveness will be adjusted to get the desired in-fight performance. The "Pitch Servo Gain" setting is used to set the aggressiveness of the pitch servo. A larger number will cause the pitch servo to more aggressively control the aircraft, and a smaller number will cause the pitch servo to less aggressively control the aircraft.
G3X Installation Manual - GSA 28 Installation Page 9-38
190-01115-01 Rev. K
9.11.3 Yaw Damper
The GSA 28 autopilot system can be expanded to support a yaw damper. A yaw damper will control the rudder to try and compensate or remove aircraft body yaw (tail wagging). The yaw damper will also try to null the lateral acceleration (center the ball) over the long term. The ball centering portion of the yaw damper is not a replacement for proper rudder trim.
NOTE
Yaw damper functionality requires a GMC 305 mode control panel.
During the flight test phase, the yaw damper is configured and set up after the basic two axis pitch and roll performance has been properly configured. This is done so the pilot can focus on properly adjusting the performance of each individual component of the autopilot system without trying to tune them all at once.
NOTE
Ensure basic autopilot functionality is properly adjusted before using the yaw damper.
During the flight test phase of the autopilot checkout, the yaw servo aggressiveness will be adjusted to get the desired in-fight performance. The "Yaw Servo Gain" setting is used to set the aggressiveness of the yaw servo. A larger number will cause the yaw servo to more aggressively control the aircraft, and a smaller number will cause the yaw servo to less aggressively control the aircraft.
9.11.4 Trim Control
The GSA28 autopilot servos can be used to control the trim system in an aircraft. When the autopilot is disengaged, the servos can adjust the trim speed based on the current aircraft airspeed. This allows the trim to run slower at high airspeeds and faster at low airspeeds. When the autopilot is engaged, the servos can adjust the trim control to minimize the force on the primary controls. This helps ensure the aircraft will be properly trimmed when the autopilot is later disengaged.
During the flight test phase, the trim system is configured and set up after the primary autopilot performance has been properly configured. This is done so the pilot can focus on properly adjusting the performance of the primary autopilot system without having the auto-trim functionality interfere.
NOTE
Ensure basic autopilot functionality is properly adjusted before enabling trim control for any servo.
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G3X Installation Manual - GSA 28 Installation Page 9-39
9.12 Step by Step On-Ground Setup
9.12.1 Servo Wiring Checkout The first phase of setting up the Garmin autopilot system is to verify the proper wiring of the GSA 28 servos while on the ground.
1. If the installation is a 1-axis (roll only) autopilot, use the LRU page in configuration mode on the PFD to configure the "Autopilot Servos" for "Roll Only".
2. If you have installed a 2-axis (pitch and roll) autopilot, use the LRU page in configuration mode on the PFD to configure the "Autopilot Servos" for "Pitch + Roll".
3. If you have installed a 3-axis (pitch, roll, and yaw) autopilot, use the LRU page in configuration mode on the PFD to configure the "Autopilot Servos" for "Pitch + Roll + YD".
4. Go to the Main page in configuration mode and verify the Roll, Pitch, and Yaw servos are properly communicating with the system indicated by a green check box.
5. Go to the Main page in configuration mode and verify the CWS/DISCONNECT INPUT is properly wired for each servo. a) The CWS/DISCONNECT input should be LOW when the autopilot disconnect button is pressed.
b) The CWS/DISCONNECT input should be OPEN when the autopilot disconnect button is NOT pressed.
G3X Installation Manual - GSA 28 Installation Page 9-40
190-01115-01 Rev. K
c) The system will compare the CWS/DISCONNECT INPUT from all servos, press and hold the autopilot disconnect button for at least 5 seconds to verify there are no SYNC faults.
6. Go to the Main page in configuration mode and verify the proper TRIM ACTIVITY if the Roll servo is connected to an auxiliary trim motor. a) Center the aileron trim switch to input no TRIM command. Verify the aileron trim switch is not moving. Verify the Roll servo is properly indicating no trim activity.
b) Use the aileron trim switch to input a roll right TRIM command. Verify the aileron trim switch properly moves for roll right trim. Verify the Roll servo is properly indicating ROLL RIGHT trim activity.
c) Use the aileron trim switch to input a roll left TRIM command. Verify the aileron trim switch properly moves for roll left trim. Verify the Roll servo is properly indicating ROLL LEFT trim activity.
d) If the aileron trim response is reversed, go to the AP CONFIG page and change the roll servo TRIM MOTOR DIRECTION to REVERSE, then repeat step all of step 6.
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G3X Installation Manual - GSA 28 Installation Page 9-41
7. Go to the Main page in configuration mode and verify the proper TRIM ACTIVITY if the Pitch servo is connected to an auxiliary trim motor. a) Center the elevator trim switch to input no TRIM command. Verify the elevator trim switch is not moving. Verify the Pitch servo is properly indicating no trim activity.
b) Use the elevator trim switch to input a nose up TRIM command. Verify the elevator trim switch properly moves for nose up trim. Verify the Pitch servo is properly indicating NOSE UP trim activity.
c) Use the elevator trim switch to input a nose down TRIM command. Verify the elevator trim switch properly moves for nose down trim. Verify the Pitch servo is properly indicating NOSE DOWN trim activity.
d) If the elevator trim response is reversed, go to the AP CONFIG page and change the pitch servo TRIM MOTOR DIRECTION to REVERSE, then repeat step all of step 7.
G3X Installation Manual - GSA 28 Installation Page 9-42
190-01115-01 Rev. K
8. Go to the Main page in configuration mode and verify the proper TRIM ACTIVITY if the Yaw servo is connected to an auxiliary trim motor. a) Center the aircraft rudder trim switch to input no TRIM command. Verify the rudder trim switch is not moving. Verify the Yaw servo is properly indicating no trim activity.
b) Use the rudder trim switch to input a yaw right TRIM command. Verify the rudder trim switch properly moves for yaw left trim. Verify the Yaw servo is properly indicating YAW RIGHT trim activity.
c) Use the rudder trim switch to input a yaw left TRIM command. Verify the rudder trim switch properly moves for yaw left trim. Verify the Yaw servo is properly indicating YAW LEFT trim activity.
d) If the rudder trim response is reversed, go to the AP CONFIG page and change the yaw damper TRIM MOTOR DIRECTION to REVERSE, then repeat step all of step 8.
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G3X Installation Manual - GSA 28 Installation Page 9-43
9. Go to the AP page in configuration mode and navigate to the Roll Servo sub-section to configure the servo direction.
a) The Servo Direction should be set to Normal. The servo arm should move clockwise to cause a bank left aileron movement and the servo arm should move counterclockwise to cause a bank right aileron movement.
BANK RIGHT
BANK LEFT
Figure 9-13 Normal Roll Servo Direction
b) The Servo Direction should be set to Reverse. The servo arm should move clockwise to cause a bank right aileron movement and the servo arm should move counterclockwise to cause a bank left aileron movement.
BANK LEFT
BANK RIGHT
Figure 9-14 Reversed Roll Servo Direction
G3X Installation Manual - GSA 28 Installation Page 9-44
190-01115-01 Rev. K
10. Go to the AP page in configuration mode and navigate to the Pitch Servo sub-section to configure the servo direction.
a) The Servo Direction should be set to Normal. The servo arm should move clockwise to cause a nose down elevator movement and the servo arm should move counterclockwise to cause a nose up elevator movement.
NOSE UP
NOSE DOWN
Figure 9-15 Normal Pitch Servo Direction
b) The Servo Direction should be set to Reverse and the servo arm should move clockwise to cause a nose up elevator movement and the servo arm should move counterclockwise to cause a nose down elevator movement.
NOSE DOWN
NOSE UP
Figure 9-16 Reversed Pitch Servo Direction
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G3X Installation Manual - GSA 28 Installation Page 9-45
11. Go to the AP page in configuration mode and navigate to the Yaw Servo sub-section to configure the servo direction.
a) The Servo Direction should be set to Normal. The servo arm should move clockwise to cause a nose left rudder movement and servo arm should move counterclockwise to cause a nose right rudder movement.
NOSE RIGHT
NOSE LEFT
Figure 9-17 Normal Yaw Damper Direction
b) The Servo Direction should be set to Reverse. The servo arm should move clockwise to cause a nose right rudder movement and the servo arm should move counterclockwise to cause a nose left rudder movement.
NOSE LEFT
NOSE RIGHT
Figure 9-18 Reversed Yaw Damper Direction
G3X Installation Manual - GSA 28 Installation Page 9-46
190-01115-01 Rev. K
12. Go to the AP page in configuration mode and verify the TRIM MOTOR CONTROL is disabled for all servos.
NOTE
Initial autopilot tuning is done with the trim control disabled to avoid the auto-trim function from interfering with the initial autopilot tuning.
a) By disabling the TRIM MOTOR CONTROL, this will disable auto-trim and airspeed scheduled trim, but the pilot can still control trim in his aircraft using the normal manual electric trim inputs. Auto-trim and airspeed scheduled trim will be setup later in the autopilot setup procedure.
13. Go to the AP gain in configuration mode and set the proper min/max airspeed limits for the pitch servo. The pitch servo will lower or raise the nose of the aircraft to try and keep it inside these airspeed limits. a) The min airspeed limit should be set above the stall speed of the aircraft with some margin. b) The max airspeed limit should be set below the never exceed speed of the aircraft with some margin.
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G3X Installation Manual - GSA 28 Installation Page 9-47
9.13 Autopilot Setup
The next phase of setting up the Garmin autopilot system is to verify the proper functionality of the autopilot system on the ground in normal mode. This phase of the checkout requires a valid aircraft heading and pitch output from the ADAHRS. This means the post installation procedures must have already been completed on the ADAHRS before performing the on ground autopilot normal mode checkout.
1. Leave the autopilot disengaged and verify the controls can be manipulated smoothly with no control system binding.
2. Engage the autopilot in HDG/PIT mode and command a nose down, left bank.
a) With no GMC 305 Controller:
i. Press the HDG/ROLL softkey on the PFD
ii. Press the AP HDG softkey on the PFD
iii. Push and hold the joystick to center the HDG bug
iv. Rotate the joystick counter-clockwise to command a left turn
v. Bump the joystick down to command a pitch down
b) With a GMC 305 Controller:
i. Press the AP button on the GMC 305
ii. Press the HDG button on the GMC 305
iii. Push the HDG softkey on the PFD
iv. Push and hold the joystick on the PFD to center the HDG bug
v. Rotate the joystick on the PFD counter-clockwise to command a left turn
vi. Rotate the wheel on the GMC 305 to command a pitch down
3. Verify the stick properly moves in a direction that would cause the aircraft to pitch down and roll to the left smoothly with no control system binding.
G3X Installation Manual - GSA 28 Installation Page 9-48
190-01115-01 Rev. K
4. Engage the autopilot in HDG/PIT mode and command a nose down, right bank. a) With no GMC 305 Controller: i. Press the HDG/ROLL softkey on the PFD ii. Press the AP HDG softkey on the PFD iii. Push the joystick to center the HDG bug iv. Rotate the joystick clockwise to command a right turn v. Bump the joystick down to command a pitch down b) With a GMC 305 Controller: i. Press the AP button on the GMC 305 ii. Press the HDG button on the GMC 305 iii. Push the HDG softkey on the PFD iv. Push the joystick on the PFD to center the HDG bug v. Rotate the joystick on the PFD clockwise to command a right turn vi. Rotate the wheel on the GMC 305 down to command a pitch down
5. Verify the stick properly moves toward the nose and toward the right wing smoothly with no control system binding.
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G3X Installation Manual - GSA 28 Installation Page 9-49
6. Engage the autopilot in HDG/PIT mode and command a nose up, right bank. a) With no GMC 305 Controller: i. Press the HDG/ROLL softkey on the PFD ii. Press the AP HDG softkey on the PFD iii. Push the joystick to center the HDG bug iv. Rotate the joystick clockwise to command a right turn v. Bump the joystick up to command a pitch up b) With a GMC 305 Controller: i. Press the AP button on the GMC 305 ii. Press the HDG button on the GMC 305 iii. Push the HDG softkey on the PFD iv. Push the joystick on the PFD to center the HDG bug v. Rotate the joystick on the PFD clockwise to command a right turn vi. Rotate the wheel on the GMC 305 up to command a pitch up
7. Verify the stick properly moves toward the tail and toward the right wing smoothly with no control system binding.
G3X Installation Manual - GSA 28 Installation Page 9-50
190-01115-01 Rev. K
8. Engage the autopilot in HDG/PIT mode and command a nose up, left bank. a) With no GMC 305 Controller: i. Press the HDG/ROLL softkey on the PFD ii. Press the AP HDG softkey on the PFD iii. Push the joystick to center the HDG bug iv. Rotate the joystick counter-clockwise to command a left turn v. Bump the joystick up to command a pitch up b) With a GMC 305 Controller: i. Press the AP button on the GMC 305 ii. Press the HDG button on the GMC 305 iii. Push the HDG softkey on the PFD iv. Push the joystick on the PFD to center the HDG bug v. Rotate the joystick on the PFD counter-clockwise to command a left turn vi. Rotate the wheel on the GMC 305 up to command a pitch up
9. Verify the stick properly moves toward the tail and toward the left wing smoothly with no control system binding.
10. If the stick position does not move the correct direction, correct the roll and pitch servo directions documented in Section 9.12.1 Step 9 and Step 10.
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G3X Installation Manual - GSA 28 Installation Page 9-51
11. Engage the autopilot and verify it can be overpowered in both the pitch and roll axis. If the autopilot cannot be overpowered, use the Autopilot Setup screen to reduce the MAX TORQUE setting for the associated servo.
a) Press MENU two times on the GDU to enter the MAIN MENU page.
b) Select the SYSTEM SETUP page.
c) Select the AUTOPILOT page.
d) Select ROLL SERVO and set the MAX TORQUE.
e) Select PITCH SERVO and set the MAX TORQUE.
12. Engage the autopilot and verify that is properly disconnects with a short press and release of the CWS/DISCONNECT button.
G3X Installation Manual - GSA 28 Installation Page 9-52
190-01115-01 Rev. K
a) If the audio output of the G3X system is connected to the aircraft audio system, verify the pilot hears an autopilot disconnect tone when disconnecting the autopilot.
9.14 Yaw Damper Setup
The next phase of setting up the Garmin autopilot system is to verify the proper functionality of the yaw damper system on the ground in normal mode. This phase of the checkout requires a valid output from the ADAHRS. This means the post installation procedures must have been completed on the ADAHRS before performing the on ground autopilot normal mode checkout.
1. Leave the yaw damper disengaged and verify the rudder pedals can be manipulated smoothly with no control system binding.
2. Engage the autopilot in YD mode. a) With no GMC 305 Controller: i. YD not supported b) With a GMC 305 Controller: i. Press the YD button on the GMC 305
3. Verify the rudder properly moves to the correct direction by standing by the tail of the aircraft, facing the vertical stabilizer, and pushing on the fuselage. The rudder should move AWAY from you (the rudder should move in the same direction that the rear fuselage is moving):
a) If the rudder does not move the correct direction, correct the yaw servo direction documented in Section 9.14 Step 11.
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G3X Installation Manual - GSA 28 Installation Page 9-53
4. Engage the yaw damper and verify it can be overpowered in yaw axis using rudder pedal inputs. If the autopilot cannot be overpowered, use the Autopilot Setup screen to reduce the MAX TORQUE setting for the yaw damper servo:
a) Press MENU two times on the GDU to enter the MAIN MENU page.
b) Select the SYSTEM SETUP page.
c) Select the AUTOPILOT page.
d) Select YAW DAMPER and set the MAX TORQUE.
5. The CWS/DISCONNECT input can optionally be connected to the Yaw Damper. If this connection was made, engage the yaw damper and verify that is properly disconnects with a short press and release of the CWS/DISCONNECT button.
a) If the audio output of the G3X system is connected to the aircraft audio system, verify the pilot hears an autopilot disconnect tone when disconnecting the autopilot.
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9.15 Step By Step In-Air Autopilot Setup
The next phase of setting up the Garmin autopilot system is to verify and tune the proper functionality of the autopilot system in the air.
WARNING
This stage of the flight test involves allowing the GSA28 autopilot servos to manipulate the flight control surfaces of the aircraft. Extreme caution should be used during the initial engagement of the autopilot system. The pilot should always have easy access to the autopilot disconnect button so he can disconnect the autopilot and take control of the aircraft at anytime.
At a minimum, please follow the following safety guidelines before the initial autopilot engagement: · Quick access to autopilot disconnect · Safe altitude above and away from all terrain and obstacles · No air traffic in the area · Safe airspeed below maneuvering speed (VA)
9.15.1 Roll Servo 1. Use the AUTOPILOT SETUP page to adjust the ROLL SERVO gain setting a) Engage the autopilot in ROL/PIT mode with the aircraft approximately level i. With no GMC 305 Controller: 1.Press, hold, and release the CWS/DISCONNECT button to engage the AP ii. With a GMC305 Controller 1.Press the AP button on the GMC305 to engage the AP 2.Press the YD button on the GMC305 to DISENGAGE the YD
b) Press MENU two times on the GDU to enter the MAIN MENU page. c) Select the SYSTEM SETUP page.
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d) Select the AUTOPILOT page.
e) Select ROLL SERVO page and highlight the SERVO GAIN entry.
f) Adjust the servo gain so that the aircraft properly responds to the roll guidance from the flight director i. Overpower the autopilot to fly away from the current flight director commanded roll ii. Release controls and monitor autopilot response and closure back to commanded roll iii. Set the SERVO GAIN higher to make the autopilot more aggressive iv. Set the SERVO GAIN lower to make the autopilot less aggressive
2. The roll servo has additional advanced and expert level settings that can be adjusted to achieve the desired lateral mode performance. These settings are detailed in Section 9.17 below and should only be adjusted after studying the description to properly understand their effect on the roll servo.
9.15.2 Pitch Servo 1. Use the AUTOPILOT SETUP page to adjust the PITCH SERVO gain setting a) Engage the autopilot in ROL/PIT mode with the aircraft approximately level i. With no GMC 305 Controller: 1.Press, hold, and release the CWS/DISCONNECT button to engage the AP ii. With a GMC 305 Controller: 1.Press the AP button on the GMC305 to engage the AP 2.Press the YD button on the GMC305 to DISENGAGE the YD
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b) Press MENU two times on the GDU to enter the MAIN MENU page. c) Select the SYSTEM SETUP page.
d) Select the AUTOPILOT page.
e) Select PITCH SERVO page and highlight the SERVO GAIN entry.
f) Adjust the servo gain so that the aircraft properly responds to the pitch guidance from the flight director
i. Overpower the autopilot to fly away from the current flight director commanded pitch
ii. Release controls and monitor autopilot response and closure back to commanded pitch
iii. Set the SERVO GAIN higher to make the autopilot more aggressive
iv. Set the SERVO GAIN lower to make the autopilot less aggressive
2. The pitch servo has additional advanced and expert level settings that can be adjusted to achieve the desired vertical mode performance. These settings are detailed in Section 9.17 below and should only be adjusted after studying the description to properly understand their effect on the roll servo.
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9.15.3 Yaw Damper Setup The next phase of setting up the Garmin yaw damper system is to verify and tune the proper functionality of the yaw damper system in the air.
WARNING
This stage of the flight test involves allowing the GSA28 autopilot servos to manipulate the flight control surfaces of the aircraft. Extreme caution should be used during the initial engagement of the autopilot system. The pilot should always have easy access to the autopilot disconnect button so he can disconnect the autopilot and take control of the aircraft at anytime. At a minimum, please follow the following safety guidelines before the initial autopilot engagement: · Quick access to autopilot disconnect · Safe altitude above and away from all terrain and obstacles · No air traffic in the area · Safe airspeed below maneuvering speed (VA) 1. Use the AUTOPILOT SETUP page to adjust the YAW DAMPER gain setting
a) Press MENU two times on the GDU to enter the MAIN MENU page. b) Select the SYSTEM SETUP page.
c) Select the AUTOPILOT page.
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d) Select YAW DAMPER page and highlight the SERVO GAIN entry.
e) Adjust the servo gain so that the aircraft properly responds to the yaw body rates (tail wagging) i. Engage the autopilot in LVL mode with the aircraft approximately level ii. With a GMC 305 Controller 1.Press the LVL button on the GMC 305 to engage the AP in LVL mode 2.Press the YD button on the GMC 305 to disengage the YD
iii. Fly a yaw doublet and engage the YD as the ball swings through the center 1.Right foot rudder to swing ball left
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2.Left foot rudder to swing ball back right
3.Engage YD by pressing the YD button onthe GMC 305 as ball swings through the center
4.Set SERVO GAIN so the established yaw body rate from the yaw doublet is properly dampened out
a.Set the SERVO GAIN higher to make the yaw damper more aggressive
b.Set the SERVO GAIN lower to make the yaw damper less aggressive
2. The yaw servo has additional advanced and expert level settings that can be adjusted to achieve the desired yaw damping performance. These settings are detailed in Section 9.17 below and should only be adjusted after studying the description to properly understand their effect on the yaw servo.
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9.16 Step by Step Trim System Setup
9.16.1 On-ground Setup
After setting up and testing the GSA28 based autopilot and yaw damper systems, the pilot can configure the trim system.
1. Go to the AP pages in configuration mode and enable the TRIM MOTOR CONTROL for all servos that are connected to auxiliary trim motors.
2. Go to the MANUAL ELECTRIC TRIM page and set the airspeed thresholds for fastest and slowest trim movement.
a) Recommend setting the fastest movement airspeed to the airspeed typically used to fly the normal aircraft landing pattern.
b) Recommend setting the slowest movement airspeed to the airspeed typically used for cruise flight.
c) Recommend setting the fastest motor speed 100% (will be adjusted later in flight)
d) Recommend setting the slowest motor speed to 25% (will be adjusted later in flight)
3. Re-verify proper trim movement in described in Section 9.12.1 Steps 6, 7, & 8.
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9.16.2 In Air Setup The next phase of setting up the Garmin GSA28 based trim control system is to verify and set the proper functionality of the trim system in the air.
WARNING
This stage of the flight test involves allowing the GSA28 autopilot servos to manipulate the flight control surfaces of the aircraft. Extreme caution should be used during this phase of the flight test. The pilot should always have easy access to the autopilot disconnect button so he can disconnect the autopilot and take control of the aircraft at anytime. At a minimum, please follow the following safety guidelines before the initial autopilot engagement: · Quick access to autopilot disconnect · Safe altitude above and away from all terrain and obstacles · No air traffic in the area · Safe airspeed below maneuvering speed (VA) 1. Use the AUTOPILOT SETUP page to adjust the TRIM MOTOR SPEED to get the desired manual electric trim response.
a) Press MENU two times on the GDU to enter the MAIN MENU page. b) Select the SYSTEM SETUP page.
c) Select the AUTOPILOT page.
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d) Select MANUAL ELECTRIC TRIM page and highlight the various trim motor speeds
e) Adjust the trim motor speeds at the two airspeed thresholds to get a desirable trim response i. Trim aircraft using manual electric trim inputs ii. Trim response should not be overly slow iii. Trim response should not be overly fast
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9.17 Detailed Autopilot Configuration Options
The installer needs to make the following autopilot configuration selections when setting up the GSA 28 based autopilot system.
9.17.1 General Configuration Page
These selections are made in configuration mode using the AP CONFIG page.
Table 9-10 General Autopilot Configuration Settings
Configuration Setting
Control Wheel Steering (Configuration mode only)
Engage AP Via CWS Input (Configuration mode only)
Description
The CWS/DISCONNECT discrete input to the GSA 28 servos is connected to a momentary pushbutton which can function either as a dedicated Autopilot Disconnect (AP DISC) button, or as a combined Autopilot Disconnect / Control Wheel Steering (AP/CWS) button.
Regardless of configuration, a short press and release of the AP DISC or AP/CWS button will disengage the autopilot if it is engaged.
If Control Wheel Steering is enabled, the pressing and holding the AP/ CWS button places the autopilot into CWS mode. In CWS mode, the servos are temporarily disengaged, allowing hand-flying the aircraft to a new aircraft attitude while continuing to hold the AP/CWS button. When the AP/CWS button is released, the autopilot exits CWS mode and the flight director synchronizes to the current aircraft attitude (if applicable for the current flight director modes).
If Control Wheel Steering is disabled, CWS is not supported and the AP button serves as a dedicated AP DISC button only. The AP DISC button will disconnect the autopilot any time it is pressed, regardless of how long it is held.
If Control Wheel Steering is enabled, the AP/CWS button can optionally be configured to engage the autopilot when pressed and held.
If "Engage AP Via CWS Input" is enabled, the autopilot will automatically engage when the AP/CWS button is pressed and held.
If "Engage AP Via CWS Input" is disabled, pressing the AP/CWS button while the autopilot is not engaged has no effect. In this state, the autopilot can only be engaged using the GMC 305 AP button or the softkeys on the PFD display.
Figure 9-19 General Autopilot Configuration Page
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9.17.2 Roll Servo Configuration
The installer needs to make the following roll servo configuration selections when setting up the GSA 28 based autopilot system. These selections are made in configuration mode using the AP CONFIG page and the roll servo setup screen in the autopilot setup menu in normal mode.
Table 9-11 Roll Servo Autopilot Configuration Settings
Configuration Setting
Description
Max Torque
The GSA 28 roll servo has a configurable maximum torque setting. This determines how much torque the servo will output before the electronic slip clutch begins to slip.
The Max Torque setting should be set high enough to not slip during in flight air loading, but the torque setting should be low enough for the pilot to override the autopilot if required.
The Max Torque setting can be adjusted from 10 to 60 inch-pounds in 5 inch-pound steps.
Servo Gain
The GSA 28 roll servo has a configurable servo gain value. This determines how aggressively the roll servo will move the aileron surfaces.
The Servo Gain should be set high enough to properly fly the desired roll, heading, and track, but low enough to avoid being overly aggressive in the aileron movements.
The servo gain setting can be adjusted from 0.05 to 10.00 in steps of 0.05.
Servo Direction (Configuration mode only)
The GSA 28 roll servo has a configurable servo direction.
The Servo Direction should be set to Normal if the servo arm should move clockwise to cause a bank left aileron movement.
The Servo Direction should be set to Reverse if the servo arm should move counterclockwise to cause a bank left aileron movement.
After selecting the proper servo direction, the installer should engage the autopilot system in normal mode and verify proper aileron response by rotating the heading bug left and right of the current heading.
Clutch Monitor (Configuration mode only)
The GSA 28 roll servo has the ability to monitor itself for a stuck clutch situation.
If the servo has a large amount of side loading (typically due to a capstan installation), this can occasionally lead to invalid stuck clutch failures.
The Clutch Monitor should be enabled for all control arm installations.
The Clutch Monitor can be disabled for capstan installations with larger side loads to prevent invalid stuck clutch failures.
Note that the user can reset clutch monitor faults by pressing the RESET softkey on the roll servo configuration page in configuration mode if an invalid stuck clutch failure occurs.
Trim Motor Control (Configuration mode only)
The GSA 28 roll servo has the ability to control an auxiliary roll trim motor.
The Trim Motor Control should be enabled if the GSA 28 roll servo was connected to an auxiliary trim motor.
The Trim Motor Control should be disabled if the GSA 28 roll servo was not connected to an auxiliary trim motor.
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Table 9-11 Roll Servo Autopilot Configuration Settings
Auto Trim Motor Speed
Fine Adjust Time (Expert Setting)
Fine Adjust Amount (Expert setting)
The GSA 28 roll servo has the ability to drive the auxiliary trim motor at various speeds.
The Auto Trim Motor Speed should be set so the auxiliary trim motor will move as slowly as possible. The slowest possible movement will ensure that there is no noticeable aircraft response when the auxiliary trim motor is run during auto-trim.
The Auto Trim Motor Speed can be adjusted in percent from 5 to 100 in steps of 5.
The GSA 28 roll servo is capable of making very small adjustments to fine tune the aileron position. The Fine Adjust Time is the rate in which these adjustments are made in seconds.
Fine Adjust Time is an expert level setting, and should generally be not be changed by the installer, the default value is 0.20.
If the installer notices the aircraft doing very small oscillations, the Fine Adjust Time and Fine Adjust Amount can be used to correct this.
The GSA 28 roll servo is capable of making very small adjustments to fine tune the aileron position. The Fine Adjust Amount is the amount in which these adjustments are made.
Fine Adjust Amount is an expert level setting, and should generally be not be changed by the installer, the default value is 0.
If the installer notices the aircraft doing very small oscillations, the Fine Adjust Time and Fine Adjust Amount can be used to correct this.
Figure 9-20 Roll Servo Autopilot Configuration Page
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9.17.3 Pitch Servo Configuration
The installer needs to make the following pitch servo configuration selections when setting up the GSA 28 based autopilot system. These selections are made in configuration mode using the AP CONFIG page and the pitch servo setup screen in the autopilot setup menu in normal mode.
Table 9-12 Pitch Servo Autopilot Configuration Settings
Configuration Setting
Description
Max Torque
The GSA 28 pitch servo has a configurable maximum torque setting. This determines how much torque the servo will output before the electronic slip clutch begins to slip.
The Max Torque setting should be set high enough to not slip during in flight air loading, but the torque setting should be low enough for the pilot to override the autopilot if required.
The Max Torque setting can be adjusted from 10 to 60 inch-pounds in 5 inch-pound steps.
Servo Gain
The GSA 28 pitch servo has a configurable servo gain value. This determines how aggressively the pitch servo will move the elevator surfaces.
The Servo Gain should be set high enough to properly fly the desired pitch, vertical speed, and altitude, but low enough to avoid being overly aggressive in the elevator movements.
The servo gain setting can be adjusted from 0.05 to 10.00 in steps of 0.05.
Servo Direction (Configuration mode only)
The GSA 28 pitch servo has a configurable servo direction.
The Servo Direction should be set to Normal if the servo arm should move clockwise to cause a nose down elevator movement.
The Servo Direction should be set to Reverse if the servo arm should move counterclockwise to cause a nose down elevator movement.
After selecting the proper servo direction, the installer should engage the autopilot system in normal mode and verify proper elevator response by rotating the pitch reference up and down from the current pitch.
Clutch Monitor (Configuration mode only)
The GSA 28 pitch servo has the ability to monitor itself for a stuck clutch situation.
If the servo has a large amount of side loading (typically due to a capstan installation), this can occasionally lead to invalid stuck clutch failures.
The Clutch Monitor should be enabled for all control arm installations.
The Clutch Monitor can be disabled for capstan installations with larger side loads to prevent invalid stuck clutch failures.
Note that the user can reset clutch monitor faults by pressing the RESET softkey on the pitch servo configuration page in configuration mode if an invalid stuck clutch failure occurs.
Trim Motor Control (Configuration mode only)
The GSA 28 pitch servo has the ability to control an auxiliary pitch trim motor.
The Trim Motor Control should be enabled if the GSA 28 pitch servo was connected to an auxiliary trim motor.
The Trim Motor Control should be disabled if the GSA 28 pitch servo was not connected to an auxiliary trim motor.
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Table 9-12 Pitch Servo Autopilot Configuration Settings
Auto Trim Motor Speed
Fine Adjust Time (Expert Setting)
Fine Adjust Amount (Expert setting)
The GSA 28 pitch servo has the ability to drive the auxiliary trim motor at various speeds.
The Auto Trim Motor Speed should be set so the auxiliary trim motor will move as slowly as possible. The slowest possible movement will ensure that there is no noticeable aircraft response when the auxiliary trim motor is run during auto-trim.
The Auto Trim Motor Speed can be adjusted in percent from 5 to 100 in steps of 5.
The GSA 28 pitch servo is capable of making very small adjustments to fine tune the aileron position. The Fine Adjust Time is the rate in which these adjustments are made in seconds.
Fine Adjust Time is an expert level setting, and should generally be not be changed by the installer, the default value is 0.20.
If the installer notices the aircraft doing very small oscillations, the Fine Adjust Time and Fine Adjust Amount can be used to correct this.
The GSA 28 pitch servo is capable of making very small adjustments to fine tune the aileron position. The Fine Adjust Amount is the amount in which these adjustments are made.
Fine Adjust Amount is an expert level setting, and should generally be not be changed by the installer, the default value is 0.
If the installer notices the aircraft doing very small oscillations, the Fine Adjust Time and Fine Adjust Amount can be used to correct this.
Figure 9-21 Pitch Servo Autopilot Configuration Page
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9.17.4 Yaw Damper Configuration
The installer needs to make the following yaw damper configuration selections when setting up the GSA 28 based yaw damper system. These selections are made in configuration mode using the AP CONFIG page and the yaw damper setup screen in the autopilot setup menu in normal mode.
Table 9-13 Yaw Damper Autopilot Configuration Settings
Configuration Setting Max Torque
Servo Gain
Servo Direction (Configuration mode only)
Clutch Monitor (Configuration mode only)
Trim Motor Control (Configuration mode only)
Description
The GSA 28 yaw damper has a configurable maximum torque setting. This determines how much torque the servo will output before the electronic slip clutch begins to slip.
The Max Torque setting should be set high enough to not slip during in flight air loading, but the torque setting should be low enough for the pilot to override the autopilot if required.
The Max Torque setting can be adjusted from 10 to 60 inch-pounds in 5 inch-pound steps.
The GSA 28 yaw damper has a configurable servo gain value. This determines how aggressively the pitch servo will move the rudder surface.
The Servo Gain should be set high enough to properly dampen yaw rates, but low enough to avoid being overly aggressive in the rudder movements.
The servo gain setting can be adjusted from 0.05 to 10.00 in steps of 0.05.
The GSA 28 yaw damper servo has a configurable servo direction.
The Servo Direction should be set to Normal if the servo arm should move clockwise to cause a nose left rudder movement.
The Servo Direction should be set to Reverse if the servo arm should move counterclockwise to cause a nose left rudder movement.
After selecting the proper servo direction, the installer should engage the yaw damper in normal mode and verify proper rudder response pushing the tail of the aircraft back and forth.
The GSA 28 yaw damper has the ability to monitor itself for a stuck clutch situation.
If the servo has a large amount of side loading (typically due to a capstan installation), this can occasionally lead to invalid stuck clutch failures.
The Clutch Monitor should be enabled for all control arm installations.
The Clutch Monitor can be disabled for capstan installations with larger side loads to prevent invalid stuck clutch failures.
Note that the user can reset clutch monitor faults by pressing the RESET softkey on the yaw damper configuration page in configuration mode if an invalid stuck clutch failure occurs.
The GSA 28 yaw damper has the ability to control an auxiliary rudder trim motor.
The Trim Motor Control should be enabled if the GSA 28 yaw damper servo was connected to an auxiliary trim motor.
The Trim Motor Control should be disabled if the GSA28 yaw damper servo was not connected to an auxiliary trim motor.
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Table 9-13 Yaw Damper Autopilot Configuration Settings
Auto Trim Motor Speed
Ball Centering Gain (Advanced Setting)
Rate Filter Constant (Expert setting)
Accel Filter Constant (Expert setting)
The GSA 28 yaw damper has the ability to drive the auxiliary rudder trim motor at various speeds.
The Auto Trim Motor Speed should be set so the auxiliary trim motor will move as slowly as possible. The slowest possible movement will ensure that there is no noticeable aircraft response when the auxiliary trim motor is run during auto-trim.
The Auto Trim Motor Speed can be adjusted in percent from 5 to 100 in steps of 5.
The GSA 28 yaw damper is capable of zeroing the aircraft's lateral acceleration or centering the ball as well as dampening aircraft yaw rates.
Ball Centering Gain is an advanced level setting and should only be changed by the installer if the yaw damper is not properly zeroing the aircraft's lateral acceleration.
Increasing the Ball Centering Gain will cause the yaw damper to more aggressively respond to non-zero lateral acceleration. Decreasing the Ball Centering Gain will cause the yaw damper to respond less aggressively to non-zero lateral acceleration.
The GSA 28 yaw damper is capable of damping out yaw body rates to keep the aircraft from shaking its tail. The Rate Filter Constant is used to filter the aircraft yaw body rate.
Rate Filter Constant is an expert level setting, and should generally be not be changed by the installer, the default value is 0.08.
The GSA 28 yaw damper is capable of zeroing the lateral acceleration of the aircraft. The Accel Filter Constant is used to filter the aircraft lateral acceleration.
Accel Filter Constant is an expert level setting, and should generally be not be changed by the installer, the default value is 0.16.
Figure 9-22 Yaw Damper Autopilot Configuration Page
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9.17.5 Pitch Gain Configuration
The installer needs to make the following pitch gain configuration selections when setting up the GSA 28 based autopilot system. These selections are made in configuration mode on the PFD under the AP tab and the pitch gain setup screen in the autopilot setup menu in normal mode.
Table 9-14 Pitch Gain Autopilot Configuration Settings
Configuration Setting
Min Airspeed Limit
Max Airspeed Limit
Vertical Speed Gain (Advanced setting)
Vertical Accel Gain (Expert setting)
Airspeed Gain (Advanced setting)
Airspeed Accel Gain (Expert setting)
Description
The GSA 28 pitch servo has a configurable minimum airspeed limit. This determines the lowest airspeed the pitch servo will allow the aircraft to fly at. If the speed drops below this limit, the pitch servo will lower the nose of the aircraft to keep the airspeed at or above the Min Airspeed Limit.
The Min Airspeed Limit should be set above the aircraft stall speed with some margin.
The GSA 28 pitch servo has a configurable maximum airspeed limit. This determines the fastest airspeed the pitch servo will allow the aircraft to fly at. If the speed rises above this limit, the pitch servo will raise the nose of the aircraft to keep the airspeed at or below the Max Airspeed Limit.
The Max Airspeed Limit should be set below the aircraft maximum speed with some margin.
The GSA 28 pitch servo is capable of holding the aircraft at a desired vertical speed.
The Vertical Speed Gain should be increased if the aircraft struggles to hold the desired vertical speed target when the flight director is in vertical speed (VS), altitude hold (ALT), or LVL modes.
The Vertical Speed Gain should be decreased if the aircraft is overly aggressive when trying to hold the desired vertical speed target.
The GSA 28 pitch servo is capable of holding the aircraft at a desired vertical speed.
The Vertical Accel Gain should be increased if the aircraft is overshooting the desired vertical speed target (when the flight director is in vertical speed (VS) mode) when closing on the bug.
The Vertical Accel Gain should be increased if the aircraft is appears to back off from the desired vertical speed target when closing on the bug.
The GSA 28 pitch servo is capable of holding the aircraft at a desired airspeed.
The Airspeed Gain should be increased if the aircraft is lazy and struggles to hold the desired airspeed target when the flight director is in IAS mode.
The Airspeed Gain should be decreased if the aircraft is overly aggressive when trying to hold the desired airspeed target.
The GSA 28 pitch servo is capable of holding the aircraft at a desired airspeed.
The Airspeed Accel Gain should be increased if the aircraft is overshooting the desired airspeed target when closing on the bug when the flight director is in IAS mode.
The Airspeed Accel Gain should be increased if the aircraft is appears to back off from the desired airspeed target when closing on the bug.
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Airspeed Track Gain
Table 9-14 Pitch Gain Autopilot Configuration Settings
The GSA28 pitch servo is capable of holding the aircraft at a desired airspeed. The Airspeed Track Gain should be increased if the aircraft is overly sluggish while tracking airspeed when the airspeed error is less than 5 knots. The Airspeed Track Gain should be decreased if the aircraft is overly aggressive while tracking airspeed when the airspeed error is less than 5 knots.
Figure 9-23 Pitch Gain Autopilot Configuration Page
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9.17.6 Manual Electric Trim Configuration
The installer needs to make the following manual electric trim configuration selections when setting up the GSA 28 based autopilot system. These selections are made in configuration mode on the PFD under the AP tab and the pitch gain setup screen in the autopilot setup menu in normal mode.
Table 9-15 Manual Electric Trim Autopilot Configuration Settings
Configuration Setting
Description
Airspeed Threshold
The GSA 28 servos are capable of airspeed scheduling the aircraft's manual electric trim.
The Airspeed Threshold Fastest Movement setting is the airspeed in which the trim motor will be moved at its fastest setting. This should be the lower of the two airspeeds.
The Airspeed Threshold Slowest Movement setting is the airspeed in which the trim motor will be moved at its slowest setting. This should be the higher of the two airspeeds.
Roll Trim Motor Speed
The GSA 28 roll servo will control the aileron trim on the aircraft.
The Roll Trim Motor Speed percentage for the Fastest Movement is the speed in which the roll servo will run the auxiliary trim motor when at or below the corresponding airspeed.
The Roll Trim Motor Speed percentage for the Slowest Movement is the speed in which the roll servo will run the auxiliary trim motor when at or above the corresponding airspeed.
Pitch Trim Motor Speed
The GSA 28 pitch servo will control the elevator trim on the aircraft.
The Pitch Trim Motor Speed percentage for the Fastest Movement is the speed in which the pitch servo will run the auxiliary trim motor when at or below the corresponding airspeed.
The Pitch Trim Motor Speed percentage for the Slowest Movement is the speed in which the pitch servo will run the auxiliary trim motor when at or above the corresponding airspeed.
Yaw Trim Motor Speed
The GSA 28 yaw servo will control the rudder trim on the aircraft.
The Yaw Trim Motor Speed percentage for the Fastest Movement is the speed in which the roll servo will run the auxiliary trim motor when at or below the corresponding airspeed.
The Yaw Trim Motor Speed percentage for the Slowest Movement is the speed in which the roll servo will run the auxiliary trim motor when at or above the corresponding airspeed.
Motor Run Time Limit
The GSA 28 servos can limit the maximum continuous run time of the trim
motor. This can be used to help prevent the potential for a trim runaway
situation.
The Motor Run Time Limit is the maximum amount of time the trim servo will be ran continuously when a manual electric trim input is detected. If the maximum time is exceeded, the pilot will need to release the Manual Electric Trim (MET) control and then reassert it to continue running trim.
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Figure 9-24 Manual Electric Trim Autopilot Configuration Page
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10 GSU 25 INSTALLATION (CORE G3X LRU)
The GSU 25 can be installed as part of the G3X system. This section contains general information as well as installation information for the GSU 25. Use this section to mount the GSU 25 unit.
10.1 Equipment Description
NOTE
There is no TSO/ETSO applicable to the GSU 25.
The GSU 25 is intended for experimental aircraft and LSA (light sport aircraft) markets. The Garmin GSU 25 Sensor Unit is not a TSO-certified product and has received no FAA approval or endorsement. The GSU 25 is intended to be used as a part of the G3X system and it is not suitable for installation in typecertificated aircraft.
The GSU 25 is an LRU that provides AHRS and Air Data information in a single mechanical package. The GSU 25 interfaces to a remote mounted GMU 22 for heading information and also computes OAT and TAS from inputs provided by the GTP 59. The GSU 25 does not provide engine/airframe interface, see Section 6 for engine/airframe interface using the GEA 24. Up to three GSU 25 units may be installed to provide redundancy and cross-checking of attitude, heading, and air data.
The GSU 25 provides the following functions:
· Attitude (pitch, roll) · 3 axis accelerations · 3 axis angular rates · Magnetic heading (with input from GMU 22) · Pressure/density altitude · Vertical speed · Indicated/true airspeed · Angle of attack · Outside and total air temperature (via GTP 59)
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Figure 10-1 GSU 25 Unit View
G3X Installation Manual - GSU 25 Installation Page 10-1
10.1.1 Status LED The GSU 25 has an LED on its outer case that indicates its current status. The status indications are:
Table 10-1 Status LED Indications
LED Indication No Light Steady Green Flashing Green Red
Alternating Red/Green
Status No Power On, but not communicating via CAN Bus On and communicating via CAN Bus Hardware Fault CAN bus network error two similar devices are configured with the same unit ID
10.2 General Specifications
See Section 2.2 for power/current specifications, and Section 2.4.1 for dimension/weight specifications.
10.3 Required Equipment
Table 10-2 lists the kits available for the GSU 25. Table 10-2 GSU 25 Available Equipment
Item
GSU 25 Unit Assembly
GSU 25 Connector Kit (contains all items in Table 10-3 and Table 10-4)
Garmin P/N 011-02929-00
K10-00181-00
Quantity 1
1
Table 10-3 Contents of 9 Pin Connector Kit (011-03002-00)
Item Backshell w/Hdw, Jackscrew, 9/15 pin CAN Termination Kit D-Sub, Crimp Socket Connector, 09 CKT Contact Socket, Mil Crimp, Size 20, 20-24 AWG
Garmin P/N 011-01855-00 011-02887-00 330-00625-09 336-00022-02
Quantity 1 1 1 9
Table 10-4 Contents of 15 Pin Connector Kit (011-03002-01) contains mounting hardware
Item Backshell w/Hdw, Jackscrew, 15/26 pin AN3-7A, Bolt AN960, Cad Plate, #10 Washer D-Sub, Crimp Socket Connector, 15 CKT Contact Socket, Mil Crimp, Size 20, 20-24 AWG
Garmin P/N 011-01855-01 211-00090-05 212-00035-10 330-00652-15 336-00022-02
Quantity 1 4 4 1 15
G3X Installation Manual - GSU 25 Installation Page 10-2
190-01115-01 Rev. K
10.3.1 Additional Equipment Required
· Wiring: The installer will fabricate cables and supply all wire for system connector kits 011-03002-00 and 011-03002-01.
· Air hoses and fittings to connect pitot air, static air, and AOA air to the GSU 25. The GSU 25 uses
a female 1/8-27 ANPT fitting for each of these ports. Use appropriate aircraft fittings to connect to pitot, static, and AOA system lines (per Section 10.4.3).
10.4 Unit Installation
Fabrication of a wiring harness is required. Sound mechanical and electrical methods and practices should be used for installation of the GSU 25. Refer to Section 2.3 for wiring considerations, and to Section 15 for pinouts.
Connector kits include backshell assemblies. Garmin's backshell connectors give the installer the ability to quickly and easily terminate shield grounds at the backshell housing. The instructions needed to install the jackscrew backshell are located in Section 16.
NOTE
Connection to a GMU 22 and GTP 59 is required for ADAHRS 1 but optional for ADAHRS 2 & 3.
10.4.1 Mounting Requirements
The GSU 25 includes an extremely sensitive strap-down inertial measurement unit, consider the following when selecting a mounting location:
· The GSU 25 can be oriented remotely in any of 16 orientations (Figure B-8.3 and Figure B-8.4), but must satisfy the mounting alignment requirements along the longitudinal/lateral axes of the aircraft. The unit can be mounted in any of the 4 cardinal directions with the connectors pointing up or down can also be mounted on a vertical surface, with the connectors facing up, down, forward, aft, left, or right.
· Mount the GSU 25 with the connectors aligned within 1.0 degree of either the longitudinal or lateral axis of the aircraft. The direction of the unit will be accounted for during the calibration procedure as shown in Figure 10-2.
· The GSU 25 must be mounted rigidly to the aircraft primary structure through strong structural members capable of supporting substantial loads, see torque specification listed on Figure B-8.2.
· The supporting plate must be rigidly connected. · The GSU 25 should be mounted within 13 feet (4.0 meters) longitudinally and 6.5 feet (2.0 meters)
laterally of the aircraft CG (center of gravity). In cases where the longitudinal distance from the CG is planned to be greater than 6.5 feet (2.0 meters), it is preferable to mount the GSU 25 forward of the aircraft CG if possible, to enable better acceleration outputs for autopilot use. · Avoid placing the GSU 25 near sources of vibration or audible noise. Examples locations to be avoided include the engine firewall, near large motors or fans, and audible buzzers and speakers. · Do not mount the GSU 25 in an enclosed area, it should be mounted in a location that provides adequate airflow. · Avoid areas that are prone to severe vibration. Excessive vibration may result in degraded accuracy. · Do not use shock mounting to mount the GSU 25. Shock mounts used for other types of inertial systems are not acceptable for the GSU 25 AHRS. The mounting system must have no resonance with the unit installed. The unit and mounting structure must not have any resonance with respect to the aircraft primary structure.
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G3X Installation Manual - GSU 25 Installation Page 10-3
· The wing is not an optimal location to mount the unit as (in addition to being away from the center of gravity) any amount of wing flex will directly translate into attitude error.
· The GSU 25 must be leveled to within 30.0° of the flight level cruise attitude and an aircraft leveling and offset calibration procedure carried out prior to flight. (This procedure is described in Section 19.3.2.)
· The mounting location for the GSU 25 should be protected from rapid thermal transients, in particular, large heat loads from nearby high-power equipment.
· Avoid placing the GSU 25 within 1 inch of magnetically mounted antennas, speaker magnets, or other strongly magnetic items.
Figure 10-2 AHRS Orientation Selection
10.4.2 Unit Mounting
For final installation and assembly, refer to the outline and installation drawing Figure B-8.1 and Figure B-8.2 of this manual.
1. Mount the unit to a suitable mounting location using the hardware in the connector kit (Table 10-4) per the requirements in Section 10.4.1.
2. Assemble the wiring harness and backshell connectors 3. Assemble the pneumatic hoses and connectors. 4. Connect backshell connector and hoses. 5. Connect CAN terminator to unit if required (see Section 2.3.1.3).
NOTE
When mounting the GSU 25 to the airframe, it is important to ensure that fastening hardware is tight for proper unit operation.
G3X Installation Manual - GSU 25 Installation Page 10-4
190-01115-01 Rev. K
10.4.3 Pneumatic Plumbing The GSU 25 has three ports that are connected to the aircraft's pitot pressure source, static pressure source, and AOA (Angle Of Attack). The ports are labeled on the unit (Figure 10-3). The pressure ports have 1/827 ANPT female threads. The mating fitting must have 1/8-27 ANPT male threads.
NOTE
The temporary port plugs attached to the pressure ports on a new GSU 25 are not suitable for flight, remove prior to installation of GSU 25 into aircraft.
Figure 10-3 GSU 25 Air Hose Fitting Locations
Use appropriate air hoses and fittings to connect the pitot and static lines to the unit. Use colored (or well marked) tubing to avoid confusing pitot, static, and AOA plumbing per Figure C-1.4. Avoid sharp bends and routing near aircraft control cables. The GSU 25 should not be at the low point of the pneumatic plumbing lines, to avoid moisture or debris collecting at or near the unit. Ensure that no deformations of the airframe surface have been made that would affect the relationship between static air pressure and true ambient static air pressure for any flight condition. Refer to part 43, Appendix E for approved practices while installing hoses and connections.
10.4.4 Pneumatic Connections
The following steps should be used to aid in the fabrication of pneumatic hose connections and in attaching the aircraft pitot pressure source and aircraft static pressure source to the GSU 25.
NOTE
If the AOA port is unused, connect it to the static port to avoid overpressuring (and causing damage to) the internal AOA sensor.
NOTE
Use of different colored tubing is recommended for static, pitot, and AOA plumbing to avoid plumbing connection errors. Incorrect plumbing connections will result in erroneous air data information calculated by the GSU 25.
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G3X Installation Manual - GSU 25 Installation Page 10-5
Observe the following cautions when connecting pneumatic lines:
1. Make sure the aircraft static pressure port is plumbed directly to the unit static pressure input port and the aircraft pitot pressure port is plumbed directly to the unit pitot pressure input port. The AOA port must be plumbed directly to the AOA pressure port or, if unused, directly to the aircraft static port.
2. Seal the threads of pneumatic fittings at the connector ports. Use caution to ensure there are no pneumatic leaks.
3. Use care to avoid getting fluids or particles anywhere within the pneumatic lines connected to the GSU 25.
The installer must fabricate any additional mounting equipment needed. Use outline and installation drawings Figure B-8.1 and Figure B-8.2 for reference.
10.5 Environmental Specifications
Table 10-5 lists general environmental specifications.
Table 10-5 GSU 25 Environmental Specifications
Characteristic Aircraft Pressure Altitude Range Aircraft Vertical Speed Range Aircraft Airspeed Range Aircraft Total Air Temperature Range Unit Operating Temperature Range
Specification -1,400 feet to 30,000 Feet -20,000 feet per minute to +20,000 feet per minute 300 Knots Indicated Airspeed
-85° C to +85° C -45° C to +70° C
10.6 Features Summary
Air Data
Pressure Altitude Density Altitude Vertical Speed Mach Number Indicated Airspeed True Airspeed
Interfaces
CAN (1) RS-232 (2 TX/2 RX) OAT Probe (GTP 59) Magnetometer (GMU 22) (1 RS-232 TX/ 1 RS-485 RX)
AHRS
Magnetic Heading Pitch Angle Roll Angle Linear Accelerations Pitch, Roll, Yaw Rotation Rates
G3X Installation Manual - GSU 25 Installation Page 10-6
190-01115-01 Rev. K
10.7 Performance Information
The GSU 25 is capable of maneuvers through a range of 360° in bank and pitch. The rotation rate capability is ±500° per second.
Pitch/roll accuracy is +/- 2 degrees, heading accuracy is 3 degrees in straight and level flight.
Pitch/roll accuracy is 3.5 degrees and heading accuracy is +/-5 degrees under normal dynamic maneuvering (bank < 35°, pitch <15°).
Due to unsuitability of the magnetic fields near the Earth's poles, operational accuracy is unknown in the following regions:
1. North of 72° North latitude at all longitudes 2. South of 70° South latitude at all longitudes 3. North of 65° North latitude between longitude 75° W and 120° W (Northern Canada) 4. North of 70° North latitude between longitude 70° W and 128° W (Northern Canada) 5. North of 70° North latitude between longitude 85° E and 114° E (Northern Russia) 6. South of 55° South latitude between longitude 120° E and 165° E (Region South of Australia and
New Zealand)
10.8 Maintenance
Per Part 43 Appendix E, paragraph (b)(2), Garmin specifies a test procedure equivalent to part 43 Appendix E, paragraph (b)(1) with two exceptions. The tests of sub-paragraph (iv)(Friction) and (vi) (Barometric Scale Error) are not applicable because the digital outputs of the GSU 25 are not susceptible to these types of errors.
The GSU 25 utilizes an Earth magnetic field model which is updated once every five years. This IGRF (International Geomagnetic Reference Field) update is expected to be available from Garmin by July 1 of 2015 and every five years thereafter, so long as the GSU 25 remains a Garmin supported product. The IGRF model is automatically updated with a GDU 37X software update. Otherwise maintenance of the GSU 25 is `on condition' only.
NOTE
If the GSU 25 is moved or replaced, the Post Installation Calibration Procedures (Section 19.3) must be repeated.
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G3X Installation Manual - GSU 25 Installation Page 10-8
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11 GSU 73 INSTALLATION (CORE G3X LRU)
The GSU 73 can be installed as part of the G3X system. This section contains general information as well as installation information for the GSU 73. Use this section to mount the GSU 73 unit.
11.1 Equipment Description
NOTE
There is no TSO/ETSO applicable to the GSU 73.
The GSU 73 is intended for the experimental aircraft and LSA (light sport aircraft) markets. The Garmin GSU 73 Sensor Unit is not a TSO-certified product and has received no FAA approval or endorsement. The GSU 73 is intended to be used as a part of the G3X system and it is not suitable for installation in typecertificated aircraft. The GSU 73 is an LRU that provides AHRS and Air Data information as well as an interface to Engine/ Airframe sensors in a single mechanical package. The GSU 73 interfaces to a remote mounted GMU 22 for heading information and also computes OAT and TAS from inputs provided by the GTP 59.
NOTE
In installations using more than one ADAHRS, the GSU 73 will always be designated as ADAHRS 1 and the GSU 25 units will be designated as ADAHRS 2,ADAHRS 3 etc.
Figure 11-1 GSU 73 Unit View
11.2 General Specifications
See Section 2.2 for power/current specifications, and Section 2.4.1 for dimension/weight specifications.
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G3X Installation Manual - GSU 73 Installation Page 11-1
11.3 Required Equipment
Table 11-1 lists the kits available for the GSU 73. Table 11-1 GSU 73 Available Equipment
Item Configuration Module w/EEPROM and Jackscrew, Kit Thermocouple Kit Unit Assembly, GSU 73 P731 Connector Kit, GSU 73 P732 Connector Kit, GSU 73 *Included in G3X w/GSU 73 LRU Kit (K10-00016-00) **Included in G3X w/GSU 73 Installation Kit (K10-00017-00)
Garmin P/N 011-00979-20** 011-00981-00** 011-01817-00* 011-01818-00** 011-01818-01**
Quantity 1 1 1 1 1
Table 11-2 Contents of P731 Connector Kit (011-01818-00)**
Item Sub-Assy,Backshell w/Hdw,Jackscrew Connector ,Hi Dens, D-Sub, Mil Crimp 62ck Contact Pin, Mil Crimp, Size 22D **Included in G3X w/GSU 73 Installation Kit (K10-00017-00)
Garmin P/N 011-01855-03 330-00185-62 336-00021-00
Quantity 1 1 20
Table 11-3 Contents of P732 Connector Kit (011-01818-01)**
Item
Garmin P/N
Sub-Assy,Backshell w/Hdw,Jackscrew
011-01855-04
Connector ,Hi Dens, D-Sub, Mil Crimp 78ck
330-00185-78
Contact Pin, Mil Crimp, Size 22D
336-00021-00
**Included in G3X w/GSU 73 Installation Kit (K10-00017-00)
Quantity 1 1 30
G3X Installation Manual - GSU 73 Installation Page 11-2
190-01115-01 Rev. K
11.3.1 GSU 73 Configuration Module
The GSU 73 configuration module stores a duplicate copy of the AHRS/Magnetometer calibration values which are recorded upon completion of post-installation calibration procedures. The GSU configuration module also provides a reference temperature measurement which is used for calculating thermocouple temperatures. All thermocouple temperature readouts will be red-x'd if the GSU configuration module is not present.
11.3.2 Additional Equipment Required
· Cables: The installer will fabricate and supply all system cables. · An example of mounting hardware is: #10-32 pan or hex head screw (4 ea.) and #10-32 self-
locking nut (4 ea) · Air hoses and fittings to connect pitot and static air to the GSU 73. The GSU 73 has a female
1/8-27 ANPT fitting for each pitot and static port. Use appropriate aircraft fittings to connect to pitot and static system lines.
11.4 Unit Installation
Fabrication of a wiring harness is required. Sound mechanical and electrical methods and practices should be used for installation of the GSU 73. Refer to Section 2.3 for wiring considerations, and to Section 15 for pinouts.
Connector kits include backshell assemblies. The backshell assembly houses the configuration module (P732 only) and a thermocouple reference junction (if applicable). Garmin's backshell connectors give the installer the ability to quickly and easily terminate shield grounds at the backshell housing. The instructions needed to install the Jackscrew Backshell, Configuration Module, and Thermocouple are located in Section 16.
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G3X Installation Manual - GSU 73 Installation Page 11-3
11.4.1 Pneumatic Plumbing
The GSU 73 has two ports that are connected to the aircraft's pitot pressure source and static pressure source. The two ports are labeled on the unit (Figure 11-2). The pressure ports have 1/8-27 ANPT female threads. The mating fitting must have 1/8-27 ANPT male threads.
Figure 11-2 GSU 73 Air Hose Fitting Locations
Use appropriate air hoses and fittings to connect the pitot and static lines to the unit. Avoid sharp bends and routing near aircraft control cables. The GSU 73 should not be at the low point of the pitot or static plumbing lines, to avoid moisture or debris collecting at or near the unit. Ensure that no deformations of the airframe surface have been made that would affect the relationship between static air pressure and true ambient static air pressure for any flight condition. Refer to part 43, Appendix E for approved practices while installing hoses and connections.
11.4.2 Pneumatic Connections
The following steps should be used to aid in the fabrication of pneumatic hose connections and in attaching the aircraft pitot pressure source and aircraft static pressure source to the GSU 73.
NOTE
Check pneumatic connections for errors before operating the GSU 73. Incorrect plumbing could cause internal component damage. Observe the following cautions when connecting pneumatic lines.
1. Make sure the aircraft static pressure port is plumbed directly to the unit static pressure input port and the aircraft pitot pressure port is plumbed directly to the unit pitot pressure input port.
2. Seal the threads of pneumatic fittings at the connector ports. Use caution to ensure there are no pneumatic leaks.
3. Use care to avoid getting fluids or particles anywhere within the pitot and static lines connected to the GSU 73.
The installer must fabricate any additional mounting equipment needed. Use outline and installation drawing Figure B-9.1 for reference.
G3X Installation Manual - GSU 73 Installation Page 11-4
190-01115-01 Rev. K
11.4.3 Mounting Requirements Mount the GSU 73 with the connectors aligned within 1.0 deg of either the longitudinal or lateral axis of the aircraft. The direction of the unit will be accounted for during the calibration procedure as shown in Figure 11-3.
Figure 11-3 AHRS Orientation Selection
The GSU 73 includes an extremely sensitive strap-down inertial measurement unit. It must be mounted rigidly to the aircraft primary structure, preferably to a metallic structure to conduct heat away from the unit. Do not mount the GSU 73 in an enclosed area, it should be mounted in a location that provides adequate airflow to comply with the maximum outer case temperature listed in Section 11.5. Do not use shock mounting to mount the GSU 73. Shock mounts used for other types of inertial systems are not acceptable for the GSU 73 AHRS. The mounting system must have no resonance with the unit installed. Excessive vibration may result in degraded accuracy. The supporting plate must be rigidly connected to the aircraft primary structure through strong structural members capable of supporting substantial loads. Avoid areas that are prone to severe vibration. The GSU 73 should be mounted within 13 feet (4.0 meters) longitudinally and 6.5 feet (2.0 meters) laterally of the aircraft center of gravity. In cases where the longitudinal distance from the CG is planned to be greater than 6.5 feet (2.0 meters), it is preferable to mount the GSU 73 forward of the aircraft center of gravity if possible, to enable better acceleration outputs for autopilot use. The mounting location for the GSU 73 should be protected from rapid thermal transients, in particular, large heat loads from nearby highpower equipment. The GSU 73 must be leveled to within 3.0° of the flight level cruise altitude and an aircraft leveling and offset calibration procedure carried out prior to flight. (This procedure is described in Section 19.3.2.) Avoid placing the GSU 73 within 1 inch of magnetically mounted antennas, speaker magnets, or other strongly magnetic items.
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G3X Installation Manual - GSU 73 Installation Page 11-5
11.4.4 Unit Mounting
For final installation and assembly, refer to the outline and installation drawing Figure B-9.1 of this manual.
1. Assemble the wiring harness and backshell connectors. 2. Assemble the pneumatic hoses and connectors. 3. Mount the unit to a suitable mounting location using (4 ea) #10-32 pan or hex head screws
(example) per the requirements in Section 11.4.3. 4. Connect backshell connector and hoses.
NOTE
When mounting the GSU 73 to the airframe, it is important to ensure that fastening hardware is tight for proper unit operation.
11.5 Environmental Specifications
Table 11-4 lists general environmental specifications.
NOTE
The GSU 73 may require a warm-up period of 15 minutes to reach full air data accuracy (30 minutes if the environmental temperature is less than 0°C).
Table 11-4 GSU 73 Environmental Specifications
Characteristic Aircraft Pressure Altitude Range Aircraft Vertical Speed Range Aircraft Airspeed Range Aircraft Mach Range Aircraft Total Air Temperature Range Unit Operating Temperature Range Max Outer Case Temperature
Specification -1,400 feet to 50,000 Feet -20,000 feet per minute to +20,000 feet per minute
450 Knots <1.00 Mach -85° C to +85° C -40° C to +70° C
+73° C
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190-01115-01 Rev. K
11.6 Features Summary
Air Data
Pressure Altitude Density Altitude Vertical Speed Mach Number Indicated Airspeed True Airspeed
Interfaces
CAN (1) RS-232 (2 TX/2 RX) ARINC 429 (4 RX/2 TX) OAT Probe (GTP 59) Magnetometer (GMU 22) (1 RS-232 TX/ 1 RS-485 RX)
AHRS
Engine/Airframe
Magnetic Heading Pitch Angle Roll Angle
27 Analog Inputs 4 Digital Inputs 4 Discrete Intputs
Linear Accelerations
2 Discrete Outputs
Pitch, Roll, Yaw Rotation Rates
11.7 Performance Information
The GSU 73 is capable of maneuvers through a range of 360° in bank and pitch. The rotation rate capability is ±200° per second.
Bank error and pitch error are within 1.25° over the range of 30° bank, left and right, and 15° pitch nose up and nose down. Heading is accurate to within 2° in straight and level flight.
Due to unsuitability of the magnetic fields near the Earth's poles, operational accuracy is unknown in the following regions:
1. North of 72° North latitude at all longitudes 2. South of 70° South latitude at all longitudes 3. North of 65° North latitude between longitude 75° W and 120° W (Northern Canada) 4. North of 70° North latitude between longitude 70° W and 128° W (Northern Canada) 5. North of 70° North latitude between longitude 85° E and 114° E (Northern Russia) 6. South of 55° South latitude between longitude 120° E and 165° E (Region South of Australia and
New Zealand)
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G3X Installation Manual - GSU 73 Installation Page 11-7
11.8 Maintenance
Per Part 43 Appendix E, paragraph (b)(2), Garmin specifies a test procedure equivalent to part 43 Appendix E, paragraph (b)(1) with two exceptions. The tests of sub-paragraph (iv)(Friction) and (vi) (Barometric Scale Error) are not applicable because the digital outputs of the GSU 73 are not susceptible to these types of errors.
A GSU 73 Field Calibration Tool can be used to adjust the calibration of GSU 73 units that have failed the 14 CFR Part 43 Appendix E tests due to altitude drift. Please contact a local Garmin dealer for more information.
The GSU 73 utilizes an Earth magnetic field model which is updated once every five years. This IGRF (International Geomagnetic Reference Field) update is expected to be available from Garmin by July 1 of 2015 and every five years thereafter, so long as the GSU 73 remains a Garmin supported product. The IGRF model is automatically updated with a GDU 37X software update. Alternatively, the IGRF model can be updated by the end user via the Garmin website (www.garmin.com), it is not necessary to return the GSU 73 to Garmin for this update. Otherwise maintenance of the GSU 73 is `on condition' only.
G3X Installation Manual - GSU 73 Installation Page 11-8
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12 GTP 59 INSTALLATION (CORE G3X LRU)
This section contains general information as well as installation information for the GTP 59. Use this section to mount the GTP 59.
NOTE
For installations using more than one ADAHRS, ADAHRS 1 must be connected to a GTP 59, but installing additional GTP 59's for other GSU 25 ADAHRS units is optional. An ADAHRS not connected to a GTP 59 will use temperature data supplied by other ADAHRS as long as both ADAHRS are communicating via the CAN bus.
Figure 12-1. GTP 59
12.1 Equipment Description
The Garmin GTP 59 is an outside mounted temperature probe that provides raw air temperature data. The temperature input device is a three-wire temperature probe interface. OAT Power Out and OAT High are connected internally at the OAT probe.
The GTP 59 is available per the following part number.
Table 12-1 GTP 59 Part Number
Item GTP 59 OAT Probe Kit
*Included in G3X w/GSU 73 LRU (K10-00016-00)
Garmin Part Number 011-00978-00*
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G3X Installation Manual - GTP 59 Installation Page 12-1
Table 12-2 contains a list of items found in the GTP 59 Outside Air Temperature (OAT) Probe kit (011-00978-00). The GTP 59 probe has an attached pigtail.
Table 12-2 GTP 59 Outside Air Temperature Kit*
Item
Garmin Part Number
Nut, 5/16", Hex, Skirt
210-00055-00
Screw, 4-40 x .250, PHP, SS/P, w/NYL
211-60234-08
Washer, Lock, Self-Sealing, 5/16
212-00026-00
Contact, Pin, Mil Crimp, Size 22D
336-00021-00
GTP 59 OAT Probe
494-00022-xx
*Included in G3X w/GSU 73 LRU Kit (K10-00016-00)
Quantity 1 2 1 5 1
12.1.1 Additional Equipment Required · Cables - The installer will supply all system cables.
12.2 General Specifications
See Section B-10.1 for mounting dimensions.
12.3 Unit Installation
NOTE
The following instructions are general guidance.
NOTE
The GTP 59 is a Resistive Temperature Device (RTD) that detects changing temperature by monitoring small changes in resistance. For optimum accuracy, take care to avoid introducing extra resistance, such as loose, dirty, or corroded connections in the wiring path between the ADAHRS and GTP 59.
NOTE
Do not mount the GTP 59 where aircraft exhaust gases will flow over it.
G3X Installation Manual - GTP 59 Installation Page 12-2
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Table 12-3 contains a list of parts needed for the GTP 59 installation and interconnect harness. Reference numbers in the table and following instructions refer to item bubble numbers shown in Figure B-10.1. Refer to Figure B-10.1 GTP 59 O.A.T. Probe Wiring Detail for wiring and mounting instructions.
Table 12-3 Parts Needed for GTP 59 Installation
Figure D-4.1
Description
Qty. Included
GPN
1
Ring Terminal
2
3-Conductor Cable
1
3
OAT Sensor
4
Nut
1
494-00022-xx 210-00055-00
5
Washer
1
212-00026-00
1. Prepare the surface. The metal body of the OAT probe should be grounded to the aircraft. The installation requirements vary depending on the airframe material composition.
a) Aluminum airframe: When a mounting location has been found, prepare the inside surface of the aircraft. Remove all paint from the contacting area and clean with a degreaser.
b) Composite airframe: If possible, mount the OAT probe through a grounded metal strap or band. Otherwise, mount the OAT probe in an area of the airframe that has a significant amount of underlying metal foil or mesh. To ensure adequate conductivity, it may be necessary to mount the OAT probe through a metal doubler. Use fasteners that allow a conductive path to the airframe.
2. Mount the OAT probe on the prepared surface. Place the ring terminal (1) over the end of the OAT probe (3). Insert the probe and ring terminal into the hole in the skin of the aircraft. Place the washer (5) over the end of the OAT probe on the outside skin of the aircraft. Thread the nut (4) onto the OAT probe. Holding the OAT probe on the inside, tighten the nut (4) to 100 inch-lbs. 20 inch-lbs.
3. Route the OAT probe cable (2) to the GSU 25/GSU 73.
4. Cut the OAT Probe cable (2) to the required length. Strip back 2.0" to 3.5" of jacket while retaining the shield on the OAT Probe cable (2). Trim away enough to leave 0.5" of shield exposed.
5. Strip back 1/8" (0.125") of insulation and crimp pins to each of the conductors in the shielded cable.
6. Cut an AWG #16 wire to 3" long. Strip back 0.5" of insulation from this cable. Connect the shield of the OAT Probe cable (2) to the AWG #16 wire.
7. Attach the ring terminal to the backshell, using the screw provided in the OAT Probe Kit and one of the tapped holes on the backshell termination area.
8. Insert newly crimped pins into the D-Sub connector and wires into the appropriate connector housing location as specified by the installation wiring diagrams.
9. Verify that all necessary pins for the GSU 25/GSU 73 have been attached to the cables and snapped into the proper slots of the 78 pin D-Sub connector.
10. Wrap the cable bundle with Silicone Fusion Tape (GPN: 249-00114-00 or a similar) at the point where the backshell strain relief and cast housing contact the cable bundle. The smooth side of the backshell strain relief should contact the tape.
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G3X Installation Manual - GTP 59 Installation Page 12-3
12.4 TSO/ETSO Compliance
The following table provides a list of applicable TSO/ETSOs for the GTP 59.
Table 12-4 Applicable TSO/ETSOs for the GTP 59
Function
TSO/ETSO
Applicable LRU SW Part Numbers
Applicable CLD Part Numbers
Air Data Computer
TSO-C106 ETSO-C106
Not Applicable
Not Applicable
12.4.1 TSO/ETSO Deviations The following deviations have been requested and granted for the GTP 59.
TSO/ETSO TSO-C106 ETSO-C106
Table 12-5 TSO/ETSO Deviations for the GTP 59
Deviation
1. Garmin was granted a deviation from TSO-C106 to use RTCA DO-160D, including changes 1, 2, and 3, instead of RTCA DO-160B as the standard for Environmental Conditions and Test Procedures for Airborne Equipment.
2. Garmin was granted a deviation from TSO-C106 to use Society of Automotive Engineers (SAE) AS 8002 Rev A instead of SAE AS 8002 as the Minimum Performance Standard.
1. Garmin was granted a deviation from ETSO-C106 to use Society of Automotive Engineers (SAE) AS 8002 Rev A instead of SAE AS 8002 as the Minimum Performance Standard.
12.4.2 GTP 59 Icing
The GTP 59 OAT probe has no icing protection. If ice accumulates on the GTP 59 OAT probe, its accuracy is unknown. Consequently, air temperature measurements may be incorrect if ice accumulates on the probe. Furthermore, computations dependent upon air temperature measurements may be affected (e.g. true airspeed and delta-ISA).
12.5 Maintenance
Maintenance of the GTP 59 is "on condition" only. Periodic maintenance of the GTP 59 is not required.
G3X Installation Manual - GTP 59 Installation Page 12-4
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13 GPS/XM ANTENNA INSTALLATION (CORE G3X LRU)
This section contains general information as well as installation information for GPS and XM antennas. Use this section to mount the GPS/XM antenna(s).
In an installation with multiple GDU 37X units, each GDU can be configured to use its own internal GPS receiver, or to receive GPS data transmitted by another GDU. A minimum of one GPS antenna is required for installations using more than one GDU 37X unit, as the GDU 37X will "share" the GPS information with all GDU 37X units. Additional GPS antennas may be used for redundancy, but are not required. See Section 17.3.13 for further information.
NOTE
Only a single GPS antenna is required for installations using more than one GDU 37X unit, as the GDU 37X will "share" the GPS information with all GDU 37X units.
13.1 Non-Garmin Antennas
Table 13-1 lists non-Garmin antennas currently supported by the GDU 37X. For non-Garmin antennas, follow the manufacturer's installation instructions. It is the installer's responsibility to ensure that their choice of antenna meets FAA standards according to the specific installation.
NOTE
The GPS antenna should provide a gain of 16 to 25 dB. The GDU 37X supplies power to the antenna at 4.5 V5V with a maximum current of 50 mA.
Table 13-1 Supported Non-Garmin Antennas
Model
Mount Style
Conn Type
Antenna Type
Mfr
Antenna Part Number
Garmin Order Number
Comant 2480-201 VHF/GPS*
Screw Mount, Teardrop Footprint
BNC TNC
VHF COM, GPS
Comant CI 2480-201
N/A
Comant
Screw Mount,
420-10 XM
ARINC 743 TNC
XM
Comant
CI 420-10
N/A
only Antenna
Footprint
*The GPS antenna connector is TNC type. The VHF COM antenna connector is BNC type.
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13.2 Garmin Antennas
If using a Garmin GA 26C or GA 26XM, refer to the accompanying installation instructions (190-00082-00 or 190-00522-03). For GA 55/55A, or GA 56 or GA 57X antennas, refer to this section and the outline and installation drawings beginning with Figure B-1.1.
Garmin recommends the antennas shown in Table 13-2. However, any equivalent GPS or XM antenna that meets the specifications listed in Table 13-3 and Table 13-4 should work with the G3X.
Table 13-2 Supported Garmin Antennas
Model GA 26C
Part Number 011-00149-04
Description GPS Antenna
GA 26XM 013-00268-10 XM Antenna
GA 55
011-01033-00 XM Antenna
GA 55A 011-01153-00 XM Antenna
GA 56 GA 57X
011-00134-00 011-01032-10
GPS Antenna
GPS/XM Antenna
Weight
NA
NA
0.25 lbs (0.11 kg) 0.43 lbs (0.20 kg) 0.24 lbs (0.11 kg) 0.47 lbs (0.21 kg)
Mounting Configuration Flange, Magnetic, or Suction Cup Mount (for in-cabin mounting) Flange, Magnetic, or Suction Cup Mount (for in-cabin mounting)
Stud mount (Tear-drop form factor)
Thru-mount (ARINC 743 style mount)
Stud mount (Tear-drop form factor)
Thru-mount (ARINC 743 style mount)
Table 13-3 GPS Antenna Minimum Requirements
Characteristics Frequency Range Gain Noise Figure Nominal Output Impedance Supply Voltage Supply Current Output Connector
Specifications 1565 to 1585 MHz 16 to 25 dB typical, 40 dB max.
<4.00 dB 50 ohms 4.5 to 5.5 VDC up to 50 mA
BNC
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Table 13-4 XM Satellite Radio Antenna Minimum Requirements
Characteristics
Specifications
Frequency Range
2332.5 to 2345 MHz
Gain (Typical)
24 dB*
Noise Figure
<1.2 dB
Nominal Output Impedance
50 ohms
Supply Voltage
3.6 to 5.5 VDC
Supply Current (maximum)
55 mA
Operating Temperature Gain
-50 to +85° C
*For each 1 dB gain over 24 dB, add 1 dB of attenuation into the antenna cable path between the antenna and the GDU 375.
It is the installer's responsibility to ensure that their choice of antenna meets FAA standards according to the specific installation. This installation manual discusses only the antennas listed in Table 13-2. Other antennas may be acceptable but their installation is not covered by this manual.
There are several critical factors to take into consideration before installing an antenna for a satellite communications system. These factors are addressed in the following sections.
13.3 Antenna Mounting Considerations
The information in this section does not pertain to in-cabin (internal) mounted antennas such as the GA 26C, refer to the accompanying installation instructions (190-00082-00).
No special precautions need be taken to provide an electrical bonding path between the GPS Antenna and the aircraft structure.
13.3.1 VHF COM/GPS Interference
On some installation VHF COM transceivers, Emergency Locator Transmitter (ELT) antennas, and Direction Finder (DF) receiver antennas can re-radiate through the GPS antenna. The GDU 37X does not interfere with its own GPS receiver. However, placement of the GPS antenna relative to a COM transceiver and COM antenna, ELT antenna, and DF receiver antenna is critical.
Use the following guidelines, in addition to others in this document, when locating the GDU 37X and its antennas.
· GPS Antenna--Locate as far as possible from all COM antennas and all COM transceivers, ELT antennas, and DF antennas. The GPS antenna is less susceptible to harmonic interference if a 1.57542 GHz notch filter is installed on the COM transceiver antenna output.
· Locate the GDU 37X as far as possible from all COM antennas.
If a COM antenna is found to be the problem, a 1.57542 GHz notch filter (Garmin P/N 330-00067-00) may be installed in the VHF COM coax, as close to the COM as possible.
If a COM is found to be radiating, the following can be done:
1. Replace or clean the VHF COM rack connector to ensure good coax ground. 2. Place grounding straps between the GDU 37X unit, VHF COM and a good ground. 3. Shield the VHF COM wiring harness.
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13.3.2 GPS/XM Antenna Mounting Location
The GPS antenna is a key element in the overall system performance and integrity for a GPS navigation system. The mounting location, geometry, and surroundings of the antenna can affect the system performance and/or availability. The following guidance provides information to aid the installer in ensuring that the optimum location is selected for the installation of the GPS antenna. The installation guidelines presented here meet the intent of AC 20-138A section 16. The greater the variance from these guidelines, the greater the chance of decreased availability. Because meeting all of these installations guidelines may not be possible on all aircraft, these guidelines are listed in order of importance to achieve optimum performance. Items 4a - 4c below are of equal importance, and their significance may depend on the aircraft installation. The installer should use their best judgment to balance the installation guidelines.
1. Mount the antenna on top of the aircraft in a location with an unobstructed view of the sky, as close to level as possible with respect to the normal cruise flight attitude of the aircraft. If the normal flight attitude is not known, substitute the waterline, which is typically referenced as level while performing a weight and balance check.
2. The GPS antenna should be mounted in a location to minimize the effects of airframe shadowing during typical maneuvers. Typically mounting farther away from the tail section reduces signal blockage seen by the GPS antenna.
3. The GPS antenna should ideally be located at the opposite end of the aircraft from the COM unit in order to make the GPS less vulnerable to harmonics radiated from the COM itself.
4a. The GPS antenna should be mounted no closer than two feet (edge to edge) and ideally three feet from any VHF COM antenna or any other antenna which may emit harmonic (or other) interference at the L1 frequency of 1575.42 MHz. An aircraft EMC (Electromagnetic Compatibility) check (Section 19.2) can verify the degradation of GPS in the presence of interference signals. If an EMC check reveals unacceptable interference, insert a GPS notch filter in line with the offending VHF COM or the (re-radiating) ELT transmitter.
NOTE
The separation requirement does not apply to GPS and COM combination antennas, provided the antenna has been tested to meet Garmin's minimum performance standards. The separating requirement includes the combination with an XM antenna element as well.
4b. The GPS antenna should be mounted no closer than two feet (edge to edge) and ideally three feet from any antennas emitting more than 25 watts of power. An aircraft EMC check can verify the degradation of GPS in the presence of interference signals.
4c. To minimize the effects of shadowing at 5° elevation angles, the GPS antenna should be mounted no closer than 6 inches (edge to edge) from other antennas, including passive antennas such as another GPS antenna or XM antenna.
5. To maintain a constant gain pattern and limit degradation by the windscreen, avoid mounting the antenna closer than 3 inches from the windscreen.
6. For multiple GPS installations, the antennas should not be mounted in a straight line from the front to the rear of the fuselage. Also varying the mounting location will help minimize any aircraft shading by the wings or tail section (in a particular azimuth, when one antenna is blocked the other antenna may have a clear view).
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Figure 13-1 shows the recommended placement of antennas. 4
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Figure 13-1 Recommended Antenna Placement
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13.3.3 Buried Antenna (below the skin covering or glareshield) Mounting There are potential performance issues related to buried antennas that the kit builder/installer should be aware of prior to electing to install a buried antenna. See also Section 13.6.2, Non-structural Installation to Glareshield.
· Some gain of the antenna may be lost as the signal needs to penetrate through the skin of the aircraft. The loss may not be apparent, but under the some of the worst case signal scenarios signal availability may be affected.
· The materials in some aircraft are not suitable for GPS signals to penetrate, care should be taken to properly modify the aircraft structure to accommodate this. Modifications of this sort are not recommended or inferred by Garmin or the installation of the GDU 37X, and the installer should seek the guidance of the kit manufacture for such modifications.
· XM FIS antennas may typically be buried without performance impact if the overlying material is fairly transparent to the satellite signal.
Figure 13-2 shows example areas of some mounting locations which have been used. Low satellite reception and tracking are compromised in these installations due to fuselage and tail blockage. It is not possible to determine the full impact of these locations, however initial flight testing has not shown any significant impact to availability, your results may vary.
Figure 13-2 Carbon/Glass Buried Antenna Area
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Mounting the antenna under the glare shield (Figure 13-3) is a good option for XM FIS antennas, although it is not typically the best option for a GPS antenna. This location results in the aft fuselage shading the antenna.
Figure 13-3 Glare Shield Buried Antenna Area
NOTE
Due to the excessive temperature environment and large areas of signal blockage caused by the fuselage, mounting the antenna under the engine cowling (forward of the firewall) is not recommended and likely will not provide adequate GPS reception.
13.3.4 Antenna Doubler/Backing Plate
The antenna installation must provide adequate support for the antenna considering a maximum drag load of 5 lbs. (at subsonic speed). When penetrating the skin with a large hole (i.e. for the coax connector) a doubler plate is required to re-instate the integrity of the aircraft skin. Never weaken the aircraft structure when choosing a mounting area. Make use of any available reinforcements where appropriate.
13.3.5 Antenna Grounding Plane
Although no ground plane is required, the antennas typically perform better when a ground plane is used. The ground plane should be a conductive surface as large as practical, with a minimum diameter of 8 inches. To use an antenna in aircraft with fabric or composite skin, a ground plane is recommended. It is usually installed under the skin of the aircraft, below the antenna, and is made of either aluminum sheet or of wire mesh.
13.3.6 Antenna Grounding
The antenna is grounded through the mounting hardware and the coax connection. The mounting hardware (washers and nuts) and doubler plate should make contact with an unpainted grounded surface ensuring proper antenna grounding. It is important to have good conductivity between the coaxial shield and the ground plane. The bottom of the antenna does not need to make contact with the ground plane (i.e. the surface may be painted). The antenna will capacitively couple to the ground plane beneath the paint or aircraft cover.
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13.4 Teardrop Footprint Antenna Installation (GA 55 and GA 56)
This section describes the structural mounting of the teardrop footprint antenna installation.
An acceptable installation method is to use Garmin P/N: 115-00846-10 doubler plate with the GA 55 or GA 56 stud mount antennas. Another acceptable method is to fabricate and install one of three doublers (Figure 13-4, Figure 13-5, and Figure 13-6), depending on the thickness of the skin. The three doubler designs vary only by number of rivets and hole preparation for installation with flush rivets. Table 13-5 provides a summary of design and installation details for selecting the appropriate antenna doubler/ backplate.
Figure 13-7 shows an example of the doubler installed between stringers on the top fuselage skin, just off centerline. The location should be flat, with no gaps between the skin and doubler, to keep from deforming the skin during installation.
Table 13-5 Teardrop Footprint Antenna Doubler Design and Installation
Aircraft Skin Thickness
0.032" to 0.049"
0.049" to 0.051"
0.051" to 0.063"
Doubler Design (Figure)
Figure 13-4
Figure 13-5
Figure 13-6
Number of Rivets Required
12
16
16
Type of Rivets Required1
MS20426AD4-x
MS20426AD4-x
MS20426AD4-x
Skin Preparation for Rivets
Dimple
Dimple
Countersink
Doubler Preparation for Rivets
Countersink
Countersink
None
Skin Cutout Detail (Figure)
Figure 13-8
Figure 13-9
Figure 13-10
Doubler Installation (Figure)
Figure 13-11
Figure 13-12
Figure 13-13
1Rivet length determined at installation, dependent on thickness of material (rivet length = grip length + 1.5 * rivet diameter)
Refer to the drawings beginning with Figure B-1.1 for Garmin Antenna installation drawings.
13.4.1 Preparation of Doubler
1. Use Garmin P/N: 115-00846-10, or refer to Table 13-5 for guidance on selecting the appropriate doubler drawing based on the thickness of skin at the antenna location. Make the doubler from 2024-T3 Aluminum (AMS-QQ-A-250/5), 0.063" sheet thickness.
2. For installation in aircraft skins of thickness less than 0.051", countersink the rivet holes in the doubler for use with flush head rivets (MS20426AD4-x).
3. When using Garmin P/N: 115-00846-10 doubler, sixteen rivet holes exist in the part. For installation of Garmin P/N: 115-00846-10 in skins of thickness between 0.032" and 0.049", only the rivets identified for use through the skin cutout detail (Figure 13-8) and doubler installation (Figure 13-11) are required.
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13.4.2 Antenna Installation Instructions
1. Refer to Table 13-5 and the outline and installation drawings beginning with Figure B-1.1 for guidance on selecting the appropriate mounting cutout. Drill or punch the holes to match the mating part (doubler).
2. Install a doubler plate to reinforce the aircraft skin, as required. Refer to Section 13.4.1 for doubler preparation and Table 13-5 for additional guidance on the doubler installation. Dimple aircraft skin when the skin thickness is less than 0.051" for installation of flush head rivets. Countersink aircraft skin when the skin thickness is between 0.051" and 0.063" for installation of flush head rivets.
3. For the stud mount teardrop footprint antenna, place install gasket on top of aircraft skin using the four screw holes to align the gasket.
4. Washers and locking nuts are required to secure the antenna. Torque the four #8-32 stainless steel locking nuts 12-15 in-lbs. Torque should be applied evenly across all mounting studs or screws to avoid deformation of the mounting area.
5. Ensure that the antenna base and aircraft skin are in continuous contact with the gasket or o-ring, as appropriate to the antenna model.
6. Seal the antenna and gasket to the fuselage using Dow Corning 738 Electrical Sealant or equivalent. Run a bead of the sealant along the edge of the antenna where it meets the exterior aircraft skin. Use caution to ensure that the antenna connectors are not contaminated with sealant.
CAUTION
Do not use construction grade RTV sealant or sealants containing acetic acid. These sealants may damage the electrical connections to the antenna. Use of these type sealants may void the antenna warranty.
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13.4.3 Reference Figures
Figure 13-4 Doubler Design, Teardrop Footprint Antenna, Skin Thickness 0.032" to 0.049"
Figure 13-5 Doubler Design, Teardrop Footprint Antenna, Skin Thickness 0.049" to 0.051"
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Figure 13-6 Doubler Design, Teardrop Footprint Antenna, Skin Thickness 0.051" to 0.063"
Figure 13-7 Sample Doubler Location, Teardrop Footprint Antenna, Metal Skin Aircraft
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Figure 13-8 Skin Cutout Detail, Teardrop Footprint Antenna, Skin Thickness 0.032" to 0.049"
Figure 13-9 Skin Cutout Detail, Teardrop Footprint Antenna, Skin Thickness 0.049" to 0.051"
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Figure 13-10 Skin Cutout Detail, Teardrop Footprint Antenna, Skin Thickness 0.051" to 0.063"
Figure 13-11 Doubler Installation, Teardrop Footprint Antenna, Skin Thickness 0.032" to 0.049"
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Figure 13-12 Doubler Installation, Teardrop Footprint Antenna, Skin Thickness 0.049" to 0.051"
Figure 13-13 Doubler Installation, Teardrop Footprint Antenna, Skin Thickness 0.051" to 0.063"
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13.5 ARINC 743 Footprint Antenna Installation (GA 55A, GA 57X)
This section describes the structural mounting of the ARINC 743 footprint antenna (GA 55A, GA 57X) installation. One acceptable method is to use Garmin P/N: 115-00846-00 doubler plate. Another acceptable method is to fabricate and install one of three doublers, Figure 13-14, Figure 13-15, or Figure 13-16, depending on the thickness of the skin. The three doubler designs vary only by number of rivets and hole preparation for installation with flush rivets. Figure 13-24 shows installation of the ARINC 743 footprint antenna.
Table 13-6 provides a summary of design and installation details for the antenna doubler. Figure 13-17 shows an example of the doubler installed between stringers on the top fuselage skin, just off centerline. The location should be flat, with no gaps between the skin and doubler, to keep from deforming the skin during installation.
Table 13-6 ARINC 743 Footprint Antenna Doubler Design and Installation
Skin Thickness
0.032" to 0.049"
0.049" to 0.051"
0.051" to 0.063"
Doubler Design (Figure)
Figure 13-14
Figure 13-15
Figure 13-16
Number of Rivets Required
12
16
16
Type of Rivets Required1
MS20426AD4-x
MS20426AD4-x
MS20426AD4-x
Skin Preparation for Rivets
Dimple
Dimple
Countersink
Doubler Preparation for Rivets
Countersink
Countersink
None
Skin Cutout Detail (GA 55A)
Figure 13-18
Figure 13-19
Figure 13-20
Doubler Installation (Figure)
Figure 13-21
Figure 13-22
Figure 13-23
1Rivet length determined at installation, dependent on thickness of material (rivet length = grip length + 1.5 * rivet diameter)
13.5.1 Preparation of Doubler
1. Use Garmin P/N: 115-00846-00, or refer to Table 13-6 for guidance on selecting the appropriate doubler drawing based on the thickness of skin at the antenna location. Make the doubler from 2024-T3 Aluminum (AMS-QQ-A-250/5), 0.063" sheet thickness.
2. For installation in aircraft skins of thickness less than 0.051", countersink the rivet holes in the doubler for use with flush head rivets (MS20426AD4-x).
3. When using Garmin P/N: 115-00846-00 doubler, sixteen rivet holes exist in the part. For installation of Garmin P/N: 115-00846-00 in skins of thickness between 0.032" and 0.049", only the rivets identified for use through the skin cutout detail (Figure 13-18) and doubler installation (Figure 13-21) are required.
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13.5.2 Antenna Installation Instructions
1. Refer to Table 13-6 (and the outline and installation drawings beginning with Figure B-1.1) for guidance on selecting the appropriate mounting cutout. Drill or punch the holes to match the mating part (doubler).
2. Install a doubler plate to reinforce the aircraft skin, as required. Refer to Section 13.5.1 for doubler preparation and Table 13-6 for additional guidance on the doubler installation. Dimple aircraft skin when the skin thickness is less than 0.051" for installation of flush head rivets. Countersink aircraft skin when the skin thickness is between 0.051" and 0.063" for installation of flush head rivets.
3. Place the install gasket on top of aircraft skin using the four screw holes to align the gasket.
4. Locking nuts are required to secure the antenna (locking nuts installed on doubler). Torque the four supplied #10-32 stainless steel screws (Garmin P/N: 211-60212-20, MS51958-67, or equivalent) 20-25 in-lbs. Torque should be applied evenly across all mounting studs to avoid deformation of the mounting area.
5. Ensure that the antenna base and aircraft skin are in continuous contact with the gasket.
6. Seal the antenna and gasket to the fuselage using Dow Corning 738 Electrical Sealant or equivalent. Run a bead of the sealant along the edge of the antenna where it meets the exterior aircraft skin. Use caution to ensure that the antenna connectors are not contaminated with sealant.
CAUTION
Do not use construction grade RTV sealant or sealants containing acetic acid. These sealants may damage the electrical connections to the antenna. Use of these type sealants may void the antenna warranty.
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13.5.3 Reference Figures
Figure 13-14 Doubler Design, ARINC 743 Footprint Antenna, Skin Thickness 0.032" to 0.049"
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Figure 13-15 Doubler Design, ARINC 743 Footprint Antenna, Skin Thickness 0.049" to 0.051"
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Figure 13-16 Doubler Design, ARINC 743 Footprint Antenna, Skin Thickness 0.051" to 0.063"
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Figure 13-17 Sample Doubler Location, ARINC 743 Antenna, Metal Skin Aircraft
Figure 13-18 Skin Cutout Detail, ARINC 743 Footprint Antenna, Skin Thickness 0.032" to 0.049"
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Figure 13-19 Skin Cutout Detail, ARINC 743 Footprint Antenna, Skin Thickness 0.049" to 0.051"
Figure 13-20 Skin Cutout Detail, ARINC 743 Footprint Antenna, Skin Thickness 0.051" to 0.063"
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Figure 13-21 Doubler Installation, ARINC 743 Footprint Antenna, SkinThickness 0.032" to 0.049"
Figure 13-22 Doubler Installation, ARINC 743 Footprint Antenna, SkinThickness 0.049" to 0.051"
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Figure 13-23 Doubler Installation, ARINC 743 Footprint, Skin Thickness 0.051" to 0.063"
Figure 13-24 Installation of ARINC 743 Footprint Antenna
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13.6 Non-Structural Mount Installation
This section provides installation examples and considerations for non-structural mounting of teardrop and ARINC 743 footprint antennas. Typical installations may be below a non-metallic glareshield, under the composite or fabric skin, or on an external, non-structural surface. Other non-structural installations may exist, but are not presented in this manual.
External mounting of the antenna is preferred, although the antenna can be mounted inside the aircraft. When mounted internally, the antenna does not have to be aligned with the aircraft forward direction, but should be equal to the aircraft typical cruise attitude.
There should be a solid mechanical base in the mounting area for the antenna, and existing surfaces or brackets may be used with the doubler plate. Alternately, non-structural brackets may be fabricated in the field as necessary to mount the antenna. Brackets should be made of minimum 0.032" thickness aluminum and should span as short a distance as possible.
Some fabric aircraft include aluminum paste in the fabric finishing process, often referred to as "silver coats". Presence of thick fabric and/or heavy "silver coats" may degrade the signal strength of the antenna.
13.6.1 Generic Non-structural Antenna Installation
Figure 13-25 shows the generic non-structural installation for the ARINC 743 footprint (GA 55A/GA 57X) antenna. The teardrop footprint antennas (GA 55, GA 56 stud mount) can also be installed in this manner.
For mounting the teardrop style antenna (GA 55 or GA 56), a doubler plate similar to Figure 13-4 or P/N 115-00846-10 can be used with the mounting surface to support the antenna. Rivets used to secure the doubler plate to the mounting surface are optional in a non-structural installation. Screws, washers, and locking nuts as shown in the outline and installation drawings beginning with Figure B-1.1, are required to secure the Teardrop style antenna to the mounting surface. Torque the locking nuts to 12-15 in-lbs, torque should be applied evenly across all mounting studs.
A doubler plate similar to Figure 13-11, or P/N 115-00846-00 (ARINC 743 style) can be used with the mounting surface to support the antenna. Rivets used to secure the doubler plate to the mounting surface are optional in a non-structural installation. Locking nuts are required to secure the ARINC 743 antenna (locking nuts installed on doubler). Torque the four supplied #10-32 stainless steel screws (Garmin P/N: 211-60212-20, MS51958-67, or equivalent) evenly across all mounting screws.
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Figure 13-25 Generic Non-structural ARINC 743 Footprint Antenna Installation
13.6.2 Non-Structural Installation to Glareshield
Figure 13-26 shows an example of a bracket created to support an antenna mounted on the underside of the glare shield. Figure 13-27 shows the non-structural mounting of the antenna under the glareshield, with the bracket assembly shown in Figure 13-26.
Figure 13-26 Example Bracket Antenna Mounting Under Glareshield
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Figure 13-27 Example Non-structural Antenna Mounting Under Glareshield
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13.6.3 Non-structural Installation to Airframe
Internal Non-structural Installation
Figure 13-28 and Figure 13-29 show examples of under the fabric skin non-structural mounting of the antenna to the airframe of a tube-and-fabric aircraft.
In Figure 13-28, a bracket is made to attach to the airframe, just under the fabric for a teardrop antenna installation. The doubler plate and mounting hardware described in the generic installation (Section 13.6.1) are used with the bracket as the antenna mounting surface. In Figure 13-29, a similar case is shown using the generic installation of the ARINC 743 footprint antenna. The doubler plate is optional for this type of installation with either the Teardrop or the ARINC 743 antenna.
Figure 13-28 Example Teardrop Antenna Installation In Airframe Under Fabric Skin
Figure 13-29 Example ARINC 743 Footprint In Airframe Under Fabric Skin
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External Non-structural Installation
Figure 13-30 is an example of an external, non-structural mounting of the antenna in a tube-and-fabric aircraft. The antenna support bracket shown should be made of 2024-T3 Aluminum with a minimum material thickness 0.032" and maximum distance between airframe tubes of 36". The bracket is installed to the airframe under the fabric, and the antenna is mounted externally to the bracket. The generic installation of the (Section 13.6.1) antenna is used, with the antenna support bracket as the mounting surface. Follow the applicable gasketing and sealant instructions in Section 13.4.2 (Teardrop style) or Section 13.5.2 (ARINC 743 style).
Figure 13-30 Example Non-structural Antenna Mounting On Airframe
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Minimum Distance from Metal Tube Structure Requirements
Figure 13-31 shows minimum distance from metal tube structure requirements for internal, non-structural mounting of the antenna. Table 13-7 presents minimum distance requirements between the tube structure and the antenna for cases where the antenna sits underneath the fabric in a metal-tube structure aircraft. Figure 13-31 illustrates the tube diameter (d) and minimum distance (l) references in the Table 13-7.
Figure 13-31 Example Teardrop Footprint Antenna Mounting Under Fabric Skin
.
Table 13-7 Minimum Distance Required Between Tube Structure and Antenna
Illustrated Case
Top of antenna at or above the center of the tube structure (Figure 13-31, top)
Top of antenna between the center and bottom of the tube structure (Figure 13-31, bottom)
Tube Diameter d (in) 0.625 0.75 1.00 1.25 0.625 0.75 1.00 1.25
Minimum Distance l (in)
3.6 4.3 5.7 7.2 7.2 8.6 11.5 14.3
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14 ENGINE/AIRFRAME SENSOR INSTALLATION (OPTIONAL)
14.1 Engine/Airframe Sensor Options
Table 14-1 lists the types of engine/airframe sensors that may be used for the various engine/airframe inputs. Many of these sensors are included in the Garmin G3X Sensor Kits (Section 14.2). Each of the sensors must be correctly installed and configured (Section 18) prior to use.
Table 14-1 Compatible Engine/Airframe Input Sensors
SENSOR TYPE
Cylinder Head Temperature (CHT)
Exhaust Gas Temperature (EGT)
COMPATIBLE SENSORS Alcor 86253 Type K thermocouple Rotax 965531
Rotax 966385
Type J thermocouple
Alcor 86255 Type K
UMA 1B3-2.5R RTD*** (Resistive Temperature
Detector)
GARMIN PART NUMBER* 494-70000-00 N/A N/A N/A 494-70001-00
494-70004-00
Oil Temperature
Rotax 965531
N/A
Rotax 966385
N/A
Jabiru (VDO 360-003)
N/A
Kavlico P4055-150G-E4A, 0-150 psiG pressure transducer
494-30004-00
Oil Pressure
UMA N1EU150G, 0-150 psiG pressure transducer
N/A
Rotax 956413
N/A
Rotax 956415
N/A
Jabiru (VDO 320-021)
N/A
Kavlico P4055-30A-E4A, 0-30 psiA pressure transducer
494-30004-01
Manifold Pressure
UMA N1EU70A, 0-70 psiA pressure transducer
N/A
Kavlico P500-30A-E4A 0-30 psiA pressure transducer
N/A
*Items with a Garmin part number may be included in a G3X Sensor Kit (Section 14.2), and are available individually from Garmin Dealers **Two sensors required for differential fuel flow ***UMA temperature sensors without the "R" designation are not compatible with the G3X system
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G3X Installation Manual - Engine/Airframe Sensor Installation Page 14-1
Table 14-1 Compatible Engine/Airframe Input Sensors
SENSOR TYPE Fuel Pressure (Injected)
Fuel Pressure (Carbureted)
COMPATIBLE SENSORS
Kavlico P4055-50G-E4A, 0-50 psiG pressure transducer
UMA N1EU70G, 0-70 psiG pressure transducer
Kavlico P4055-15G-E4A, 0-15 psiG pressure transducer
UMA N1EU07D, 0-7 psi differential pressure transducer
UMA N1EU35G, 0-35 psiG pressure transducer
UMA 1A3C-2
UMA T1A9-1 (Slick Mag)
UMA T1A9-2 (Bendix Mag)
GARMIN PART NUMBER* 494-30004-02
N/A
494-30004-03
N/A
N/A N/A 494-50005-00 494-50005-01
RPM
Electronic Ignition (1, 2, 3, or 4 pulses/rev)
N/A
Rotax Trigger Coil
N/A
Jabiru Alternator Output (Single Phase, 6 pulses/rev)
N/A
Resistive
N/A
Fuel Quantity
Capacitive (requires conversion
to a voltage signal or pulsed
N/A
output), refer to Appdx G
Turbine Inlet Temperature (TIT)
Type K thermocouple
494-70002-00
Coolant Pressure
Kavlico P4055-50G-E4A, 0-50 psiG pressure transducer
494-30004-02
Bus Voltage
10-29 Vdc input
N/A
Bus Current
Shunt Type UMA 1C4 +/-50 Amp, 100 Amp
Hall Effect Type - Amploc KEY100 +/-100 Amp
909-D0000-00 N/A
Fuel Flow
EI FT-60** Floscan Series 200**
494-10001-00 N/A
*Items with a Garmin part number may be included in a G3X Sensor Kit (Section 14.2), and are available individually from Garmin Dealers **Two sensors required for differential fuel flow ***UMA temperature sensors without the "R" designation are not compatible with the G3X system
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Table 14-1 Compatible Engine/Airframe Input Sensors
SENSOR TYPE
COMPATIBLE SENSORS
GARMIN PART NUMBER*
Discrete Inputs
Active High or Low: Canopy
Warning, Gear Down Reminder,
N/A
etc.
UMA 1B10R***
494-70005-00
Carburetor Temperature
Rotax 965531
N/A
Rotax 966385
N/A
Trim servo with integrated
Position Sensor
position sensor or standalone slide potentiometer (0-5 K
N/A
variable resistor)
RTD (e.g. UMA 1B3XR series)
N/A
Auxiliary Temperature
50-150C Thermistor (e.g. VDO 320-XXX series)
N/A
*Items with a Garmin part number may be included in a G3X Sensor Kit (Section 14.2), and are available individually from Garmin Dealers **Two sensors required for differential fuel flow ***UMA temperature sensors without the "R" designation are not compatible with the G3X system
The Engine inputs being monitored are displayed as gauges on the EIS display (Figure 14-1) and also on the MFD's Engine Page.
Figure 14-1 EIS Display (Engine Bar) The following list of gauges, (if configured) are specifically required by FAR 91.205 and will always be displayed on the EIS display (engine bar). Other gauges will be displayed as space permits based on a predefined priority and user selections.
RPM Coolant Temperature
Oil Temperature Fuel Quantity
Oil Pressure
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G3X Installation Manual - Engine/Airframe Sensor Installation Page 14-3
14.2 Garmin G3X Sensor Kits
Table 14-2, Table 14-3, and Table 14-4 list Garmin sensor kits available for G3X installations. Refer to Sensor Interface drawings in Appendix F when installing Sensor Kits K00-00512-00 and K00-00513-00. Refer to Sensor Interface drawings in Appendix G when installing Sensor Kit K00-00514-00.
Table 14-2 Contents of G3X Sensor Kit, 4 Cylinder Lycoming/Continental (K00-00512-00)
Item Fuel Flow Transducer, EI FT-60 Oil Pressure Transducer, Powered, 150 psi, Gage, w/connector, Kavlico P4055-150G-E4A Manifold Pressure Transducer, Powered, 30 psi, Absolute, w/connector, Kavlico P4055-30A-E4A Type K Thermocouple, Bayonet, CHT, Alcor 86253 Type K Thermocouple, 3/8-24 Bayonet, EGT, Alcor 86255 RTD, Oil Temperature, UMA 1B3-2.5R Shunt, Ammeter, +/-50 mV, 100 amps, UMA 1C4
Garmin P/N 494-10001-00
494-30004-00
Quantity 1
1
494-30004-01
1
494-70000-00
4
494-70001-00
4
494-70004-00
1
909-D0000-00
1
Table 14-3 Contents of G3X Sensor Kit, 6 Cylinder Lycoming/Continental (K00-00513-00)
Item Fuel Flow Transducer, EI FT-60 Oil Pressure Transducer, Powered, 150 psi, Gage, w/connector, Kavlico P4055-150G-E4A Manifold Pressure Transducer, Powered, 30 psi, Absolute, w/connector, Kavlico P4055-30A-E4A Type K Thermocouple, Bayonet, CHT, Alcor 86253 Type K Thermocouple, 3/8-24 Bayonet, EGT, Alcor 86255 RTD, Oil Temperature, UMA 1B3-2.5R Shunt, Ammeter, +/-50 mV, 100 Amps, UMA 1C4
Garmin P/N 494-10001-00
494-30004-00
Quantity 1
1
494-30004-01
1
494-70000-00
6
494-70001-00
6
494-70004-00
1
909-D0000-00
1
Table 14-4 Contents of G3X Sensor Kit, Rotax 912 (K00-00514-00)
Item
Manifold Pressure Transducer, Powered, 30 psi, Absolute, w/ connector, Kavlico P4055-30A-E4A
Fuel Pressure Transducer, Powered, 15 psi, Gage, w/connector, Kavlico P4055-15G-E4A
Type K Thermocouple, 3/8-24 Bayonet, EGT, Alcor 86255
Shunt, Ammeter, +/-50 mV, 100 Amps, UMA 1C4
Garmin P/N 494-30004-01
Quantity 1
494-30004-03
1
494-70001-00
2
909-D0000-00
1
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14.3 Engine Sensor Installation
NOTE
The following sections contain general guidance on engine and airframe sensor installation. This information is provided for reference only. The installer should always follow any installation guidance and instructions provided by the applicable engine, sensor, or kit-plane manufacturer. Additionally, all installation practices should be done in accordance with AC 43.13-1B.
Appendix E, Appendix F, Appendix G, and Appendix H contain interface drawings for sensor installations using the Garmin sensor kits, and for other sensor installations. 14.3.1 CHT (Cylinder Head Temperature) Type J grounded thermocouple - This type of sensor is typically used on Jabiru engines. See Jabiru Guidance for thermocouple installation.
Type K grounded thermocouple - This type of sensor is applicable to the Lycoming and Continental engines and is installed in CHT well.
NOTE
If ungrounded thermocouples are used, the low side must be connected to a GEA 24/ GSU 73 ground pin.
Rotax 965531 CHT Sensor - See Rotax Guidance for CHT Sensor installation. Rotax 966385 CHT Sensor - See Rotax Guidance for CHT Sensor installation.
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14.3.1.1 Lycoming and Continental Engine Sensor Installation General Installation Guidance To maintain measurement accuracy, thermocouple (TC) wire must be connected directly to the inputs of the GEA 24/GSU 73. If the supplied sensor wires are not long enough to connect directly to the GEA 24/GSU 73, then Type K TC extension wire must be used. To minimize risk of breakage, it is recommended that a high-quality stranded (as opposed to solid) thermocouple wire be used. One such example of appropriate wire is TT-K-22S Type K thermocouple wire from Omega Engineering. When using Alcor Type K probes, refer to Alcor CHT Installation Instructions (P/N 59167) for complete installation details. Engine manufacturer's guidance should always be consulted for proper location of CHT probes. A finger sized loop should be provided to allow sufficient strain relief of the probe assembly, and care should be taken to ensure that no chafing of the wires occurs.
Figure 14-2 CHT Probe Package
Figure 14-3 CHT Probe Well
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Figure 14-4 One Piece CHT Probe Installed
14.3.2 EGT (Exhaust Gas Temperature)
Sensor Description Type K grounded thermocouple probe with integrated clamp for mounting in an exhaust pipe.
NOTE
If ungrounded thermocouples are used, the low side must be taken to a GEA 24/GSU 73 ground pin.
14.3.2.1 Engine Sensor Installation
General Installation Guidance To maintain G3X Engine Indicating System (EIS) measurement accuracy, thermocouple (TC) wire must be connected directly to the inputs of the GEA 24/GSU 73. If the supplied sensor wires are not long enough to connect directly to the GEA 24/GSU 73, then Type K TC extension wire must be used. To minimize risk of breakage, it is recommended that a high quality stranded (as opposed to solid) thermocouple wire be used. TT-K-22S Type K thermocouple wire from Omega Engineering is one such example of appropriate wire. When using Alcor Type K probes, refer to Alcor EGT Installation Instructions (P/N 59180) for complete installation details. Engine manufacturer's guidance should be consulted and followed for proper location of EGT probes.
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Perform the following steps and refer to Figure 14-5, Figure 14-6, and Figure 14-7 to install an EGT sensor.
1. EGT probes (Figure 14-5) should optimally be mounted between 2 and 4 inches from the cylinder head on a flat portion of the exhaust tube. To maintain consistent readings across cylinders, all probes should be mounted an equal distance from the exhaust flanges.
2. Carefully center punch the probe hole locations so that the external portion of the probe does not interfere with any other parts of the engine or cowling (Figure 14-6). It may be desirable to angle the probes towards the rear of the engine to allow efficient wire routing back to the cockpit. If angling the probes towards the rear of the engine, take care to ensure that sufficient clearance is provided to service the spark plugs.
3. Carefully insert probe into the exhaust pipe and tighten the clamp snugly with screwdriver (35 inlbs torque max.).
4. Connect the EGT probes to the thermocouple extension wire. Provide strain relief for the assembly by either fastening the probe leads to the valve covers with a clamp, or by tying the extension wire to the intake tubes or other suitable location. A finger-sized loop should be provided to allow appropriate strain relief, and care should be taken to ensure that no chafing of the wires occurs. See Figure 14-7 for an example of an installed EGT probe.
Figure 14-5 EGT Package
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Figure 14-6 Exhaust Pipe Drilled
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Figure 14-7 Installed EGT Probe Orientation
G3X Installation Manual - Engine/Airframe Sensor Installation Page 14-9
14.3.3 Oil Temperature Threaded 5/8-18 Platinum Resistance Temperature Detector (RTD) probe - This sensor is applicable to the Lycoming and Continental engines.
Rotax 965531 or Rotax 966385 Oil Temperature Sensor - See Rotax guidance for sensor installation.
Jabiru Oil Temperature Sensor - See Jabiru guidance for sensor installation.
14.3.3.1 Lycoming and Continental Engine Sensor Installation General Installation Guidance Refer to the applicable engine manual for proper location of the oil temperature sensor. The sensor is usually installed near the oil filter.
1. Cut the safety wire and remove the existing vent plug (Figure 14-8), if installed. 2. To prevent galling of the threads, apply a small amount of engine oil to the probe threads. 3. Ensure that an unused copper crush gasket is present on the probe, and install the probe into the
engine (black side of crush gasket down).
NOTE
Crush gaskets can only be used once. A new gasket must be installed any time the probe is removed and installed.
4. Tighten the probe to the torque as specified by the engine manufacturer. 5. Safety-wire the probe to the engine case as appropriate. 6. Connect the supplied connector to the appropriate inputs on the GEA 24/GSU 73 as referenced in
the G3X interconnects in Appendix F. Secure the connector and wire assembly to an appropriate location in the engine compartment to provide strain relief.
Figure 14-8 Vent Plug
Figure 14-9 Oil Temperature Figure 14-10 Oil Temperature
Probe
Probe Installed (Crush
Gasket Not Shown)
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14.3.4 Pressure (Fuel, Manifold, Oil, and Coolant)
General Installation Guidance The specified pressure transducers provide for two different mounting options:
Figure 14-11 Pressure Transducer Mounting Block
a) Sensor body secured to the engine mount or firewall via an appropriately sized Adel clamp (preferred)
OR
b) Mounted to a transducer mounting block located on the firewall. UMA sensor mounting may require the use of a stainless steel AN911 fitting (union).
NOTE
To minimize the possibility of cracking or breaking of the transducer due to vibration, the sensor should not be mounted directly to the engine. Mechanical failure of the transducer could result in loss of engine pressure for the sensed parameter (oil, fuel, manifold, coolant).
Once a suitable sensor mounting arrangement has been identified, the following installation procedures should be followed:
1. Mount the sensor using one of the two methods noted above. 2. Refer to the applicable engine manual to identify the appropriate connecting port on the engine for
the parameter being sensed. Once identified, use appropriate aircraft-grade hoses and fittings to connect the corresponding port on the engine to the sensor. The male threads on Kavlico sensors are designed to mate with a 1/8" NPT female thread. The female threads on UMA sensors are designed to mate with a 1/8" NPT male thread.
NOTE
The fuel and oil pressure fittings on the engine port should have a restrictor hole where appropriate to minimize potential fluid loss in the event of breakage.
3. Connect the supplied connector to the appropriate inputs of the GEA 24/GSU 73 as referenced in the Sensor Interface Drawings in Appendices F, G, and H. Secure the connector and wire assembly to an appropriate location in the engine compartment to provide strain relief.
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14.3.4.1 Fuel Pressure Sensor Kavlico P4055-15G-E4A - 0 15 psiG pressure transducer for all carbureted engines. Kavlico P4055-50G-E4A - 0 50 psiG pressure transducer for all fuel injected engines. UMA N1EU07D - 0-7 psiD differential pressure transducer for turbocharged carbureted engines (Rotax 914) UMA N1EU35G - 0 35 psiG pressure transducer for carbureted engines. UMA N1EU70G - 0 70 psiG pressure transducer for fuel injected engines.
NOTE
Lycoming EIS display ranges are typically set to correspond with the pressure at the inlet to the fuel injector. Continental EIS display ranges are typically set to correspond to unmetered fuel pressure values.
14.3.4.2 Manifold Pressure Sensor Kavlico P4055-30A-E4A - 0 30 psiA pressure transducer. Kavlico P500-30A-E4A - 0 30 psiA pressure transducer. UMA N1EU70A - 0 70 psiA pressure transducer. 14.3.4.3 Oil Pressure Sensor Kavlico P4055-150G-E4A - 0 150 psiG pressure transducer. This pressure sensor is applicable to Lycoming and Continental engines. Rotax P/N 956413 or 956415 pressure transducer - These pressure sensors are applicable to Rotax engines. Refer to Rotax Installation Instructions for complete installation details Jabiru Oil Temperature Sensor - See Jabiru guidance for sensor installation. UMA N1EU150G - 0 150 psiG pressure transducer. 14.3.4.4 Coolant Pressure Sensor Kavlico P4055-50GE4A - 0 50 psiA pressure transducer. This type of sensor is applicable to all liquidcooled engines.
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190-01115-01 Rev. K
14.3.5 RPM (Revolutions Per Minute) UMA 1A3C-2 - Standard mechanical tach drive sensor (0 5 volt square wave, 2 pulses per crankshaft rev) UMA N/T1A9-X - Magnetic pickup tach sensor (installed on mag bleed port) Electronic Ignition - Tach signal output at 1, 2, 3, or 4 pulses per revolution. Jabiru Alternator - Direct connection to alternator output (6 pulses per revolution) Rotax Trigger Coil RPM Sensor - This RPM sensor is applicable to Rotax engines. Refer to Rotax Installation Instructions for complete installation details.
NOTE
Aircraft with dual electronic ignition systems can connect the tachometer signal output from the second ignition to the GEA 24/GSU 73 RPM2 input (see Figure F-2.1). The value displayed on the RPM gauge will be the higher of the two RPM signals.
NOTE
Electronic ignition systems with open-collector tachometer signal outputs may require a pull-up resistor between the tachometer signal output and +5VDC or +12VDC.
14.3.5.1 Lycoming and Continental Engine Sensor Installation
General Installation Guidance
Electronic Ignition - Refer to vendor documentation for proper installation.
UMA 1A3C-2 1. Remove the cap from the tachometer drive output (Figure 14-12) from the back of the engine. 2. Insert adapter tang into slotted keyway in sensor drive port. 3. Screw tach sensor onto threaded driver port, ensuring that the adapter tang on the sensor aligns with the slotted keyway in the drive port (Figure 14-13). 4. Connect the supplied connector to the appropriate inputs on the GEA 24/GSU 73 as referenced in the G3X interconnects in Appendix F. Secure the connector and wire assembly to an appropriate location in the engine compartment to provide strain relief.
NOTE
The body of the sensor unit can be offset slightly to eliminate potential interference with other engine accessories. If the interference cannot be alleviated by offsetting the sensor directly, the builder may either install a magnetic pickup sensor or use a short tachometer drive extension cable to remote mount the sending unit to the engine mount (or other suitable location).
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G3X Installation Manual - Engine/Airframe Sensor Installation Page 14-13
Figure 14-12 Tachometer Drive Output Figure 14-13 Installed Tachometer Sensor
UMA N/T1A9-X
The magnetic pickup tach sensor is installed in the magneto bleed port. It is recommended that it be installed in the non-impulse magneto, but it can be installed in the impulse magneto if only one magneto exists (engines with single electronic ignition). The N/T1A9-X sensors are suitable for non-pressurized magnetos only. Given that the bleed port size on Slick and Bendix magnetos differ, the installer should verify that the sensor part number is appropriate for the magneto type.
1. Remove the existing vent plug from the magneto bleed port (Figure 14-14). 2. Lightly apply thread sealer such as Loctite 242 (or equivalent) to the threads of the sensor. Be
careful not to apply too much, and ensure sealer is applied only to the threads and not the pickup face itself. 3. Install the sensor into the port (Figure 14-16). The sensor should be installed finger tight plus 1/6 turn. Do not over-tighten. 4. Connect the supplied connector to the appropriate inputs on the GEA 24/GSU 73 as referenced in the G3X interconnects in Appendix F. Secure the connector and wire assembly to an appropriate location in the engine compartment to provide strain relief.
Figure 14-14 Magneto Bleed Port
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190-01115-01 Rev. K
NOTE
There are two plugs on a Slick/Unison 43xx series magneto where the tach sender could fit. The one closest to the rotating magnet, with the hex-shaped plug, is correct. The one on the opposite side, with a round plug, is incorrect.
CORRECT TACH SENSOR PORT
WRONG PORT
CORRECT TACH SENSOR PORT
Figure 14-15 Plugs on Slick/Unison 43XX Magneto
WRONG PORT
Figure 14-16 Magneto Tach Sensor Installed
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14.3.6 Fuel Quantity
14.3.6.1 Resistive Type Fuel Quantity Sensors
Resistive type fuel quantity sensors with a 0500 range are currently supported. Wiring methods vary based on the GEA 24/GSU 73 channel being used. Please see Appendices E-H for proper wiring considerations.
14.3.6.2 Capacitive Type Fuel Quantity Sensors
The GSU 73 supports two frequency inputs for fuel quantity, the GEA 24 supports four frequency inputs for fuel quantity.The P-300C receives a +5 V excitation input from the GEA 24/GSU 73 and outputs ±5 V square wave from 600 Hz to 3.8 KHz. See Appendix E for proper wiring considerations.
Capacitive fuel quantity sensors have either frequency or voltage-based ouputs. Capacitive sensors with 5 V or 12 V, 0-50 kHz frequency outputs (including the EI P-300C), are connected to the GEA 24/GSU 73 digital (frequency) fuel quantity inputs (CAP FUEL 1/2). Fuel quantity sensors with 0-5 VDC or 0-12 VDC analog outputs (such as the Skysports or Westach capacitive sensors), are connected to the GEA 24/ GSU 73 analog fuel quantity inputs (FUEL 1/2/3/4). See Figure E-2.1 for examples of each type.
NOTE
Vision Microsystems capacitive level senders may require installing a 5 k pull-down resistor at the sensor output.
NOTE
Princeton capacitive converters may require being connected to aircraft power as a voltage source instead of using the 12V transducer power output.
14.3.7 TIT (Turbine Inlet Temperature) Sensor
Sensor Description Type K grounded thermocouple probe with screw-in type adapter. This type of sensor is applicable to all turbocharged engines.
General Installation Guidance To maintain G3X Engine Indicating System (EIS) measurement accuracy, thermocouple (TC) wire must be connected directly to the inputs of the GEA 24/GSU 73. If the supplied sensor wires are not long enough to connect directly to the GEA 24/GSU 73, then Type K TC extension wire must be used. To minimize risk of breakage, it is recommended that a high-quality stranded (as opposed to solid) thermocouple wire be used. One such example of appropriate wire is TT-K-22S Type K thermocouple wire from Omega Engineering.
14.3.8 Bus Voltage Monitor
Bus voltage is normally sensed from an external voltage signal connected to a GEA 24/GSU 73 analog input (refer to Appendix E for interface drawings). Optionally, the GEA 24/GSU 73 can be configured to measure bus voltage without requiring an external connection, by sensing the voltage of its power supply inputs. See Section 18.3.2 (Volts 1 and Volts 2 Inputs) for configuration guidance.
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14.3.9 Bus Current
14.3.9.1 Hall Effect Ammeter Sensor
Sensor Description Hall Effect: Amploc KEY100, +/- 100 Amp or equivalent. Sensor output is 15.9 mV/Amp. This type of sensor is applicable to all engines.
14.3.9.2 Ammeter Shunt
Sensor Description 1C4: 100 Amp / 50 mv shunt. This type of sensor is applicable to all engines.
General Installation Guidance Current sensing on the G3X can be done via the use of a traditional ammeter shunt (Figure 14-17). The ammeter shunt has two holes in the base for mounting with #10 screws. The current-carrying wires are attached to the large 1/4" lugs, while the current sense wires are attached via the use of #8 ring terminals.
Figure 14-17 Ammeter Shunt
NOTE
It is important that no metal portion of the shunt touch any other portion of the aircraft or exposed wiring. Large voltages and current are present in the shunt, and an electrical short or fire could result from inadvertent contact.
The shunt should be installed in-line with the current being sensed. As noted below, the appropriate wire should be cut and attached to each of the large ¼" lugs. A one amp fuse or other form of circuit protection must be installed between the shunt and the applicable GEA 24/GSU 73 inputs to prevent inadvertent damage to the GEA 24/GSU 73. Connect the two sense wires (attached to the #8 terminals) to the appropriate inputs on the GEA 24/GSU 73 as referenced in the G3X interconnects in Appendices E-H . If the ammeter readings are shown with the opposite polarity, check to see if the sense wire connections are reversed.
An alternator ammeter shunt should be installed inline in the alternator output ("B" terminal). A battery ammeter shunt should be installed between the battery positive terminal and the battery contactor. Depending on the location of the alternator or battery relative to its supported electrical bus, it is typically desirable to install the shunt on the firewall near where the alternator or battery output would normally penetrate the firewall.
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14.3.10 Fuel Flow
Electronics International FT-60 (Red Cube) - This sensor is applicable to all engines. Refer to the Electronics International FT-60 Flow Transducer (Red Cube) document # 1030032 for installation guidance.
General Installation Guidance (Floscan Series 200) This sensor is applicable to all engines. The below is taken from the Floscan Series 200 Flow Transducer Application Notes:
1. The inlet and outlet ports in series 200 flow transducers have ¼" NPT threads. Use only ¼" NPT hose or pipe fittings to match. When assembling fittings into the inlet and outlet ports, DO NOT EXCEED a torque of 15 ft. lbs. (180 inch lbs.), or screw the fittings in more than 2 full turns past hand tight WHICHEVER HAPPENS FIRST. Floscan Instrument Co., Inc. will not be responsible for cracked castings caused by failure to use ¼" NPT fittings, over-torquing the fittings, or assembling them beyond the specified depth.
2. A screen or filter should be installed upstream of the flow transducer to screen out debris which could affect rotor movement or settle in the V-bearings. As turbulence upstream of the transducer affects its performance, there should be a reasonable length of straight line between the transducer inlet and the first valve, elbow, or other turbulence producing device.
3. Install the flow transducer with wire leads pointed UP to vent bubbles and insure that the rotor is totally immersed in liquid. For maximum accuracy at low flow rates, the transducer should be mounted on a horizontal surface.
Some additional mounting considerations should be noted as follows:
1. When installing the NPT fittings into the transducer, use fuel lube such as EZ TURN © or an equivalent thread sealer. Teflon tape should NEVER by used in a fuel system.
2. To minimize inaccuracies caused by turbulence in the fuel flow, the sensor should be mounted with approximately 5-6" of straight tubing before and after the sensor. If special circumstances exist that prevent an extended length of straight tubing before and after the sensor, then a gently curved hose may be acceptable. 45 degree or 90 degree elbow fittings should NOT be used immediately before or after the sensor.
3. Specific sensor mounting location is left to the builder. Ideally, the sensor should be placed prior to the fuel distribution device (carburetor or fuel injection distribution device).
4. On a Continental fuel injected engine, the transducer must be located between the metering unit and the flow divider valve.
5. Sensor wires should be connected to the appropriate inputs on the GEA 24/GSU 73 as referenced in the G3X interconnects in Appendices E-H.
For engines with a fuel return line, a second flow sensor must be used to measure the quantity of unused fuel that is returned from the engine to the fuel tank. Connect the return fuel flow sensor to the GEA 24/ GSU 73 FUEL FLOW 2 input (see Figure E-2.1). The value displayed on the fuel flow gauge will be the difference between the main (supply) fuel flow and secondary (return) fuel flow measurements.
G3X Installation Manual - Engine/Airframe Sensor Installation Page 14-18
190-01115-01 Rev. K
14.3.10.1 K-Factor for Floscan 201B-6 The Floscan 201B-6 (201-030-000) fuel flow sensor ranges from 28,000 to 31,000 pulses/gallon. The G3X default K factor for the 201B-6 is set to 29,500 pulses/gallon. Some Floscan fuel flow sensors come with a tag that lists the K factor number measured during unit calibration (see Figure 14-18).
NOTE
If the Floscan tag shown in Figure 14-18 is lost, the serial number of the Floscan sensor can be supplied to Floscan to obtain the calibrated K factor value.
Actual K Factor measured at 16 GPH
Figure 14-18 Example Floscan Fuel Flow Sensor The tag shown in Figure 14-18 lists a K Factor of 16-2890. The first two digits (16) represent Gallons Per Hour, while the last four digits (2890) represent the number of electrical pulses (divided by 10) output by the sensor per gallon of fuel flow. The numbers on the tag are used in determining the K-Factor to be entered as part of the Fuel Flow Calibration described in Section 18.3.3. To determine this number, a zero should be added to the four digit number on the tag. In the example above after adding the zero to 2890, the resulting K-Factor to be entered on the Fuel Flow Calibration page would be 28900. 14.3.10.2 K-Factor for Electronics International FT-60 (Red Cube) The G3X default K factor for the FT-60 is set to 68,000 pulses/gallon. No sensor specific calibration is required for the FT-60 but variations in the installation can affect the K factor. Reference Electronics International document #1030033 and Section 18.3.3 for additional information.
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G3X Installation Manual - Engine/Airframe Sensor Installation Page 14-19
14.3.11 Carburetor Temperature Sensor
UMA 1B10R - Threaded ¼-28 Platinum Resistance Temperature Detector (RTD) probe. This sensor is applicable to all carbureted Lycoming and Continental engines.
Rotax 965531 or Rotax 966385 - This sensor is applicable to all carbureted Rotax engines. Refer to Rotax Installation Instructions for complete installation details.
14.3.11.1 Lycoming and Continental Engine Sensor Installation
General Installation Guidance:
1. Locate and remove the threaded ¼-28 brass plug (Figure 14-19 and Figure 14-20) on the side of the carburetor as shown in Figure 14-19. If a threaded plug is not present (as is the case with many older carburetors), consult the engine and/or carburetor manufacturer for instructions on how to drill and tap the lead plug adjacent to the butterfly valve.
2. Install a very small amount of thread lubricant on the probe threads and insert into the carburetor (Figure 14-21).
3. Connect the supplied connector to the appropriate inputs of the GEA 24/GSU 73 as referenced in the G3X interconnects in Appendices F and G. Secure the connector and wire assembly to an appropriate location in the engine compartment to provide strain relief.
Figure 14-19 Carb Temp Sensor Mounting Location
Figure 14-20 Carb Temp Sensor Mounting Location
w/Screw Removed
Figure 14-21 Carb Temp Sensor Installed
14.3.12 Position Sensor
Sensor Description Integrated trim servo with position sensor or standalone slide potentiometer (0 5 KOhm variable resistor)
General Installation Guidance Each position sensor installation will vary widely according to the aircraft, motion being sensed, and mechanical installation. For trim servos with integrated position sensing, no external position sensor is required. If mechanical trim is used or no trim servo is present on a particular system (i.e. flaps), then a standalone position sensor can be used. A standalone position sensor should ideally be mounted such that the full travel of the sensor corresponds with the full travel of the control surface.
Refer to the supplied servo or sensor installation manual and G3X interconnects in Appendix E for proper wiring connections. Section 18.3.2 provides calibration instructions.
G3X Installation Manual - Engine/Airframe Sensor Installation Page 14-20
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14.3.13 Rotax 912iS used as FADEC Interface
The G3X system is capable of monitoring the following engine parameters from the Rotax 912iS FADEC digital interface, when connected via a GEA 24:
· RPM · Manifold pressure · Oil pressure · Oil temperature · Exhaust gas temperature · Coolant temperature · Fuel flow · ECU bus voltage
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G3X Installation Manual - Engine/Airframe Sensor Installation Page 14-22
190-01115-01 Rev. K
15 LRU PINOUTS
Use the information in this section (along with other applicable sections/appendices in this document) to construct the wiring required for the G3X installation.
Connector references JXXX(X) and PXXX(X) are used throughout this section and in Appendices C through H. The letter "J" or "P" designates the connector (whether on the LRU or wiring harness). "J" (Jack) refers to the connector on the LRU, and "P" (Plug) refers to the connector on the wiring harness. "J" or "P" designate the connector only, regardless of contact type (pin or socket).
15.1 GAD 29
15.1.1 J291 Connector
Figure 15-1 J291 on GAD 29, as viewed looking at connector on unit
Pin
Pin Name
I/O
1
CAN HI
I/O
2
CAN LO
I/O
3
RESERVED
--
4
RESERVED
--
5
RESERVED
--
6
GROUND
--
7
AIRCRAFT POWER 1
In
8
AIRCRAFT POWER 2
In
9
GROUND
--
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G3X Installation Manual - LRU Pinouts Page 15-1
15.1.2 J292 Connector
Figure 15-2 J292 on GAD 29, as viewed looking at connector on unit
Pin
Pin Name
I/O
1
RESERVED
--
2
RESERVED
--
3
RESERVED
--
4
ARINC RX 4B
In
5
ARINC RX 3B
In
6
ARINC TX 2B
Out
7
8
RESERVED
--
9
CAN TERM 1
--
10
ARINC RX 2B
In
11
ARINC RX 1B
In
12
ARINC TX 1B
Out
13
14
GROUND
--
15
RESERVED
--
16
ARINC RX 4A
In
17
ARINC RX 3A
In
18
ARINC TX 2A
Out
19
20
GROUND
--
21
CAN TERM 2
--
22
ARINC RX 2A
In
23
ARINC RX 1A
In
24
ARINC TX 1A
Out
25
G3X Installation Manual - LRU Pinouts Page 15-2
190-01115-01 Rev. K
15.1.3 Power
This section covers the power input requirements. AIRCRAFT POWER 1 and AIRCRAFT POWER 2 are "diode ORed" to provide power redundancy.
Pin Name AIRCRAFT POWER 1 AIRCRAFT POWER 2 POWER GROUND POWER GROUND
Connector
Pin
I/O
J291
7
In
J291
8
In
J291
6
--
J291
9
--
15.1.4 ARINC 429 RX/TX
The ARINC 429 outputs conform to ARINC 429 electrical specifications when loaded with up to 5 standard ARINC 429 receivers. Each ARINC 429 Transmitter pin is physically connected to two DSUB pins. When running one transmitter to two receivers use two separate pins to avoid splicing wires. Running one transmitter to more than two receivers will require splicing wires.
Pin
Connector
Pin Name
I/O
23
J292
ARINC RX 1A
In
11
J292
ARINC RX 1B
In
24
J292
ARINC TX 1A
Out
25
12
J292
ARINC TX 1B
Out
13
22
J292
ARINC RX 2A
In
10
J292
ARINC RX 2B
In
18
J292
ARINC TX 2A
Out
19
6
J292
ARINC TX 2B
Out
7
17
J292
ARINC RX 3A
In
5
J292
ARINC RX 3B
In
16
J292
ARINC RX 4A
In
4
J292
ARINC RX 4B
In
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G3X Installation Manual - LRU Pinouts Page 15-3
15.1.5 CAN Bus
The CAN Bus conforms to the BOSCH standard for Controller Area Network 2.0-B, and complies with ISO 11898. Pins 9 and 21 are used to terminate the CAN bus. To terminate the CAN bus at the GAD 29 short the pins (9 and 21) together. Refer to Section 2.3.1.3 for details on configuring and terminating the CAN bus. The CAN bus on J241 shall be used for communications between G3X LRUs.
CAN HI CAN LO CAN TERM 1 CAN TERM 2
Pin Name
Connector
Pin
I/O
J291
1
I/O
J291
2
I/O
J292
9
--
J292
21
--
G3X Installation Manual - LRU Pinouts Page 15-4
190-01115-01 Rev. K
15.2 GDU 37X
15.2.1 J3701 Connector
PIN 1
PIN 17
PIN 18
PIN 33
PIN 34
PIN 50
Figure 15-3 J3701 on GDU 37X, as viewed looking at connector on unit
Pin
Pin Name
I/O
1
MONO AUDIO OUT HI
Out
2
STEREO AUDIO OUT LO
--
3
STEREO AUDIO OUT LEFT
Out
4
SPARE
--
5
SPARE
--
6
SPARE
--
7
SPARE
--
8
SPARE
--
9
CDU SYSTEM ID PROGRAM* 2
In
10
CDU SYSTEM ID PROGRAM* 1
In
11
RESERVED FOR FUTURE DEVELOPMENT, DO NOT USE
--
12
RESERVED FOR FUTURE DEVELOPMENT, DO NOT USE
--
13
RS-232 OUT 3
Out
14
RS-232 IN 2
In
15
POWER GROUND
--
16
POWER GROUND
--
17
CONFIG MODULE POWER OUT
Out
18
MONO AUDIO OUT LO
--
19
STEREO AUDIO OUT RIGHT
Out
20
STEREO AUDIO OUT LO
--
21
SPARE
--
22
SPARE
--
23
SPARE
--
24
SPARE
--
*Indicates Active Low
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G3X Installation Manual - LRU Pinouts Page 15-5
Pin
Pin Name
I/O
25
CDU SYSTEM ID PROGRAM* 3
In
26
28V LIGHTING BUS HI
In
27
SIGNAL GROUND
--
28
CAN BUS TERMINATION
--
29
RS-232 IN 3
In
30
RS-232 OUT 2
Out
31
AIRCRAFT POWER 2
In
32
AIRCRAFT POWER 1
In
33
CONFIG MODULE CLOCK
I/O
34
SIGNAL GROUND
--
35
SIGNAL GROUND
--
36
SIGNAL GROUND
--
37
SIGNAL GROUND
--
38
SPARE
--
39
SPARE
--
40
SPARE
--
41
SPARE
--
42
CDU SYSTEM ID PROGRAM* 4
In
43
14V LIGHTING BUS HI
In
44
SIGNAL GROUND
--
45
CAN BUS LO
I/O
46
CAN BUS HI
I/O
47
RS-232 IN 1
In
48
RS-232 OUT 1
Out
49
CONFIG MODULE GROUND
--
50
CONFIG MODULE DATA
I/O
*Indicates Active Low
NOTE
The GDU 37X rear connector (J3701) is electrically isolated. For installations using shielded cables, a ground pin must be tied to the connector shell.
G3X Installation Manual - LRU Pinouts Page 15-6
190-01115-01 Rev. K
15.2.2 Aircraft Power
The GDU can operate using power from one or both inputs (AIRCRAFT POWER 1 AND AIRCRAFT POWER 2). The pins are internally connected using diodes to prevent current from flowing between the two power inputs. AIRCRAFT POWER 2 is for connecting to an alternate power source, such as on aircraft with two electrical buses.
AIRCRAFT POWER 1 AIRCRAFT POWER 2 POWER GROUND POWER GROUND
Pin Name
Connector
Pin
I/O
J3701
32
In
J3701
31
In
J3701
15
--
J3701
16
--
15.2.3 Mode Selections
In a single-display system, configure the display as PFD1. In a two display-system, configure one display as PFD1 and the other display as MFD. In a three-display system, one display is PFD1, one is the MFD, and the third is PFD2.
Configure the GDU 37X units per the following tables.
A GDU 37X can be manually placed in reversionary mode by wiring Pin 25 to a two pole switch that toggles between open and ground. When the switch is open, the display will operate normally. When the switch is grounded, the display changes to reversionary mode, showing the engine bar at the top of the display and a split screen PFD and MFD below. Other displays in the system will not be affected by manually placing a display into reversionary mode.
Do not connect a switch to ground for pins 9 or 10, doing so can cause communication errors.
Grounding pin 42 will place the GDU 37X in Demo mode, which is for in-store demonstration use only, never ground pin 42 in an aircraft installation.
CDU SYSTEM ID PROGRAM* 1, J3701 Pin 10
Open Ground Open Ground
CDU SYSTEM ID PROGRAM* 2, J3701 Pin 9
Open Open Ground Ground
GDU Mode
MFD PFD1 PFD2 Do Not Use
CDU SYSTEM ID PROGRAM* 3 J3701 Pin 25
Open
Ground
GDU Mode
Auto Reversionary Forced Reversionary
CDU SYSTEM ID PROGRAM* 4 J3701 Pin 42
Open
Ground
GDU Mode
Normal Operation Demo Mode
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G3X Installation Manual - LRU Pinouts Page 15-7
15.2.4 Serial Data 15.2.4.1 RS-232 3 Channels of RS-232 I/O data.
RS-232 IN 1 RS-232 OUT 1 RS-232 IN 2 RS-232 OUT 2 RS-232 IN 3 RS-232 OUT 3
Pin Name
Connector Pin
I/O
J3701
47
In
J3701
48
Out
J3701
14
In
J3701
30
Out
J3701
29
In
J3701
13
Out
15.2.4.2 CAN Bus
This data bus conforms to the BOSCH standard for Controller Area Network 2.0-B. This bus complies with ISO 11898. CAN BUS TERMINATION should be connected to CAN BUS LO for the GDU that is located at the end of the bus (farthest from the GSU 73), see Section 2.3.1.3 for details.
CAN BUS HI CAN BUS LO CAN BUS TERMINATION
Pin Name
Connector Pin
I/O
J3701
46
I/O
J3701
45
I/O
J3701
28
--
15.2.4.3 Configuration Module Connect the configuration module to the PFD1 unit; do not connect a config module to PFD2 or the MFD.
Pin Name CONFIG MODULE CLOCK CONFIG MODULE DATA CONFIG MODULE POWER OUT CONFIG MODULE GROUND
Wire Color WHITE (WHT) YELLOW (YEL)
RED (RED) BLACK (BLK)
Connector Pin
I/O
J3701
33
I/O
J3701
50
I/O
J3701
17
Out
J3701
49
--
G3X Installation Manual - LRU Pinouts Page 15-8
190-01115-01 Rev. K
15.2.5 Lighting
The GDU 37X display brightness can be configured to track 28 VDC or 14 VDC lighting busses using these inputs.
14V LIGHTING BUS HI 28V LIGHTING BUS HI
Pin Name
Connector Pin
I/O
J3701
43
In
J3701
26
In
15.2.6 Audio
15.2.6.1 Mono Audio
The mono audio output provides audio alerts for connection to an unswitched input on an intercom or audio panel.
MONO AUDIO OUT HI MONO AUDIO OUT LO
Pin Name
Connector Pin
I/O
J3701
1
Out
J3701
18
--
15.2.6.2 Stereo Audio
The stereo audio output provides XM audio for connection to an entertainment input on an intercom or audio panel. Audio alerts may optionally be reproduced on the stereo audio output in addition to the mono audio output. See Section 17.3.11 for instructions regarding the sound config page.
The left and right common pins (pins 2 and 20) may be tied together or only one may be used. It is not necessary to use both common pins.
Pin Name STEREO AUDIO OUT LEFT STEREO AUDIO OUT LO STEREO AUDIO OUT RIGHT STEREO AUDIO OUT LO
Connector Pin
I/O
J3701
3
Out
J3701
20
--
J3701
19
Out
J3701
2
--
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G3X Installation Manual - LRU Pinouts Page 15-9
15.3 GEA 24
15.3.1 J241 Connector
Figure 15-4 J241 on GEA 24, as viewed looking at connector on unit
Pin
Pin Name
I/O
1
CAN HI
I/O
2
CAN LO
I/O
3
RESERVED
--
4
RESERVED
--
5
RESERVED
--
6
GROUND
--
7
AIRCRAFT POWER 1
In
8
AIRCRAFT POWER 2
In
9
GROUND
--
G3X Installation Manual - LRU Pinouts Page 15-10
190-01115-01 Rev. K
15.3.2 J242 Connector
Figure 15-5 J242 on GEA 24, as viewed looking at connector on unit
Pin
Pin Name
I/O
1
RESERVED
--
2
CHT6 LO / CHT 2 RESISTIVE LO
In
3
EGT6 LO
In
4
CHT5 LO / CHT 1 RESISTIVE LO
In
5
EGT5 LO
In
6
CHT4 LO
In
7
EGT4 LO
In
8
CHT3 LO
In
9
EGT3 LO
In
10
CHT2 LO
In
11
EGT2 LO
In
12
CHT1 LO
In
13
EGT1 LO
In
14
CHT6 HI / CHT 2 RESISTIVE HI
In
15
EGT6 HI
In
16
CHT5 / CHT 1 RESISTIVE HI
In
17
EGT5 HI
In
18
CHT4 HI
In
19
EGT4 HI
In
20
CHT3 HI
In
21
EGT3 HI
In
22
CHT2 HI
In
23
EGT2 HI
In
24
CHT1 HI
In
25
EGT1 HI
In
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G3X Installation Manual - LRU Pinouts Page 15-11
15.3.3 J243 Connector
Figure 15-6 J243 on GEA 24, as viewed looking at connector on unit
Pin
Pin Name
1
FUEL PRESS GND
2
FUEL PRESS
3
FUEL PRESS XDCR +12V
4
FUEL PRESS XDCR +5V
5
RPM XDCR GND_2
6
RPM 2
7
RPM XDCR GND_1
8
RPM 1
9
RPM XDCR +12V_1
10
RPM XDCR +12V_2
11
RESERVED / SPARE
12
MANIFOLD PRESS GND
13
MANIFOLD PRESS
14
MANIFOLD PRESS XDCR +12V
15
MANIFOLD PRESS XDCR +5V
16
OIL PRESS GND
17
OIL PRESS HI
18
OIL PRESS XDCR +12V
19
OIL PRESS XDCR +5V
20
FUEL XDCR GND_1
21
FUEL RETURN (shared w/Pin 37, J244 connector)
22
FUEL XDCR GND_2
23
FUEL FLOW (shared with Pin 36, J244 connector)
24
FUEL XDCR +12V_1
25
FUEL XDCR +12V_2
26
GP +5V_1
27
GP GND_1
28
POS 7 / TIT 2 / MISC TEMP 2 LO
29
POS 7 / TIT 2 / MISC TEMP 2 HI
*Indicates Active Low
G3X Installation Manual - LRU Pinouts Page 15-12
I/O -In Out Out -In -In Out Out In -In Out Out -In Out Out -In -In Out Out Out -In In
190-01115-01 Rev. K
Pin
Pin Name
I/O
30
POS 6 / TIT 1 / MISC TEMP 1 LO
In
31
POS 6 / TIT 1 / MISC TEMP 1 HI
In
32
OIL TEMP LO
In
33
OIL TEMP HI
In
34
SHUNT 2 LO (shared with Pin 47, J244 connector)
In
35
SHUNT 2 HI (shared with Pin 46, J244 connector)
In
36
SHUNT 1 LO
In
37
SHUNT 1 HI
In
*Indicates Active Low
15.3.4 J244 Connector
PIN 1
PIN 17
PIN 18
PIN 33
PIN 34
PIN 50
Figure 15-7 J244 on GEA 24, as viewed looking at connector on unit
Pin
Pin Name
I/O
1
SYSTEM ID 1A
In
2
SYSTEM ID1B / GND
--
3
SYSTEM ID 2A
In
4
SYSTEM ID 2B / GND
--
5
FUEL QTY +5V_1
Out
6
FUEL QTY 1
In
7
FUEL QTY 1 GND
--
8
FUEL QTY +5V_2
Out
9
FUEL QTY 2
In
10
FUEL QTY 2 GND
--
11
POS 3 HI / +5V_3
Out
12
POS 3 / GP 3 / FUEL QTY 3
In
13
POS 3 LO / GND
--
14
POS 4 HI / +5V_4
Out
15
POS 4 / GP 4 / FUEL QTY 4
In
*Indicates Active Low
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G3X Installation Manual - LRU Pinouts Page 15-13
Pin
Pin Name
16
POS 4 LO / GND
17
CAN2_H
18
GP1 HI / +5V
19
GP1 / POS 1
20
GP1 LO / GND
21
GP2 HI / +5V
22
GP2 / POS 2
23
GP2 LO / GND
24
GP +5V_2
25
VOLTS 1
26
GP GND_2
27
GP +5V_3
28
VOLTS 2
29
GP GND_3
30
POS 5 HI / +5V
31
POS 5 / MISC PRESS
32
POS 5 LO / GND
33
CAN2_L
34
FUEL XDCR +12V_3
35
FUEL XDCR +12V_4
36
FUEL FLOW (shared with Pin 23, J243 connector)
37
FUEL RETURN (shared with Pin 21, J243 connector)
38
FUEL XDCR GND_3
39
FUEL XDCR GND_4
40
DISCRETE IN** 1
41
DISCRETE IN** 2
42
DISCRETE IN** 3
43
DISCRETE IN** 4
44
DISCRETE OUT* 1 / MASTER WARNING
45
DISCRETE OUT* 2 / MASTER CAUTION
46
SHUNT 2 HI (shared with Pin 35, J243 connector)
47
SHUNT 2 LO (shared with Pin 34, J243 connector)
48
RESERVED / SPARE 1
49
RESERVED / SPARE 2
50
GP +12V
*Indicates Active Low **Can be configured as active high or active low
G3X Installation Manual - LRU Pinouts Page 15-14
I/O -I/O Out In -Out In -Out In -Out In -Out In -I/O Out Out In In --In In In In In In In In In In Out
190-01115-01 Rev. K
15.3.5 Aircraft Power
The GEA 24 has two pins for aircraft power inputs of 14/28 Vdc, and can operate using power from one or both inputs (AIRCRAFT POWER 1 AND AIRCRAFT POWER 2). The pins are internally connected using diodes to prevent current from flowing between the two power inputs. AIRCRAFT POWER 2 is for connecting to an alternate power source, such as on aircraft with two electrical buses. The two aircraft power inputs may optionally be used to monitor aircraft bus voltage (see Section 18.3.2.16 for
configuration).
AIRCRAFT POWER 1 AIRCRAFT POWER 2 GROUND GROUND
Pin Name
Connector
Pin
I/O
J241
7
In
J241
8
In
J241
6
--
J241
9
--
15.3.6 CAN Bus
Both data buses conform to the BOSCH standard for Controller Area Network 2.0-B. The busses comply with ISO 11898. Refer to Section 2.3.1.3 for details on configuring and terminating the CAN bus. The CAN bus on J241 shall be used for communications between G3X LRUs. The CAN 2 bus on J244 shall be used to communicate with FADEC engine controllers and shall not be connected to other G3X LRUs. The CAN2 bus is not terminated at the unit, refer to the wiring diagrams for how to terminate the second CAN bus if used.
CAN HI CAN LO CAN2_HI CAN2 LO
Pin Name
Connector
Pin
I/O
J241
1
I/O
J241
2
I/O
J244
17
I/O
J244
33
I/O
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G3X Installation Manual - LRU Pinouts Page 15-15
15.3.7 Digital Inputs
The inputs are capable of sensing frequencies of the range 1 Hz to 100 kHz with a configurable debounce filter. Sensed signals can be either an AC voltage with a peak to peak value of greater than 1 V or an opencollector type input. These inputs are configured by the GDU (refer to Section 18).
NOTE
There are 2 Fuel Flow Input Channels (channels 1 & 2) on J243 and 2 Fuel Flow Input Channels on connector J244. As both channel 1 inputs are connected internally, and both channel 2 inputs are connected internally, the GEA 24 effectively has only 2 two Fuel Flow input channels. Use Channel 1 and/or Channel 2 inputs as desired, but only connect inputs from one connector (either the 37 pin connector or the 50 pin connector) for each
channel.
Pin Name FUEL XDCR +12V_2 FUEL FLOW (shared with Pin 36, J244 connector) FUEL XDCR GND_2 FUEL XDCR +12V_1 FUEL RETURN (shared w/Pin 37, J244 connector) FUEL XDCR GND_1 FUEL XDCR +12V_3 FUEL FLOW (shared with Pin 23, J243 connector) FUEL XDCR GND_3 FUEL XDCR +12V_4 FUEL RETURN (shared with Pin 21, J243 connector) FUEL XDCR GND_4 RPM 1 RPM XDCR GND_1 RPM 2 RPM XDCR GND_2 RPM XDCR +12V_1 RPM XDCR +12V_2 FUEL QTY +5V_1 FUEL QTY 1 FUEL QTY 1 GND FUEL QTY +5V_2 *Indicates Active Low
Connector
Pin
I/O
J243
25
Out
J243
23
In
J243
22
--
J243
24
Out
J243
21
In
J243
20
--
J244
34
Out
J244
36
In
J244
38
--
J244
35
Out
J244
37
In
J244
39
--
J243
8
In
J243
7
--
J243
6
In
J243
5
--
J243
9
Out
J243
10
Out
J244
5
Out
J244
6
In
J244
7
--
J244
8
Out
G3X Installation Manual - LRU Pinouts Page 15-16
190-01115-01 Rev. K
Pin Name FUEL QTY 2 FUEL QTY 2 GND POS 3 HI / +5V POS 3 / GP 3 / FUEL QTY 3 FUEL QTY 3 GND POS 4 HI / +5V POS 4 / GP 4 / FUEL QTY 4 FUEL QTY 4 GND *Indicates Active Low
Connector
Pin
I/O
J244
9
In
J244
10
--
J244
11
Out
J244
12
In
J244
13
--
J244
14
Out
J244
15
In
J244
16
--
15.3.8 Discrete Inputs
The GEA 24 has 4 configurable discrete inputs that can be used as either Active High or Active Low. These inputs are configured by the GDU (refer to Section 18).
When configured as Active Low the inputs conform to the following specification: a) Low: 0 VDC < Vin < 3.5 VDC, OR Rin < 375 ohms (active) b) High: 8 VDC < Vin < 36 VDC OR Rin> 100k ohms (inactive)
When configured as Active High the inputs conform to the following specification: a) Low: 0 VDC < Vin < 3.5 VDC, OR Rin> 100k ohms OR Rin < 375 ohms (inactive) b) High: 8 VDC < Vin < 36 VDC (active)
DISCRETE IN 1 DISCRETE IN 2 DISCRETE IN 3 DISCRETE IN 4
Pin Name
Connector
Pin
I/O
J244
40
In
J244
41
In
J244
42
In
J244
43
In
190-01115-01 Rev. K
G3X Installation Manual - LRU Pinouts Page 15-17
15.3.9 Discrete Outputs
The GEA 24 has 2 annunciator outputs, these outputs do not require any configuration and can be optionally wired to an external annunciator. Discrete Out 1 acts as a master warning annunciator and is active any time a warning CAS message (Red Alert) is displayed on the PFD. Discrete Out 2 acts as a master caution annunciator and is active any time a caution CAS message (Yellow Alert) is displayed on the PFD. Reference Appendix E for wiring guidance.
DISCRETE OUT 1 is "master warning" - goes low when a red (warning) CAS alert is active.
DISCRETE OUT 2 is "master caution" - goes low when a yellow (caution) CAS alert is active.
The two states of these outputs are as follows:
INACTIVE: Floating (can be pulled up to externally sourced Vout in the range 0 Vout 33 VDC)
Leakage current in the INACTIVE state is typically 10 uA to ground
ACTIVE: Vout 0.5 VDC with 20 mA sink current
Sink current must be externally limited to 20 mA max
Pin Name DISCRETE OUT 1 / MASTER WARNING DISCRETE OUT 2 / MASTER CAUTION
Connector
Pin
I/O
J244
44
In
J244
45
In
15.3.10 Fuel Quantity
Fuel Quantity inputs have an internal pull-up resistor that can be enabled for resistive fuel sensor inputs. The inputs can also support capacitive sensors as either voltage inputs or digital inputs. These inputs are configured by the GDU (refer to Section 18).
Pin Name FUEL QTY +5V_1 FUEL QTY 1 FUEL QTY 1 GND FUEL QTY +5V_2 FUEL QTY 2 FUEL QTY 2 GND POS 3 HI / +5V POS 3 / GP 3 / FUEL QTY 3 FUEL QTY 3 GND POS 4 HI / +5V POS 4 / GP 4 / FUEL QTY 4 FUEL QTY 4 GND
Connector
Pin
I/O
J244
5
Out
J244
6
In
J244
7
--
J244
8
Out
J244
9
In
J244
10
--
J244
11
Out
J244
12
In
J244
13
--
J244
14
Out
J244
15
In
J244
16
--
G3X Installation Manual - LRU Pinouts Page 15-18
190-01115-01 Rev. K
15.3.11 GP (General Purpose) Inputs
These inputs are configured by the GDU (refer to Section 18) and are capable of reading any voltage up to 40 Vdc. The GEA 24 has 7 position inputs, labeled POS 1 through 7, and 7 general purpose inputs, GP 1 through 7 (to limit the length of pin names, "GPX" is not used on all pins), each of these are paired together.
Potentiometer based sensors can be used by connecting the potentiometer across a +5 V supply and ground and reading back the center tap voltage on GP1-G7/POS1-7. Some General Purpose inputs have multiple functions.
Pin Name GP1 HI / +5V GP1 / POS 1 GP1 LO / GND GP2 HI / +5V GP2 / POS 2 GP2 LO / GND GP +5V_2 GP GND_2 GP +5V_3 GP GND_3 POS 3 HI / +5V POS 3 / GP 3 / FUEL QTY 3 POS 4 HI / +5V POS 4 / GP 4 / FUEL QTY 4 POS 5 HI / +5V POS 5 / GP 5 / MISC PRESS POS 5 LO / GP 5 / GND GP +12V POS 6 / GP 6 / TIT 1/ MISC TEMP 1 HI POS 6 / GP 6 / TIT 1/ MISC TEMP 1 LO POS 7 / GP7 / TIT 2/ MISC TEMP 2 HI POS 7 / GP 7 / TIT 2/ MISC TEMP 2 LO GP +5V GP GND
Connector
Pin
I/O
J244
18
Out
J244
19
In
J244
20
--
J244
21
Out
J244
22
In
J244
23
--
J244
24
Out
J244
26
--
J244
27
Out
J244
29
--
J244
11
Out
J244
12
In
J244
14
Out
J244
15
In
J244
30
Out
J244
31
In
J244
32
--
J244
50
Out
J243
31
In
J243
30
In
J243
29
In
J243
28
In
J243
26
Out
J243
27
--
190-01115-01 Rev. K
G3X Installation Manual - LRU Pinouts Page 15-19
15.3.12 Pressure Inputs
All pressure inputs are capable of accepting input voltages of up to 40 Vdc. The oil pressure input can also accommodate resistive and constant current source sensors. These inputs are configured by the GDU (refer to Section 18).
Pin Name FUEL PRESS GND FUEL PRESS FUEL PRESS XDCR +12V FUEL PRESS XDCR +5V MANIFOLD PRESS MANIFOLD PRESS GND MANIFOLD PRESS XDCR +12V MANIFOLD PRESS XDCR +5V OIL PRESS HI OIL PRESS GND OIL PRESS XDCR +12V OIL PRESS XDCR +5V
Connector
Pin
I/O
J243
1
--
J243
2
In
J243
3
Out
J243
4
Out
J243
13
In
J243
12
--
J243
14
Out
J243
15
Out
J243
17
In
J243
16
--
J243
18
Out
J243
19
Out
15.3.13 Voltage Inputs
The two bus voltage inputs are capable of accepting voltages of up to 40 Vdc. These inputs are configured by the GDU (Section 18).
VOLTS 1 VOLTS 2
Pin Name
Connector
Pin
I/O
J244
25
In
J244
28
In
15.3.14 Shunt
Shunt Channel 2, has two inputs (either pin 34 & 35 of the J243 or pin 46 & 47 of the J244) for the single channel. Use the inputs from one connector (J243 or J244) only.
SHUNT 1 HI SHUNT 1 LO SHUNT 2 HI* SHUNT 2 LO* SHUNT 2 HI* SHUNT 2 LO*
Pin Name
Connector
Pin
I/O
J243
37
In
J243
36
In
J243
35
In
J243
34
In
J244
46
In
J244
47
In
G3X Installation Manual - LRU Pinouts Page 15-20
190-01115-01 Rev. K
15.3.15 System ID
Pins 1, 2, 3, and 4 must be left open (floating) for a single GEA 24 installation. When using a GEA 24 and GSU 73 in the same system, pins 1 and 2 should be connected together in order to configure the GEA 24 as the EIS #2 LRU.
SYSTEM ID 1A SYSTEM ID 1B / GND SYSTEM ID 2A SYSTEM ID 2B / GND
Pin Name
Connector
Pin
I/O
J244
1
In
J244
2
--
J244
3
In
J244
4
--
15.3.16 Temperature Inputs
Some thermocouple inputs are multi-purpose capable and have several configuration options. CHT5/ CHT6, GP6/GP7, MISC TEMP 1/MISC TEMP 2, and Oil Temp can be used for resistive based temperature sensors. These inputs are configured by the GDU (refer to Section 18).
NOTE
If installing an ungrounded thermocouple to an Analog In input, a DC reference must be added to the LO input. This can be accomplished by adding a resistance of 1 M or less between ground and the Analog In LO input that the ungrounded thermocouple is installed on.
Pin Name CHT1 HI CHT1 LO CHT2 HI CHT2 LO CHT3 HI CHT3 LO CHT4 HI CHT4 LO CHT5 HI / CHT 1 RESISTIVE HI CHT5 LO / CHT 1 RESISTIVE LO CHT6 HI / CHT 2 RESISTIVE HI CHT6 LO / CHT 2 RESISTIVE LO EGT1 HI EGT1 LO EGT2 HI
Connector
Pin
I/O
J242
24
In
J242
12
In
J242
22
In
J242
10
In
J242
20
In
J242
8
In
J242
18
In
J242
6
In
J242
16
In
J242
4
In
J242
14
In
J242
2
In
J242
25
In
J242
13
In
J242
23
In
190-01115-01 Rev. K
G3X Installation Manual - LRU Pinouts Page 15-21
Pin Name EGT2 LO EGT3 HI EGT3 LO EGT4 HI EGT4 LO EGT5 HI EGT5 LO EGT6 HI EGT6 LO POS 6 / GP 6 / TIT 1 / MISC TEMP 1 HI POS 6 / GP 6 / TIT 1 / MISC TEMP 1 LO POS 7 / GP 7 / TIT 2 / MISC TEMP 2 HI POS 7 / GP 7 / TIT 2 / MISC TEMP 2 LO OIL TEMP HI OIL TEMP LO
Connector
Pin
I/O
J242
11
In
J242
21
In
J242
9
In
J242
19
In
J242
7
In
J242
17
In
J242
5
In
J242
15
In
J242
3
In
J243
31
In
J243
30
In
J243
29
In
J243
28
In
J243
33
In
J243
32
In
NOTE
The pinout of J242 is compatible with 25-pin thermocouple wiring harnesses used in some third-party EIS systems.
G3X Installation Manual - LRU Pinouts Page 15-22
190-01115-01 Rev. K
15.3.17Transducer Output Power
The GEA 24 supplies output power for engine/airframe sensors that may require supply voltage excitation. The GEA 24 outputs voltage levels of +5 and +12 Vdc. Each output can supply a maximum of 50 mA. If more than 50 mA is needed for a sensor, 3 outputs of the same voltage may be spliced together to allow an output current of up to 100 mA. Transducers that require more current (such as Princeton capacitive fuel quantity converters) must be supplied from aircraft power instead of GEA 24 transducer power output pins.
The transducer output pins are listed in the following table. Additionally, the pins are also listed in the tables for their respective default functionality.
Pin Name FUEL PRESS XDCR +12V FUEL PRESS XDCR +5V RPM XDCR +12V_1 RPM XDCR +12V_2 MANIFOLD PRESS XDCR +12V MANIFOLD PRESS XDCR +5V OIL PRESS XDCR +12V OIL PRESS XDCR +5V FUEL XDCR +12V_1 FUEL XDCR +12V_2 GP +5V_1 FUEL QTY +5V_1 FUEL QTY +5V_2 POS 3 HI / +5V_3 POS 4 HI / +5V_4 GP1 HI / +5V GP2 HI / +5V GP +5V_2 GP +5V_3 POS 5 HI / +5V FUEL XDCR +12V_3 FUEL XDCR +12V_4 GP +12V *Indicates Active Low
Connector J243 J243 J243 J243 J243 J243 J243 J243 J243 J243 J243 J244 J244 J244 J244 J244 J244 J244 J244 J244 J244 J244 J244
Pin 3 4 9 10 14 15 18 19 24 25 26 5 8 11 14 18 21 24 27 30 34 35 50
I/O Out Out Out Out Out Out Out Out Out Out Out Out Out Out Out Out Out Out Out Out Out Out Out
190-01115-01 Rev. K
G3X Installation Manual - LRU Pinouts Page 15-23
15.4 GMC 305
15.4.1 J3051 Connector
Figure 15-8 J3051 on GMC 305, as viewed looking at connector on unit
Pin
Pin Name
I/O
1
RS-232 OUT 1
Out
2
RS-232 IN 1
In
3
RS-232 OUT 2
Out
4
RS-232 IN 2
In
5
POWER GROUND
--
6
SIGNAL GROUND
--
7
AIRCRAFT POWER 1
In
8
SIGNAL GROUND
--
9
AIRCRAFT POWER 2
In
10
RESERVED
--
11
LIGHTING BUS HI
In
12
LIGHTING BUS LO
In
13
RESERVED
--
14
RESERVED
--
15
POWER GROUND
--
15.4.2 Power
This section covers the power input requirements. AIRCRAFT POWER 1 and AIRCRAFT POWER 2 are "diode ORed" to provide power redundancy.
Pin Name AIRCRAFT POWER 1 AIRCRAFT POWER 2 POWER GROUND POWER GROUND
Connector
Pin
I/O
J3051
7
In
J3051
9
In
J3051
5
--
J3051
15
--
G3X Installation Manual - LRU Pinouts Page 15-24
190-01115-01 Rev. K
15.4.3 Serial Data
The RS-232 outputs conform to EIA Standard RS-232C with an output voltage swing of at least ±5 V when driving a standard RS-232 load.
RS-232 channel 1 should be connected to an available RS-232 port on a GDU 37X display. RS-232 channel 2 should be connected to the GSA 28 roll servo RS-232 port in a Garmin autopilot system (see Figure C-1.5).
Pin Name RS-232 OUT 1 RS-232 IN 1 RS-232 OUT 2 RS-232 IN 2 SIGNAL GROUND SIGNAL GROUND
Connector J3051 J3051 J3051 J3051 J3051 J3051
Pin
I/O
1
Out
2
In
3
Out
4
In
6
--
8
--
15.4.4 Lighting
The GMC 305 can track a 14 VDC lighting bus using these inputs. The GMC 305 can also automatically adjust for ambient lighting conditions based on photocell input. If no (0 VDC) voltage is supplied to the lighting bus input (and unit is configured for 14 V supply), the GMC 305 will automatically adjust for ambient lighting conditions using its built-in photocell.
Pin Name LIGHTING BUS HI LIGHTING BUS LO*
Connector
Pin
I/O
J3051
11
In
J3051
12
In
190-01115-01 Rev. K
G3X Installation Manual - LRU Pinouts Page 15-25
15.5 GMU 22
15.5.1 J441 Connector
Figure 15-9 J441 on GMU 22, as viewed looking at connector on unit
Pin 1 SIGNAL GROUND 2 RS-485 OUT B 3 SIGNAL GROUND 4 RS-485 OUT A 5 SPARE 6 POWER GROUND 7 SPARE 8 RS-232 IN 9 +12 VDC POWER
Pin Name
15.5.2 Power Function Power-input pins accept supply voltage from ADAHRS (GSU 25/73).
Pin Name +12 VDC POWER, GMU 22 POWER GROUND, GMU 22
Connector J441 J441
15.5.3 Serial Data 15.5.3.1 RS-232 The RS-232 input pin accepts data from the ADAHRS (GSU 25/73).
RS-232 IN
Pin Name
Connector J441
I/O -Out -Out ---In In
Pin
I/O
9
In
6
--
Pin
I/O
8
In
15.5.3.2 RS-485 The RS-485 pins provide data to the ADAHRS (GSU 25/73).
RS-485 OUT A RS-485 OUT B
Pin Name
Connector J441 J441
Pin
I/O
4
Out
2
Out
G3X Installation Manual - LRU Pinouts Page 15-26
190-01115-01 Rev. K
15.6 GSA 28
15.6.1 J281 Connector
Figure 15-10 J281 on GSA 28, as viewed looking at connector on unit
Pin
Pin Name
1
CAN_H
2
CAN_L
3
CAN_TERM_1
4
CAN_TERM_2
5
ID_STRAP_1
6
ID_STRAP_2
7
ID_STRAP_3/(RS-232 TX for Roll Servo Only)
8
ID_STRAP_4/(RS-232 RX for Roll Servo Only)
9
AIRCRAFT GROUND
10
AIRCRAFT POWER
11
TRIM_IN_1
12
TRIM_IN_2
13
TRIM_OUT_1
14
TRIM_OUT_2
15
AP_DISCONNECT
15.6.2 Power Function Supply voltage (14/28Vdc) inputs.
AIRCRAFT POWER AIRCRAFT GROUND
Pin Name
I/O I/O I/O --In In In In -In In In Out Out
Connector J281 J281
Pin
I/O
10
In
9
--
190-01115-01 Rev. K
G3X Installation Manual - LRU Pinouts Page 15-27
15.6.3 AP Disconnect
AP Disconnect should be connected to an active low push-button switch that disengages the autopilot, and optionally engages it, if configured. Press and hold the switch to allow for control wheel steering by disengaging the clutch and servo motor. The AP Disconnect input must be connected to both the pitch and the roll servos, and can optionally be connected to the yaw damper servo.
AP_DISCONNECT
Pin Name
Connector J281
Pin
I/O
15
In
15.6.4 CAN Bus
This data bus conforms to the BOSCH standard for Controller Area Network 2.0-B. This bus complies with ISO 11898. See Section 2.3.1.3 for CAN Bus details.
CAN_H CAN_L CAN_TERM_1 CAN_TERM_2
Pin Name
Connector J281 J281 J281 J281
Pin
I/O
1
I/O
2
I/O
3
--
4
--
15.6.5 ID STRAP The ID Strap inputs are used to configure the GSA 28 as a roll, pitch, or yaw servo by installing a jumper wire or not installing a jumper wire per the following:
Roll Servo: No jumper wire installed Pitch Servo: Jumper wire installed from pin 5 to pin 8 Yaw Servo: Jumper wire installed from pin 6 to pin 7
Pin Name ID_STRAP_1 ID_STRAP_2 ID_STRAP_3/(RS-232 TX for Roll Servo Only) ID_STRAP_4/(RS-232 RX for Roll Servo Only)
Connector J281 J281 J281 J281
Pin
I/O
5
In
6
In
7
In
8
In
15.6.6 RS-232 Pins 7 and 8 (TX and RX) connect to the GMC305 RS232 channel 2 on the ROLL SERVO ONLY.
Pin Name ID_STRAP_3/(RS-232 TX for Roll Servo Only) ID_STRAP_4/(RS-232 RX for Roll Servo Only)
Connector J281 J281
Pin
I/O
7
Out
8
In
G3X Installation Manual - LRU Pinouts Page 15-28
190-01115-01 Rev. K
15.6.7 Trim
The trim inputs should connect to the panel trim switch. The trim outputs should connect to the trim servo, maximum output current of the trim outputs is 1 Amp. If the GSA 28 is not powered, a fail-safe feature causes the trim inputs to connect directly to the trim outputs. If the servo is powered and configured for speed scheduling, the servo drives the trim outputs based on the trim inputs and aircraft speed. If the servo is powered with the autopilot and auto trim feature is enabled, the servo has full control of the trim outputs.
A removal adapter (GPN 011-03158-00) is provided (with each GSA 28 connector kit) that can be used when a GSA 28 is removed. The adapter keeps that node on the CAN bus in the same state as when the servo was connected (either terminated or un-terminated). The adapter also allows trim signals to pass through when the servo is removed.
TRIM_IN_1 TRIM_IN_2 TRIM_OUT_1 TRIM_OUT_2
Pin Name
Connector J281 J281 J281 J281
Pin
I/O
11
In
12
In
13
Out
14
Out
190-01115-01 Rev. K
G3X Installation Manual - LRU Pinouts Page 15-29
15.7 GSU 25
15.7.1 J251
Figure 15-11 J251 on GSU 25, as viewed looking at connector on unit
Pin
Pin Name
I/O
1 CAN H
I/O
2 CAN L
--
3 RESERVED
--
4 RS-232 RX 1
In
5 RS-232 TX 1
Out
6 GROUND
--
7 AIRCRAFT POWER 1
In
8 AIRCRAFT POWER 2
In
9 GROUND
--
G3X Installation Manual - LRU Pinouts Page 15-30
190-01115-01 Rev. K
15.7.1.1 J252
Figure 15-12 J252 on GSU 25, as viewed looking at connector on unit
Pin
Pin Name
I/O
1 OAT POWER
Out
2 OAT HIGH
In
3 OAT LOW
In
4 UNIT ID 1 GROUND
--
5 UNIT ID 1
In
6 +12V MAGNETOMETER POWER
Out
7 MAGNETOMETER GROUND
--
8 RESERVED
--
9 RS-232 TX 3
Out
10 RS-232 RX 3
In
11 GROUND
--
12 RS-485 RX A
In
13 RS-485 RX B
In
14 GROUND
--
15 RS-232 TX 2
Out
190-01115-01 Rev. K
G3X Installation Manual - LRU Pinouts Page 15-31
15.7.2 Aircraft Power
The GSU 25 can operate using power from one or both inputs (AIRCRAFT POWER 1 AND AIRCRAFT POWER 2). The pins are internally connected using diodes to prevent current from flowing between the two power inputs. AIRCRAFT POWER 2 is for connecting to an alternate power source, such as on aircraft with two electrical buses.
AIRCRAFT POWER 1 AIRCRAFT POWER 2 POWER GROUND POWER GROUND
Pin Name
Connector
Pin
I/O
J251
7
In
J251
8
In
J251
6
--
J251
9
--
The GSU 25 outputs supply voltage to the GMU 22 via pins 6 & 7.
Pin Name +12V MAGNETOMETER POWER MAGNETOMETER GROUND
Connector
Pin
I/O
J252
6
Out
J252
7
--
15.7.3 Serial Data
15.7.3.1 RS-232
2 Channels of RS-232 RX, and 3 Channels of RS-232 TX data.
RS-232 1: Can optionally be connected to a GDU 37X display to provide a redundant path for attitude data. Also used to configure a GSU 25 as ADAHRS #3.
RS-232 2: Transmits data to the GMU 22.
RS-232 3: Connects to a GTX transponder to provide pressure altitude data and remote transponder control. Transponder should only be connected to ADAHRS 1 (not 2 or 3).
RS-232 RX 1 RS-232 TX 1 RS-232 TX 2 RS-232 RX 3 RS-232 TX 3
Pin Name
Connector Pin
I/O
J251
4
In
J251
5
Out
J252
15
Out
J252
10
In
J252
9
Out
G3X Installation Manual - LRU Pinouts Page 15-32
190-01115-01 Rev. K
15.7.3.2 RS-485 Input
The GSU 25 contains one channel of RS-485 serial data communications for receiving data from the GMU 22.
RS-485 RX A RS-485 RX B
Pin Name
Connector Pin
I/O
J252
1
In
J252
2
In
15.7.3.3 CAN Bus
This data bus conforms to the BOSCH standard for Controller Area Network 2.0-B. This bus complies with ISO 11898. See Section 2.3.1.3 for details.
CAN BUS HI CAN BUS LOW
Pin Name
Connector Pin
I/O
J251
1
I/O
J251
2
--
15.7.4 Temperature Inputs
Temperature input is used for Outside Air Temperature (OAT) computations. The temperature input is a three-wire temperature probe interface. OAT Power Out and OAT High are connected internally at the OAT probe. A GTP 59 or other supported temperature probe is required for the ADAHRS (GSU 25/73) installation that is configured as ADAHRS 1. The GTP 59 is a Resistive Temperature Device (RTD). Refer to Figure B-10.1 for the temperature probe interconnect.
OAT POWER OAT HIGH OAT LOW
Pin Name
15.7.5 Unit ID Refer to Figure C-1.4 for connection drawing.
Connector Pin
I/O
J252
1
Out
J252
2
In
J252
3
In
UNIT ID 1 GROUND UNIT ID 1
Pin Name
Connector Pin
I/O
J252
4
--
J252
5
In
Unit ID ADAHRS #1 ADAHRS #2
ADAHRS #3
Comment
Leave pins 4 and 5 (of J252) unconnected
Connect pin 4 (of J252) to pin 5 (of J252)
Connect pin 4 (of J252) to pin 5 (of J252) and connect RS-232 RX 1 to RS-232 TX 1 (pins 4 and 5 on J251)
190-01115-01 Rev. K
G3X Installation Manual - LRU Pinouts Page 15-33
15.8 GSU 73
15.8.1 Connector Description
The GSU 73 has one 62-pin connector (J731) and one 78-pin connector (J732) located on the connector end of the unit, as shown below. J731 and J732 are clearly marked on the connector end plate.
Figure 15-13 Rear View of Connector End Plate 15.8.2 J731 Connector
Figure 15-14 J731 on GSU 73, as viewed looking at connector on unit
J731 pins are configured as shown in preceding figure. J731 pin assignments are given in the following table, additional tables group pin connections by function.
Pin
Pin Name
I/O
1
MAGNETOMETER RS-485 IN B
In
2
MAGNETOMETER RS-485 IN A
In
3
SIGNAL GROUND
--
4
RESERVED
--
5
RESERVED
--
6
RESERVED
--
7
CAN BUS HI
I/O
8
CAN BUS LO
I/O
9
DISCRETE IN* 1
In
10
DISCRETE IN* 2
In
11
DISCRETE IN* 3
In
12
DISCRETE IN* 4
In
*Indicates Active Low
G3X Installation Manual - LRU Pinouts Page 15-34
190-01115-01 Rev. K
Pin
Pin Name
13
DISCRETE OUT* 1
14
DISCRETE OUT* 2
15
MAGNETOMETER RS-232 OUT
16
RS-232 IN 2 (RESERVED)
17
RS-232 OUT 2 (RESERVED)
18
RS-232 IN 3 (RESERVED)
19
RS-232 OUT 3 (GPS/ALT ENCODER)
20
ARINC 429 OUT 1 A
21
ARINC 429 OUT 1 B
22
ARINC 429 OUT 2 A
23
ARINC 429 OUT 2 B
24
SIGNAL GROUND
25
ARINC 429 IN 1 A
26
ARINC 429 IN 1 B
27
ARINC 429 IN 2 A
28
ARINC 429 IN 2 B
29
CAN BUS TERMINATION
30
ARINC 429 IN 3 A
31
ARINC 429 IN 3 B
32
ARINC 429 IN 4 A
33
ARINC 429 IN 4 B
34
SIGNAL GROUND
35
SIGNAL GROUND
36
SIGNAL GROUND
37
SIGNAL GROUND
38
MAGNETOMETER POWER OUT
39
MAGNETOMETER GROUND
40
SIGNAL GROUND
41
SPARE
42
SPARE
43
SIGNAL GROUND
44
SPARE
45
SPARE
46
SPARE
47
AIRCRAFT POWER 1
48
SPARE
49
AIRCRAFT POWER 2
50
SPARE
51
SPARE
52
SPARE
53
SIGNAL GROUND
*Indicates Active Low
190-01115-01 Rev. K
I/O Out Out OUT In Out In Out Out Out Out Out -In In In In -In In In In ----Out --------In -In -----
G3X Installation Manual - LRU Pinouts Page 15-35
Pin
Pin Name
54
SIGNAL GROUND
55
SPARE
56
SPARE
57
SPARE
58
SIGNAL GROUND
59
POWER GROUND
60
SIGNAL GROUND
61
POWER GROUND
62
SPARE
*Indicates Active Low
15.8.2.1 J732 Connector
I/O ----------
Figure 15-15 J732 on GSU 73, as viewed looking at connector on unit
Pin
Pin Name
I/O
1
CHT 2 LO
In
2
CHT 3 HI
In
3
EGT 2 LO
In
4
EGT 3 LO
In
5
FUEL 1 LO
In
6
MAN PRESS LO
In
7
POS 3/GP 3/FUEL 3 LO
In
8
POS 2/GP 2/TIT 2 LO
In
9
THERMOCOUPLE REF IN LO
In
10
THERMOCOUPLE REF IN HI
In
11
EGT 6/MISC PRESS LO
In
12
VOLTS 2 LO
In
13
CHT 6 LO
In
14
OIL TEMP LO
In
15
OAT PROBE IN HI
In
16
OAT PROBE POWER OUT
Out
17
RPM
In
18
SIGNAL GROUND
--
19
FUEL FLOW
In
*Indicates Active Low
G3X Installation Manual - LRU Pinouts Page 15-36
190-01115-01 Rev. K
Pin
Pin Name
I/O
20
CONFIG MODULE CLOCK
Out
21
CHT 2 HI
In
22
CHT 3 LO
In
23
EGT 2 HI
In
24
EGT 3 HI
In
25
FUEL 1 HI
In
26
FUEL PRESS HI
In
27
POS 3 / GP 3 / FUEL 3 HI
In
28
POS 2 / GP 2 / TIT 2 HI
In
29
EGT 5 LO
In
30
EGT 5 HI
In
31
EGT 6 / MISC PRESS HI
In
32
VOLTS 2 HI
In
33
CHT 6 HI
In
34
OIL TEMP HI
In
35
OAT PROBE IN LO
In
36
CAP FUEL 1 / RPM 2
In
37
SIGNAL GROUND
--
38
CAP FUEL 2 / FUEL FLOW 2
In
39
CONFIG MODULE DATA
I/O
40
CHT 4 LO
In
41
CHT 1 LO
In
42
EGT 4 LO
In
43
EGT 1 LO
In
44
FUEL 2 LO
In
45
FUEL PRESS LO
In
46
POS 4 / GP 4 / FUEL 4 LO
In
47
POS 1 / GP 1 / TIT 1 HI
In
48
SHUNT 2 HI
In
49
OIL PRESS LO
In
50
SHUNT 1 LO
In
51
VOLTS 1 LO
In
52
POS 5 / MISC TEMP LO
In
53
CHT 5 LO
In
54
SPARE
--
55
+12 VDC TRANSDUCER POWER OUT
Out
56
TRANSDUCER POWER OUT LO (GROUND)
--
57
TRANSDUCER POWER OUT LO (GROUND)
--
*Indicates Active Low
190-01115-01 Rev. K
G3X Installation Manual - LRU Pinouts Page 15-37
Pin
Pin Name
I/O
58
+10 VDC TRANSDUCER POWER OUT
Out
59
CONFIG MODULE POWER OUT
Out
60
CHT 4 HI
In
61
CHT 1 HI
In
62
EGT 4 HI
In
63
EGT 1 HI
In
64
FUEL 2 HI
In
65
MAN PRESS HI
In
66
POS 4 / GP 4 / FUEL 4 HI
In
67
POS 1 / GP 1 / TIT 1 LO
In
68
SHUNT 2 LO
In
69
OIL PRESS HI
In
70
SHUNT 1 HI
In
71
VOLTS 1 HI
In
72
POS 5 / MISC TEMP HI
In
73
CHT 5 HI
In
74
TRANSDUCER POWER OUT LO (GROUND)
--
75
+5 VDC TRANSDUCER POWER OUT
Out
76
FUEL SENSOR PULL-UP 2 (FUEL 2)
Out
77
FUEL SENSOR PULL-UP 1 (FUEL 1)
Out
78
CONFIG MODULE GROUND
--
*Indicates Active Low
15.8.3 Power I/O
15.8.3.1 Aircraft Power
The GSU 73 has four inputs for aircraft power bus inputs of 14/28 Vdc, and can operate using power from one or both inputs (AIRCRAFT POWER 1 AND AIRCRAFT POWER 2). The pins are internally connected using diodes to prevent current from flowing between the two power inputs. AIRCRAFT POWER 2 is for connecting to an alternate power source, such as on aircraft with two electrical buses. The two aircraft power inputs may optionally be used to monitor aircraft bus voltage (see Section 18.3.2.16 for configuration).
Pin
Connector
Pin Name
I/O
47
J731
AIRCRAFT POWER 1
IN
49
J731
AIRCRAFT POWER 2
IN
59
J731
POWER GROUND
--
61
J731
POWER GROUND
--
G3X Installation Manual - LRU Pinouts Page 15-38
190-01115-01 Rev. K
15.8.3.2 Transducer Output Power
The GSU 73 supplies output power for engine/airframe sensors that may require supply voltage excitation. The GSU 73 outputs voltage levels of +5, +10, and +12 Vdc, these outputs may be spliced to allow connection to multiple sensors if needed. Max current specs are listed in the following table.
Transducers that require more current (such as Princeton capacitive fuel quantity converters) must be supplied from aircraft power instead of GSU 73 transducer power output pins.
Power Supply Output +5VDC Transducer Power Out +10VDC Transducer Power Out +12VDC Transducer Power Out
Maximum Continuous Output Current 125 mA 100 mA 150 mA
Pin
Connector
Pin Name
55
J732
+12VDC TRANSDUCER POWER OUT
56
J732
TRANSDUCER POWER OUT LO (GROUND)
58
J732
+10VDC TRANSDUCER POWER OUT
57
J732
TRANSDUCER POWER OUT LO (GROUND)
75
J732
+5VDC TRANSDUCER POWER OUT
74
J732
TRANSDUCER POWER OUT LO (GROUND)
15.8.3.3 Magnetometer Power The GSU 73 outputs supply voltage to the GMU 22 via pins 38 & 39.
Pin
Connector
Pin Name
38
J731
MAGNETOMETER POWER OUT
39
J731
MAGNETOMETER GROUND
I/O OUT
-OUT
-OUT
--
I/O OUT
--
190-01115-01 Rev. K
G3X Installation Manual - LRU Pinouts Page 15-39
15.8.4 Serial Data Electrical Characteristics
15.8.4.1 ARINC 429 Input/Output
The ARINC 429 outputs conform to ARINC 429 electrical specifications when loaded with up to 5 standard ARINC 429 receivers.
Pin
Connector
Pin Name
20
J731
ARINC 429 OUT 1A
21
J731
ARINC 429 OUT 1B
22
J731
ARINC 429 OUT 2A
23
J731
ARINC 429 OUT 2B
25
J731
ARINC 429 IN 1A
26
J731
ARINC 429 IN 1B
27
J731
ARINC 429 IN 2A
28
J731
ARINC 429 IN 2B
30
J731
ARINC 429 IN 3A
31
J731
ARINC 429 IN 3B
32
J731
ARINC 429 IN 4A
33
J731
ARINC 429 IN 4B
I/O OUT OUT OUT OUT
IN IN IN IN IN IN IN IN
15.8.4.2 RS-232 Input/Output
The RS-232 outputs conform to EIA Standard RS-232C with an output voltage swing of at least ±5 V when driving a standard RS-232 load. RS-232 OUT 2 is not currently active. RS-232 IN/OUT 3 is used for connection to a transponder (Figure D-2.2 & Figure D-2.3), and is not configurable (always on by default).
Pin
Connector
Pin Name
15
J731
MAGNETOMETER RS-232 OUT
16
J731
RS-232 IN 2 (RESERVED)
17
J731
RS-232 OUT 2 (RESERVED)
18
J731
RS-232 IN 3 (TRANSPONDER)
19
J731
RS-232 OUT 3 (TRANSPONDER)
I/O OUT
IN OUT
IN OUT
G3X Installation Manual - LRU Pinouts Page 15-40
190-01115-01 Rev. K
15.8.4.3 RS-485 Input
The GSU 73 contains one channel of RS-485 serial data communications for receiving data from the GMU 22.
Pin
Connector
Pin Name
I/O
1
J731
MAGNETOMETER RS-485 IN B
IN
2
J731
MAGNETOMETER RS-485 IN A
IN
15.8.4.4 CAN Bus
This data bus conforms to the BOSCH standard for Controller Area Network 2.0-B. This bus complies with ISO 11898. One GDU 37X should be terminated (CAN BUS TERMINATION connected to CAN BUS LO) and the GSU should be terminated if GSU is located at the end of the bus (see Appendix C). See Section 2.3.1.3 for details.
Pin
Connector
Pin Name
I/O
7
J731
CAN BUS HI
I/O
8
J731
CAN BUS LO
I/O
29
J731
CAN BUS TERMINATION
--
15.8.4.5 Configuration Module Interface Connect the GSU 73 to the configuration module using the 4 pins listed below.
Pin
Connector
Pin Name
Wire Color
20
J732
CONFIG MODULE CLOCK
WHITE (WHT)
39
J732
CONFIG MODULE DATA
YELLOW (YEL)
59
J732
CONFIG MODULE POWER OUT
RED (RED)
78
J732
CONFIG MODULE GROUND
BLACK (BLK)
I/O OUT I/O OUT
--
190-01115-01 Rev. K
G3X Installation Manual - LRU Pinouts Page 15-41
15.8.5 Discrete I/O 15.8.5.1 Active Low Discrete Inputs The GSU 73 has 4 configurable discrete inputs conforming to:
Low: 0 VDC < Vin < 3.5 VDC, OR Rin < 375 ohms (active) High: 8 VDC < Vin < 36 VDC OR Rin> 100k ohms (inactive)
Pin
Connector
Pin Name
I/O
9
J731
DISCRETE IN* 1
IN
10
J731
DISCRETE IN* 2
IN
11
J731
DISCRETE IN* 3
IN
12
J731
DISCRETE IN* 4
IN
*Indicates Active Low
15.8.5.2 Discrete Outputs
The GSU 73 has 2 annunciator outputs, these outputs do not require any configuration and can be optionally wired to an external annunciator. Discrete Out 1 acts as a master warning annunciator and is active any time a warning CAS message (Red Alert) is displayed on the PFD. Discrete Out 2 acts as a master caution annunciator and is active any time a caution CAS message (Yellow Alert) is displayed on the PFD. Reference Appendix E for wiring guidance.
DISCRETE OUT 1 is "master warning" - goes low when a red (warning) CAS alert is active. DISCRETE OUT 2 is "master caution" - goes low when a yellow (caution) CAS alert is active.
The two states of these outputs are as follows:
INACTIVE: Floating (can be pulled up to externally sourced Vout in the range 0 Vout 33 VDC)
Leakage current in the INACTIVE state is typically 10 uA to ground
ACTIVE: Vout 0.5 VDC with 20 mA sink current Sink current must be externally limited to 20 mA max
Pin
Connector
13
J731
14
J731
*Indicates Active Low
Pin Name DISCRETE OUT* 1 DISCRETE OUT* 2
I/O OUT OUT
G3X Installation Manual - LRU Pinouts Page 15-42
190-01115-01 Rev. K
15.8.6 Analog Input Configuration
Some analog inputs are multi-purpose capable and have several configuration options. These inputs are configured by the GDU (refer to Section 18).
NOTE
If installing an ungrounded thermocouple to an Analog In input, a DC reference must be added to the LO input. This can be accomplished by adding a resistance of 1 M or less between ground and the Analog In LO input that the ungrounded thermocouple is installed on.
Pin
Connector
Pin Name
I/O
61
J732
CHT 1 HI
IN
41
J732
CHT 1 LO
IN
21
J732
CHT 2 HI
IN
1
J732
CHT 2 LO
IN
2
J732
CHT 3 HI
IN
22
J732
CHT 3 LO
IN
60
J732
CHT 4 HI
IN
40
J732
CHT 4 LO
IN
73
J732
CHT 5 HI
IN
53
J732
CHT 5 LO
IN
33
J732
CHT 6 HI
IN
13
J732
CHT 6 LO
IN
63
J732
EGT 1 HI
IN
43
J732
EGT 1 LO
IN
23
J732
EGT 2 HI
IN
3
J732
EGT 2 LO
IN
24
J732
EGT 3 HI
IN
4
J732
EGT 3 LO
IN
62
J732
EGT 4 HI
IN
42
J732
EGT 4 LO
IN
30
J732
EGT 5 HI
IN
29
J732
EGT 5 LO
IN
34
J732
OIL TEMP HI
IN
14
J732
OIL TEMP LO
IN
72
J732
POS 5 / MISC TEMP HI
IN
52
J732
POS 5 / MISC TEMP LO
IN
25
J732
FUEL 1 HI
IN
5
J732
FUEL 1 LO
IN
190-01115-01 Rev. K
G3X Installation Manual - LRU Pinouts Page 15-43
Pin
Connector
Pin Name
I/O
64
J732
FUEL 2 HI
IN
44
J732
FUEL 2 LO
IN
26
J732
FUEL PRESS HI
IN
45
J732
FUEL PRESS LO
IN
65
J732
MAN PRESS HI
IN
6
J732
MAN PRESS LO
IN
71
J732
VOLTS 1 HI
IN
51
J732
VOLTS 1 LO
IN
32
J732
VOLTS 2 HI
IN
12
J732
VOLTS 2 LO
IN
31
J732
EGT 6 / MISC PRESS HI
IN
11
J732
EGT 6 / MISC PRESS LO
IN
69
J732
OIL PRESS HI
IN
49
J732
OIL PRESS LO
IN
47
J732
POS 1 / GP 1 / TIT 1 HI
IN
67
J732
POS 1 / GP 1 / TIT 1 LO
IN
28
J732
POS 2 / GP 2 / TIT 2 HI
IN
8
J732
POS 2 / GP 2 / TIT 2 LO
IN
27
J732
POS 3 / GP 3 / FUEL 3 HI
IN
7
J732
POS 3 / GP 3 / FUEL 3 LO
IN
66
J732
POS 4 / GP 4 / FUEL 4 HI
IN
46
J732
POS 4 / GP 4 / FUEL 4 LO
IN
70
J732
SHUNT 1 HI
IN
50
J732
SHUNT 1 LO
IN
48
J732
SHUNT 2 HI
IN
68
J732
SHUNT 2 LO
IN
10
J732
THERMOCOUPLE REF IN HI
IN
9
J732
THERMOCOUPLE REF IN LO
IN
G3X Installation Manual - LRU Pinouts Page 15-44
190-01115-01 Rev. K
15.8.7 Temperature Inputs
Temperature input is used for Outside Air Temperature (OAT) computations. The temperature input is a three-wire temperature probe interface. OAT Power Out and OAT High are connected internally at the OAT probe. A GTP 59 or other supported temperature probe is required for the GSU 73 installation. The GTP 59 is a Resistive Temperature Device (RTD). Refer to Figure B-10.1 for the temperature probe interconnect.
Pin
Connector
Pin Name
15
J732
OAT PROBE IN HI
16
J732
OAT PROBE POWER OUT
35
J732
OAT PROBE IN LO
I/O IN OUT IN
15.8.8 Frequency Counter Inputs
Digital signals are updated to the display at a rate of 10 times per second (10 Hz). Digital inputs are low when the signal is 2 Vdc or the resistance to ground is 375 , and high when the signal is > 3.5 Vdc or the resistance to ground is > 100 k.
Pin
Connector
Pin Name
I/O
17
J732
RPM
IN
19
J732
FUEL FLOW
IN
36
J732
CAP FUEL 1 / RPM 2
IN
38
J732
CAP FUEL 2 / FUEL FLOW 2
IN
The following table lists the minimum frequency, maximum frequency, and duty cycles for each of these inputs.
Pin Name RPM FUEL FLOW CAP FUEL 1 CAP FUEL 2/FUEL FLOW 2
Minimum Frequency 1 Hz 1 Hz 1 Hz 1 Hz
Maximum Frequency 500 Hz/100 KHz 500 Hz/100 KHz 500 Hz/100 KHz 500 Hz/100 KHz
Duty Cycle 50% 50% 50% 50%
Each frequency counter channel will be configured for a high or low speed input based on the signal being measured.
· RPM (Rotax) - Maximum Frequency = 6.5 kHz · RPM (other) - Maximum Frequency = 4 kHz · Fuel Flow (Floscan 201-B6) - Maximum Frequency = 500 Hz · Fuel Flow (EI FT60) - Maximum Frequency = 1.1 kHz · Fuel Quantity (Capacitive) - Maximum Frequency = 50 kHz
190-01115-01 Rev. K
G3X Installation Manual - LRU Pinouts Page 15-45
15.8.9 Fuel Select Outputs
If a resistive fuel level sensor is connected to the FUEL 1 or FUEL 2 inputs, the corresponding FUEL SENSOR PULL-UP 1 or 2 pin must be connected to the +10 V TRANSDUCER POWER pin (58) for the fuel level sensor to work properly. If using resistive fuel level sensors with the GP 3/FUEL 3 or GP 4/FUEL 4 inputs, connect the high side of the input to +10 V power through a 1 k resistor, as shown in Appendix E.
Pin Connector
Pin Name
76
J732
FUEL SENSOR PULL-UP 2 (FUEL 2)
77
J732
FUEL SENSOR PULL-UP 1 (FUEL 1)
I/O OUT OUT
G3X Installation Manual - LRU Pinouts Page 15-46
190-01115-01 Rev. K
15.9 GTX 23
15.9.1 Connector Description
The GTX 23 has one 62-pin connector (J2301) as shown below. All electrical connections are made through J2301 except for the antenna and shield ground. 15.9.2 J2301 Connector
21 20 19 18 17 16 15 14 13 12 11 10 9 8 7 6 5 4 3 2 1
42 41 40 39 38 37 36 35 34 33 32 31 30 29 28 27 26 25 24 23 22
62 61 60 59 58 57 56 55 54 53 52 51 50 49 48 47 46
44
Figure 15-16. J2301 on GTX 23, as viewed looking at connector on unit
Pin
Pin Name
I/O
1 NOT USED
--
2 NOT USED
--
3 NOT USED
--
4 NOT USED
--
5 NOT USED
--
6 NOT USED
--
7 NOT USED
--
8 NOT USED
--
9 NOT USED
--
10 NOT USED
--
11 NOT USED
--
12 EXTERNAL IDENT SELECT*
In
13 EXTERNAL STANDBY SELECT*
In
14 NOT USED
--
15 NOT USED
--
16 NOT USED
--
17 NOT USED
--
18 NOT USED
--
19 NOT USED
--
20 NOT USED
--
21 AIRCRAFT POWER 1
In
22 RS-232 IN 1
In
23 RS-232 OUT 1
Out
24 RS-232 IN 2
In
25 RS-232 OUT 2
Out
26 NOT USED
--
27 NOT USED
--
28 ARINC 429 OUT 2 B
Out
29 NOT USED
--
30 ARINC 429 OUT 2 A
Out
*Denotes active low (ground to activate)
190-01115-01 Rev. K
G3X Installation Manual - LRU Pinouts Page 15-47
Pin
Pin Name
I/O
31 MUTUAL SUPPRESSION I/O
I/O
32 NOT USED
--
33 NOT USED
--
34 ARINC 429 OUT 1 B
Out
35 NOT USED
--
36 NOT USED
--
37 ARINC 429 OUT 1 A
Out
38 NOT USED
--
39 POWER GROUND
--
40 NOT USED
--
41 NOT USED
--
42 AIRCRAFT POWER 1
In
43 RS-232 GROUND
--
44 NOT USED
--
45 NOT USED
In
46 TIS CONNECT SELECT*
In
47 NOT USED
--
48 NOT USED
--
49 NOT USED
--
50 RS-232 GROUND 2
--
51 NOT USED
--
52 NOT USED
--
53 NOT USED
--
54 NOT USED
--
55 NOT USED
--
56 AIRCRAFT POWER 2
In
57 NOT USED
--
58 POWER GROUND
--
59 NOT USED
--
60 AIRCRAFT POWER 2
In
61 NOT USED
--
62 NOT USED
--
*Denotes active low (ground to activate)
G3X Installation Manual - LRU Pinouts Page 15-48
190-01115-01 Rev. K
15.9.3 Aircraft Power
Power input requirements are listed in the following tables. The power input pins accept 14/28 Vdc. Refer to Figure C-1 and C-2 for power interconnections. AIRCRAFT POWER 1 and AIRCRAFT POWER 2 are "diode ORed" to provide power redundancy.
AIRCRAFT POWER 1 AIRCRAFT POWER 1 AIRCRAFT POWER 2 AIRCRAFT POWER 2 POWER GROUND POWER GROUND
Pin Name
Connector
Pin
I/O
J2301
21
In
J2301
42
In
J2301
56
In
J2301
60
In
J2301
39
--
J2301
58
--
15.10 Discrete Functions
15.10.1 Discrete Outputs
External suppression should be connected if a DME or TCAS is installed in the aircraft avionics system. The GTX 23 suppression I/O pulses may not be compatible with all models of DME or TCAS. Known incompatible DME units include the Bendix/King KN 62, KN 64 and KNS 80. These models have an output-only suppression port and can be damaged by the GTX 23 mutual suppression output. In this case, do not connect the GTX 23's suppression pin to the incompatible unit's suppression pin; however, do connect the GTX 23's suppression pin to any other compatible unit's suppression pin.
Pin Name EXTERNAL SUPPRESSION I/O (TXP/DME)
Connector
Pin
I/O
J2301
31
I/O
15.10.2Discrete Inputs
Sink current is internally limited to 200 uA max for a grounded input
EXTERNAL IDENT SELECT (remote IDENT) is a momentary input. When grounded, it activates the IDENT pulse for 18 seconds in Mode A replies.
EXTERNAL STANDBY SELECT (remote STANDBY) is not a momentary input. When EXTERNAL STANDBY SELECT is grounded, the GTX 23 operates in standby mode. In this mode, the transponder will not squitter or reply to interrogations.
TIS CONNECT SELECT is a momentary input. When grounded, it toggles whether TIS-A is in standby or operating.
Pin Name
Connector
Pin
I/O
EXTERNAL IDENT SELECT*
J2301
12
In
EXTERNAL STANDBY SELECT*
J2301
13
In
TIS CONNECT SELECT
J2301
46
In
*Inactive State: 10 Vin 33 Vdc or Rin 100 k, Active State: Vin 1.9 Vdc with 75 uA sink current, or Rin 375
190-01115-01 Rev. K
G3X Installation Manual - LRU Pinouts Page 15-49
15.11 Serial Data Electrical Characteristics
15.11.1 RS-232 Input/Output
RS-232 input channel 1 is used to receive pressure altitude and control commands, and to provide status, TIS-A traffic, and other data. RS-232 output channel 1 provides unit status and TIS data. RS-232 channel 1 input and output are also used for software upgrades. RS-232 port channel 1 on the GTX should be connected to the channel 1 RS-232 port on ADAHRS 1.
For installations that enable ADS-B, RS-232 input channel 2 should be connected to a GNS 400W/500Wseries WAAS enabled unit or a GTN 6XX/7XX series unit. This connection provides the GTX 23 with GPS data for ADS-B. The RS-232 output channel 2 is unused on the GTX 23.
The RS-232 outputs conform to EIA Standard RS-232C with an output voltage swing of at least ±5 V when driving a standard RS-232 load. Refer to figures in Appendix C for the RS-232 serial data interconnect.
RS-232 OUT 1 RS-232 GROUND 1 RS-232 IN 1 RS-232 OUT 2 RS-232 IN 2 RS-232 GROUND 2
Pin Name
Connector
Pin
I/O
J2301
23
Out
J2301
43
--
J2301
22
In
J2301
25
Out
J2301
24
In
J2301
50
--
15.11.2 ARINC 429 Input/Output
The ARINC 429 outputs conform to ARINC 429 electrical specifications when loaded with up to five standard ARINC 429 receivers. ARINC 429 Out Channel 1 is configured for low-speed TIS-A data, and ARINC 429 Out Channel 2 is configured for high-speed TIS-A data for a GNS 4XX/5XX unit.
ARINC 429 OUT 1A ARINC 429 OUT 1B ARINC 429 OUT 2A ARINC 429 OUT 2B SIGNAL GROUND SIGNAL GROUND
Pin Name
Connector
Pin
I/O
J2301
37
Out
J2301
34
Out
J2301
30
Out
J2301
28
Out
J2301
51
--
J2301
58
--
G3X Installation Manual - LRU Pinouts Page 15-50
190-01115-01 Rev. K
15.12 RS-232 Input/Output, Software Update Connections
NOTE
GTX 23 software updates can only be performed by a Garmin dealer.
GTX 23 software is updated using the RS-232 #1 interface. When wiring the RS-232 #1 interface to the rest of the system, it may be useful to splice in a pigtail connector that could be plugged into a laptop computer. Also when wiring, consider that the GTX 23 must be turned on (during software update) and the other avionic equipment attached to the RS-232 #1 interface (e.g. GSU or GDU) must be turned off. Instead of turning the other avionic equipment off, a relay can be installed that disconnects the avionic equipment and connects the laptop to the GTX 23. This connector may be useful for updating software to comply with new ADS-B regulation. The connector can be mounted anywhere convenient for access, such as under the instrument panel, on a remote avionics shelf next to the unit, or in the instrument panel itself. Label the connector "For Software Update". Do not include the Test Mode Select switch in the aircraft. See Figure 15-17 for software update connections.
CAUTION
If the unit is removed from the aircraft and operated, always connect J2302 to an antenna or a 50 , 5-Watt load (Figure 15-17). The GTX 23 transmits Mode S acquisition squitter replies about once per second whether interrogations are received or not. The unit may become damaged if J2302 is not connected to a 50 , 5-Watt load when the unit transmits.
GTX 23
50 5 WATT
Figure 15-17. GTX 23 Software Update Connections
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16 CONNECTOR INSTALLATION INSTRUCTIONS
16.1 Thermocouple Installation into a Backshell
Table 16-1 lists parts needed to install a Thermocouple. Parts for this installation are included in the Thermocouple Kit (011-00981-00), which is included in the G3X w/GSU 73Installation Kit (K10-00017-00).
Table 16-1 Thermocouple Kit GPN 011-00981-00
Figure Ref 1 2 3
Description 3" Thermocouple, K type
Pins #22 AWG Screw
Qty. Needed 1 2 1
PN or MIL spec 925-L0000-00 336-00021-00 211-60234-08
NOTE
For the following steps please refer to indicated item numbers in Figure 16-1 and Figure 16-2.
1. Strip back approximately 0.17 inches of insulation from both the positive and negative thermocouple leads (item 1) and crimp a pin (item 2) to each lead. It is the responsibility of the installer to determine the proper length of insulation to be removed. Wire must be visible in the inspection hole after crimping and the insulation must be 1/64 1/32 inches from the end of the contact as shown in Figure 16-1.
Figure 16-1 Insulation/Contact Clearance
2. Insert newly crimped pins and wires (items 1 & 2) into the appropriate connector housing (item 4) location as specified by the installation specific wiring diagram.
3. Place thermocouple (item 1) body onto backshell (item 5) boss. Upon placing the thermocouple (item 1) body, orient it such that the wires exit downward.
4. Attach thermocouple (item 1) tightly to backshell (item 5) using screw (item 3).
5. Attach cover (item 6) to backshell (item 5) using screws (item 7).
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Figure 16-2 Jackscrew Backshell Thermocouple Installation
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16.2 Jackscrew Configuration Module Installation into a Jackscrew Backshell
Table 16-2 & Table 16-3 list parts needed to install a Jackscrew Configuration Module with pins or with sockets. Parts for these installations are included in the 011-00979-20 and 011-00979-22 kits, which are included in the G3X w/GSU 73 Installation Kit (K10-00017-00).
Configuration modules are to be installed in the backshells of the P732 connector for the GSU 73 (use 011-00979-20 below), and the P3701 connector for the GDU 37X designated as PFD1 (use 011-00979-22 below).
Table 16-2 GPN: 011-00979-20 Kit (w/EEPROM and pins)
Figure Ref
1
3 4 10
Description Potted Module (w/EEPROM and Temp.sensor) 4 cond. Cable harness Pins Size 22D Pan head screw
Qty. Needed
1
1 4 1
GPN or MIL spec
011-02179-00
325-00122-00 336-00021-00 211-60232-07
Table 16-3 GPN: 011-00979-22 Kit (w/EEPROM and sockets)
Figure Ref
1
3 9 10
Description Potted Module (w/EEPROM and Temp.sensor) 4 cond. Cable harness Socket, Size 20, 26-30 AWG Pan head screw
Qty. Needed
1
1 4 1
GPN or MIL spec
011-02179-00
325-00122-00 336-00022-01 211-60232-07
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NOTE
For the following steps please refer to Figure 16-3 & Figure 16-4.
1. Strip back approximately 0.17 inches of insulation from each wire of the four conductor wire harness (item 3) and crimp either a pin (item 4) or a socket (item 9) to each conductor. It is the responsibility of the installer to determine the proper length of insulation to be removed. Wire must be visible in the inspection hole after crimping and the insulation must be 1/64 1/32 inches from the end of the contact as shown in Figure 16-3.
Figure 16-3 Insulation/Contact Clearance
2. Insert newly crimped pins (or sockets) and wires (items 3 and 4) into the appropriate connector housing (item 5) location as specified by the installation specific wiring diagram.
3. Attach the module (item 1) to backshell (item 6) using screw (item 10). 4. Plug the four conductor wire harness (item 3) into the connector on the module (item 1). 5. Orient the connector housing (item 5) so that the inserted four conductor wire harness (item 3) is on
the same side of the backshell (item 6) as the module (item 1)--as shown in drawing. 6. Attach cover (item 7) to backshell (item 6) using screws (item 8).
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Figure 16-4 Jackscrew Backshell Installation
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16.3 Jackscrew Backshell Installation Instructions
16.3.1 Shield Block Installation Parts
Table 16-4 and Table 16-5 list the parts needed to install a Shield Block. Parts listed in Table 16-4 are supplied in the LRU Connector Kits (see Table 1-11). Parts listed in Table 16-5 are to be provided by the installer.
Table 16-4 Parts supplied for a Shield Block Installation (Figure 16-5)
Figure Ref 1 6 12 13 14 15
Description Cast Backshell Housing Contacts Clamp Screw,4-40x.375,PHP,SS/P,w/Nylon Cover Screw,4-40x.187,FLHP100,SS/P,w/Nylon
GPN or MIL spec 125-00175-00 336-00094-00 115-01078-04 211-60234-10 115-01079-04 211-63234-06
Table 16-5 Parts not supplied for a Shield Block Installation (Figure 16-5)
Figure Ref 2 3 4 5
7
8
9
10 11
Description
GPN or MIL spec
Multiple Conductor Shielded Cable (2-conductor shown in Figure B-1)
Drain Wire Shield Termination (method optional)
Braid, Flat (19-20 AWG equivalent, tinned plated copper strands 36 AWG, Circular Mil Area 1000 -1300)
Floating Shield Termination (method optional)
Ring terminal, #8, insulated, 18-22 AWG Ring terminal, #8, insulated, 14-16 AWG Ring terminal, #8, insulated, 10-12 AWG Screw, PHP, 8-32x.312", Stainless Screw, PHP, 8-32x.312", Cad Plated Steel Split Washer, #8, (.045" compressed thickness) Stainless Split Washer, #8, (.045" compressed thickness) Cad-plated steel Flat Washer, Stainless, #8, .032" thick, .174"ID, .375" OD Flat washer, Cad-plated Steel, #8, .032" thick, .174"ID, .375" OD Silicon Fusion Tape
Parts used depend on method chosen
Parts used depend on method chosen
Parts used depend on method chosen
Parts used depend on method chosen
MS25036-149
MS25036-153
MS25036-156
MS51957-42
MS35206-242
MS35338-137
MS35338-42
NAS1149CN832R
NAS1149FN832P
-
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NOTE
In Figure 16-5, "AR" denotes quantity "As Required" for the particular installation.
Figure 16-5 Shield Install onto a Jackscrew Backshell (78 pin example)
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16.3.2 Shield Termination Technique Method A.1 (Standard)
NOTE
For the following steps please refer to the drawings showing the installation of a Jackscrew Backshell.
1. The appropriate number of Jackscrew Backshells will be included in the particular LRU connector kit.
Figure 16-6 Method A.1 for Shield Termination
Backhell Size
1 2 3 4 5
Table 16-6 Shielded Cable Preparations for Garmin Connectors
Number of Pins Std/
HD 9/15 15/26 25/44 37/62 50/78
Float Min (inches)
1.25 1.5 1.5 1.5 1.5
Float Max (inches)
2.25 2.5 2.5 2.5 2.5
Ideal Float (inches)
1.75 2.0 2.0 2.0 2.0
Window Min
(inches) 2.75 3.0 3.0 3.0 3.0
Window Max
(inches) 5.25 5.5 5.5 5.5 5.5
Ideal Window (inches)
4.25 4.5 4.5 4.5 4.5
2. At one end of a shielded cable (item 2) measure a distance between "Window Min" to "Window Max" (Table 16-6) and cut a window (max size 0.35") in the jacket to expose the shield (Figure 16-6). Use caution when cutting the jacket to avoid damaging the individual braids of the shield. When dealing with a densely populated connector with many cables, it may prove beneficial to stagger the windows throughout the "Window Min" to "Window Max" range. If staggering is not needed the "Ideal Window" length is recommended.
Suggested tools to accomplish the window cut:
· Coaxial Cable Stripper · Thermal Stripper · Sharp Razor Blade
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3. Connect a Flat Braid (item 4) to the shield exposed through the window of the prepared cable assembly (item 2) from step 2. The Flat Braid should go out the front of the termination towards the connector. It is not permitted to exit the rear of the termination and loop back towards the connector (Figure 16-6). Make this connection using an approved shield termination technique.
NOTE
FAA AC 43.13-1B Chapter 11, Section 8 (Wiring Installation Inspection Requirements) may be a helpful reference for termination techniques.
Preferred Method:
Slide a solder sleeve (item 3) onto the prepared cable assembly (item 2) and connect the Flat Braid (item 4) to the shield using a heat gun approved for use with solder sleeves. It may prove beneficial to use a solder sleeve with a pre-installed Flat Braid versus having to cut a length of Flat Braid to be used. The chosen size of solder sleeve must accommodate both the number of conductors present in the cable and the Flat Braid (item 4) to be attached.
Solder Sleeves with pre-installed Flat Braid A preferred solder sleeve would be the Raychem S03 Series with the thermochromic temperature indicator (S03-02-R-9035-100, S03-03-R-9035-100, S03-04-R-9035-100). These solder sleeves come with a pre-installed braid and effectively take the place of items 3 and 4. For detailed instructions on product use, reference Raychem installation procedure RCPS 10070.
Raychem recommended heating tools:
·HL1802E ·AA-400 Super Heater ·CV-1981 ·MiniRay ·IR-1759
Individual solder sleeves and Flat Braid
Solder Sleeves: Reference the following MIL-Specs for solder sleeves. (M83519/1-1, M83519/1-2, M83519/1-3, M83519/1-4, M83519/1-5)
Flat Braid: If the preferred Raychem sleeves are not being used, the individual flat braid selected should conform to ASTMB33 for tinned copper and be made up of 36 AWG strands to form an approximately 19-20 AWG equivalent flat braid. A circular mil area range of 1000 to 1300 is required. The number of individual strands in each braid bundle is not specified. (e.g. QQB575F36T062)
NOTE
Flat Braid as opposed to insulated wire is specified in order to allow continuing air worthiness by allowing for visual inspection of the conductor.
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Secondary Method:
Solder a Flat Braid (item 4) to the shield exposed through the window of the prepared cable assembly (item 2). Ensure a solid electrical connection through the use of acceptable soldering practices. Use care to avoid applying excessive heat that burns through the insulation of the center conductors and shorts the shield to the signal wire. Slide a minimum 0.75 inches of Teflon heat shrinkable tubing (item 3) onto the prepared wire assembly and shrink using a heat gun. The chosen size of heat shrinkage tubing must accommodate both the number of conductors present in the cable and the Flat Braid (item 4) to be attached.
Teflon Heat Shrinkable Tubing:
Reference the following MIL-Spec for Teflon heat shrinkable tubing (M23053/5-X-Y).
4. At the same end of the shielded cable (item 2) and ahead of the previous shield termination, strip back "Float Min" to "Float Max" (Table 16-6) length of jacket and shield to expose the insulated center conductors (Figure 16-6). The "Ideal Float" length may be best to build optimally.
Preferred Method:
The jacket and shield should be cut off at the same point so no shield is exposed. Slide 0.75 inches minimum of Teflon heat shrinkable tubing (item 5) onto the cable and use a heat gun to shrink the tubing. The chosen size of heat shrinkage tubing must accommodate the number of conductors present in the cable.
Secondary Method:
Leave a max 0.35 inches of shield extending past the jacket. Fold this 0.35 inches of shield back over the jacket. Slide a solder sleeve (item 5) over the end of the cable and use a heat gun approved for solder sleeves to secure the connection. The chosen size of solder sleeve must accommodate the number of conductors present in the cable.
5. Strip back approximately 0.17 inches of insulation from each wire of the shielded cable (item 2) and crimp a contact (item 6) to each conductor. It is the responsibility of the installer to determine the proper length of insulation to be removed. Wire must be visible in the inspection hole after crimping and the insulation must be 1/64 1/32 inches from the end of the contact as shown in Figure 16-7.
Figure 16-7 Insulation/Contact Clearance
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6. Insert newly crimped pins and wires into the appropriate connector housing location as specified by the installation wiring diagrams.
7. Cut the Flat Braid (item 4) to a length that, with the addition of a ring terminal, will reach one of the tapped holes of the Jackscrew backshell (item 1) (Figure 16-5). An appropriate amount of excess length without looping should be given to the Flat Braid (item 4) to allow it to freely move with the wire bundle.
NOTE
Position the window splice to accommodate a Flat Braid (item 4) length of no more than 4 inches.
8. Guidelines for terminating the newly cutoff Flat Braid(s) (item 4) with insulated ring terminals (item 7): · Each tapped hole on the Jackscrew Backshell (item 1) may accommodate only two ring terminals (item 7). · It is preferred that only two Flat Braid(s) (item 4) be terminated per ring terminal. Two Flat Braids per ring terminal will necessitate the use of a Ring terminal, #8, insulated, 14-16 AWG (MS25036-153). · If only a single Flat Braid is left or if only a single Flat Braid is needed for this connector a Ring terminal, #8, insulated, 18-22 AWG (MS25036-149) can accommodate this single Flat Braid. · If more braids exist for this connector than two per ring terminal, it is permissible to terminate three braids per ring terminal. This will necessitate the use of a Ring terminal, #8, insulated, 10-12 AWG (MS25036-156).
9. Repeat steps 2 through 8 as needed for the remaining shielded cables. 10. Terminate the ring terminals to the Jackscrew Backshell (item 1) by placing items on the Pan Head
Screw (item 8) in the following order: Split Washer (item 9), Flat Washer (item 10) first Ring Terminal, second Ring Terminal (if needed) before finally inserting the screw into the tapped holes on the Jackscrew Backshell. Do not violate the guidelines presented in Step 8 regarding ring terminals. 11. It is recommended to wrap the cable bundle with Silicone Fusion Tape (item 11) (GPN: 249-00114-00 or a similar version) at the point where the backshell clamp and cast housing will contact the cable bundle.
NOTE
Choosing to use this tape is the discretion of the installer.
12. Place the smooth side of the backshell clamp (item 12) across the cable bundle and secure using the three screws (item 13). Warning: Placing the grooved side of the clamp across the cable bundle may risk damage to wires.
13. Attach the cover (item 14) to the backshell (item 1) using the two screws (item 15).
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16.3.3 Shield Termination Technique - Method A.2 (Daisy Chain)
In rare situations where more braids need to be terminated for a connector than three per ring terminal it is allowable to daisy chain a maximum of two shields together before coming to the ring terminal (Figure 16-8). All other restrictions and instructions for the shield termination technique set forth for Method A.1 are still applicable.
NOTE
The maximum length of the combined braids should be approximately 4 inches.
Figure 16-8 Method A.2 (Daisy Chain) for Shield Termination
16.3.4 Shield Termination Method B.1 (Quick Term)
If desired, the drain wire termination (item 3) and the floating shield termination (item 5) can be effectively combined into a "Quick Term". This method eliminates the float in the cable insulation and moves the placement of the window which was described by the dimensions "Window Min" and "Window Max" from Method A. This technique is depicted in Figure 16-9.
NOTE
The original purpose for separating the shield drain termination (item 3) from the float termination (item 5) in Method A was to allow for a variety of lengths for the drain wires so that the shield drain terminations (item 3) would not all "bunch up" in the harness and to eliminate loops in the drain wires. If Method B is chosen, as described in this section, care must be taken to insure that all drain shield terminations can still be inspected. With connectors which require a large number of shield terminations it may be best to use Method A. This will allow the drain shield terminations (item 3) a larger area to be dispersed across.
Using this method, the instructions from Section 16.3.2 (Method A) are followed except that:
1. Step 2 is eliminated 2. Steps 3 and 4 are replaced by the following:
At the end of the shielded cable (item 2), strip "Quick Term Min" to "Quick Term Max" (Table 16-7) length of the jacket to expose the shield. Next trim the shield so that at most 0.35 inches remains extending beyond the insulating jacket. Fold this remaining shield back over the jacket.
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Connect a Flat Braid (item 4) to the folded back shield of the prepared cable assembly. The flat braid should go out the front of the termination towards the connector. It is not permitted to exit the rear of the termination and loop back towards the connector. (Figure 16-9). Make this connection using an approved shield termination technique.
NOTE
FAA AC 43.13-1B Chapter 11, Section 8 (Wiring Installation Inspection Requirements) may be a helpful reference for termination techniques.
Preferred Method:
Slide a solder sleeve (item 3) onto the prepared cable assembly (item 2) and connect the Flat Braid (item 4) to the shield using a heat gun approved for use with solder sleeves. It may prove beneficial to use a solder sleeve with a pre-installed Flat Braid versus having to cut a length of Flat Braid to be used. The chosen size of solder sleeve must accommodate both the number of conductors present in the cable and the Flat Braid (item 4) to be attached.
NOTE
Reference Section 16.3.2 for recommended solder sleeves and flat braid. The same recommendations are applicable to this technique.
Secondary Method:
Solder a Flat Braid (item 4) to the folded back shield on the prepared cable assembly (item 2). Ensure a solid electrical connection through the use of acceptable soldering practices. Use care to avoid applying excessive heat that burns through the insulation of the center conductors and shorts the shield to the signal wire. Slide a minimum of 0.75 inches of Teflon heat shrinkable tubing (item 3) onto the prepared wire assembly and shrink using a heat gun. The chosen size of heat shrinkage tubing must accommodate both the number of conductors present in the cable as well as the Flat Braid (item 4) to be attached.
Teflon Heat Shrinkable Tubing: Reference the following MIL-Spec for general Teflon heat shrinkable tubing (M23053/5-X-Y)
Figure 16-9 Method B.1 (Quick Term) for Shield Termination
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Table 16-7 Shielded Cable Preparations (Quick Term)
Backshell Size
1 2 3 4 5
Number of Pins Std/HD 9/15 15/26 25/44 37/62 50/78
Quick Term Min (inches) 1.25 1.5 1.5 1.5 1.5
Quick Term Max (inches) 2.25 2.5 2.5 2.5 2.5
Quick Term Float (inches)
1.75 2.0 2.0 2.0 2.0
16.3.5 Shield Termination-Method B.2 (Daisy Chain-Quick Term)
In rare situations where more braids need to be terminated for a connector than three per ring terminal it is allowable to daisy chain a maximum of two shields together before coming to the ring terminal (Figure 16-10). All other restrictions and instructions for the shield termination technique set forth for Method B.1 are still applicable.
NOTE
The maximum length of the combined braids should be approximately 4 inches.
Figure 16-10 Method B.2 (Daisy Chain-Quick Term) for Shield Termination
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16.3.6 Daisy Chain between Methods A and B
In rare situations where more braids need to be terminated for a connector than three per ring terminal and a mixture of Methods A and B have been used, it is allowable to daisy chain a maximum of two shields together from a Method A termination to a Method B (Figure 16-11). All other restrictions and instructions for the shield termination technique set forth for Method A and B are still applicable.
NOTE
The maximum length of the combined braids should be approximately 4 inches.
Figure 16-11 Daisy Chain between Methods A and B
16.3.7 ID Program Pins (Strapping)
NOTE
The GDU 37X rear connector (J3701) is electrically isolated. For installations using programming pins, a ground pin must be tied to the connector shell.
ID Program Pins provide a ground reference used by the hardware as a means of configuration for system identification. The following instructions will illustrate how this ground strapping should be accomplished with the Jackscrew Backshell:
1. Cut a 4 inch length of 22 AWG insulated wire.
WARNING
Flat Braid is not permitted for this purpose. Use only insulated wire to avoid inadvertent ground issues that could occur from exposed conductors.
2. Strip back approximately 0.17 inches of insulation and crimp a contact (item 6) to the 4" length of 22 AWG insulated wire. It is the responsibility of the installer to determine the proper length of insulation to be removed. Wire must be visible in the inspection hole after crimping and the insulation must be 1/64 1/32 inches from the end of the contact as shown in Figure 16-7.
3. Insert newly crimped pins and wires into the appropriate connector housing location as specified by the installation wiring diagrams.
4. At the end opposite the pin on the 22 AWG insulated wire strip back 0.2 inches of insulation.
5. Terminate this end via the ring terminals with the other Flat Braid per Steps 8 and 11 pertaining to shield termination. If this ground strap is only wire to terminate, attach a Ring terminal, #8, insulated, 18-22 AWG (MS25036-149).
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16.3.8 Splicing Signal Wires
NOTE
Figure 16-12 illustrates that a splice must be made within a 3 inch window from outside the edge of clamp to the end of the 3 inch max mark.
WARNING
Keep the splice out of the backshell for pin extraction, and outside of the strain relief to avoid preloading.
Figure 16-12 shows a two wire splice, but a maximum of three wires can be spliced. If a third wire is spliced, it is located out front of splice along with signal wire going to pin.
Splice part numbers: ·Raychem D-436-36/37/38 ·MIL Spec MIL-S-81824/1
This technique may be used with shield termination methods: A.1, A.2, B.1, B.2, C.1 and C.2.
Figure 16-12 D-Sub Spliced Signal Wire illustration
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17 CONFIGURATION, SOFTWARE, DATABASES, AND XM ACTIVATION
17.1 Configuration Mode
Some of the software loading, and all of the configuration settings are performed in the configuration mode. To enter configuration mode, hold down the left-hand softkey (softkey #1) while powering on the GDU 37X. In a two-display system hold down softkey #1 on the PFD 1 display.
The Configuration pages (MAIN, LRU, AHRS, ACFT, AOA, AP, W/B, UNITS, DSPL, SOUND, COMM, GPS, XPDR, LOG, ENG) are only available in Configuration mode.
17.2 Software Loading Procedure
GDU software loading can be performed in either normal or configuration mode. Section 17.2.1 describes the GDU software load procedures. Section 17.2.2 describes the GDL 39/39R software load procedure 17.2.1 GDU Software Loading Procedure
1. Power on the GDU in normal mode, then insert the properly formatted SD card into the SD card slot.
NOTE
It is also acceptable to insert the SD card before powering on the unit.
2. A software update pop-up will appear on the screen, highlight YES and press the ENT key to begin the update.
NOTE
If the preceding software update pop-up does not appear, select the Database Information Menu to update the software using the UPDATE SW softkey.
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3. The unit will reboot, then GDU software update will begin automatically.
4. Ensure power is not removed while the update is being performed.
5. The unit will reboot after the update is complete.
6. Other connected non-display LRUs will automatically be updated to the correct software version. Software for all CAN LRUs (GSU 25, GSU 73, GEA 24, GSA 28, GAD 29) and also the GDL 39/ 39R will automatically be loaded by the display with no user action required. In configuration mode, the MAIN Configuration page will display "Updating..." next to any device that is currently performing a software update.
7. Repeat for each GDU in the aircraft.
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17.2.2 GDL 39/GDL 39R Software Update
GDL 39/39R software updates are loaded through the GDU. After the steps in Section 17.2.1 have been completed, the GDU will identify the software version currently in use for the GDL 39/39R and compare it to the GDL 39/39R software version stored in internal GDU memory. If the current GDL 39/39R software is different than the GDL 39/39R software stored in GDU memory, the GDU will automatically begin updating the GDL 39/39R9. An "Updating..." indication for the GDL 39/39R (and for any LRU being updated) is displayed on the Main Configuration page. Another indication of the update is found on the Data Link Information Page (normal mode). Allow the update to complete. After the update, the GDL 39/ 39R will resume normal operation.
CAUTION
It is critical that GDU power is not removed during the software update. An interruption in supplied power or turning the unit off during the SW update may damage the GDL 39/39R causing it to be non-functional.
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17.3 Configuration Pages
17.3.1 Main Configuration Page
The Main Configuration Page is used to display LRU (device) specific information such as Software Version, Unit ID's, System ID's, and Database information for the various databases used by the G3X. This page has no user-selectable options. Faults are indicated by a Red X next to the affected LRU.
1. In configuration mode (Section 17.1), use the FMS Joystick to select and view the MAIN Page. The user may also review info in the device INFO box by using the FMS Joystick to scroll through the items in the list.
2. This page can be used to update the software in the LRUs (highlight the System Software in the INFO box and press the UPDATE softkey), and also test the annunciator outputs on the EIS and GMC 305 LRUs by pressing the ANNUN TEST softkey.
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17.3.2 LRU Configuration Page
The LRU configuration page is used to configure which optional LRUs are connected to the system. If a particular LRU is not installed, or a particular LRU function (such as AOA) is not desired, change that setting on the LRU configuration to "Disabled".
For example, if a GSU 25 is connected as ADAHRS 2 but no GMU 22 or GTP 59 is connected, configure ADAHRS 2 to "Enabled" and Magnetometer 2 and OAT 2 to "Disabled". Also change any AOA item to "Disabled" if the installed ADAHRS LRU does not support AOA (e.g. the GSU 73) or if the AOA pneumatic connection is not connected to that ADAHRS LRU.
The Engine Interface item is used to configure which numbered EIS LRU should be used. This should be left configured for EIS1 except in the case of a system that includes a GSU 73 and a GEA 24, the latter of which would be wired as EIS2.
The Autopilot Servos item is used to configure how many GSA 28 servos are installed. Select "Roll Only" if a single roll servo is installed, "Pitch + Roll" for a two-axis autopilot servo installation, or "Pitch +Roll+ YD" for a two-axis autopilot installation with a third yaw damper servo.
1. In configuration mode (Section 17.1), use the FMS Joystick to select and view the LRU Page.
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2. Use the FMS Joystick to enable or disable the listed LRUs.
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17.3.3 AHRS (Attifude/Heading Reference System) Configuration Page
The AHRS Configuration Page is used to perform post-installation calibration for both the GSU 25 and/or GSU 73 (as applicable).
1. In configuration mode, use the FMS Joystick to select the AHRS Page.
2. Use the FMS Joystick to select the desired configurable item and make the desired change. Then press the ENT Key or use the FMS Joystick to select the next item. Press the FMS Joystick to move the cursor to the page selection menu when finished.
Attitude/Heading Reference SystemThe Air Data, GPS Data, and Magnetometer checkboxes confirm operational status of these LRUs with a green check, no green check indicates no communication with LRU.
1. Use the FMS Joystick to select which AHRS (1, 2 or 3) is being configured. Calibration ProceduresSee Section 17.2 (SW loading procedure) , Section 19.3 (GSU 25/73/GMU 22 Post Installation Calibration Procedures), and Section 20.6 (Post Installation Calibration Procedures) for further information regarding the AHRS Configuration Page.
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17.3.4 Angle of Attack (AOA)
The AOA Configuration page is accessible only when an AOA input is enabled on the LRU Configuration page (Section 17.3.2). The configuration mode page only allows viewing and deleting the AOA calibration values, the AOA calibration cannot be performed in configuration mode. See Section 19.4 for the AOA Calibration procedure.
17.3.5 AP (Autopilot) Configuration Page
See Section 9.11 through Section 9.17 for autopilot configuration instructions.
17.3.6 FD (Flight Director) Configuration Page
This page allows configuration of certain options for the flight director. It will only appear in installations that include an autopilot.
The Maximum Bank Angle field allows adjustment of the maximum roll angle that will be commanded by the flight director. This setting should not be adjusted from the default of 30 degrees except for very high performance aircraft that have bank angle limitations at high speeds.
If an EIS discrete input is configured for "AFCS TO/GA", fields will appear on the FD config page. These fields allow customization of the pitch attitudes that will be commanded when the flight director is in Takeoff (TO) or Go-Around (GA) mode, to suit the performance characteristics of the aircraft. The default value for both settings is 5 degrees.
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17.3.7 ACFT Configuration Page
The Aircraft Configuration Page allows setting the parameters for Reference Speeds and Flight Planning. The aircraft identifier and map symbol can also be entered on this page.
Reference SpeedsThe aircraft Vspeeds can be entered using the FMS Joystick. A label can be added to the Custom (1-4) reference speed fields. The entered label text will be displayed on the airspeed tape (in normal mode) at the entered speed. If no text is entered for the label, a small triangle will appear instead. To clear a reference field:
1. Highlight the desired reference speed field. 2. Press the CLR key, or set the speed to 0.
To clear a label field:
1. Highlight the desired label field. 2. Press the CLR key.
The IAS (Indicated Air Speed)/TAS (True Air Speed) selection controls how Vne (never exceed Velocity) is displayed on the PFD airspeed tape. If Vne is set to IAS, the redline indication for Vne is always displayed at a constant indicated airspeed, as it would be indicated on a mechanical airspeed gauge. In the following example, Vne will alwas be displayed at 205 knots indicated airspeed. At an IAS of 190 knots, the aircraft speed is below Vne.
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For certain aircraft types, maximum airspeed is limited by true airspeed (TAS), not indicated airspeed. If Vne is configured to show true airspeed, the PFD airspeed tape will use a red color band to show the indicated airspeed at which the aircraft's true airspeed will exceed the value of Vne. In the following example, the aircraft is flying at a density altitude such that a TAS of 205 knots can be achieved at 186 knots IAS (displayed as a solid red color band). At an IAS of 190 knots, the aircraft's TAS has already exceeded the adjusted Vne.
At sea level and standard conditions, IAS and TAS are equal, so these two ways of displaying Vne would appear identical. As altitude increases (and air density decreases), the margin by which TAS exceeds IAS becomes greater, thus the effect on adjusted Vne is also greater.
Flight PlanningThe flight planning fields let you adjust the default values (cruise speed and fuel flow) used in normal mode for flight planning calculations (ETE, Leg Fuel, etc.). Aircraft IdentifierThe aircraft identifier is used in the data log file and on the Flight Log page, it can be entered using the FMS Joystick. G MeterThe G-Meter fields allow for setting the minimum and maximum G values displayed on the PFD G-meter. The G-meter may be displayed at any time via the PFD Setup page. Not entering any values, or clearing the values, disables the G-Meter entirely. Setting Auto Display to On allows the G-Meter to appear in place of the HSI when G-loads on the aircraft exceed a fixed threshold (setting Auto Display to Off disables Auto Display of the G-Meter). Map SymbolThe aircraft symbol that is displayed on the Map page can be selected from five different vehicles that are stored internally to the unit. Additional vehicles may be downloaded from www.garmin.com/vehicles.
NOTE
The downloaded aircraft symbols are stored as .srf files located in the `Garmin/Vehicle/' directory on the SD card(s). For installations with multiple GDUs, the .srf file must be present on each SD card inserted into each of the GDUs. If the file is not present, the GDU will use the default black-and-white airplane symbol.
1. In configuration mode, use the FMS Joystick to select the ACFT Page.
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2. Use the FMS Joystick to select the desired configurable item and make the desired change. Then press the ENT Key or use the FMS Joystick to select the next item. Press the FMS Joystick to move the cursor to the page selection menu when finished.
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17.3.8 W/B (Weight/Balance) Configuration Page
The W/B Configuration Page allows setting the weight and balance parameters for the airplane. These parameters are then used on the Main Menu W/B Page in normal mode. Weight/Balance may be used during pre-flight preparations to verify the weight and balance conditions of the aircraft. By entering the weight and arm values into the Aircraft Empty window, the GDU 37X can calculate the total weight, moment, and center of gravity (CG).
Before entering the various figures, the empty weight of the airplane and the arm (or "station") for each weight should be determined. These figures should be determined using the pilot's operating handbook for the airplane, which also notes the weight limitations and fore/aft CG limits. Compare those figures to the values calculated by the GDU 37X.
Each station listed in the Station window has an editable name and arm location. This allows the setting of the units of measure used for that station (weight, or units of avgas or jet fuel). An optional maximum value can be set for a particular station (e.g. a fuel tank might have a max capacity of 50 gallons) or the max can be set to zero so that no maximum will be imposed.
The Loading Limits window contains fields for the entry of minimum and maximum aircraft weight, and the minimum and maximum CG location.
1. In configuration mode, use the FMS Joystick to select the W/B Page.
2. Use the FMS Joystick to select the desired configurable item and make the desired change, then press the ENT Key or use the FMS Joystick to select the next item.
3. To create a new station, highlight a blank line (in the Station window), press the ENT key, enter the name, units, max weight, and arm, then highlight DONE and press the ENT key.
4. To edit or delete a station, highlight the desired station, then press the ENT softkey.
5. Press the FMS Joystick to move the cursor to the page selection menu when finished.
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17.3.9 UNITS Configuration Page The Units Configuration Page allows selection of the desired displayed units for the listed items in the Units Configuration window. The various settings for Location Format, Map Datum, and Heading can be accessed in the Position Configuration window. See the G3X Pilot's Guide for a description of Location Format and Map Datum.
1. In configuration mode, use the FMS Joystick to select the UNITS Page.
2. Use the FMS Joystick to select the desired configurable item and make the desired change. Then press the ENT Key or use the FMS Joystick to select the next item. Press the FMS Joystick to move the cursor to the page selection menu when finished.
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17.3.10 DSPL (Display) Configuration Page
The DSPL Configuration Page allows setting the parameters for display backlight and display options configuration.
1. In configuration mode, use the FMS Joystick to select the DSPL Page.
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2. Use the FMS Joystick to select the desired configurable item and make the desired change. Then press the ENT Key or use the FMS Joystick to select the next item. Press the FMS Joystick to move the cursor to the page selection menu when finished.
3. Press the Options softkey to switch between the Display Configuration Page and the Backlight Configuration Page. Each of these pages are detailed in the following sections.
17.3.10.1 Display Configuration Page
Display Backlight Configuration Window:
Backlight Intensity: Can be set to Auto or Manual (this setting is also available in normal mode on the Display Setup page).
AutoSets the backlight intensity (display brightness) based on the aircraft's instrument lighting bus voltage. ManualAllows setting the display brightness by changing the Backlight Intensity (0-9) setting found beside the `Manual' setting.
Default Mode: Can be set to Auto or Manual (described above). This controls the backlight mode that will be active each time the system is powered on.
Automatic Backlight Control Window (settings apply only to `Auto' setting):
Input VoltageDisplays the current lighting bus voltage
Backlight LevelDisplays the current backlight level (0-100%)
GraphBrightness is displayed as the vertical (Y) axis, and aircraft lighting bus voltage is displayed as the horizontal (X) axis. The graph changes according to the auto backlight control settings, and the lighting bus voltage.
Off ThresholdSets the lighting bus threshold voltage. At the threshold voltage, the backlighting is turned on per the Min Brightness setting. Below the threshold voltage, the backlighting defaults to a Backlight Level of 100% . The '±' setting controls the range that the Off Threshold voltage is in effect. Default values are 2.9 V & ±0.15 V. If the Off Threshold value is set to 0.0 V, it will be be ignored, and the display brightness will remain at the Min Brightness level for any voltage between zero volts and the Min Brightness voltage setting.
Min Brightness (Voltage and Percentage)Sets the lower bus voltage required to turn the backlighting on to the percentage of brightness set by the Min % setting. Default values are 3. 0 V and 10%.
Max Brightness (Voltage and Percentage)Sets the upper bus voltage required to turn the backlighting on to the percentage of brightness set by the Max % setting. Default values are 12.0 V and 100%.
Input TypeSets the aircraft lighting bus voltage for either 12 or 24 V input to match the aircraft lighting bus voltage.
Time ConstantAdjusts the speed (in seconds), that the brightness level responds to changes in the input voltage level.
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17.3.10.2 Display Options Window (press the Options softkey):
EIS Display LocationControls which GDU the EIS Display (Engine Bar) appears on in a multi-screen system.
AutoIn a single-display system (or in a reversionary condition) the EIS Display appears on the PFD; in a two or three display system the EIS Display appears on the MFD.
PFDThe EIS Display will always appear on the PFD, even in a multi-display system. PFD1 LayoutControls the screen layout for PFD1.
AutoPFD1 is a dedicated full-screen PFD display (when in a multi-display system and not in reversionary mode).
Split ScreenPFD1 always remains in split-screen mode.
User Selected-(default setting) Allows changing PFD1 layout in normal mode from the Display Setup page in the main menu.
PFD2 LayoutControls the screen layout for PFD2 (for 3-display systems only).
AutoPFD2 is a dedicated full-screen PFD display (when not in reversionary mode).
Split ScreenPFD2 always remains in split-screen mode.
Full PFD/MFDPFD2 displays a page sequence that includes a full-screen PFD display as well as full-screen MFD pages.
User Selected(default setting) Allows changing PFD2 Layout in normal mode from the Display Setup page in the main menu.
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PFD Attitude SymbolAffects the appearance of the airplane symbol on the PFD attitude display. Options are Default, Alternate 1, and Alternate 2. This option is not selectable if an autopilot is configured. The "Alternate 1 Symbol" shown below will be used if an autopilot (GSA 28 or 3rd party) is configured.
Default Symbol
Alternate 1 Symbol
Alternate 2 Symbol
PFD HSI OrientationAllows setting the PFD HSI Orientation to either Heading or User Selected (default). The Heading selection displays the HSI (on the PFD) in a heading-up orientation. The User Selected setting enables an HSI Orientation option on the PFD Setup page, see the G3X Pilot's Guide (190-01115-00) for more info.
ScreenshotAllows setting the Screenshot function to either Enabled or Disabled (default). This function allows a `screenshot' of the current display to be stored to an SD card while in configuration mode. When enabled, with an SD card in the SD card slot, press and hold the Menu key to save a screenshot bitmap file to the SD card (indicated by a screen flash).
Traffic PageSets the dedicated Traffic page to displayed (SHOW) or not displayed (HIDE). Only applicable when configured for traffic input, otherwise not displayed.
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17.3.11 SOUND Configuration Page The SOUND Configuration Page allows setting the parameters for various alert and message tones. A TEST softkey is used to test audio volume and configuration.
1. In configuration mode, use the FMS Joystick to select the SOUND Page.
2. Use the FMS Joystick to select the desired configurable item and make the desired change. Then press the ENT Key or use the FMS Joystick to select the next item. Press the FMS Joystick to move the cursor to the page selection menu when finished.
The configuration options for the SOUND Configuration Page are listed/described as follows: Alert Volume Controls the volume level (settings 1-10) of audio alerts (Altitude, CAS, Integrated Autopilot, Terrain, Traffic)
Message Volume Controls the volume level (settings 1-10, or OFF) of message tones (Airspace Advisory Messages, Approaching VNAV Target Altitude Message, etc.)
Terrain Audio Enables/disables terrain awareness audio alerts
Traffic Audio Enables/disables Traffic Audio alerts
Traffic N/A Enables/disables Traffic Not Available alerts
AOA Alert Enables/disables AOA Alert tone
Altitude Alert Enables/disables the Altitude Alert tone
Altitude Minimums Enables/disables the Altitude Minimums tone
Alert Source If more than one GDU 37X is installed, an Alert Source field will appear on the SOUND Configuration page. The Alert Source field allows the user to select which GDU will generate the alert sounds. The Alert Source options are: PFD1, PFD2, MFD, or Auto (which will use whichever unit is present, in the order PFD1, MFD, PFD2). Alert Output If set to MONO + STEREO, alert tones and messages will be output on both the mono and stereo outputs. If set to MONO ONLY, alert tones and messages will be output only on the mono output.
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17.3.12 COMM Configuration Page The COMM Configuration Page allows setting the parameters for the communication ports on the GDU 37X displays, the GSU 73, and the ARINC 429 ports on the GAD 29 or GSU 73.
1. In configuration mode, use the FMS Joystick to select the COMM Page.
2. Use the FMS Joystick to select the desired configurable item and make the desired change. Then press the ENT Key or use the FMS Joystick to select the next item. Press the FMS Joystick to move the cursor to the page selection menu when finished.
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A green checkmark will appear next to the name of each Comm port when it is receiving valid data. No checkmark is displayed if data has not yet been received. A red X is diplayed if no data has been received after an intial timeout period, or if data has been received and then interrupted.
G3X installations with a single GDU 37X will display the RS-232 and ARINC 429 configuration settings on separate soft-key selectable pages. 17.3.12.1 RS-232 (PFD 1, MFD, and PFD 2 Comm Port) Configuration options Each connected GDU 37X has three configurable RS-232 channels, the optional settings are: Garmin Data Transfer - The proprietary format used to exchange data with a PC or a GDL 39 Garmin Instrument Data - Used for connecting to compatible Garmin LRUs (e.g. GSU 25, GMC 305) Garmin HSDB - Used for connecting to compatible Garmin LRUs (e.g. GTS 8XX, see Appendix D) NMEA Out - Supports the output of standard NMEA 0183 version 3.01 data at a baud rate of 4800. The GDU outputs data from the selected GPS source (internal GPS or external GPS1/GPS2) via NMEA sentences. A setting that allows switching the NMEA output between "Normal" and "Fast" speeds is accessed by pressing the MENU Key on the Comm Page (at least one output must be set to NMEA Out) followed by the ENT Key.
A pop-up window appears which allows the selection of the Lat/Lon format and the output rate. These settings affect all RS-232 ports that are configured to output NMEA data. The selected speed is displayed following the baud rate now for all ports configured for NMEA output. This feature is useful for sending data to devices that require the full set of NMEA sentences at a slower pace. Fast (every second): GPBOD, GPRMB, GPRMC, PGRMH, PGRMZ Normal (every two seconds): GPAPB, GPBOD, BPBWC, GPGGA, GPGLL, GPGSA, GPGSV,GPRMB, GPRMC, GPRTE, GPVTG, GPWPL, GPXTE, PGRME, PGRMH, PGRMM, PGRMZ
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Text Out Selecting Text Out enables a pop-up menu to appear when the Menu key is pressed (while on the COM Configuration Page). This pop-up menu allows setting three selections (Attitude/Air Data, Engine/Airframe Data, and GPS Position/Velocity) to On or Off. The On setting allows the output of Text Data as described in Appendix I.
Aviation In - The proprietary format used for input to the G3X (baud rate of 9600) from an FAA certified Garmin panel mount unit. Allows the G3X to display a Go To or route selected on the panel mount unit, which eliminates the need to enter the destination on both units. If the external GPS navigator supports both the Aviation In and MapMX formats, Garmin recommends using the preferred MapMX format. Aviation In/NMEA & VHF Out - Receives aviation data and transmits out both NMEA data, at 9600 baud, and VHF frequency tuning information to a Garmin Nav/Comm radio. MapMX - The preferred data source when interfacing with an external navigator, and is only available from Garmin units with a WAAS GPS receiver. When MapMX data is received, the G3X display can show more accurate information about the external navigator flight plan (e.g. DME, arcs, and holding patterns).
TIS-A In - Receives TIS A-data from a Garmin Mode-S panel-mount transponder. If the transponder is connected to the ADAHRS 1 LRU (as shown in Appendix D), it is not necessary to connect its output to a GDU RS-232 port.
TIS-A In/NMEA & VHF Out - Receives TIS-A data and transmits out both NMEA data, at 9600 baud, and VHF frequency tuning information to a Garmin Nav/Comm radio. Note that if a transponder is connected to the ADAHRS 1 LRU (as shown in Appendix D), it is not necessary to select TIS-A In, as the transponder data is received via the ADAHRS 1 LRU. Garmin VHF Nav/Comm - Outputs frequency tuning and radial selection data to an SL30 or GNC 2XX Nav/Comm radio, and receives lateral and vertical NAV deviation signals. Garmin VHF Comm - Outputs frequency tuning data to an SL40 or GTR 2XX Comm radio.
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Integrated Autopilot For use with Autopilots that use both ARINC 429 and bi-directional RS-232 data (ARINC 429 output set to Autopilot). Integrated Autopilot is a proprietary serial format that provides autopilot control softkeys and status annunciations on the G3X PFD. See wiring examples in Appendix D.
Note the following when configuring the communication settings:
· Each GNS 400/500, GNS 480, or GTN 600/700 series unit must be connected to an MapMX/
Aviation RS-232 input on one of the GDU 37X units (in addition to the ARINC 429 connection(s)). ARINC 429 data input from a GNS 400/500, GNS 480, or GTN 600/700 series unit will be ignored unless a corresponding MapMX/Aviation RS-232 input is also configured.
· When connecting two GNS 400/500, GNS 480, or GTN 600/700 series units to the G3X system,
connect the MapMX/Aviation RS-232 output from NAV 1 to an RS-232 input on PFD1, and connect the MapMX/Aviation RS-232 output from NAV 2 either to an RS-232 input on the MFD, or to a higher-numbered RS-232 input on PFD1.
· Highlight the `GPS1', `GPS2', etc. fields on the Main Configuration page to verify which RS-232
and ARINC 429 inputs the G3X system is currently using for NAV 1 and NAV 2.
Vertical Power A 3rd party LRU that integrates with the G3X to monitor and control the entire electrical system via the GDU.
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17.3.12.2 ARINC 429 Configuration options
The configuration options for the 2 ARINC 429 output and 4 ARINC 429 input ports on the GAD 29 or GSU 73 are detailed in this section.
ARINC 429 Outputs:
EFIS/Airdata Outputs EFIS and air data labels to a 4XX/5XX series unit. A second selection is used to determine if the EFIS/Airdata output is addressed to NAV 1, NAV 2, or both (NAV 1+ 2). The transmitted labels are as follows:
100P Selected Course 1 206 Indicated Airspeed 212 Vertical Speed 320 Magnetic Heading
203 Pressure Altitude 210 True Airspeed 213 Static Air Temperature 371G Manufacturer ID
204 Baro Corrected Altitude 211 Total Air Temperature 235 Baro Setting (BCD) 377 Equipment ID
Autopilot - For use with Autopilots that use both RS-232 and ARINC 429 data. The transmitted labels are as follows:
001 Distance To Waypoint (BCD) 012 Ground Speed (BCD)
100P Selected Course 1
101 Selected Heading
102 Selected Altitude
104 Selected Vertical Speed
114 Desired Track (True)
115 Waypoint Bearing (True) 116G Cross Track Distance
117G Vertical Deviation
121 Roll Command
122 Pitch Command
147G Magnetic Variation
203 Pressure Altitude
204 Baro Corrected Altitude
206 Indicated Airspeed
212 Vertical Speed
235 Baro Setting (BCD)
251 Distance To Waypoint
312 Ground Speed
313 Ground Track
320 Magnetic Heading
324 Pitch Angle
325 Roll Angle
371G Manufacturer ID
377 Equipment ID
ARINC 429 Inputs: Garmin GPS Receives GPS labels from a GNS 400/500, GNS 480, or GTN 600/700 series unit. A second selection is used to determine if the GPS input is from NAV 1 or NAV 2.
Garmin VOR/ILS Receives VOR/ILS labels from a GNS 400/500,GNS 480, or GTN 600/700 series unit. A second selection is used to determine if the GPS input is from NAV 1 or NAV 2.
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17.3.13 GPS Configuration Page The GPS Configuration Page allows selecting the GPS source for each GDU. Each installed GDU can select either the GPS antenna directly connected to that GDU, or `No GPS Antenna Connected'. If `No GPS Antenna Connected' is selected, that GDU will use GPS data from the GDU that is connected to a GPS Antenna. Only one GDU need be connected to a GPS Antenna, that GDU will "share" the GPS info will all other GDUs.
NOTE
Failure of a single GDU or GPS antenna (in a multi-display/multi-antenna installation) would cause the system to use GPS information from the remaining functional GDU. If no GPS data is available from any operating GDU, the remaining GDUs will use GPS position data from an external GPS navigator (GNS 400/500, GNS 480, or GTN 600/700 series unit, see Appendix D). Accuracy will be degraded when using an external GPS navigator.
1. In configuration mode, use the FMS Joystick to select the GPS Page.
2. Use the FMS Joystick to select the desired configurable item and make the desired change. Then press the ENT Key or use the FMS Joystick to select the next item. Press the FMS Joystick to move the cursor to the page selection menu when finished.
If an external GPS navigator is configured, the GPS config page displays "Select External GPS At Powerup". This setting controls whether the user's choice to use the internal GPS nav source will be retained between power cycles (disabled), or if the system should always return to using the configured external GPS nav source at powerup (enabled).
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17.3.14 XPDR Configuration Page The Transponder Configuration Page allows selection of the installed Garmin Transponder. .
1. In configuration mode, use the FMS Joystick to select the Transponder Page.
2. Use the FMS Joystick to select the applicable Transponder Type, then press the ENT Key.
3. Use the FMS Joystick to select the desired configurable item and make the desired change. Then press the ENT Key or use the FMS Joystick to select the next item. Press the FMS Joystick to move the cursor to the page selection menu when finished
Configurable items are as follows (note that available configurable items differ by model):
Mode S Address: Can be set to US Tail #, Octal, or Hex, as applicable. A valid Mode S Address will be indicated by a green status box, an invalid Mode S address or other invalid Mode S configuration data is indicated by a red X in the status box.
Aircraft Type: Can be set to Unknown, Fixed Wing, or Rotorcraft, as applicable. If Fixed Wing is selected, a field to enter the aircraft's approximate maximum weight is displayed.
Flight ID: Can be set to Set By Pilot or Other, as applicable. If Set By Pilot is selected, the flight ID can be entered in normal mode. Flight ID can also be set to Same As Tail Number if US Tail # was selected as the Modes S Address.
Aircraft Max Speed: Enter aircraft maximum speed.
Aircraft Length: Enter Aircraft Length.
Aircraft Width: Enter Aircraft Width.
GPS Antenna Offset: Enter the distance from the nose of the aircraft to the GPS antenna used to provide position data to the transponder.
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TIS-A Traffic Data: Can be set to Enabled or Disabled, as applicable. Controls only if traffic information will be displayed, it does not affect whether the transponder will output traffic data. PFD Page Controls: Can be set to Show or Hide the transponder controls on the PFD as desired for a panel-mounted transponder.
ADS-B Transmit: Sets Automatic Dependent Surveillance-Broadcast (ADS-B) to DISABLE, ENABLE, or PILOT SET. DISABLE is the default. When ADS-B is set to DISABLE the BDS (refer to the applicable transponder installation manual for BDS information) items that are marked "ES Enabled Units Only" are not active (no extended squitter). When ADS-B is set to PILOT SET, ADS-B transmissions are active at power-on. ADS-B UAT In: Set to SUPPORTED if the aircraft is equipped with a receiver that provides ADS-B In capability using the 978 MHz UAT frequency, such as the GDL 39. ADS-B 1090ES In: Set to SUPPORTED if the aircraft is equipped with a receiver that provides ADS-B In capability using the 1090 MHz frequency, such as the GDL 39. Enhanced Surveil: Sets Enhanced Surveillance (EHS) to DISABLE or ENABLE. ENABLE is the default. When EHS is set to DISABLE the BDS (refer to the applicable transponder installation manual for BDS information) items that are marked "EHS Only" are not active (no enhanced surveillance). Positions Integrity: Refers to the integrity level of the separate TSO WAAS GPS input that can be connected to the transponder. Can be set to 1E-3, 1E-5 (recommended for 4XX/5XX W), or 1E-7, as applicable. Set to "VFR GPS" if no TSO WAAS GPS input is connected to the transponder. Refer to the applicable TSO GPS receiver Installation Manual for the recommended GPS Integrity setting. VFR Code: This field is the four-digit code that is selected when the user presses the VFR key. In the United States, 1200 is the VFR code for any altitude. The default is set to 1200.
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17.3.15 ADS-B Configuration Page
The ADS-B Data Link Configuration Page is only displayed when the unit is configured to communicate with and has successfully communicated with a GDL 39 (see Appendix D for interface and configuration info). Aircraft Type should be set to "Not Pressurized". The Mode S Address field is displayed (and is editable) if configured for a Mode S Transponder or not configured for any transponder. The Mode S Address field is not displayed if configured for a non-Mode S Transponder, such as a GTX 327.
17.3.16 LOG Configuration Page The Data Logging Configuration page enables the storage of flight data as .csv files to the "data_log" folder on an SD card. If data logging is enabled, the files are automatically written to the SD card after it is inserted into the card slot. These files can be opened in Excel, or imported into Google Earth for viewing using the Garmin Flight Log Conversion tool. The tool and instructions needed to import the files into Google Earth are available from the G3X Product Page found on the Garmin website www.garmin.com.
Select On or Off for SD Card Data Logging and set the maximum number of log files to be stored.
17.3.17 ENG Configuration Page
The Engine/Airframe Input Configuration section of the Engine Configuration Page allows enabling/ disabling and customization of the engine/airframe input options that make up the EIS display and the Engine Page on the MFD. Refer to Section 18 Engine/Airframe Sensor Configuration, for configuring items listed in the Engine/Airframe Input Configuration section of the Engine Configuration page.
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17.3.18 Configuration Sync Status The Configuration Sync Status items appear at the bottom of the Engine Configuration Page. A green checked box indicates a GDU or GSU that is communicating with PFD1, and that "agrees" with PFD1's engine configuration . A red X in the config sync status box indicates a GDU that is connected but has different data from PFD1. After a few seconds it should change back to a green checkmark as the units get back in sync. Units that are not connected are shown in subdued (gray) text.
17.4 Garmin Database Updates
The G3X database updates can be obtained by visiting the `flyGarmin' website (www.fly.garmin.com). The `flyGarmin' website requires the unit's System ID to update databases, this allows the databases to be encrypted with the unit's unique System ID when copied to the SD Card. The System ID is displayed on the System Setup Menu in normal mode, or on the Main Page in configuration mode.
NOTE
A single database update purchased from flyGarmin will allow all displays in the G3X system with matching System ID to be updated, therefore a database purchase is not required for each display.
Since all databases are stored internally in each GDU(except the Chartview database which resides on the SD card), each GDU will need to be updated separately. The SD card may be removed from the applicable GDU after installing the database(s). After the databases have been updated, check that the appropriate databases are initialized and displayed on the splash screen during power-up.
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17.4.1 Updating Garmin Databases Equipment required to perform the update is as follows:
· Windows-compatible PC computer (Windows 2000 or XP recommended) · Verbatim 96504 SD Card Reader or equivalent card reader · Updated database obtained from the flyGarmin website · SD Card, 2 GB recommended (Garmin recommends SanDisk® brand) After the data has been copied to the SD card, perform the following steps: 1. Insert the SD card in the card slot of the GDU 37X to be updated. 2. Turn on the GDU 37X to be updated (in normal mode). 3. Upon turn-on, a screen appears which lists the databases on the SD card. A green checkbox
indicates that the database already installed on the G3X is up to date, an empty checkbox indicates that the database on the SD card is more current and should be installed.
4. The database(s) can be updated by either highlighting UPDATE ALL and pressing the ENT key; or by using the FMS Joystick to highlight a single database and pressing the ENT Key.
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5. When the update process is complete, the screen displays the database status.
6. Once the database(s) have been updated, the SD card can be removed from the unit
7. The unit must be restarted by pressing the Restart softkey. 8. Repeat steps 1-7 for each installed GDU 37X.
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17.4.2 Available Databases
Jeppesen® Aviation Data (NavDataTM) The Jeppesen database contains the general aviation data (NavData) used by pilots (Airports, VORs, NDBs, SUAs, etc.) and is updated on a 28-day cycle.
Jeppesen® ChartviewTM Database ChartView is an optional feature that must be activated by purchasing a ChartView unlock card (010-00769-53). ChartView resembles the paper version of Jeppesen terminal procedures charts. The ChartView database is stored on an SD memory card that remains in the display during normal operation. The ChartView database is updated by removing the database card, updating the database on the card, and reinserting the card. ChartView data is updated by purchasing database subscription updates from Jeppesen Sanderson.
Terrain The terrain database contains the elevation data which represents the topography of the earth. This database is updated on an "as needed" basis and has no expiration date.
Basemap The basemap contains data for the topography and land features, such as rivers, lakes, and towns. It is updated only periodically, with no set schedule. There is no expiration date.
Obstacle The obstacle basemap contains data for obstacles, such as towers, that pose a potential hazard to aircraft. Obstacles 200 feet and higher are included in the obstacle database. It is very important to note that not all obstacles are necessarily charted and therefore may not be contained in the obstacle database. This database is updated on a 56-day cycle.
SafeTaxi The SafeTaxi database contains detailed airport diagrams for selected airports. These diagrams aid in following ground control instructions by accurately displaying the aircraft position on the map in relation to taxiways, ramps, runways, terminals, and services. This database is updated on a 56-day cycle.
FliteCharts The FliteCharts database contains terminal procedure charts for the United States only. This database is updated on a 28-day cycle. If not updated within 180 days of the expiration date, FliteCharts will no longer be user-accessible.
AOPA Airport Directory The AOPA Airport Directory provides data on airports and heliports throughout the U.S. and offers detailed information for over 5,300 U. S. airports, along with the names and phone numbers of thousands of FBOs. Used to look up taxi services, plan an overnight, and choose fuel stops; plus find ground transportation, lodging, restaurants, local attractions, etc. This database is updated every 56 days.
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17.5 XM Activation Instructions (GDU 375 only)
Follow the below instructions to activate the XM receiver in the GDU 375.
Before XM Satellite Weather can be used, the service must be activated by calling XM at 1.800.985.9200. Service is activated by providing XM Satellite Radio with a Radio ID. XM Satellite Radio uses the Radio ID to send an activation signal that allows the G3X MFD to display weather data and/or entertainment programming. XM service should activate in 45 to 60 minutes.
1. The Radio ID can be displayed by accessing the XM Audio Page, and then pressing the INFO Softkey. Record the Radio ID for reference during XM Activation.
2. Make sure that the aircraft's XM antenna has an unobstructed view of the southern sky. It is highly recommended that the aircraft be outside of and at least 25 feet away from the hangar.
3. Hook up the aircraft to external power if available. The complete activation process may take 4560 minutes or more, depending on the demand on the XM activation system.
4. Power on the avionics and allow the G3X to power up. Do not power cycle the units during the activation process.
5. Go to the XM Info Page. During the activation process the unit may display several different activation levels, this is normal and should be ignored. When the service class (Aviator Lite, Aviator, or Aviator Pro) and all of the weather products for the class that you subscribed to are displayed, the activation is complete. Wait 30 seconds to allow the GDU 375 to store the activation before removing power.
NOTE
During the activation process do not change channels or pages.
If the XM receiver will not receive, an Activation Refresh may resolve the issue. An Activation Refresh may be performed by visiting the link http://www.xmradio.com/refresh/rapidrefresh.xmc and following the instructions listed there.
17.6 GDU Splash Screen
Users can create a custom splash screen (screen displayed during power up) by storing a bitmap file on the root directory of the SD card which is inserted into the SD card slot. This function is not available on a single display system. File details are as follows:
· File must be named logo.bmp · Must be uncompressed Windows bitmap, 8bpp or 24bpp with no alpha mask · Max size 480x480 pixels · Store file on root directory of an SD card, inserted in the MFD before power on
17.7 Checklist Editor
The Aviation Checklist Editor (ACE) is available for free download from the Garmin website www.garmin.com. Click on the Software link on the G3X product page and follow the on-screen instructions to download the checklist editor software.
NOTE
The checklist file should be named with a `.ace' file extension, and placed in the root directory of the SD card. Only one checklist file should be placed on the SD card
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18 ENGINE/AIRFRAME SENSOR CONFIGURATION
18.1 Engine/Airframe Sensors
Each of the sensors must be correctly installed (Section 14) and configured prior to use. The Engine inputs being monitored are displayed as gauges on the EIS display (Figure 18-1) and also on the MFD's Engine Page.
Figure 18-1 EIS Display (Engine Bar)
The following list of gauges, (if configured) are specifically required by FAR 91.205 and will always be displayed on the EIS display (engine bar). Other gauges will be displayed as space permits based on a predefined priority and user selections.
RPM
Oil Temperature
Oil Pressure
Fuel Quantity
18.2 Engine Sensor Installation
NOTE
The following sections contain general guidance on engine and airframe sensor installation. This information is provided for reference only. The installer should always follow any installation guidance and instructions provided by the applicable engine, sensor, or kit-plane manufacturer. Additionally, all installation practices should be done in accordance with AC 43.13-1B.
Appendices E through H contain interface drawings for sensor installations using the Garmin sensor kits, and for other sensor installations.
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18.3 Engine/Airframe Input Configuration
The Engine/Airframe Input Configuration section of the Engine Configuration Page allows selection of the engine/airframe inputs that are connected to the GEA 24 or GSU 73, and for customizing the displayed resulting information on the EIS display and the MFD Engine Page. A list of analog, digital, and discrete inputs appropriate for the connected EIS LRU type (GEA 24, Figure 18-2 or GSU 73, Figure 18-3) will be displayed.
Figure 18-2 GEA 24 Engine/Airframe Input Configuration Page
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Figure 18-3 GSU 73 Engine/Airframe Input Configuration Page
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For factory-installed systems, the Engine/Airframe Input Configuration section is replaced with an EIS Configuration page that allows access to calibration functions and time adjustments, but does not allow changing EIS configuration values. See Section 18.3.3 for calibration information, Section 18.3.2.23 for Engine Time, and Section 18.3.2.24 Total Time information.
Refer to Section 17.1 for configuration mode instructions, then follow the below steps to make changes to the Engine/Airframe Input Configuration.
1. In configuration mode, use the FMS Joystick to select the Engine/Airframe Input Configuration Page.
2. Use the FMS Joystick to select the desired configurable item and make the desired change(s) (Section 18.1, including 18.3.1 - 18.3.3.).
3. Press the Save softkey to store settings or press the Cancel softkey to cancel changes and return to the Engine Configuration Page.
4. Press the FMS Joystick to move the cursor to the page selection menu when finished.
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18.3.1 Common Configuration Options
Many of the items listed in the Engine/Airframe Input Configuration section of the Engine Configuration Page have the same (or similar) configuration options, this section describes those similar configuration options.
Gauge Configuration Nearly all of the configuration options (except Discrete 1 4, Engine Time, & Total Time) have a Gauge Marking and a Gauge Display Range section. These gauge options are uniform for all applicable items and are described below.
Gauge Markings Used to select the desired color displayed on the applicable gauge. The Yellow Range + Alert and Red Range + Alert settings will issue a CAS (Crew Alerting System) on-screen alert anytime the value is within that range. The Red Range + Alert settings will issue a CAS audible and on-screen alert anytime the value is within that range The following are the available gauge marking options:
White Range
Cyan Range
Green Range
Yellow Range
Yellow Range +Alert
Red Range
Red Range + Alert
Tick Mark
Cyan Line
Green Line
Yellow Line
Red Line
Gauge Display Range The Gauge Display Range allows for setting the minimum and maximum values of each gauge.
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The below screenshot of the CHT Input Configuration page shows an example of the Gauge Display Range and Gauge Markings settings and the resultant CHT gauge.
Dual Gauge
The EIS display will show a "dual gauge" (two pointers on the same scale, no number) for related quantities, whenever possible for fuel quantity, volts, amps, TIT, and for CHT and EGT (if set for two cylinders). To be displayed, the two sides must have the same values for min and max. If the software can't pair up two related gauges, it will display them as separate gauges with unique names (chosen by the software), such as "VOLTS 1" and "VOLTS 2". If there is not enough room to display both related gauges then neither gauge will be displayed in the EIS display (but will be displayed on the MFD's Engine Page).
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EIS Display The Hide setting removes the item from the EIS display, although the item will be displayed on the MFD ENG page. The Auto setting displays items based upon hierarchy and the availability of EIS display space.
The following list of gauges, (if configured) are specifically required by FAR 91.205 and will always be displayed on the EIS display. These required gauges do not have an EIS Display setting. Other gauges will be displayed as space permits based upon hierarchy.
RPM
Oil Temperature
Oil Pressure
Fuel Quantity
18.3.2 Engine/Airframe Input Configuration Items This section briefly describes how to configure the engine/airframe inputs for each supported sensor type, using the Engine Configuration page. Where applicable, differences between the GEA 24 and GSU 73 are noted. Refer to appendices C through H for wiring guidance.
18.3.2.1 CHT (Cylinder Head Temperature)
Thermocouples: Up to six thermocouples can be connected to the CHT thermocouple inputs on the GEA 24 or GSU 73. Both J-type and K-type thermocouples are supported. Select 1, 2, 4, or 6 cylinders of CHT thermocouple monitoring.
Rotax CHT sensors: Rotax CHT sensor part numbers 965531 and 966385 are supported. For the GEA 24, Rotax CHT sensors are configured using the same CHT input page but are connected to different GEA 24 input pins (Appendix G.1). For the GSU 73, Rotax CHT sensors are connected and configured using the GSU 73 general purpose (GP) inputs (Appendix G.2).
18.3.2.2 Exhaust Gas Temperature (EGT)
Thermocouples: Up to six Type-K thermocouples can be connected to the EGT thermocouple inputs on the GEA 24 or GSU 73. Select 1, 2, 4, or 6 cylinders of EGT thermocouple monitoring. If Lean Assist using EGT is desired, change the Lean Assist setting to "Enabled". (see Section 18.3.2.20 for more information).
Rotax 912iS: For the GEA 24, select "Rotax FADEC" as the EGT configuration to use EGT data from the Rotax 912iS FADEC interface.
NOTE
The EGT 6/MISC PRESS input on the GSU 73 has multiple functions. If the GSU 73 EGT 6/MISC PRESS input has been configured for a sensor that is not an EGT thermocouple, only four EGT thermocouples can be configured.
18.3.2.3 Turbine Inlet Temperature (TIT)
One or two Type K thermocouples can be connected for turbine inlet temperature monitoring, using the TIT 1 and TIT 2 inputs on the GEA 24 or GSU 73. If Lean Assist using TIT is desired, change the Lean Assist setting to "Enabled". (see Section 18.3.2.20 for more information).
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18.3.2.4 RPM
The following sensors can be configured for the RPM 1 input on the GEA 24, or the RPM input on the GSU 73:
· UMA 1A3C Mechanical RPM Sender · UMA T1A9 Magneto Port RPM Sender (4- or 6-cylinder) · Electronic Ignition Tachometer Signal (1, 2, 3, or 4 pulses per revolution - Lycoming and
Continental electronic ignitions typically output 2 pulses/revolution for 4-cylinder engines and 3 pulses/revolution for 6-cylinder engines) · Rotax Trigger Coil RPM · Jabiru Alternator RPM (6 pulses per revolution)
Rotax 912iS: For the GEA 24, select "Rotax FADEC" as the RPM configuration to use engine speed data from the Rotax 912iS FADEC interface.
NOTE
External components are required when using the Rotax Trigger Coil configuration with the GSU 73 (see Figure G-3.1).
18.3.2.5 RPM 2
A second RPM input is provided (RPM 2 input on the GEA 24, CAP FUEL 1 / RPM 2 on the GSU 73). If both RPM inputs are configured, the highest of the two valid RPM values will be displayed. This configuration is useful for aircraft equipped with dual electronic ignitions, where the tach signal ceases to function during a pre-takeoff ignition check.
18.3.2.6 Manifold Pressure
The following sensors can be configured for the Manifold Pressure input on the GEA 24 or GSU 73:
· Kavlico P4055-30A · Kavlico P500-30A · UMA N1EU70A Rotax 912iS: For the GEA 24, select "Rotax FADEC" for the manifold pressure configuration to use manifold pressure data from the Rotax 912iS FADEC interface.
18.3.2.7 Oil Pressure
The following sensors can be configured for the Oil Pressure input on the GEA 24 or GSU 73:
· Kavlico P4055-150G · UMA N1EU150G Rotax/Jabiru oil pressure sensors: Rotax oil pressure sensor part numbers 956413 and 956415, and Jabiru / VDO oil pressure sensor part number 360-003 (or similar VDO 0-5 Bar pressure sensor) are supported. For the GEA 24, these sensors connect to the Oil Pressure Input and are configured using the same page. For the GSU 73, these sensors connect to a general purpose (GP) input.
Rotax 912iS: For the GEA 24, select "Rotax FADEC" to use oil pressure data from the Rotax 912iS FADEC interface.
NOTE
The Rotax 956413 oil pressure sensor requires an external resistor for proper functioning (see Figure G-2.2 for GEA 24 and Figure G-3.1 for GSU 73).
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18.3.2.8 Oil Temperature
The following sensors can be configured for the Oil Temperature input on the GEA 24 or GSU 73:
· UMA 1B3-2.5R · Rotax 965531 · Rotax 966385 · Jabiru / VDO 320-021 (or similar VDO 50-150°C thermistor sensor) Rotax 912iS: For the GEA 24, select "Rotax FADEC" to use oil temperature data from the Rotax 912iS FADEC interface.
18.3.2.9 Fuel Pressure
The following sensors can be configured for the Fuel Pressure input on the GEA 24 or GSU 73:
· Kavlico P4055-15G (0-15 PSI, for most carbureted engines) · Kavlico P4055-50G (0-50 PSI, for most fuel-injected engines) · UMA NAEU07D (0-7 PSI differential, for some turbocharged carbureted engines such as the
Rotax 914) · UMA N1EU35G (0-35 PSI, for most carbureted engines) · UMA N1EU705G (0-70 PSI, for most fuel-injected engines)
18.3.2.10 Carburetor Temperature
The following sensors can be configured to monitor carburetor temperature on the GEA 24 or GSU 73 MISC TEMP 1 inputs, or the GEA 24 MISC TEMP 2 input:
· UMA 1B10R · Rotax 965531 · Rotax 966385
18.3.2.11 Coolant Pressure
The Kavlico P4055-50G sensor can be configured to monitor engine coolant pressure on the GEA 24 or GSU 73 MISC PRESS input.
18.3.2.12 Coolant Temperature
The following sensors can be configured to monitor engine coolant temperature on the GEA 24 or GSU 73 MISC TEMP 1 inputs, or the GEA 24 MISC TEMP 2 input:
· UMA 1B10R (or any Pt100-type RTD sensor) · Rotax 965531 (or any similar VDO 50-150°C thermistor sensor) · Rotax 966385 Rotax 912iS: For the GEA 24, select "Rotax Coolant Temp (FADEC)" for the MISC TEMP 1 input to use coolant temperature data from the Rotax 912iS FADEC interface.
18.3.2.13 Miscellaneous Temperature
The following sensors can be configured to monitor a single miscellaneous (AUX) temperature using the GEA 24 or GSU 73 MISC TEMP 1 inputs, or the GEA 24 MISC TEMP 2 input:
· Thermistor (any 50-150°C thermistor such as the Rotax 965531 or the VDO 320-xxx series) · UMA 1BxR-C (or any Pt100-type RTD sensor)
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18.3.2.14 Fuel Quantity The GEA 24 and GSU 73 support fuel quantity inputs from both analog (resistance or voltage) and digital (frequency) sensors. "Float" type resistive fuel quantity sensors are analog devices. Capacitive fuel quantity sensors may be analog or digital devices, depending on whether they output a voltage (analog) or a frequency (digital).
The GEA 24 supports four fuel quantity inputs (FUEL 1 through 4), any of which can be used with an analog or digital fuel quantity sensor.
The GSU 73 supports four analog fuel quantity inputs (FUEL 1 through 4) and two digital fuel quantity inputs (CAP FUEL 1 and 2). Of these inputs, up four can be configured at any one time.
For both the GEA 24 and GSU 73, up to four fuel quantity measurements may be configured, using one item from each of the following groups:
· Group 1 - Fuel Quantity 1, Main Fuel 1 · Group 2 - Fuel Quantity 2, Main Fuel 2 · Group 3 - Aux Fuel 1 · Group 4 - Aux Fuel 2 Analog and digital fuel quantity inputs may be configured interchangeably for the above listed Groups 1-4. The "Fuel Quantity" and "Main Fuel" configurations are functionally the same, only the displayed text differs.
NOTE
The GSU 73 FUEL 3 and 4 analog inputs require an external pull-up resistor when used with a resistive analog fuel quantity sensor (see Figure E-3.1).
The analog and digital fuel quantity inputs require calibration (see Section 18.3.3).
NOTE
Note: After performing fuel quantity calibration, it is advised to back up the calibration data to an SD card (see Section 18.3.3). Changing the configuration for a fuel quantity input may reset calibration data.
18.3.2.15 Position The GEA 24 and GSU 73 each have multiple POS inputs. Each POS input can be used with a resistive (potentiometer) sensor to monitor the following position measurements:
· Elevator Trim · Aileron Trim · Rudder Trim · Flap Position These inputs require calibration (see section Section 18.3.3).
Vertical Power: When using a Vertical Power unit, trim and flap positions will automatically be displayed. Connecting, configuring, and calibrating the POS inputs is not required when the position sensors are connected to a Vertical Power unit.
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18.3.2.16 Voltage
The GEA 24 and GSU 73 have provisions to monitor bus voltage from two different sources. Bus voltage can be connected to the physical input pins, measured internally by the LRU, or communicated from another data source.
Voltage inputs: The VOLTS 1 and VOLTS 2 input pins on the GEA 24 and GSU 73 can be configured to monitor a directly connected bus voltage. VOLTS 1 can be configured either as "Bus 1" or "Main Bus", and VOLTS 2 can be configured either as "Bus 2" or "Aux Bus". The only difference is the text labels used to display the voltage gauges in the EIS display and Engine Page.
EIS power input: Instead of monitoring a voltage on a physical input pin, the GEA 24 and GSU 73 can monitor the voltage applied to their AIRCRAFT POWER pins. Configure the VOLTS 1 input to "EIS Power Input 1 Volts" to monitor AIRCRAFT POWER 1, and configure the VOLTS 2 input to "EIS Power Input 2 Volts" to monitor AIRCRAFT POWER 2.
Vertical Power: When using a Vertical Power unit, configure VOLTS 1 to "Vertical Power Main Batt Volts" or "Vertical Power Bus 1 Volts" to use primary battery/bus voltage data from the Vertical Power unit. Configure VOLTS 2 to "Vertical Power Aux Batt Volts" or "Vertical Power Bus 2 Volts" to use secondary battery/bus voltage data from the Vertical Power unit.
Rotax 912iS: For the GEA 24, configure the VOLTS 1 input to "Rotax FADEC ECU Bus A Volts" to use power supply voltage data from Lane A of the Rotax 912iS ECU. Configure the VOLTS 2 input to "Rotax FADEC ECU Bus B Volts" to power supply voltage data from ECU Lane B.
18.3.2.17 Current
The GEA 24 and GSU 73 have provisions to monitor bus current from two different sources. Current can be measured either using a shunt resistor such as the UMA 1C4 (50mV/100A type) or a Hall effect sensor such as the Amploc KEY100 series.
Shunt sensors: Shunt sensors are connected to the SHUNT 1 and SHUNT 2 inputs on the GEA 24 and GSU 73 (see Figure E-2.2 and Figure E-3.2). The SHUNT 1 input can be configured to display either "Bus 1 Amps" or "Main Bus Amps". The SHUNT 2 input can be configured to display either "Bus 2 Amps" or "Essential Bus Amps".
Hall effect sensors: Hall effect current sensors are connected to the GEA 24 or GSU 73 general purpose (GP) inputs (see Figure E-2.2 and Figure E-3.2). Hall effect sensors can optionally be calibrated to adjust for installation differences (see Section 18.3.3). The supported configurations for Hall effect current sensors on GP inputs are similar to those supported for shunt current sensors:
· Bus 1 Amps (Hall) · Bus 2 Amps (Hall) · Main Bus Amps (Hall) · Essential Bus Amps (Hall)
Vertical Power: When using a Vertical Power unit, configure SHUNT 1 to "Vertical Power Main Bus Amps" or "Vertical Power Bus 1 Amps" to use primary bus current data from the Vertical Power unit. Configure Shunt 2 to "Vertical Power Bus 2 Amps" to use secondary bus current data from the Vertical Power unit.
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18.3.2.18 Fuel Flow
The following sensors can be configured for the Fuel Flow input on the GEA 24 or GSU 73:
· Electronics International FT-60 · Floscan 201B-6 The fuel flow input requires calibration (see Section 18.3.3).
Rotax 912iS: For the GEA 24, configure the FUEL FLOW input to "Rotax FADEC" to use fuel flow data from the Rotax 912 FADEC interface.
The GEA 24 and GSU 73 also have provisions for a second fuel flow input (FUEL FLOW 2) to use in aircraft that require a second fuel flow sensor for differential fuel flow measurement. If both fuel flow inputs are configured, the displayed fuel flow will be FUEL FLOW 1 (feed) minus FUEL FLOW 2 (return).
18.3.2.19 Discrete Inputs
The GEA 24 and GSU 73 support up to four discrete inputs (DISCRETE 1 through 4) which can be connected to a variety of external switches or voltage signals and used to generate system alerts or control other system functions. For instance, a discrete input could be configured to generate an audible alert and a CAS (Crew Alerting System) message on the PFD display when an external switch is closed.
To configure a discrete input, first select whether the input should be Active Low or Active High. An Active High input will be considered active when the input voltage is above an upper threshold, and inactive when the input voltage is below a lower threshold. An Active Low input will be considered active when the input voltage is below a certain threshold, and inactive when the input voltage is above a certain threshold, or if the input is floating (not connected). In general, most switch-type inputs that are either open or connected to ground should be configured as Active Low. See Section 15.3.8 and Section 15.8.5.1 for the specific voltage levels used for discrete input sensing on the GEA 24 and GSU 73.
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After a discrete input is configured for either Active Low or Active High, it is assigned to a specific function. The following discrete input functions are supported:
· Canopy Closed - Used with a switch that activates the input when the aircraft canopy is closed and locked. A solid yellow CANOPY OPEN message will appear on the PFD if the Canopy Closed input is not active. If engine power is increased or the aircraft is airborne, the CANOPY OPEN message will flash red and an alert tone will sound.
· Door Closed - Same as Canopy Closed except alert text is DOOR OPEN. · Gear Down - Used with a switch that activates the input when the aircraft's landing gear is down
and locked. When active, a solid green GEAR DOWN indication is displayed on the PFD. If inactive, and the aircraft is at a low engine power setting and a low altitude, a red CHECK GEAR alert message appears and a warning tone sounds continuously. · Gear Up - Used with a switch that activates the discrete input when the aircraft's landing gear is fully retracted. A Gear Up input should be used in conjunction with another discrete input that is configured for the Gear Down function. If neither the Gear Up nor Gear Down inputs are active, a red GEAR UNSAFE alert will be displayed if the landing gear is in transition (neither fully up nor fully down). · Stall Switch - When the input is active, a red flashing STALL message appears on the PFD and a warning tone sounds continuously. · Squat Switch - Used with a weight-on-wheels switch that activates the input when the aircraft is on the ground. If a Stall Switch input is also configured, the Squat Switch input will override it (to reduce nuisance alerting when the stall switch is activated while the aircraft is on the ground). The Squat Switch input is also used as an additional factor for determining airborne/on-ground status. · AFCS TO/GA - Used in conjunction with the automatic flight control system (AFCS) flight director to activate Takeoff or Go-Around mode. This input should be connected to a momentary pushbutton located near the pilot's throttle control. · User-Defined Alert - Used to display a custom alert on the PFD when the discrete input is active. Both the message text and the message color can be entered. A yellow alert will generate an audible caution tone, and a red alert will generate an audible warning tone.
18.3.2.20 Lean Assist
Lean Assist is a feature that monitors and detects peak temperatures for EGT or TIT as the pilot leans the engine's air/fuel mixture. When configuring EGT or TIT inputs, Lean Assist can be enabled or disabled. If Lean Assist is enabled, the LEAN softkey will appear on the ENG page in normal mode. Lean Assist should be disabled for engines that do not have pilot-controllable air/fuel mixture.
18.3.2.21 Annunciator Outputs
The GEA 24 and GSU 73 have two discrete output pins, which can be used to drive external indicator lamps. These outputs are optional and do not require any configuration.
DISCRETE OUT 1 acts as a Master Warning annunciator, and is active (pulled low) any time a warninglevel (red) alert is displayed on the PFD.
DISCRETE OUT 2 acts as a Master Caution annunciator, and is active (pulled low) any time a cautionlevel (yellow) alert is displayed on the PFD.
See Figure E-2.2 and Figure E-3.2 for guidance on wiring indicator lamps to the annunciator output pins.
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18.3.2.22 Engine Power Estimated engine power can be calculated for Lycoming and Continental engines, using inputs from RPM, manifold pressure, and fuel flow sensors (all three all required for engine power calculation). On the Engine Power Configuration page, select the appropriate engine type (Lycoming or Continental, turbocharged or normally-aspirated). Then enter the engine's maximum rated power and RPM (for example, 180 horsepower at 2750 RPM). For a turbocharged engine, enter the manifold pressure for maximum rated power. Configuring maximum manifold pressure is not required for a normally-aspirated engine, as it is assumed to produce maximum power at sea level pressure.
Engine power is displayed (in percentage) between the RPM and manifold pressure gauges in the EIS display and on the Engine page.
NOTE
The Engine Power item is disabled when a FADEC engine is configured. For FADEC configurations, engine power or other related status information from the FADEC data interface (for example, an Economy mode indication) will be displayed if available.
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18.3.2.23 Engine Time
Engine Time The Engine Time displays the total operating time in hours of the engine. This time is displayed on both the Engine Configuration Page and the Engine Time Configuration Page. The Engine Time (Current Hours) can only be changed after unlocking the Engine Time Configuration page by pressing softkeys 2, 3, and 4 in order, then using the FMS Joystick to highlight the Current Hours field. The standard value of 2300 RPM is used as a default setting for 1 hour of engine time (i.e. 1 hour of engine operation at 2300 RPM equals 1 hour of engine time). This value can be changed on the Engine Time Configuration Page (below).
NOTE
The Engine Time item is disabled when a FADEC engine is configured. For FADEC configurations engine hours from the FADEC data interface will be displayed.
18.3.2.24 Total Time
Total Time The Total Time displays the total operating time in hours of the aircraft. This time is displayed on both the Engine Configuration Page and the Total Time Configuration Page. The Total Time (Current Hours) can only be changed after unlocking the Total Time Configuration page by pressing softkeys 2, 3, and 4 in order (softkeys are numbered consecutively left-right, see Section 17.1), then using the FMS Joystick to highlight the Current Hours field. The Record Mode selections are listed in Table 18-1.
Table 18-1 Record Mode Selections
Record Mode Selections
Description
None
Total Time is not recorded
Oil Pressure
Records Total Time when engine oil pressure is greater than 5 PSI
Flight Time
Records Total Time when aircraft is airborne as determined by GPS data and the indicated airspeed
RPM
Records Total Time when engine RPM is greater than 100
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18.3.3 Input Configuration Items Requiring Calibration
Fuel Input Calibration The G3X has two fuel calibration curves, the standard `in-flight' or normal flight attitude calibration curve and an optional `on-ground' or ground/taxi attitude calibration curve. The ground/taxi calibration curve can be used for aircraft that have a significantly different attitude when on the ground, such as tailwheel aircraft. If no calibration data is entered for the ground/taxi curve, the normal flight calibration curve will be used when the aircraft is in flight and on the ground. The calibration curve being used to display fuel quantity switches automatically and is determined by GPS groundspeed, indicated airspeed, and height above ground.
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Softkeys on the calibration page are used to switch between the normal flight and the ground/taxi calibration curves. Since the ground/taxi attitude calibration is optional and only availabe when the normal flight attitude calibration data has been entered, the `GROUND' softkey is greyed out (unavailable) until calibration points are entered for the normal flight attitude curve. To perform the Fuel Quantity calibration:
1. Press the Calibrate softkey to display the Calibration Page. 2. Orient the aircraft appropriately for the calibration curve (normal flight or ground/taxi) being per-
formed. 3. Drain all usable fuel from the tank and calibrate at 0.0 gallons. 4. Put a known quantity of fuel (e.g. 5.0 gallons) into the empty fuel tank and enter that same amount
into the Actual Fuel Quantity field. 5. Note the resulting sensor value displayed in the Sensor Value field (the sensor value should change
with each added amount of fuel), wait at least 2 minutes for the reading to stabilize. 6. Highlight and press the Calibrate button. 7. Repeat this process until the fuel tank is full. The user determines the best interval values of fuel to most accurately calibrate the full range of the tank. The greater number of calibration points that are used (maximum of 50 points), the more accurate the calibration will be. A yellow line on the graph indicates potentially incorrect/invalid info. The Digital (frequency) Fuel Inputs are calibrated in the same manner as the resistive fuel inputs, except that the resulting frequency (in kHz) from the sensor is displayed instead of the voltage.
To delete a calibration value, highlight the desired data point in the list and press the CLR Key. Then highlight Yes on the pop-up window, and press the ENT Key, the calibration data is removed.
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Fuel Quantity Calibration Data Backup This option allows the user to back up fuel calibration data to an SD card placed in the SD card slot of the PFD. Access the Read/Write Calibration File menu by pressing the Menu key when displaying the Fuel Quantity Calibration Page
Write Calibration File Stores fuel quantity calibration data to a file on the SD card. Calibration data is saved to the /Garmin/cal/ directory on the card. This data storage must be repeated for each calibrated tank (if backup is desired). Read Calibration File Reads the stored fuel quantity calibration data from the SD card. Fuel Flow Calibration The Fuel Flow input requires calibration as detailed below.
K-Factor Enter the `K' factor for the fuel flow sensor (Section 14.3.10.1).
When installing the fuel flow sensor, the installer should take note of number on the tag attached to the sensor (if applicable). This number is the calibrated K factor of the sensor. For sensors that are not supplied with a specific calibration value, use the default K factor value provided.
The K-Factor represents the number of electrical pulses output by the sensor per gallon of fuel flow. Aspects unique to each installation will affect the accuracy of the initial K-Factor, and as a result, the KFactor must generally be adjusted up or down to increase the accuracy of the fuel flow calibration.
If the fuel usage reported by the G3X differs from the actual fuel usage, as measured at the fuel pump (or other trusted method of measurement), use the following formula to calculate a corrected K-Factor, which can then be used to calibrate the fuel flow.
Corrected K-Factor = ( [G3X reported fuel used] x [previous K-factor] ) / [actual fuel used].
Full Fuel Sets the Full Fuel quantity for the fuel computer. Set according to the fuel tank capacity (set to zero if not used).
Partial Fuel 1 & 2 The Partial Fuel values may be used if the fuel tanks have `tabs' or some other method of putting in a known quantity of fuel (other than completely full tanks). If the Partial Fuel function is not applicable or not desired, these settings can be left blank or set to zero.
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Fill Threshold This setting is used to determine if the fuel quanitity should be confirmed upon system power up. During power up, the sytem compares the current fuel quantity to the fuel quantity recorded when the system was last shut down. If the current fuel quantity exceeds the previous fuel quantity by more than the fill threshold amount (10 gallons shown in previous figure) the system will assume that fuel has been added and will pop up a reminder page prompting the pilot to confirm the quantity of fuel on board. Trim/Flap Position Input Calibration The POS inputs require calibration if configured for any of the trim positions (elevator, aileron, rudder) or flap position.
To perform the Trim/Flap Position calibration: 1. Press the Calibrate softkey to display the Calibration Page. 2. Position the elevator to match the trim position (up/left, neutral, down/right) displayed on the calibration page, or position the flap to the desired position. 3. Note the resulting sensor value (in volts) displayed in the Sensor Value field (the sensor value should change with each change in trim/flap position. 4. Highlight and press the Calibrate button. 5. Repeat this process for each of the Trim/Flap Positions.
NOTE
Flap position values (up to 8) should coincide with the angle of the flap position as expressed in degrees (-90° +90°).
To delete a calibration value, highlight the desired data in the list, and press the CLR Key. Then highlight Yes on the pop-up window, and press the ENT Key, the calibration data is removed.
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Bus 1 and Bus 2 Amps (Hall Effect) Calibration The Bus 1 and Bus 2 inputs can be calibrated (if desired) as detailed below.
Scale Factor For most installations, the scale factor will remain set to the default (1.00) value. A typical use for the scale factor is for a Hall Effect current sensor that has the current-carrying conductor looped through the sensor twice; in that case the scale factor should be set to 0.50 to give the correct current reading.
Amps Offset The Amps Offset calibration can be performed to compensate for any residual current readings that cannot be "zero'ed out". For example, if the Amps gauge reads +0.2 Amps, with no current being drawn, an Amps Offset of -0.2 can be entered and saved, thus correcting the Amps gauge reading to 0.0 Amps. If no compensation is needed, calibration is not necessary and the default value of 0.0 will be used. This setting is most commonly used with Hall effect current sensors because of the inherent variability of some of these type sensors.
Zero Deadband Sets a range of values that will be displayed as zero on the gauge. In the example shown in the following screenshot, any readings from -0.5 to +0.5 will be displayed as zero.
Sensor Value Displays the actual or `raw' current value as measured by the sensor.
Calibrated Amps Value shown will be displayed on current gauge. This value is derived from the Sensor Value plus any adjustments made by the Scale Factor, Amps Offset, and Zero Deadband settings. The measured current is first multiplied by the scale factor, then the offset value is added. If the resulting current value is less than the deadband value, the displayed current will be zero.
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19 POST-INSTALLATION CHECKOUT AND CALIBRATION PROCEDURES
The checkout procedures in this section are recommended to be performed after installing the G3X. The calibration procedures are required to be performed after installing the G3X. It is assumed that the person performing these checks is familiar with the aircraft, has a working knowledge of typical avionics systems, and has experience using the test equipment defined in this section. The calibration procedures in this section are performed in the configuration mode. To enter configuration mode, hold down the left-hand softkey while powering on the GDU 37X. In a two-display or three-display system hold down the left-hand softkey on PFD 1 while powering on the unit. The calibration procedures (Section 19.3.1 Section 19.3.5) may require that certain status boxes on the GSU Page (configuration mode) indicate a positive state (green check marks) before starting the procedure. Table 19-2 and Table 19-3 list the status box requirements for each calibration procedure.
NOTE
Some procedures in this section require that the GPS receiver is receiving sufficient satellite signal to compute a present position (Table 19-2). This requires outdoor line-ofsite to GPS satellite signals or a GPS indoor repeater.
NOTE
As these procedures involve engine run-up and moving the aircraft, it is recommended that the installer read this entire section before beginning the checkout procedure.
NOTE
Unless otherwise noted, all procedures apply to one, two, and three display systems.
CAUTION
Be sure to check all aircraft control movements before flight is attempted to ensure that the wiring harness does not touch any moving part.
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19.1 Recommended Test Equipment
The following test equipment is recommended to conduct and complete all post installation checkout procedures in this section: (All test equipment should have current calibration records)
· Pitot/static ramp tester · Digital Multi-Meter (DMM) · Ground power unit capable of supplying 14/28 Vdc power to the aircraft systems and avionics · Outdoor line-of-sight to GPS satellite signals or GPS indoor repeater · Digital Level or equivalent
19.2 GDU 37X Test Procedure
Test the GPS Receiver: 1. Power on unit and use the FMS Joystick to select the Info Page.
2. Verify that the GPS receiver is functional and able to calculate its present position.
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Test the GPS Receiver for COM Interference:
This test must be conducted outside, as the use of a GPS repeater inside a hangar may result in a failed test. Once the signal acquisition test from Section 13.2 has been completed successfully, perform the following steps:
1. Power on the unit in configuration mode and use the FMS Joystick (scroll down) to view GPS Status on the Main Page.
2. Monitor GPS status on the Main Page. Possible GPS status indications include:
· NO ANTENNA · AUTOLOCATE · LOST GPS FIX · 2D GPS FIX · 3D GPS FIX*
· SEARCHING THE SKY · ACQUIRING · NO GPS FIX · 2D DIFFERENTIAL FIX · 3D DIFFERENTIAL FIX*
*Indicates valid GPS position fix for this test
3. Select 121.150 MHz on the COM transceiver.
4. Transmit for a period of 30 seconds while monitoring GPS status.
5. During the transmit period, verify that GPS status does not lose a valid GPS position fix on the Main Page in configuration mode.
6. Repeat steps 3 through 5 for the following frequencies:121.175 MHz, 121.200 MHz, 131.250 MHz, 131.275 MHz, and 131.300 MHz.
7. Repeat steps 3 through 6 for other installed COM transceivers (if applicable).
8. If an installed COM supports 8.33 MHz channel spacing, repeat steps 3 through 5 (while transmitting for a period of 35 seconds), for the following frequencies: 121.185 MHz, 121.190 MHz, 130.285 MHz, and 131.290 MHz .
9. Repeat step 8 for other installed COM transceivers supporting 8.33 MHz channel spacing (if applicable).
10. This COM interference test should be repeated for each installed GDU 37X with a connected antenna.
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NOTE
GPS Status may also be monitored on the Info page in normal mode. The signal strength bars are a real-time representation of GPS signal strength, which may be useful for troubleshooting a failed COM interference test.
Test the XM Receiver (if applicable): 1. Power on unit and use the FMS Joystick to select the XM Page.
2. Verify that the XM receiver is functioning correctly as indicated by the green signal strength bars. See Section 17.5 for XM Activation Instructions if needed.
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19.3 GSU 25/GSU 73/GMU 22 Post-Installation Calibration Procedures
After mechanical and electrical installation of the GSU 25/GSU 73 AHRS and GMU 22 magnetometer have been completed, prior to operation, a set of post-installation calibration procedures must be carried out.
Table 19-1 describes the calibration procedures:
Table 19-1 Post-Installation Calibration Procedure Summary
Calibration Procedure
A B
C
D E
Procedure Name
Procedure Description
AHRS Orientation
Validate GSU Orientation
Pitch/Roll Offset Compensation
Level Aircraft
Magnetometer Interference Test
Validate no magnetic interference with GMU 22
Magnetometer Calibration
Compass Rose Taxi Maneuver
Engine Run-Up Vibration Test
Validate vibration characteristics of installation
Installations Requiring Procedure
Procedure A is required for all installations
Procedure B is required for all installations
Procedure C is required for initial installation verification. This test should also be repeated to verify all subsequent electrical changes associated with devices within 10.0 feet of the GMU 22 magnetometer. Such changes include, but are not limited to, wiring, shielding or grounding changes to any light, strobe, beacon or other electrical device located in the vicinity of the GMU 22 unit. Likewise, this test should also be repeated to verify all subsequent changes to materials within 10.0 feet of the GMU 22. Such changes include, but are not limited to, addition, removal or modification of ferrous or electrically conductive materials located in the vicinity of the GMU 22 unit. Garmin recommends this test be performed at least once every 12 months.
Procedure D is required for all installations. This calibration must be performed after every Pitch/Roll Offset Compensation and following a removal or replacement of the GMU 22 unit, or degaussing of the area near the GMU 22 location.
Procedure E is required for all installations
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For each Calibration Procedure, Table 19-2 lists the LRU's that require valid calibration data. Table 19-2 Data Validity Requirements for AHRS Calibration Procedures
AHRS Calibration Procedure
AHRS Mounting Orientation Identification Pitch/Roll Offset
Magnetometer Calibration
Engine Run-Up
Magnetometer Interference Test
Valid Status Required for GSU 25 Calibrations None None
GPS and Magnetometer None
Magnetometer
Valid Status Required for GSU 73 Calibrations
None
GPS or Air Data Air Data, GPS, and
Magnetometer GPS or Air Data GPS or Air Data. Magnetometer always required.
Table 19-3 lists the type of valid calibration data required to be output by each LRU for the Calibration Procedures listed in Table 19-2.
Table 19-3 Configuration Mode AHRS Page Status Boxes
Status Box Magnetometer Air Data GPS
Valid Status
Measurement of local 3D magnetic field available
True Airspeed (TAS) available. NOTE: A valid outside air temperature (OAT) measurement is required for TAS to be valid.
3D or 3D Differential GPS solution available
The AHRS Configuration Page status boxes referred to in Table 19-2 and Table 19-3 are shown in the following figure.
If removal and replacement of a GMU 22 unit is required after post-installation calibration has been completed, the GMU 22 mounting rack must not be moved. If the mounting screws that secure the GSU 25/GSU 73 unit or the GMU 22 mounting rack are loosened for any reason, post-installation calibration procedure, A, B, D and E must be repeated before the aircraft can be returned to service.
Any GMU 22 removal or replacement requires repeating the magnetometer calibration.
A repeat of the pitch/roll offset procedure (Procedure B) requires a repeat of the magnetometer calibration procedure (Procedure D).
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The addition, removal, or modification of components that are ferrous, or otherwise magnetic, within 10.0 feet of the GMU 22 magnetometer location after the magnetometer interference test or magnetometer calibration procedure were completed requires a repeat of both procedures. Furthermore, electrical changes to the installation that affect components within 10.0 feet of the GMU 22 magnetometer after the magnetometer calibration and magnetometer interference procedures were completed will require a repeat of the magnetometer interference test. If new magnetic interference is detected, it must be resolved and then the magnetometer calibration procedure must be repeated. Wiring or grounding changes associated with a device located in the vicinity of the GMU 22 is a good example of such a change. 19.3.1 Calibration Procedure A: AHRS ORIENTATION
1. Enter configuration mode by holding down the left-hand softkey while powering on the PFD 1 display.
2. Use the FMS Joystick to select the AHRS Page.
3. Use the FMS Joystick to select which AHRS (1, 2 or 3) is being configured.
4. Use the FMS Joystick to select Unit Orientation and press the ENT key.
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5. For a GSU 73, refer to Figure B-9.2 to determine the correct LRU orientation. Select the correct orientation from the pull-down list, then press the ENT key. For a GSU 25, proceed to the next step (6).
6. For a GSU 25, refer to Figure B-8.3 and Figure B-8.4 to determine the correct LRU orientation, then select that orientation from the pull-down list.
7. Read the description of the selected orientation to ensure the proper orientation has been selected, then press the Save softkey to store the orientation.
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19.3.2 Calibration Procedure B: Pitch/Roll Offset Compensation by Aircraft Leveling.
NOTE
This procedure requires orienting the aircraft to normal flight attitude (can be done by using jacks or placing wood blocks under the nose-wheel, for example). As another example, if the number of degrees `nose high' the aircraft flies in straight and level cruise is known, a digital level can be used to orient the aircraft to normal flight attitude prior to the calibration.
NOTE
The GSU 73 must be leveled within 3.0 degrees of the aircraft in flight level cruise attitude. In flight level cruise attitude is not necessarily the same as the level reference provided by the manufacturer (such as fuselage longerons).
NOTE
The GSU 25 must be leveled within 30.0 degrees of the aircraft in flight level cruise attitude. In flight level cruise attitude is not necessarily the same as the level reference provided by the manufacturer (such as fuselage longerons).
Figure 19-1 Flight Level Cruise Attitude 1. Enter configuration mode by holding down the left-hand softkey while powering on the PFD 1
display (if needed). 2. Use the FMS Joystick to select the AHRS Page (if needed).
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3. Ensure that all the required status boxes are checked (Table 19-2 and Table 19-3). Use the FMS Joystick to select which AHRS (1, 2 or 3) is being configured.
4. Use the FMS Joystick to select PITCH/ROLL OFFSET, press the ENT key.
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5. Ensure that aircraft and AHRS comply with all on-screen instructions, press the START softkey.
NOTE
Per the following figure, GSU 73 units must have the AHRS pitch and roll within 3 degrees of level, GSU 25 units must have the AHRS pitch and roll within 30 degrees of level.
6. "Pitch/Roll Offset Calibration in Progress" appears on the display along with calibration information. The GSU 73 pitch/roll offset procedure completes in a few seconds. The GSU 25 pitch/roll offset procedure has a 30 second countdown timer that resets when the aircraft moves.
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7. When the calibration has completed "Success" or "Failure" will be displayed, press the DONE softkey to return to the AHRS Configuration screen.
The magnetometer calibration (Calibration Procedure D) must be completed after each pitch/roll offset calibration.
NOTE
The pilot may adjust the displayed pitch attitude in normal mode by using the PFD Setup page (see G3X Pilot's Guide,190-01115-00). The maximum amount of pitch display adjustment available in Normal Mode is +/- 2.5°. This feature should not be used to compensate for a non-conforming GSU 25/GSU 73 installation that does not meet the requirements of Calibration Procedure Pitch/Roll Offset Compensation.
NOTE
If the installation has multiple AHRS and the pitch/roll offset procedure is performed for one AHRS, it should be performed on all other AHRS before moving the aircraft.
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19.3.3 Calibration Procedure C: Magnetometer Interference Test
NOTE
Calibration Procedure C is only required for initial installation verification. This test should also be repeated to verify all subsequent electrical changes associated with devices within 10.0 feet of the GMU 22 magnetometer. Such changes include, but are not limited to, wiring, shielding, or grounding changes to any light, strobe, beacon, or other electrical device located in the vicinity of the GMU 22 unit. Likewise, this test should also be repeated to verify all subsequent changes to materials within 10.0 feet of the GMU 22. Such changes include but are not limited to: addition, removal, or modification of ferrous or electrically conductive materials located in the same wing as a GMU 22 unit. This procedure validates that no electronic device is interfering with the operation of the GMU 22 magnetometer which directly impacts the determination of attitude and heading by the GSU 25/GSU 73 AHRS. Calibration Procedures A and B are not required prior to this execution of this procedure.
CAUTION
The real time readout displayed during the interference test is only valid for the location of the GMU when the test was initiated. If using this procedure to evaluate multiple mounting locations, the test must be started over for each location, failure to do so could provide incorrect test results.
NOTE
Garmin recommends this test be performed at least once every 12 months.
1. Enter configuration mode by holding down the left-hand softkey while powering on the PFD 1 display (if needed).
2. Use the FMS Joystick to select the AHRS Page (if needed).
3. Ensure that all the required status boxes are checked (Table 19-2 and Table 19-3). Use the FMS Joystick to select which AHRS (1, 2 or 3) is being configured.
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4. Use the FMS Joystick to select Magnetic Interference Test and press the ENT key.
5. Ensure that the aircraft has been properly prepared per the on-screen instructions. See Table 19-4 for a sample test sequence. Press the Start softkey to begin the test.
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6. The operator should carry out the actions called for in the prepared test sequence. During calibration, a real-time value is displayed that represents the current magnetic field strength as a percentage of the maximum limit.
NOTE
It is important that all actions are carried out in the order and at the precise elapsed time as specified in the prepared test sequence.
7. After completing the prepared test sequence, press the Done softkey. Ensure that a PASSED message appears on the display. The magnetic deviation value is displayed to indicate the pass or fail margin of the test. Press the Done softkey to return to the AHRS Page.
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Table 19-4 Magnetometer Interference Test Sequence Example
Elapsed Time Since Start of Test (min:secs) 0:00 0:10 0:20 0:30 0:40 0:50 1:00 1:20 1:40 1:50 2:00 2:10 2:20 2:30 2:40 2:50 3:00 3:10 3:20 3:30 3:40 3:50 4:00 4:10 4:20 4:30 4:40 4:50 5:00 5:10
5:20
5:30 5:40 5:50 6:00 6:10 6:20
Action Test begins Aileron full right Aileron full left Aileron level Elevator up Elevator down Elevator level Rudder left Rudder right Rudder center Flaps down Flaps up Autopilot on Autopilot off Landing gear up Landing gear down Speed brake up Speed brake down Navigation lights on Navigation lights off Landing lights on Landing lights off Taxi lights on Taxi lights off Landing + Taxi lights on Landing + Taxi lights off Strobes on Strobes off Recognition lights on Recognition lights off Turn on all wing-tip lights simultaneously (typically will include navigation lights, recognition lights and strobe) Turn off all wing-tip lights simultaneously Beacon on Beacon off Pitot heat on Pitot heat off End of test
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If the test fails, the installation should be considered unreliable until the source of magnetic interference is identified and remedied. The magnetometer interference test must be repeated until passed. When the magnetometer interference test fails, record the three magnetometer maximum deviation values and their corresponding timestamps. A maximum deviation value greater than 100% of the total limit in any axis indicates a problem that must be resolved. Compare the corresponding timestamps with the prepared test sequence to identify which action produced the problem. Contact Garmin for assistance in resolving the problem.
NOTE
Two common reasons for a failed magnetometer interference test are: 1) New equipment is installed in close proximity to the GMU 22 magnetometer. 2) An existing or new electronic device has become grounded through the aircraft structure instead of via the proper ground wire in a twisted shielded pair.
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19.3.4 Calibration Procedure D: Magnetometer Calibration
NOTE
Calibration Procedure B must be successfully completed prior to Calibration Procedure D.
NOTE
Calibration Procedure D must be carried out at a location that is determined to be free of magnetic disturbances, such as a compass rose. Attempting to carry out this maneuver on a typical ramp area will not yield a successful calibration. The accuracy of the AHRS cannot be guaranteed if this calibration is not performed at a magnetically clean location. A method for evaluating the magnetic disturbances at a candidate site is described in Section 19.5.
Taxi the aircraft to a site that has been determined to be free of magnetic disturbances. Ensure that there are no nearby magnetic materials on or near the perimeter of the site. If unavoidable, maneuver the aircraft to keep the magnetometer from passing within twenty feet (6.1 meters) of such objects. Additionally ensure that vehicles or other aircraft are an adequate distance [forty feet (12.2 meters)] away from the aircraft under test.
At the site, align the aircraft to a heading of magnetic north (5°). It is best to offset the aircraft position to the left (west) of the North/South axis to allow turning clockwise around the site as indicated in Figure 19-2.
Figure 19-2 Aircraft Alignment
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With the aircraft stationary, initiate the GSU 25/GSU 73 AHRS magnetometer calibration procedure as follows:
1. Enter configuration mode by holding down the left-hand softkey while powering on the PFD 1 display (if needed).
2. Use the FMS Joystick to select the AHRS Page (if needed).
3. Ensure that all the required status boxes are checked (Table 19-2 and Table 19-3). Use the FMS Joystick to select which AHRS (1, 2 or 3) is being configured.
4. On the AHRS page, use the FMS Joystick to select Magnetometer Calibration and press the ENT key.
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5. Ensure that all on-screen instructions have been complied with, then press the Start softkey to begin the calibration.
6. Follow the on-screen instructions, the dots at the end of the text will be removed as the test progresses.
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7. Follow the on-screen instructions by slowly turning the aircraft to the right, the dots at the end of the text will be removed as the aircraft rotates 30 degrees. When all of the dots have been removed, and the text changes to `Hold Position', stop turning the aircraft, and wait for further instructions.
8. Continue following the on-screen instructions until the calibration is completed. The calibration will go through 12 cycles of holding, then turning to the right before completing a full circle.
9. When the calibration is finished, ensure that a Calibration Status of "Success" is displayed, press the Done softkey to return to the AHRS Configuration Page.
NOTE
If more than one magnetometer is installed, it is recommended to perform the Magnetic Calibration Procedure for both magnetometers consecutively, one procedure immediately followed by the next. This is especially important if something about the airplane has been changed that required a repeat of the Magnetic Calibration Procedure.
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19.3.5 Calibration Procedure E: Engine Run-Up Vibration Test
NOTE
Calibration Procedure E is required for all installations to validate the vibration characteristics of the installation. Calibration Procedures B through D are not required prior to this procedure.
NOTE
Passing the Engine Run-Up Vibration test does not remove the requirement to rigidly mount the GSU 25/GSU 73 to the aircraft primary structure. The Engine Run-Up Vibration Test is intended to help discover mounting issues but successful completion of the test does not validate the mounting of the GSU and GMU, and does not account for all possible vibration profiles that may be encountered during normal aircraft operation
1. Enter configuration mode by holding down the left-hand softkey while powering on the PFD 1 display (if needed).
2. Use the FMS Joystick to select the AHRS Page (if needed).
3. Ensure that all the required status boxes are checked (Table 19-2 and Table 19-3). Use the FMS Joystick to select which AHRS (1, 2 or 3) is being configured.
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4. Use the FMS Joystick to select ENGINE RUN-UP TEST and press the ENT key.
5. Ensure that the aircraft has been properly positioned per the on-screen instructions, then press the Start softkey to begin the test.
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6. Gradually increase power from idle to full throttle and back to idle over the course of 1-2 minutes, the test data is displayed as the test progresses.
.
NOTE
If failures are indicated, the engine run-up test may be repeated up to three times. If the test does not pass after three attempts, the installation should be considered unreliable until the source of the vibration problem is identified and remedied. If the engine run-up test fails repeatedly, record the values that are reported to be out of range for future reference. 7. Press the Done softkey when engine runup has been completed, the test results will be displayed. Ensure that test results indicate Passed, then press the Done softkey to return to the AHRS page.
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The following are potential causes for failure of the engine run-up test:
a) Excessive flexing of GSU 25/GSU 73 and/or GMU 22 mechanical mounting with respect to airframe (see Section 10, Section 11, and Section 8 for applicable mounting requirements and instructions).
b) Vibration or motion of GSU 25/GSU 73 and/or GMU 22 caused by neighboring equipment and/or supports.
c) Mounting of GSU 25/GSU 73 at a location that is subject to severe vibrations (example; close to an engine mount.)
d) Mounting screws and other hardware for GSU 25/GSU 73 and/or GMU 22 not firmly attached.
e) Absence of recommended mounting supports.
f) GSU 25/GSU 73 connector not firmly attached to unit.
g) Cabling leading to GSU 25/GSU 73 or GMU 22 not firmly secured to supporting structure.
h) An engine/propeller combination that is significantly out of balance.
NOTE
In some aircraft, attempting the engine run-up test on a day with very strong and/or gusty winds may cause the test to occasionally fail. However, windy conditions should not be taken as evidence that the test would pass in calm conditions; an actual pass is required before the installation can be considered adequate.
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19.4 AOA (Angle of Attack) Calibration (Performed In-flight)
Installations that include a GAP 26 and which have Angle of Attack (AOA) enabled require that an AOA calibration be performed to enable AOA functionality. The AOA calibration is used to determine the four AOA settings shown in Figure 19-3. This calibration must be done while in flight. The AOA Setup page (Figure 19-5) on PFD 1 is used for the AOA cal procedure, and is accessed in normal mode (requires that an AOA input is enabled on the LRU Configuration page, see Section 17.3.2).
WARNING
AOA calibration involves flying the aircraft at low airspeeds and angles of attack at or near the stall point. Do not perform AOA calibration until the aircraft's stall recovery characteristics are well-understood. Before AOA calibration, ensure that the aircraft is clear of all traffic and at a safe altitude for stall recovery.
Stall Warning AOA
Approach Target AOA
Caution Alert AOA
Minimum Visible AOA Figure 19-3 Angle of Attack (AOA) Display
AOA is the angle between the aircraft's wing and the oncoming airflow (see Figure 19-4). As AOA increases, eventually it will reach a critical value (determined by the physical characteristics of the wing), whereupon the airflow will separate, the wing will stop producing lift, and the aircraft will stall. The primary purpose of an AOA system is to monitor the wing's angle of attack and provide feedback to the pilot when the aircraft is approaching the critical AOA.
LOW ANGLE OF ATTACK
MEDIUM ANGLE OF ATTACK
EXCESSIVE ANGLE OF ATTACK Air Flow is Broken. No Lift to Sustain the Airplane.
Figure 19-4 Angle of Attack (AOA) Illustration
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19.4.1 AOA Calibration Procedure
Perform the procedure steps in Section 19.4.1, Section 19.4.1.1, Section 19.4.1.2, Section 19.4.1.3, and Section 19.4.1.4. Any of the calibration procedures can be repeated to fine-tune the behavior of the AOA gauge and audio alerting.
NOTE
For best results, perform all AOA calibration in smooth air. Turbulence or rough air can affect the calibration.
NOTE
The calibration values displayed for the AOA calibration points are proportional to actual AOA (the greater the calibration value, the greater the AOA) but are not otherwise representative of any specific unit of measure.
For the calibration to be valid:
· The stall warning AOA calibration value (resultant from the calibration procedure) must be greater than the minimum visible AOA calibration value (see Figure 19-5).
· The caution alert AOA calibration value (resultant from the calibration procedure) must be greater than the minimum visible AOA calibration value and less than the stall warning AOA calibration value (see Figure 19-5).
Figure 19-5 Angle of Attack Setup Page
1. In normal mode on PFD 1, press the MENU Key twice to display the Main Menu. 2. Use the FMS Joystick to select System Setup.
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3. Press the ENT Key to display the System Setup page, use the FMS Joystick to select Angle of Attack.
4. Press the ENT Key to display the Angle of Attack Setup page. 5. If AOA calibration has not yet been performed, the calibration fields will be blank. "AOA
Pressure Measurement Not Valid" will be displayed if an air pressure sensor is not connected, or if the aircraft is on the ground. To delete an existing AOA calibration, highlight the calibration field, then press the CLR key.
NOTE
The following Angle Of Attack Setup page is also accessible in configuration mode. The configuration mode page only allows viewing and deleting the AOA calibration values, the AOA calibration cannot be performed in configuration mode.
6. Perform the 3 required calibration points (minimum visible AOA, caution alert AOA, and stall warning AOA), plus 1 optional calibration point (approach target AOA, if desired) in the following recommended order.
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19.4.1.1 Minimum Visible AOA Calibration This procedure sets the AOA value for the bottom of the AOA gauge green arc (Figure 19-6), which is also the AOA value at which the gauge will first appear on the PFD. Perform this calibration while flying the aircraft at an AOA somewhat higher than a normal cruise flight (1.5 x stall speed is suggested) to avoid nuisance frequent appearances of the AOA gauge.
Minimum Visible AOA Figure 19-6 Minimum Visible AOA 1. Use the FMS Joystick to select the Calibrated Minimum Visible AOA calibration field, then press the Calibrate softkey. 2. Follow the onscreen instructions, then press the Start softkey to begin the calibration.
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3. Follow the onscreen instructions, then press the Done softkey when finished.
4. Verify that the calibration is successful, then press the Done softkey when finished.
5. Proceed to Section 19.4.1.2.
NOTE
After calibrating all required AOA points, if the AOA gauge appears too frequently or not frequently enough, the Minimum Visible AOA calibration step can be repeated to set a new value.
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19.4.1.2 Caution Alert AOA Calibration This procedure sets the AOA value for the bottom of the yellow "chevron" section of the AOA gauge (Figure 19-7), which is also the AOA value at which the audible stall warning sound will begin to intermittently play. Perform this calibration while flying the aircraft at an AOA below the aircraft's stall AOA (1.1 x stall speed is suggested).
Caution Alert AOA (Audio Tone Sounds Inermittently)
Figure 19-7 Caution Alert AOA 1. Use the FMS Joystick to select the Calibrated Caution Alert AOA calibration field, then press the
Calibrate softkey. 2. Follow the onscreen instructions, then press the Start softkey to begin the calibration.
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3. Press the Calibrate softkey when in compliance with the onscreen instructions.
4. Verify that the calibration is successful, then press the Done softkey when finished.
5. Proceed to Section 19.4.1.3.
NOTE
After calibrating all required AOA points, if the AOA caution alert and audio warning occur too frequently or not frequently enough, the Caution Alert AOA calibration step can be repeated to set a new value.
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19.4.1.3 Stall Warning AOA Calibration This procedure sets the AOA value for the top of the red "chevron" section of the AOA gauge (Figure 19-8), which is also the AOA value at which the audible stall warning sound will play continuously (just before stall break is suggested).
Stall Warning AOA (Indicator Flashes and Audio
Tone Sounds Continuously)
Figure 19-8 Stall Warning AOA 1. Use the FMS Joystick to select the Calibrated Stall Warning AOA calibration field, then press the
Calibrate softkey. 2. Follow the onscreen instructions, then press the Start softkey to begin the calibration.
3. Press the Calibrate softkey when in compliance with the onscreen instructions.
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4. Verify that the calibration is successful, then press the Done softkey when finished.
5. If desired, repeat the Stall Warning AOA calibration using a different flap setting. 6. If desired, proceed to Section 19.4.1.4. If the Approach Target AOA Calibration procedure is not
desired, the AOA Calibration Procedure is complete.
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19.4.1.4 Approach Target AOA Calibration (Optional) This procedure sets a specific point (1.3 x stall speed is suggested) on the AOA gauge to use as the ideal target AOA for an approach, glide, short-field landing, etc. If calibrated, the approach target AOA will display as a green circle on the AOA gauge (Figure 19-9). To be valid, the approach target AOA must be between the minimum visible (green) and caution alert (yellow chevron) AOA points.
Approach Target AOA
Figure 19-9 Approach Target AOA 1. Use the FMS Joystick to select the Calibrated Approach Target AOA calibration field, then press
the Calibrate softkey. 2. Follow the onscreen instructions, then press the Start softkey to begin the calibration.
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3. Press the Calibrate softkey when in compliance with the onscreen instructions.
4. Verify that the calibration is successful, then press the Done softkey when finished. 5. This completes the AOA calibration procedure.
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19.5 External Interface Configuration (Garmin units only)
Refer to Appendix D for wiring the interface connections between GDU 37X LRUs and any external Garmin units such as the GNS 4XX/5XX, GNS 480, GTN 6XX/7XX, and GTX transponder products. See the Configuration Guidance instructions on the drawings in Appendix D for specific unit configuration settings. This section lists specific instructions for changing the configuration settings of the external Garmin units (the SL30 and SL40 units do not require configuration).
19.5.1 GNS 400/500 Series Units (including `A', `TAWS', & `WAAS' models)
Entering Configuration Mode:
1. With power applied to the aviation rack and the 400/500 Series unit turned off, press and hold the ENT key and turn the unit on.
2. Release the ENT key when the display activates. The unit is now in configuration mode. After the database pages, the first page displayed is the MAIN ARINC 429 CONFIG page.
3. While in configuration mode, pages can be selected by ensuring the cursor is off and rotating the small right knob, select the desired Config Page.
NOTE
Make configuration changes only as described in this section, changing other configuration settings is not recommended and may significantly alter the unit's operation. Garmin recommends recording all configuration settings (before making any changes) for reference.
Changing data on the displayed configuration pages:
1. Press the small right knob to turn on the cursor. 2. Turn the large right knob to change between data fields. 3. Turn the large or small right knob to change data in the selected field. 4. Press the ENT key to accept the entry. 5. Turn unit off and then back on to return to normal operation.
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Installation Configuration Pages
The configuration pages are in the order found when rotating the right small knob clockwise starting at the MAIN ARINC 429 CONFIG page. Follow the preceding procedures to enter configuration mode and to select the desired configuration settings (the following figures are for reference only and may vary from actual screens/settings, refer to instructions on the drawings in Appendix D).
4XX Main ARINC 429 Config Page
5XX Main ARINC 429 Config Page
4XX Main RS232 Config Page
5XX Main RS232 Config Page
4XX Main CDI/OBS Config Page
5XX Main CDI/OBS Config Page
4XX Main VOR/LOC/GS 429 Config Page
5XX Main VOR/LOC/GS 429 Config Page
NOTE
Each output channel can be used to drive up to three RS-232 devices.
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19.5.2 GTX 23/33/327/328/330 Transponder
Refer to the applicable transponder (GTX 23/33/327/328/330) installation manual for configuration mode instructions. The configuration settings are detailed in Appendix D of this document.
NOTE
Make configuration changes only as described in Appendix D, changing other configuration settings is not recommended and may significantly alter the unit's operation. Garmin recommends recording all configuration settings (before making any changes) for reference.
19.5.3 GTN 625/635/650/725/750 Unit
Configuration Mode Operations
Before configuring the GTN, ensure that no Configuration Module service messages are displayed in the message queue. This would indicate that the config module is improperly wired or damaged. Configuration mode is used to configure the GTN settings for each specific installation. While in configuration mode, pages can be selected by touching the desired key on the display. Some pages may require page scrolling to view all of the information and keys on the page. Scrolling is done by touching the screen and dragging the page in the desired direction, or by touching the Up or Down keys.
Entering Configuration Mode:
1. With the GTN turned off (circuit breaker pulled), touch and hold the HOME key and reapply power to the GTN (push in the circuit breaker).
2. Release the HOME key when the display activates and the name `Garmin' appears fully lit on the screen.
3. The first page displayed is the Configuration Mode Home Page (the following figures are for reference only and may vary from actual screen/settings, refer to instructions on the drawings in Appendix D).
4. Touch the GTN Setup key.
GTN 7XX Configuration Mode Home Page
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5. Follow configuration instructions per applicable drawing in Appendix D.
GTN 6XX GTN Setup Page
GTN 7XX GTN Setup Page
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20 TROUBLESHOOTING
In this section the term `Red-X' refers to a red "X" that appears on different areas of the display to indicate the failure of that particular function. Refer to the G3X Pilot's Guide (190-01115-00) for a complete listing of System Status Messages. For additional assistance, contact your G3X Dealer, then for further help (if needed), contact Garmin Aviation Product Support at US Toll Free Number 1-888-606-5482, or US 1-913-397-8200.
NOTE
Any advisory or warning message indicated on the Info Page whlie on-ground should be investigated and resolved before flight.
NOTE
The information in this section is for troubleshooting use only and does not supersede any approved Maintenance or Installation Manual instructions.
20.1 General Troubleshooting
1. Review the airframe logbook to verify if any G3X or other avionics or electrical maintenance had been performed recently that may have contributed to the failure.
2. Check for loose wire terminals on the circuit breaker connections on the power wire(s) causing intermittent power connections. Also, check for intermittent circuit breakers.
3. Have ground power put on the aircraft.
4. Turn on the G3X and record the system software level on the GDU start up page.
5. After the system is initialized, note any Red-X's on the displays, ALERT messages and Red-X's on the GDU.
If the failure cannot be verified, proceed to the following physical inspection.
1. Turn off the G3X and remove the interior panels to gain access to the GSU 73. Inspect the physical installation of the affected LRU.
2. Check that the connectors are fully seated, and that the jack screw connectors are fully tightened on both sides of the affected LRU's connector.
3. Check for a loose wire harness that is able to move around during flight. This condition may cause the wire to pull on or vibrate the connector, making intermittent connections.
4. Ensure that the affected LRU is mounted securely. Use a screwdriver to check the tightness of the four mounting screws.
5. Look in the vicinity of the affected LRU for any heavy objects that may not be fastened tight to the structure and induce GSU 25/GSU 73 vibration.
6. Look for evidence of water or fluid contamination in the area around the affected LRU.
7. Unplug the affected LRU's connector and check for bent pins.
8. Inspect the wire harness clamp on the rear of the connector to verify that it is not too tight and smashing/shorting the wires. If the wire clamp is installed upside down, it has sharp edges that can cut into the wires. Verify the presence of protective wire wrap between the wires and the clamp.
If the condition is not resolved by following the preceding instructions, contact Garmin Product Support for additional assistance. A Garmin Field Service Engineer may ask the technician to download the fault logs to a PC and email the logs back to Garmin to help determine if the condition is caused by a G3X LRU or in the aircraft.
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20.1.1 Status LED
The GAD 29, GEA 24, GSA 28, and GSU 25 units have an LED on their outer cases that indicates the LRUs current status. The status indications are:
Table 20-1 Status LED Indications
LED Indication No Light Steady Green Flashing Green Red
Alternating Red/Green
Description No Power On, but not communicating via CAN Bus On and communicating via CAN Bus Hardware Fault CAN bus network error two similar devices are configured with the same unit ID
20.2 GDU 37X
20.2.1 SD Card Slot
A stuck or sticking SD card issue can sometimes be caused by the card thickness variability (especially if there is more than one label on the card). This is usually caused by the card sticking in the overlay opening, not by the card sticking to the socket inside the unit. Try another card (without a label if possible) to confirm the problem before returning. If the second card sticks, the SD socket board inside the unit may be misaligned with the overlay and the GDU 37X will require repair. If the thickness of the card was the cause, see if more than one label was on the card. If the labels weren't the cause, determine what brand of SD card was being used (Garmin recommends using SanDisk® brand cards).
20.2.2 Unit Communication Error Messages (Two or Three GDU Systems)
Error messages occur if there is a mismatch in GDU 37X software versions. If this occurs, the GDU's will not communicate with each other, and a software mismatch message will be reported on the INFO page (press the MSG softkey). Ensure both displays are running the same software version to clear the issue. Unit communication error related messages are as follows:
· GDU Software Version Mismatch - Indicates that two or more GDU displays are using incompatible software versions. All GDUs in the aircraft must be updated to use the same software version.
· Network Fault - Duplicate GDU Detected - Indicates that more than one GDU is configured to be the same unit type (e.g. two displays are configured as PFD1). See section Section 15.2.3 for information on GDU mode pin connections.
· Network Address Changed - Indicates that the state of a GDU's mode pins was detected. Check for loose connections and see Section 15.2.3 for information on GDU mode pin connections.
· Navigation/Terrain/Obstacle Database Missing - Indicates that a required database is missing on the specified GDU display. A database update is required.
· Navigation/Terrain/Obstacle Database Mismatch - Indicates that two or more GDU displays have different versions of the specified database. Update the databases in all GDU displays to the same cycle number.
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20.3 Air Data Troubleshooting
Under normal operating conditions, the GSU 73 provides the following air data information: · Total Air Temperature is measured · Outside Air Temperature (OAT) · Indicated Airspeed (IAS) · True Airspeed (TAS) · Barometric Altitude · Density Altitude · Pressure Altitude · Static Pressure · Differential Pressure
NOTE
TAS information can only be displayed at speeds greater than 20 Knots (TAS is invalid when the aircraft is sitting still, or if no OAT probe is connected).
If the TAS indication remains dashed out at speeds greater than 20 knots and/or the OAT indication is dashed out (as shown in Figure 20-1):
1. Check the GTP 59 OAT probe wiring and connection for faults. 2. Check GSU 73 configuration module wiring for damage, replace if any is found. 3. Replace the GTP 59 OAT probe. 4. If the problem persists, replace the GSU 73 with a known good unit.
Figure 20-1 No info for TAS & OAT If the Airspeed and/or Altitude is failed and shows a Red-X condition as shown in Figure 20-2:
Figure 20-2 Airspeed and Altitude Failure Indications 1. Inspect GSU 73 pitot/static plumbing integrity. 2. Inspect pitot/static ports and associated equipment. 3. If the problem persists replace the GSU 73 with a known good unit.
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20.4 Engine Indication Troubleshooting
To troubleshoot an Engine Indication failure (Figure 20-3), gather answers to the following questions. This information may be helpful to the installer/pilot, the G3X Dealer, or to Garmin Aviation Product Support in troubleshooting the failure.
Figure 20-3 Engine/Airframe Failure Indications (Reversionary or Split-Screen PFD)
1. Does cycling power restore operation? 2. Did the operator give it sufficient time to start and initialize? 3. Did the problem begin after a software or configuration load? 4. Did the problem happen on the ground or while airborne? 5. Is only the EGT/CHT (i.e. thermocouple inputs) Red-X'd? If so, the GSU 73 configuration
module, configuration module wiring, thermocouple reference, or applicable thermocouple is defective. Check the wiring and replace the configuration module or applicable thermocouple. 6. Are there one or more temperatures that drop as the electrical load increases? If a temperature probe shorts (usually where the bayonet is crimped) a ground loop is created forcing the reference (low side) to increase which causes the temperature reading to decrease. 7. Does the EGT temperature slowly drift up and eventually flag? This is an indication of an (electrical) open in the temperature probe or wiring. 8. Is the air data information on the PFD intermittently Red-X'ing? If the GSU 73 +5 VDC transducer power supply is shorted to ground, it will cause an intermittent air data Red-X issue to occur. 9. If the AMP indication is Red-X'd, check the Alternator Shunt for correct resistance. Refer to the applicable sensor documentation. 10. If the Position Indication is Red-X'd, check the sensor and wiring. 11. For single wire temperature inputs, ensure that the LO input pin is tied to ground as close as is practical to the sensor, grounding the LO input pin away from the sensor may result in inaccurate or invalid readings.
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20.5 AHRS Troubleshooting
20.5.1 Heading Red-X
Figure 20-4 Heading Failure Indication (Full-Screen PFD)
If a Red-X (steady or intermittent) is displayed on the heading (Figure 20-4), check the following while the aircraft is on the ground:
1. When taxiing without reliable GPS information, heading performance is susceptible to the presence of magnetic anomalies (metal buildings, underground steel culverts, steel grates in the ramp, rebar). Localized sources of interference on the ground may consistently cause a Red-X to be displayed on the heading in the same spot while taxiing, this is not caused by a failure of the GMU 22 or its calibration.
2. When the aircraft is taxiing on the ground with a yaw rate of less than 1.5 degrees/second (i.e., taxiing essentially in a straight line) GPS track information is used to update heading information. This logic is applied regardless of magnetic anomaly detection.
3. The GDU may display Red-X on the heading if the GSU 73 does not have GPS information, or if it senses a magnetic anomaly.
4. While a magnetic anomaly is detected and the aircraft is determined to be stationary, the value of the heading output is frozen. When either the aircraft is determined to be no longer stationary or the magnetic anomaly ceases, heading will be unfrozen and determined as useable. In this context, the aircraft is considered to be stationary when its yaw rate is less than 1.0 degrees/second and all other angular rate and acceleration values are sufficiently small. (moving or shaking the wings or tail for example can cause a Red-X to be displayed).
5. Check to see if any new equipment has been installed on the aircraft, and reference Table 8-4 for minimum distances for installed equipment from the GMU 22 to prevent interference.
If the GMU 22 heading is not present on the GDU 37X, there may be a problem with the RS-232 or RS-485 line between the GSU 25/73 and GMU 22. Troubleshoot any possible wiring/connector issues before replacing either unit.
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20.5.2 Attitude/Heading Failure Troubleshooting
Figure 20-5 Attitude and Heading Failure Indications (Reversionary or Split-Screen PFD)
Prior to troubleshooting an Attitude Failure, gather answers to the following questions. This information may be helpful to the installer/pilot, the G3X Dealer, or to Garmin Aviation Product Support in troubleshooting the failure.
1. What specifically was the nature of the failure? Was it a Red-X of only heading, only pitch/roll, or both?
2. If there was a Red-X of pitch or roll information, did the PFD display the "AHRS Align: Keep Wings Level" message (which is indicative of an AHRS reset), or the "Attitude Fail" message (which is indicative of either AHRS invalidating its output, or a communication path failure)?
3. What exactly was the aircraft doing in the two minutes that preceded the failure (taxing on the ground, flying straight-and-level flight, turning, climbing, etc)? If the problem occurred on the ground, was it within 100 feet of a hanger using GPS repeaters?
4. How long did the failure last? Was it brief or sustained? Was it repetitive in nature? If it was repetitive, about how many times did it happen? Did it happen on more than one day?
5. Was the problem correlated with a specific maneuver or a specific geographic area?
6. Can the problem be repeated reliably?
7. Were any of the following message advisory alerts observed (must navigate to the INFO page and press the MSG softkey to see them) within an hour of the occurrence of the problem?
· AHRS not receiving airspeed · AHRS not receiving any GPS information · AHRS magnetic-field model out of date · AHRS extended operation in no-GPS mode
8. Did the onset of the problem occur shortly after a software upload to one or more of the G3X LRU's, or shortly after a repeat of the magnetometer calibration procedure?
9. Were there any GPS Alert messages or loss of position lock?
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The GSU 25/73 may not be able to provide valid heading/pitch/roll data for the following reasons:
1. If an "AHRS not Calibrated" message is displayed, the GSU 25/73 external memory module in the harness (that stores the installation configuration parameters) is either not present or not wired properly. In this case, either: · The GSU 25/73 configuration module is inoperative. OR · The external installation configuration parameters are not calibrated and the AHRS and/or Magnetometer calibration needs to be performed. If either of these is not calibrated, the GSU 25/73 heading, pitch, and roll may all be flagged as invalid. Calibrate the unit to the installation.
2. There is not sufficient or valid sensor information being provided to the GSU 73 for it to compute valid attitude information.
20.6 Post Installation Calibration Procedures
The calibration procedures in Section 19.3.3 and Section 19.3.5 may be performed during troubleshooting. Table 19-2 and Table 19-3 list the status box requirements for each calibration procedure. The Magnetometer Interference Test may be used to determine if the location of the GMU 22 is susceptible to magnetic interference. The Engine Run-Up Vibration Test can be used to determine if the mounting of the GSU 73 and GMU 22 are susceptible to aircraft vibration.
NOTE
Passing the Engine Run-Up Vibration test does not remove the requirement to rigidly mount the GSU 73 to the aircraft primary structure. The Engine Run-Up Vibration Test is intended to help discover mounting issues but successful completion of the test does not validate the mounting of the GSU and GMU, and does not account for all possible vibration profiles that may be encountered during normal aircraft operation
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20.7 GSU 73 Data Logging
The GSU 73 Data Logger may be used to help troubleshoot G3X issues. Operational data can be gathered from the GSU 73 during flight or on ground, and stored in a data file on a PC. The data file can then be uploaded to the Garmin website and used by Garmin product support to diagnose the issue.
20.7.1 Downloading and Installing the GSU 73 Data Logger
The GSU 73 Data Logger can be downloaded for free via the G3X product page on the Garmin website www.garmin.com. Download and install the data logger by using the link and following the on-screen prompts.
The installation wizard for the GSU 73 USB logging tool creates a desktop shortcut, adds the tool to the program menu, and installs any required programs that could not be found on the target machine. The wizard allows the installer to choose the folder location that will store the program and the associated data logger files. The installation requires that the target machine has a Windows XP or later operating system and that the user is an administrator on that PC. Once the file has been downloaded and installed, it can be used to create a diagnostic data file to be uploaded to Garmin product support.
20.7.2 GSU 73 USB Logging Tool Operation
Connect one end of a USB cable to the USB port of the PC, and the other end to the mini-USB connector on the GSU 73. The cable can be connected before or after the PC and the G3X are powered on.
NOTE
The "found new hardware" pop-up may be displayed during the initial connection of the GSU 73 to the PC. Follow the on-screen prompts to locate the device driver, disconnect and reconnect the GSU 73, then proceed with the following instructions.
1. Make sure that the PC and the G3X are powered on. 2. Start the GSU 73 Data Logger by double-clicking on the desktop shortcut. 3. To begin USB logging, click the `Start' button.
Figure 20-6 Data Logger, Start Screen
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4. The Data Logger requests product data, then downloads 7 regions from the GSU 73 to the PC. The full path is displayed on the user interface of the logging tool. The log file name includes the date and time when the logging began. Each power-on of the GSU 73 or Start/Stop of the tool has a separate log file.
Figure 20-7 Data Logger, Download Screen
5. After the region download process has completed, `Recording!' is displayed and the logging tool begins storing received data in the specified log file.
6. Click on the Stop button to end the data recording session.
Figure 20-8 Data Logger, Recording Screen
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7. If the logging tool loses data connection to the GSU 73, it will continuously check to see if the connection has been reestablished. This allows the tool to auto-restart, and eliminates the need for pilots to interact with the tool in flight.
Figure 20-9 Data Logger, Connection Screen 20.7.3 Uploading the Data File To upload a data file created with the GSU 73 Data Logging Tool, return to the G3X product page (on the Garmin website www.garmin.com) and select the Data Log Upload Form. Follow the on-screen instructions to enter the required information and attach the data file to upload, then select Submit. The file and associated information is then sent to the Garmin Aviation Product Support team for analysis.
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21 RETURN TO SERVICE INFORMATION
These return to service procedures are intended to verify the serviceability of the appliance only. These tests alone do not verify or otherwise validate the airworthiness of the installation.
21.1 GDU 37X
21.1.1 Original GDU 37X is Reinstalled No software or configuration loading is required if the original GDU 37X is reinstalled. Continue to Section 21.2.
21.1.2 Original GDU 37X(s) Installed in a Different Position No software or configuration loading is required if the GDU 37X is installed in a different location. Continue to Section 21.2.
21.1.3 New GDU 37X(s) Installed If a new GDU 37X is installed (new serial number), verify the correct software version on the MAIN page in configuration mode. Additionally verify that all installed displays have the same software version, as well as NavData, terrain, and obstacle databases. If the correct software version is not installed, update the displays to the current G3X system software available on the web. No configuration is required if the configuration module is still operational. Continue to Section 21.2.
21.1.4 New GDU 37X (PFD) Configuration Module Installed Ensure that a new configuration module is obtained for the replacement installation. If a new configuration module is installed and no change is made to the PFD, the PFD will write the required configuration information to the configuration module. If the PFD and the configuration module are both replaced, the system will need to be configured (Section 17).
NOTE
Do not use a used GDU configuration module as a replacement. Data that may reside on the used configuration module may cause system configuration errors.
21.2 GSU 73
NOTE
A pitot/static check as outlined in 91.411 and Part 43 Appendix E must be completed if the pitot/static lines are broken.
21.2.1 Original GSU 73 is Reinstalled No software or configuration loading is required if the original GSU 73 is reinstalled in its original mounting location. Continue to Section 21.4. 21.2.2 New GSU 73 Installed If a new GSU 73 is installed (new serial number), verify the correct software version on the MAIN page in configuration mode. The correct GSU 73 software version will automatically be loaded from the GDU. If the configuration module is operational, no software configuration is required. Continue to Section 21.4.
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21.3 GSU 25
21.3.1 Original GSU 25 is Reinstalled
No software or calibration is required if the original GSU 25 is reinstalled in its original mounting location. Continue to Section 21.4.
21.3.2 New GSU 25 is Installed
Any time a new GSU 25 is installed, or an existing GSU 25 is moved to a different mounting location, the AHRS unit orientation (Section 19.3.1), pitch/roll offset (Section 19.3.2), and magnetometer calibration procedures (Section 19.3.4) must be performed. The correct GSU 25 software version will automatically be loaded from the GDU.
21.4 GMU 22
NOTE
If the GMU 22 is removed, the anti-rotation properties of the mounting screws must be restored. This may be done by replacing the screws with new Garmin P/N 211-60037-08. If original screws must be re-used, coat screw threads with Loctite 242 (blue) threadlocking compound, Garmin P/N 291-00023-02, or equivalent. Important: Mounting screws must be brass.
21.4.1 GMU 22 is Reinstalled
Any time a GMU 22 is reinstalled, a new magnetometer calibration is required (Section 19.3.4). Continue to Section 21.4.2
21.4.2 New GMU 22 Installed
If a new GMU 22 is installed (new serial number), a new magnetometer calibration (Section 19.3.4) and verification of the correct software version (Section 17.2) is required. If the correct software version is not installed, load the GMU 22 software contained in the G3X system software which is loaded to the displays (Section 17.2). Following a successful magnetometer calibration, and software verification the Return to Service Procedure is complete.
21.5 GEA 24
No additional action is required when a GEA 24 is reinstalled or replaced. The correct GEA 24 software version and EIS configuration will automatically be loaded from the GDU.
21.6 GSA 28
21.6.1 GSA 28 is removed
No additional action is required when a GSA 28 is reinstalled or replaced. The correct GSA 28 software version and autopilot configuration settings will automatically be loaded from the GDU.
21.7 GAD 29
No additional action is required when a GAD 29 is reinstalled or replaced. The correct GAD 29 software version and ARINC 429 configuration will automatically be loaded from the GDU.
21.8 GMC 305
No additional action is required when a GMC 305 is reinstalled or replaced.
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APPENDIX A AIRFRAME SPECIFIC INSTALLATION GUIDANCE
A.1 Introduction
Garmin has included in this manual some installation guidelines to aid the builder in the placement of various units which make up the G3X. It is at the discretion of the builder whether he or she wants to follow a typical layout or design an installation completely unique to their aircraft. The following information is provided as guidance only and does not account for variations in specific installations.
NOTE
Although the potential GMU 22 mounting locations shown in this manual have been tested on appropriate type aircraft, Garmin cannot take into account the wide variation of aircraft specific installations and therefore cannot guarantee the provided locations will work for all installations in a particular aircraft type. Garmin strongly recommends the installer conduct a thorough review of Section when choosing an appropriate mounting location for the GMU 22. In addition to reviewing the guidance provided in Section , the installer should use the Garmin GMU Site Survey Tool to conduct a GMU 22 site evaluation prior to permanent installation of the GMU 22 mounting bracket. The GMU Site Survey Tool and the AHRS/Magnetometer Installation Considerations document (which contains instructions) can be downloaded from the Dealer Resource Center portion of the Garmin website www.garmin.com. Please contact your G3X dealer for additional information on setup and use of the GMU Site Survey Tool.
NOTE
The typical installations contained in this manual are known to fit each aircraft. In addition, custom brackets and mounting which should be incorporated to properly support the units are detailed in the typical installation. Unsupported avionics or inferior mounting brackets can contribute to cracking of the mounting trays or a unit becoming dislodged, intermittent or to fail completely. The guidance of FAA advisory circulars AC 43.13-1B and AC 43.13-2A may be found useful.
NOTE
It is recommended the builder at least review the typical installation prior to embarking on his/her own design, and determine what additional components may be required to suit their particular installation.
A.1.1 GMU 22 The integrity and reliability of the G3X heading and attitude information is entirely dependent upon the installation quality of the GMU 22 Magnetometer. Garmin strongly recommends the purchase of the prefabricated parts indicated in Table . Failure to use Garmin approved brackets may result in severe degradation of system performance. Garmin cannot guarantee acceptable system performance if any variations from these designs are made. It is essential that installation accuracy requirements specified in the following sections be maintained in any GMU 22 installation, if the installer chooses to follow the typical installation guidance.
Table A-1 GMU 22 Mount Kits
Airframe
GMU 22 Mount Kit
Lancair IV/IV-P
011-01788-00
Lancair ES/ES-P
011-01779-00
RV-7/7A, -9/9A
011-01796-00
RV-10
011-01779-00
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A.2 Van's Aircraft
A.2.1 RV-7/9
A.2.1.1 GMU 22 Mounting Bracket
An RV-7/9 GMU 22 Mounting Bracket Kit is available under Garmin part number 011-01796-00, see Figure A-1. The aft deck was chosen as an installation location, as it provides a level pitch and roll reference and acceptable separation from excessive magnetic disturbances. The mounting bracket is predrilled to ensure proper alignment with the longitudinal (yaw) axis.
Figure A-1 RV-7/9 GMU 22 Mounting Bracket (115-01027-00)
A.2.1.1.1 GMU 22 Mounting Bracket Installation Guidance The RV-7/9 GMU 22 Mounting Bracket can be installed on the F-714 aft deck forward of the horizontal stabilizer. Prior to installing the mounting bracket on the aft deck, the GMU 22 mounting plate (115-00481-00) should be riveted to the mounting bracket. When riveting the mounting plate to the bracket, ensure that the "Forward" arrow is pointing towards the front of the airplane and is parallel to the longitudinal axis of the aircraft. As shown in Appendix B-4.1, the mounting plate should be attached to the bracket with the supplied AN426AD5-6 rivets.
NOTE
The GMU 22 mounting bracket outer dimensions are used for alignment. To minimize inadvertent misalignment caused by edge alteration, it is recommended that the installer NOT deburr the edges of the GMU 22 mounting bracket.
NOTE
After the GMU 22 mounting plate has been installed on the mounting bracket, the following procedure should be followed to attach the mounting bracket to the F-714 aft deck:
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1. Draw a centerline down the middle of the F-714 aft deck. 2. Place the GMU 22 mounting bracket on the F-714 aft deck (see Figure A-2). 3. Slide the GMU 22 mounting bracket forward, ensuring the front edge is against the vertical portion
of the F-714 aft deck (see Figure A-2).
NOTE
It is vital that the front edge be squarely positioned against the flange. The GMU 22 rack alignment points are based on the mount being perpendicular to the flange. The inner edge should be aligned with the centerline on the fuselage.
4. SECURELY clamp the mounting bracket to the aft deck so that no movement occurs with the front edge flush with the vertical portion of the F-714 aft deck.
5. Drill the six attach points with a #30 drill bit. 6. Rivet the mounting bracket to the aft deck using AN470AD4 or LP4-3 rivets. Alternatively, the
builder may elect to install the mounting bracket with non-ferrous fasteners (screws, washers, and nuts).
Figure A-2 RV-7/9 GMU 22 Mounting Bracket on the F714 Aft Deck
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A.3 Lancair Aircraft
A.3.1 Lancair IV/IV-P
Differences exist between the Lancair IV/IV-P and the ES series aircraft that result in different mounting techniques for the GMU 22.
A.3.1.1 GMU 22 Mounting Bracket
The Lancair IV/IV-P GMU 22 mount (011-01788-00) is composed of a top (115-01052-00) and bottom (115-01052-01) assembly. An aircraft specific mounting bracket has been developed to accommodate the full wing tank option and thin wing tip area remaining. The bracket is specific to the right wing tip, and can be used with the standard tip or winglet.
A.3.1.1.1 GMU 22 Mount Installation Guidance
One possible mounting location for the GMU 22 is in the right wingtip (refer to Figure A-3). The bottom assembly should be screwed and glued to the bottom of the wingtip using the dimensions below. Care must be taken to accurately align the mount parallel to the edge of the wingtip. This will ensure the finished installation will have the proper alignment with the aircraft's heading.
NOTE
It is recommended the wingtip antenna option be omitted from this wingtip to prevent interference with the magnetometer.
Figure A-3 Lancair IV/IV-P Right Wingtip GMU 22 Installation
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1. Rivet the GMU 22 Installation Rack (115-00481-00) to the Top Bracket Assembly (115-01052-00) as shown in Figure A-4.
Figure A-4 Lancair IV/IV-P GMU 22 Mounting Bracket 2. Attach the GMU 22 to the Top Bracket Assembly (115-01052-00) using screws (211-60037-08) as
shown in Figure A-5.
Figure A-5 Lancair IV/IV-P GMU 2222 Mounting Bracket
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3. Attach the Top Bracket Assembly (115-01052-00) to the Bottom Bracket Assembly (115-01052-01) as shown in Figure A-6.
Figure A-6 Lancair IV/IV-P GMU 22 Mounting Bracket
4. After the installation, the pigtail of the GMU 22 should mate with the aircraft wiring that is routed through the wing. Due to the narrow thickness of the wingtip in this location, install chafe protection between the pigtail of the GMU 22 and all surfaces of the wingtip that may come in contact with the pigtail.
· When routing the GMU 22 wiring with other power sources, ensure each power source contains an adequate return ground. It is important to route the return ground with the power wire to help cancel stray magnetic fields.
· Route NAV light wiring as far as practical away from the GMU 22.
5. Refrain from installing any ferrous metals near the GMU 22, including the mounting screws and nut plates used to attach the wingtip. Stainless steel fasteners are recommended.
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A.3.2 Lancair ES/ES-P A.3.2.1 GMU 22 Mounting Bracket The Lancair ES/ES-P uses the G3X generic GMU 22 mount. The mount is comprised of two sheet metal parts, a bottom bracket (Garmin part number 115-00939-00) and a top bracket (Garmin part number 11501017-00) that holds the GMU 22 mounting plate. The set is purchased as a sub-assembly kit under Garmin part number 011-01779-00. A.3.2.1.1 GMU 22 Mount Installation Guidance One possible mounting location for the GMU 22 is the last wing rib in the right wingtip (refer to Figure A-7). The wing tip should be removable to gain proper access to the GMU 22. At a minimum, a removable access panel under the wingtip is required. The GMU 22 is removed by lifting the unit up and out, the entire bracket assembly would need to be unscrewed from the rib in order to service it from underneath. Considerations for both GMU 22 bracket attachments and wingtip attachments should be made to ensure access to the GMU 22.
Figure A-7 Right Wingtip GMU 22 Installation
· The GMU 22 Installation Rack (115-00481-00) should be installed parallel to the mounting surface of the Magnetometer Bracket (115-01017-00) to ensure the finished GMU 22 installation will be in alignment with the Lancair ES/ES-P aircraft heading.
· The GMU 22 Installation Rack (115-00481-00) should be installed with the forward arrow (marked on the ring) indicating a direction parallel with the outboard wing rib, which acts as a reference for the aircraft's forward direction.
NOTE
There are two small alignment holes on the GMU 22 bracket and a "V" cut into the GMU 22 Installation Rack. Temporarily placing a drill bit in this hole will aid in making a perfectly parallel alignment of the GMU 22.
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1. Clamp the GMU 22 Installation Rack (Figure A-8) in place and match drill the GMU 22 Bracket through three countersunk mounting holes.
2. Mark the center of the three mounting screw holes. 3. Remove the GMU 22 mounting plate. 4. Drill the clearance holes in the GMU 22 Mounting Bracket.
Figure A-8 GMU 22 Installation Rack (ES / ES-P) 5. Rivet the GMU 22 Installation Rack (115-00481-00) to the Top Bracket Assembly
(115-01017-00) as shown in Figure A-9.
Figure A-9 GMU 22 Installation Rack (ES/ES-P)
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6. Rivet the Top Bracket Assembly (115-01017-00) to the Universal Bracket Assembly (115-0093900) as shown in Figure A-10 and Figure A-11.
Figure A-10 Lancair IV/IV-P GMU 22 Mounting Bracket Assembly
NOTE
The assembled bracket can be shifted to accommodate for wing dihedral. Figure A-11 illustrates the offset rivet holes which may be utilized to tilt the GMU 22 up (plus) from the mounting surface or down (minus) from the mounting surface.
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Figure A-11 Adjusting for Wing Dihedral
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7. With the GMU 22 mount setup for installation in the right wing, shift the bracket to the minus 2 degree setting and rivet it in place using six 1/8" button head rivets as illustrated in Figure A-12.
Figure A-12 Rivet shifted Magnetometer Mount 8. Attach the GMU 22 to the GMU 22 Mounting Bracket as illustrated in Figure A-13 using brass
screws.
Figure A-13 Secure GMU 22 to the Mounting Bracket Assembly
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9. Fabricate two disks from 2 BID sheet to the dimensions shown in Figure A-14.
Figure A-14 2 BID Sheet Disk 10. Align one stainless steel nutplate MS21048-3 (or K1001-3) to each disk using the center hole as a
guide. Match drill 0.098 holes to nutplate and countersink 100° on one side. Refer to Figure A-15.
Figure A-15 Aligned Nutplate And Disk 11. Rivet nutplate to disk with MS20426AD3-4 rivets as shown in Figure A-16.
Figure A-16 Riveted Nutplate And Disk
12. Place the Magnetometer Mounting Assembly aft of the spare and level with the typical flight attitude. Make sure there is sufficient head room for the pig tail to bend clear of the wing tip.
13. Match drill the Magnetometer Bracket to the wing rib.
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14. Apply epoxy resin to the flat side of the nutplate washers, see Figure A-17.
Figure A-17 Nutplate Washers 15. Apply a small amount of release agent on the stainless steel MS51958 screw threads. 16. Attach GMU assembly to wing rib as shown in Figure A-18.
Figure A-18 Magnetometer Assembly attached to Wing Rib
NOTE
Stainless steel hardware (nutplates and screws) must be used to attach the GMU 22 bracket to the wing.
NOTE
The wing tip should also be attached with stainless steel hardware (nutplates and screws).
NOTE
Never use a magnetic screwdriver to remove or install wingtip hardware.
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A.3.3 Lancair Legacy A.3.3.1 GMU 22 Magnetometer Installation Guidance
1. A possible mounting location is in the upper section of the fuselage cavity, just forward of the vertical tail section. The recommended location is shown in Figure A-19.
RECOMMENDED LOCATION
RECOMMENDED LOCATION
Figure A-19 Lancair Legacy Magnetometer Location 2. In determining a shelf location, ensure there is enough room above the shelf to install or remove
the magnetometer, as well as provide clearance for the associated cable harness as shown in Figure A-20.
MAGNETOMETER SHELF (REF)
UP FWD
MAGNETOMETER SHELF (REF)
Figure A-20 View Looking AFT At Recommended Magnetometer Location
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3. Measure the fuselage in multiple locations to determine the size of the shelf. The shelf will have an approximate trapezoidal shape and should have a depth of at least 4.0 in. Cut the shelf from 0.25 in. thick, 2-ply per side prepreg. Cut a 2.50 in. diameter hole in the center of the shelf, as shown in Figure A-21. Alternately, the 2.50 in. diameter hole can move left or right on the shelf, so long as there is adequate clearance to install or remove the magnetometer. By placing the hole in the center of the shelf, the elevator control tube can be used more effectively in a later step to align the GMU 22 Installation Rack with the aircraft's forward direction. Prepare for shelf installation by sanding, roughing up, and cleaning all bonding areas on the shelf and fuselage for best adhesion.
Figure A-21 Example Magnetometer Shelf 4. Fill gap between sides of fuselage and shelf with epoxy/flox mixture. Be sure to make a radius at
the corners as shown in Figure A-22 to smooth the corners for laying glass in the following steps. When aligning the shelf, ensure the shelf remains level to within 3° of the pitch and roll axes.
FILL WITH EPOXY/FLOX MIX TURE
Figure A-22 Fill Detail For Corner Radii And Magnetometer Shelf
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5. Secure the shelf to the fuselage with one layer of 3.0 in. wide, 2 bid strips at each corner above and below the shelf. The lay up is shown in Figure A-23.
UP
3" WIDE, 2 BID STRIPS, 4 PLACES
FWD
MAGNETOMETER SHELF
Figure A-23 Magnetometer Shelf With Lay up 6. The shelf installation must be fully cured before proceeding with the magnetometer installation.
Using the elevator control tube as the aircraft centerline reference, project a parallel line on to the magnetometer shelf. The parallel line serves as an indication of the aircraft's forward direction, as shown in Figure A-24. The alignment of the magnetometer is critical and needs to be within 0.5° of the aircraft's forward direction.
MAGNETOMETER SHELF
ELEVATOR CONTROL TUBE
Figure A-24 Alignment Of Magnetometer Cutout With Aircraft's Forward Direction
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Alternately, if the 2.50 in. diameter hole is drilled off of centerline as shown in Figure A-25, project a parallel line to the aircraft's centerline reference using the elevator control tube as a reference line. Mark a parallel line at the offset cutout to create the forward direction reference.
MAGNETOMETER SHELF
ELEVATOR CONTROL TUBE MAINTAIN PARALLEL TO FORWARD DIRECTION
Figure A-25 Alignment Of Magnetometer Cutout With Aircraft's Forward Direction With Offset Magnetometer Cutout
Clamp the GMU 22 Installation Rack (115-00481-00) in place above or below the shelf, whichever corresponds to the side with the centerline reference mark, allowing the inside diameter of the cutout in the GMU 22 Installation Rack to be concentric with the circular cutout in the magnetometer shelf. Align the notch on the GMU 22 Installation Rack (indicating forward direction) with the aircraft centerline mark at the forward end of the shelf. The cutout alignment needs to be within 0.5° of the aircraft's forward direction. Address the six holes for the magnetometer install rack as shown in Figure A-26 by either match drilling or marking the holes as shown. Match drill the magnetometer shelf through the three countersunk holes found on the Installation Rack. Mark the center of the three mounting screw holes. Remove the GMU 22 Installation Rack and drill the three marked locations to 0.203 in. diameter, as these are clearance holes for the GMU 22 Magnetometer unit installation.
NOTE
The GMU 22 Installation Rack must be set, drilled, and installed after the shelf has been mounted in the aircraft and cured.
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FWD
115-00481-00 G M U 22 INSTALLATION RACK
60° TYP
M ARK LO CATIO N Ø 0 .2 0 3
3 PLACES
M ATCH DRILL Ø 0.164 3 PLACES
Figure A-26 Magnetometer Shelf With Hole Pattern For GMU 22 Installation Rack 7. Assemble the GMU 22 Installation Rack to the magnetometer shelf as shown in Figure A-27.
3X 6-32 STAINLESS SCREWS, 100° COUNTERSUNK (MS24693C OR EQUIVALENT)
115-00481-00 GMU 22 INSTALLATION RACK
MAGNETOMETER SHELF (REF)
UP
3X AN960C6 WASHERS 3X 6-32 STAINLESS NUTS (MS21083C06 OR EQUIVALENT)
FWD
Figure A-27 Assembly Of GMU 22 Installation Rack To Magnetometer Shelf
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8. Install the GMU 22 Magnetometer in the installation rack with the hardware provided as shown in Figure A-28.
UP
211-60037-08 SCREW 6-32 x .25 BRASS (3X)
FWD
GMU 22 MAGN ETOM ET ER
MAGNETOMETER SHELF (REF)
Figure A-28 Installation Of GMU 22 Magnetometer
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Figure B-1.1 GA 55/55A Installation Drawing
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FORWARD
2X 1.750 44.45 1.000 25.40 2X .89 22.6
4.23 107.4
GA 55 STUD MOUNT
011-00134-00 ANTENNA, AVIATION,
GA 55
FORWARD
253-00002-00 GASKET, NEOPRENE
1.91 48.5
FORWARD
4.23 107.4
.22 5.6 4X #8-32 STUD
SIDE VIEW
.50 12.7
.60 15.2 .83 [21.1]
AIRCRAFT SKIN ON TOP OF FUSELAGE
115-00031-00 BACKING PLATE 4X 210-10004-09 #8-32 SELF LOCKING NUT
2.59 65.8
BNC CONNECTOR FRONT VIEW
2X 1.25 31.8
5.00 127.0
3.00 76.2
BACKING PLATE OUTLINE
2X 1.625 41.28 .813 20.64
4X .188 4.78
.625 15.88 2.59 [65.8] MOUNTING CUTOUT (ANTENNA OUTLINE)
GA 55A FLANGE MOUNT
FORWARD
4X 211-60212-20 #10-32 PHP x 1.00[25.4] TORQUE 20 TO 25 in-lbs
011-01153-00 GA 55A XM ANTENNA
253-00138-00 MOLDED GASKET
AIRCRAFT SKIN
.49 12.3
FABRICATE AND INSTALL DOUBLER PLATE AS REQUIRED TO COMPLY WITH APPLICABLE AIRWORTHINESS REGULATIONS
2.90 73.7 .80 20.2
.60 15.2
FORWARD
4.70 119.4 2.37 60.2
.25 6.4
XM TNC CONNECTOR
FORWARD
.65 16.5 2X 0 .800 20.3 2X 1.600 40.64
.70 17.8 2X 0
011-01153-00 ANTENNA OUTLINE
2.350 59.69 2X 3.300 83.82
.750 19.05 .625 15.88
4X .220 5.59
NOTES: 1. DIMENSIONS: INCHES[mm]
MOUNTING CUTOUT
APPENDIX B OUTLINE & INSTALLATION DRAWINGS
Figure B-1.2 GA 56 Installation Drawing
G3X Installation Manual - Outline & Installation Drawings Page B-2
GA 56 STUD MOUNT
011-00134-00 ANTENNA, AVIATION,
GA 56
FORWARD
253-00002-00 GASKET, NEOPRENE
1.91 48.5
FORWARD
4.23 107.4
.22 5.6 4X #8-32 STUD
SIDE VIEW
.50 12.7
.60 15.2 .83 [21.1]
AIRCRAFT SKIN ON TOP OF FUSELAGE
115-00031-00 BACKING PLATE 4X 210-10004-09 #8-32 SELF LOCKING NUT
2.59 65.8
BNC CONNECTOR FRONT VIEW
2X 1.25 31.8
5.00 127.0
3.00 76.2
BACKING PLATE OUTLINE
2X 1.625 41.28 .813 20.64
4X .188 4.78
.625 15.88 2.59 [65.8] MOUNTING CUTOUT (ANTENNA OUTLINE)
FORWARD
2X 1.750 44.45 1.000 25.40 2X .89 22.6
4.23 107.4
190-01115-01 Rev. K
Figure B-1.3 GA 57X Installation Drawing
G3X Installation Manual - Outline & Installation Drawings Page B-3
190-01115-01 Rev. K
.49 12.3
2.90 73.7
FORWARD
4.70 119.4 2.35 59.7
.80 20.2
.60 15.2
.25 6.4 GPS BNC CONNECTOR
XM TNC CONNECTOR
FORWARD
.65 16.5 2X 0 2X .800 20.3 2X 1.600 40.64
.70 17.8 2X 0
1.000 25.40
2.350 59.69
011-01032-00 ANTENNA OUTLINE
2X
.750 .625
19.05 15.88
2X 3.300 83.82
NOTES: 1. DIMENSIONS: INCHES[mm]
MOUNTING CUTOUT
4X .220 5.59
FORWARD
4X 211-60212-20 #10-32 PHP x 1.00[25.4] TORQUE 20 TO 25 in-lbs
011-01032-10 GA 57X GPS/XM ANTENNA
253-00138-00 MOLDED GASKET
AIRCRAFT SKIN
FABRICATE AND INSTALL DOUBLER PLATE AS REQUIRED TO COMPLY WITH APPLICABLE AIRWORTHINESS REGULATIONS
Figure B-2.1 GAD 29 Outline Drawing
G3X Installation Manual - Outline & Installation Drawings Page B-4
2X .250 6.35 2X .369 9.37 2X 2.352 59.74
5.095 129.41
2X 5.600 142.24
2.950 74.93 CENTER OF GRAVITY
NOTES: 1. DIMENSIONSIN INCHES [mm]. METRIC VALUES ARE FOR REFERENCE ONLY. 2. DIMENSIONS ARE NOMINAL AND TOLERANCES ARE NOT IMPLIED UNLESS SPEIFICALLY STATED. 3. REFER TO 190-01115-01 FOR ADDITIONAL PARTS LIST.
5.539 140.68
WITH CAN TERMINATOR 5.095[129.41]
WITHOUT CAN TERMINATOR
1.479 37.57
.100 2.54
6.100 154.94
.040 1.02 TYPICAL THICKNESS BENEATH FASTENER HEAD
3.235 82.17 3.090 78.49 2.350 59.69 CENTER OF GRAVITY
.675 17.15 CENTER OF GRAVITY
190-01115-01 Rev. K
330-00625-09 011-01855-00
GAD 29 011-03236-00
P291
330-00624-25
P292
GAD 29 CONNECTOR KIT
011-03271-00 011-01855-02
Figure B-2.2 GAD 29 Installation Drawing (no CAN terminator)
190-01115-01 Rev. K
G3X Installation Manual - Outline & Installation Drawings Page B-5
Figure B-2.3 GAD 29 Installation Drawing (with CAN terminator)
G3X Installation Manual - Outline & Installation Drawings Page B-6
GAD 29 011-03236-00
GAD 29 CONNECTOR KIT
011-03271-00
330-00624-25
011-01855-02
P292
P291
330-00625-09 011-01855-00
CAN TERMINATOR 011-02887-00 [OPTIONAL]
IMPORTANT NOTE: DEPENDING ON HOW THE SYSTEM IS PHYSICALLY WIRED, THIS ADAPTER MAY OR MAY NOT BE NEEDED IN THE INSTALLATION. THE G3X CAN BUS MUST BE TERMINATED AT ONLY THE TWO MOST EXTREME POINTS ON THE CAN BACKBONE. REFER TO THE G3X INSTALL MANUAL FOR USAGE OF THIS PART AND SPECIFIC GUIDANCE OF THE G3X CAN BUS WIRING.
190-01115-01 Rev. K
Figure B-3.1 GAP 26 Outline Drawing
G3X Installation Manual - Outline & Installation Drawings Page B-7
190-01115-01 Rev. K
A
A
.821 20.84
10.180±.250 258.57±6.35
6.12 155.40
.790 20.07
PITOT
AOA 13.130 333.50
13.480±.25 342.39±6.35
15.995 406.27
UNLESS OTHERWISE STATED: 1. INTERPRET PER ASME Y14.5M-1994. 2. DIMENSIONS: INCHES [mm] DIMENSIONS IN BRACKETS ARE FOR REFERENCE ONLY.
SECTION A-A
190-01115-01 Rev. K
Figure B-4.1 GDU 37X Outline Drawing
G3X Installation Manual - Outline & Installation Drawings Page B-8
2X 1.72 43.7
.004
0.1
FRONT SURFACE OF PANEL
3.89
98.7
#6-32 CAPTIVE
3.41
SCREW (4 PLCS)
[86.7]
7.83 198.8
.28 7.2 .93 23.7
4.50 114.4
5.47 139.1
2.98 75.8
6.04 153.4
1.09 27.7
.59 15.0
1.08 27.5
NOTES: 1. DIMENSIONS: INCHES[MM] 2. DIMENSIONS ARE SHOWN FOR REFERENCE ONLY.
1.92 48.7
3.41 86.7
.29 7.3
2X 2.34 59.4
XM CONN.
7.25 184.2 GPS CONN.
190-01115-01 Rev. K
DIMENSIONS SHOWN FOR REFERENCE ONLY.
Figure B-4.2 GDU 37X Outline Drawing
G3X Installation Manual - Outline & Installation Drawings Page B-9
190-01115-01 Rev. K
Figure B-5.1 GEA 24 Outline Drawing
G3X Installation Manual - Outline & Installation Drawings Page B-10
2X 0.20 5.1
2X 6.40 162.6
3.4 86 CENTER OF GRAVITY
6.80 172.7
2.00 50.8 2X 0.42 10.7
NOTE: 1. DIMENSION: INCHES[mm]. METRIC VALUES ARE FOR REFERENCE ONLY. 2. DIMENSIONS ARE NOMINAL AND TOLERANCES ARE NOT IMPLIED UNLESS SPECIFICALLY STATED
4.98 126.6
2.94 74.7 0.2 4
CENTER OF GRAVITY
0.04 1 TYPICAL THICKNESS BENEATH FASTENER HEAD
2.00 50.8
1.1 27 CENTER OF
GRAVITY
GEA 24 UNIT 011-02848-00 GEA 24 CONNECTOR KIT 011-02886-00
Figure B-5.2 GEA 24 Assembly Drawing (no CAN terminator)
190-01115-01 Rev. K
G3X Installation Manual - Outline & Installation Drawings Page B-11
Figure B-5.3 GEA 24 Assembly Drawing (with CAN terminator)
G3X Installation Manual - Outline & Installation Drawings Page B-12
GEA 24 UNIT 011-02848-00
GEA 24 CONNECTOR KIT 011-02886-00
(OPTIONAL) GEA 24 CAN TERMINATION KIT 011-02887-00
IMPORTANT NOTE: DEPENDING ON HOW THE SYSTEM IS PHYSICALLY WIRED, THIS ADAPTER MAY OR MAY NOT BE NEEDED IN THE INSTALLATION. THE G3X CAN BUS MUST BE TERMINATED AT ONLY THE TWO MOST EXTREME POINTS ON THE CAN BACKBONE. REFER TO THE G3X INSTALL MANUAL FOR USAGE OF THIS PART AND SPECIFIC GUIDANCE OF G3X CAN BUS WIRING.
190-01115-01 Rev. K
Figure B-6.1 GMC 305 Outline Drawing
G3X Installation Manual - Outline & Installation Drawings Page B-13
190-01115-01 Rev. K
5.34 135.6 .86 21.8
3.31 84.0 1.27 32.2
.46 11.6 TYP.
6.25 158.8
FRONT SURFACE OF AIRCRAFT PANEL
.51 13.0
1.85 47.0
.34 8.6
NOTES: 1. DIMENSIONS: INCHES[mm]. METRIC VALUES ARE FOR REFERENCE ONLY. 2. DIMENSIONS ARE NOMINAL AND TOLERANCES ARE NOT IMPLIED UNLESS SPECIFICALLY STATED.
.080 2.03 TYP.
1.24 31.4 1.69 42.9
Figure B-6.2 GMC 305 Installation Drawing
G3X Installation Manual - Outline & Installation Drawings Page B-14
AIRCRAFT PANEL (REF.)
4X 210-00104-04 SUPPLIED WITH 010-12034-00 INSTALLATION KIT
CONNECTOR KIT SUPPLIED WITH 010-12034-00 INSTALLATION KIT
4X 211-00169-01 SUPPLIED WITH 010-12034-00 INSTALLATION KIT
GMC 305 UNIT 011-03226-XX
190-01115-01 Rev. K
Figure B-6.3 GMC 305 Cutout Drawing (Not to Scale)
G3X Installation Manual - Outline & Installation Drawings Page B-15
190-01115-01 Rev. K
.925 23.50 .865 21.97 2X .660 16.76
0 0.00
2X .660 16.76 .865 21.97 .925 23.50
3.125 79.38 6X 2.860 72.64
2.690 68.33 0 0.00
2.690 68.33 6X 2.860 72.64
3.125 79.38
GMC 305 PANEL CUTOUT
5.380 136.65
1.730 43.94
4X R.065 1.65 MAX.
4X .150 3.81 4X .218 5.54
4X .219 5.56 8X .098 THRU
.176 4.47 X 100°
NOTES:
1. DIMENSIONS: INCHES [mm]
2. TOLERANCES: INCH
mm
.XX±.02
.X±0.5
.XXX±.010 .XX±0.25
Figure B-7.1 GMU 22 Mounting Rack
G3X Installation Manual - Outline & Installation Drawings Page B-16
GMU 22 MOUNTING RACK 115-00481-00
3.370 85.60 2.520 64.01
AIRCRAFT MOUNTING HOLES FOR
115-00481-00
3X .213 5.41 OPTIONAL CLEARANCE HOLES FOR HOLD-DOWN SCREWS
TOLERANCES
INCHES
mm
.XX 0.010 .X 0.25
.XXX 0.005 .XX 0.13
3X .164 4.17 THRU (IN THIN MATERIAL, USING LOCKING NUTS) OR DRILL AND TAP #6-32 UNC IN MATERIAL THICKER THAN 3/16 [4.8]
2.175 55.25
2X 1.485 37.72 .725 18.42
120°
FORWARD
120°
0
2.51 63.75 2.49 63.25
.795 20.19
.061 1.54 0
1.256 31.90 2.511 63.79 2.572 65.33
NOTE: 1. DIMENSIONS: INCHES [mm]. METRIC VALUES ARE FOR REFERENCE ONLY. 2. FOLLOW "FORWARD" AND "TOP" INDICATIONS ON UNIT AND RACK.
190-01115-01 Rev. K
Figure B-7.2 GMU 22 Top Mounted Installation
G3X Installation Manual - Outline & Installation Drawings Page B-17
190-01115-01 Rev. K
GMU 22 INSTALLATION FROM ABOVE (PREFERRED)
GMU 44
16.2 412
3.37 85.60
.3 8
AIRCRAFT MOUNTING SURFACE
2.38 60.33
115-00481-00 OR 115-00481-10 AIRCRAFT
MOUNTING RACK (-00 IS SHOWN)
2.10 53.34 1.84 46.61
#6-32 PAN HEAD BRASS SCREWS 0.24 [6.1] MAX THREAD LENGTH WITHOUT CLEARANCE HOLES (211-60037-08 SUPPLIED WITH 011-00871-00 GMU 22 CONNECTOR KIT)
#6-32 100 FLAT HEAD BRASS SCREWS REQUIRED
NOTES: 1. DIMENSIONS: INCHES [mm]. METRIC VALUES ARE FOR
REFERENCE ONLY. 2. DIMENSIONS ARE NOMINAL AND TOLERANCES ARE
NOT IMPLIED UNLESS SPECIFICALLY STATED.
190-01115-01 Rev. K
Figure B-7.3 GMU 22 Bottom Mounted Installation
G3X Installation Manual - Outline & Installation Drawings Page B-18
GMU 22 INSTALLATION FROM BELOW
(NOT PREFERRED)
115-00481-00 OR 115-00481-10
AIRCRAFT MOUNTING RACK
(-00 IS SHOWN)
16.2 412
3.370 85.60
.3 8
2.38 60.33
AIRCRAFT MOUNTING SURFACE
GMU 44
2.23 56.52
#6-32 PAN HEAD BRASS SCREWS 0.24 [6.1] MAX THREAD LENGTH WITHOUT CLEARANCE HOLES (211-60037-08 SUPPLIED WITH 011-00871-00 GMU 22 CONNECTOR KIT)
#6-32 100 FLAT HEAD BRASS SCREWS REQUIRED
NOTES: 1. DIMENSIONS: INCHES [mm]. METRIC VALUES ARE FOR
REFERENCE ONLY. 2. DIMENSIONS ARE NOMINAL AND TOLERANCES ARE
NOT IMPLIED UNLESS SPECIFICALLY STATED.
190-01115-01 Rev. K
NOTE: 1. BUBBLE NUMBERS IN THIS DRAWING REFER TO
REFERENCE NUMBERS LISTED IN TABLES 3-8 AND 3-9.
Figure B-7.4 GMU 22 Wiring Details
G3X Installation Manual - Outline & Installation Drawings Page B-19
Figure B-8.1 GSU 25 Outline Drawing
G3X Installation Manual - Outline & Installation Drawings Page B-20
.299 7.59
3.400 86.36
.249 6.32
2.1 53
3.500 88.90
.249 6.32
2.000 50.80
4x .209 5.32 SEE NOTE 4
2.61 66.2
1.52 38.6
1.0 25
4.00 101.5
.9 24
2.50 63.4
NOTES: 1. DIMENSIONS: INCHES [mm]. METRIC VALUES ARE FOR REFERENCE ONLY. 2. DIMENSIONS ARE NOMINAL AND TOLERANCES ARE NOT IMPLIED UNLESS SPECIFICALLY STATED. 3. CENTER OF GRAVITYLOCATION INCLUDES UNIT WITH CONNECTOR KITS. 4. THE GSU25 MOUNTING HOLES HAVE AN OFFSET SPACING PATTERN. THE DIFFERENCE PREVENTS THE
UNIT FROM BEING RE-INSTALLED IN THE WRONG ORIENTATION.
2.12 53.9
190-01115-01 Rev. K
190-01115-01 Rev. K
CAN TERMINATOR KIT 011-02887-00
IMPORTANT NOTE:
GSU25 WITH CONNECTOR KITS AND HARDWARE
GSU 25 UNIT
Figure B-8.2 GSU 25 Installation Drawing
G3X Installation Manual - Outline & Installation Drawings Page B-21
GSU 25 CONNECTOR KIT, 9 PIN 011-03002-00
GSU 25 CONNECTOR KIT, 15 PIN, W/ HDWR 011-03002-01
GSU 25 POSSIBLE ORIENTATIONS
Figure B-8.3 GSU 25 Orientation Drawings (page 1 of 2)
G3X Installation Manual - Outline & Installation Drawings Page B-22
190-01115-01 Rev. K
190-01115-01 Rev. K
GSU 25 POSSIBLE ORIENTATIONS
Figure B-8.4 GSU 25 Orientation Drawings (page 2 of 2)
G3X Installation Manual - Outline & Installation Drawings Page B-23
Figure B-9.1 GSU 73 Outline Drawing
G3X Installation Manual - Outline & Installation Drawings Page B-24
2X .25 6.4 .65 16.6
4.25 108.0
2X 5.00 127.0 2.8 71
.40 10.2
4.50 114.3
P732 CONNECTOR KIT 011-01818-01
CONFIGURATION MODULE KIT (NOT SHOWN) 011-00979-20
THERMOCOUPLE KIT (NOT SHOWN) 011-00981-00
4X .210 5.33 SEE NOTE 3
PITOT AIR FITTING 1/8-27 ANPT FEMALE THREAD
1.96 49.8 STATIC AIR FITTING 1/8-27 ANPT FEMALE THREAD
.87 22.1
2X 1.17 29.7
4.46 113.2 5.50 139.7
P732
P731 TYP 3.96 100.6
NOTES: 1. DIMENSIONS: INCHES[mm]. 2. DIMENSIONS ARE SHOWN FOR REFERENCE ONLY. 3. MOUNTING HOLES FOR #10 PAN HEAD OR HEX HEAD FASTENERS. 4. CENTER OF GRAVITY LOCATION INCLUDES UNIT WITH CONNECTOR KITS.
P731 CONNECTOR KIT 011-01818-00
GSU 73 UNIT 011-01817-00
1.45 36.7
3.2 81 2X 5.50 139.8 2X 7.33 186.2
1.8 46
190-01115-01 Rev. K
GSU 73 POSSIBLE ORIENTATIONS
190-01115-01 Rev. K
Figure B-9.2 GSU 73 Orientation Drawings
G3X Installation Manual - Outline & Installation Drawings Page B-25
1.57 .57
.050 SEE NOTE 2
0 .50
Figure B-10.1 GTP 59 O.A. T. Probe Installation Drawing
G3X Installation Manual - Outline & Installation Drawings Page B-26
.03 x 45 CHAMFER
.02 x 45 CHAMFER
.255
5/16 - 32 UNEF-2A
.563
+.000 -.012
SEE NOTE 3
NOTES: 1. DIMENSIONS: INCHES 2. MAX HEIGHT OF INCOMPLETE THREAD: 0.050 3. CABLE: M27500-22TE3V14. CABLE LENGTH TO BE 10 FEET 6 INCHES 4. 16 AWG WIRE: M22759/16-16. LENGTH OF WIRE OUTSIDE OF CASE TO BE 3.5 INCHES +0.25, -0. 5. SOLDER TERMINAL: MS25036-109 6. SHIELD OF CABLE ELECTRICALLY CONNECTED TO 16 AWG WIRE. 7. BUBBLE NUMBERS IN THIS DRAWING REFER TO REFERENCE NUMBERS LISTED IN TABLE 5-5.
SEE NOTE 4
190-01115-01 Rev. K
APPENDIX C G3X W/GSU 25 AND/OR GAD 29 INTERCONNECT DRAWINGS C.1 Core Interconnect Drawings w/GSU 25 and/or GAD 29
NOTES:
1. UNLESS OTHERWISE NOTED, ALL STRANDED WIRE MUST CONFORM TO MIL-W-22759/16 OR EQUIVALENT 2. UNLESS OTHERWISE NOTED, ALL SHIELDED WIRE MUST CONFORM TO MIL-C-27500 OR EQUIVALENT 3. UNLESS OTHERWISE NOTED, ALL WIRES ARE 24 GAUGE MINIMUM 4. SYMBOL DESIGNATIONS:
TWISTED SHIELDED SINGLE CONDUCTOR SHIELD TERMINATED TO GROUND
TWISTED SHIELDED SINGLE CONDUCTOR SHIELD FLOATS
TWISTED SHIELDED 4 CONDUCTOR SHIELD TERMINATED TO GROUND
W HT TWISTED SHIELDED PAIR BLU SHIELD TERMINATED TO GROUND
W HT TWISTED SHIELDED PAIR BLU SHIELD FLOATS
W HT BLU ORN
TWISTED SHIELDED 3 CONDUCTOR SHIELD TERMINATED TO GROUND
TWISTED SHIELDED 4 CONDUCTOR SHIELD FLOATS
AIRCRAFT GROUND
GARMIN SHIELD BLOCK GROUND
S
(REFER TO 190-00313-09)
WIRE SPLICE CONNECTION
W HT BLU ORN
TWISTED SHIELDED 3 CONDUCTOR SHIELD FLOATS
COAXIAL CABLE N/C = NO CONNECTION
5. UNLESS OTHERWISE NOTED, ALL SHIELD GROUNDS MUST BE MADE TO THE RESPECTIVE UNIT BACKSHELLS. ALL OTHER GROUNDS SHOULD BE TERMINATED TO AIRCRAFT GROUND AS CLOSE TO THE RESPECTIVE UNIT AS POSSIBLE.
6. WIRE COLORS ARE NOTED FOR ADVISORY PURPOSES ONLY, EXCEPT FOR THE CONFIG MODULE AND GTP 59.
7. N/A
8. INSTALLATION INFORMATION IS PROVIDED FOR CONFIGURATION MODULES AND THERMOCOUPLES IN SECTION 2, FOR GMU 22 IN SECTION 8, AND FOR THE GTP 59 IN SECTION 12.
9. IN A 2 DISPLAY INSTALLATION, THE SECOND DISPLAY CAN BE CONNECTED AS SHOWN. 10. OPTIONAL INTERFACE.
11. THE GDU 37X CAN BE CONFIGURED TO ACCEPT A 14V OR 28V LIGHTING BUS INPUT (SEE SECTION 17 FOR CONFIGURATION).
12. ONLY ONE GDU 37X GPS ANTENNA CONNECTION IS REQUIRED FOR THE G3X SYSTEM. ADDITIONAL ANTENNAS CAN BE ADDED FOR REDUNDANCY IF DESIRED, SEE SECTION 17 FOR GPS CONFIGURAITON INFORMATION.
13. IN A 2 DISPLAY SYSTEM WHERE A GDU IS USED AS A CAN BUS TERMINATION, THE CAN BUS SHOULD ONLY BE TERMINATED AT ONE GDU 37X. 14. TO MINIMIZE THE CHANCE OF THE SYSTEM RESETTING DURING ENGINE CRANKING, THE OPTIONAL REDUNDANT (DIODE OR'D) POWER INPUTS MAY BE
CONNECTED TO AN AUXILIARY BATTERY (SUCH AS THE TCW TECHNOLOGIES INTEGRATED BACK-UP BATTERY SYSTEM) OR STABILIZED POWER INPUT (SUCH AS THE TCW TECHNOLOGIES INTELLIGENT POWER STABILIZER IPS-12V-8A) TO MAINTAIN THE NECESSARY LRU MINIMUM INPUT VOLTAGE. HAVING A STABILIZED SOURCE OF POWER DURING ENGINE CRANKING SHOULD ALLOW THE SYSTEM TO PROVIDE CONTINUOUS ENGINE INDICATING SYSTEM (EIS) OPERATION DURING ENGINE START AND MAINTAIN ANY DESIRED PRE-FLIGHT SYSTEM SETUP OR FLIGHT PLANNING THAT WAS ACCOMPLISHED PRIOR TO ENGINE START. VISIT WWW.TCWTECH.COM FOR ADDITIONAL DETAILS. 15. THE DISCRETE OUTPUT FROM THE TCW BBS CAN BE WIRED TO A DISCRETE INPUT ON THE GEA 24 TO PROVIDE THE PILOT WITH AN ANNUNCIATION WHEN THE BACK-UP BATTERY IS BEING UTILIZED. SEE THE G3X INSTALLATION MANUAL FOR MORE INFORMATION ON CONFIGURATION OF GEA 24 DISCRETE INPUTS.
SEE NOTE 9
P3701 GDU 37X (PFD #1)
CAN BUS TERMINATION AT GAD 29, GEA 24, GSA 25, OR GSU 25 SEE SECTION 2.3.1.3
SEE NOTE 13
49 CONFIG MODULE GROUND 17 CONFIG MODULE POWER 50 CONFIG MODULE DATA 33 CONFIG MODULE CLOCK
CAN BUS HI CAN BUS LO
WHT BLU
WHT BLU
46 CAN BUS HI 45 CAN BUS LO 28 CAN BUS TERMINATION
WHT BLU
WHT BLU
P3701
OPTIONAL GDU 37X (MFD)
46 CAN BUS HI
45 CAN BUS LO
28 CAN BUS TERMINATION
Figure C-1.1 Core Interconnect Notes and 2 Display CAN Bus Interconnect Drawing
190-01115-01 G3X Installation Manual - G3X w/GSU 25 and/or GAD 29 Interconnect Drawings
Rev. K
Page C-1
Figure C-1.2 GDU 37X/GMU 22/GSU 25 Interconnect Drawing
G3X Installation Manual - G3X w/GSU 25 and/or GAD 29 Interconnect Drawings 190-01115-01
Page C-2
Rev. K
GAD 29, GEA 24, GMC 305, OR GSU 25
P291 P241P3051P251
(GAD 29) (GEA 24)(GMC 305) (GSU 25)
5
15
GEA 24
P244
GAD 29, GEA 24, GMC 305, OR GSU 25
Figure C-1.3 Power, Backup Power, and Antennas Interconnect Drawing
190-01115-01 G3X Installation Manual - G3X w/GSU 25 and/or GAD 29 Interconnect Drawings
Rev. K
Page C-3
WHT BLU ORN
WHT BLU ORN
14/28 VDC
NOTE: THIS RS-232 CHANNEL USED FOR OPTIONAL BACKUP BUS TO DISPLAY FOR ADAHRS #1 AND #2. FOR ADAHRS #3, INSTALL JUMPER BETWEEN PIN 4 AND 5
CONFIGURATION GUIDANCE 1. G3X
A. ON THE GDU 37X CONFIG MODE LRU EQUIPMENT CONFIGURATION PAGE ENABLE ADAHRS 1, 2, OR 3 AS APPROPRIATE FOR THIS UNIT ENABLE MAGNETOMETER FOR THIS UNIT IF CONNECTED ENABLE OAT PROBE FOR THIS UNIT IF CONNECTED ENABLE AOA FOR THIS UNIT IF CONNECTED TO GAP 26 PROBE
Figure C-1.4 GMU 22/GSU 25/GTP 59 Interconnect Drawing
G3X Installation Manual - G3X w/GSU 25 and/or GAD 29 Interconnect Drawings 190-01115-01
Page C-4
Rev. K
SERVO POWER
SERVO POWER GND
9
TO ROLL TRIM MOTOR TO ROLL TRIM MOTOR
TO PITCH TRIM MOTOR TO PITCH TRIM MOTOR
TO YAW TRIM SWITCH TO YAW TRIM SWITCH TO YAW TRIM MOTOR TO YAW TRIM MOTOR
CONFIGURATION GUIDANCE 1. G3X
A. ON THE GDU 37X CONFIG MODE COM PORT CONFIGURATION PAGE SET COM PORT CONNECTED TO GMC 305 TO "GARMIN INSTRUMENT DATA"
B. ON THE GDU 37X CONFIG MODE LRU EQUIPMENT CONFIGURATION PAGE SET AUTOPILOT SERVOS TO ONE OF THE FOLLOWING: "ROLL ONLY", "PITCH + ROLL", OR "PITCH + YAW"
Figure C-1.5 GMC 305/GSA 28 Interconnect Drawing
190-01115-01 G3X Installation Manual - G3X w/GSU 25 and/or GAD 29 Interconnect Drawings
Rev. K
Page C-5
SINGLE TRIM SWITCH
GSA 28 TRIM IN 1
P281 11
TRIM IN 2
12
DPDT MOMENTARY CENTER OFF, 2A
TRIM OUT 1 13
S
M TRIM MOTOR
TRIM OUT 2 14
12 VDC
DUAL TRIM SWITCHES
GSA 28
P281
TRIM IN 1 11
TRIM IN 2 12
TRIM OUT 1 13
TRIM OUT 2 14
M TRIM MOTOR
3RD PARTY TRIM MIXING DEVICE
(DISABLE SPEED CONTROL IF EQUIPPED)
TO TRIM SWITCH #1
USE SWITCHES AS REQUIRED BY 3RD PARTY TRIM MIXING DEVICE INSTALLATION INSTRUCTIONS
TO TRIM SWITCH #2
Figure C-1.6 GSA 28 - Trim Switch Interconnect Drawing
G3X Installation Manual - G3X w/GSU 25 and/or GAD 29 Interconnect Drawings 190-01115-01
Page C-6
Rev. K
C.2 External Interconnect Drawings w/GSU 25
NOTES:
1. UNLESS OTHERWISE NOTED, ALL STRANDED WIRE MUST CONFORM TO MIL-W-22759/16 OR EQUIVALENT 2. UNLESS OTHERWISE NOTED, ALL SHIELDED WIRE MUST CONFORM TO MIL-C-27500 OR EQUIVALENT 3. UNLESS OTHERWISE NOTED, ALL WIRES ARE 24 GAUGE MINIMUM 4. SYMBOL DESIGNATIONS:
TWISTED SHIELDED SINGLE CONDUCTOR SHIELD TERMINATED TO GROUND
TWISTED SHIELDED SINGLE CONDUCTOR SHIELD FLOATS
TWISTED SHIELDED 4 CONDUCTOR SHIELD TERMINATED TO GROUND
W HT TWISTED SHIELDED PAIR BLU SHIELD TERMINATED TO GROUND
W HT TWISTED SHIELDED PAIR BLU SHIELD FLOATS
W HT BLU ORN
TWISTED SHIELDED 3 CONDUCTOR SHIELD TERMINATED TO GROUND
TWISTED SHIELDED 4 CONDUCTOR SHIELD FLOATS
AIRCRAFT GROUND
GARMIN SHIELD BLOCK GROUND
S
(REFER TO 190-00313-09)
WIRE SPLICE CONNECTION
W HT BLU ORN
TWISTED SHIELDED 3 CONDUCTOR SHIELD FLOATS
COAXIAL CABLE N/C = NO CONNECTION
5. UNLESS OTHERWISE NOTED, ALL SHIELD GROUNDS MUST BE MADE TO THE RESPECTIVE UNIT BACKSHELLS. ALL OTHER GROUNDS SHOULD BE TERMINATED TO AIRCRAFT GROUND AS CLOSE TO THE RESPECTIVE UNIT AS POSSIBLE.
6. RS-232 CHANNEL ASSIGNMENTS ARE SHOWN FOR REFERENCE ONLY. CONNECTIONS CAN BE REASSIGNED TO DIFFERENT CHANNELS OR TO CHANNELS ON AN OPTIONAL SECOND OR THIRD DISPLAY. RS-232 INPUT/OUTPUT LINES SHOULD ONLY BE CONNECTED TO ONE DEVICE AT A TIME. SEE THE G3X INSTALLATION MANUAL FOR RS-232 INPUT/OUTPUT CONFIGURATION GUIDANCE.
7. N/A
8. CONNECTIONS FOR THIRD PARTY AUTOPILOT SERVOS, AP DISCONNECT, AND OTHER AUTOPILOT FUNCTIONALITY NOT SHOWN. CONSULT AUTOPILOT VENDOR DOCUMENTATION FOR ADDITIONAL DETAILS.
9. REFER TO FIG. C-2.11 FOR MORE DETAILED INFORMATION ON CONNECTION OF THIRD PARTY AUTOPILOTS.
10. THE GSU 25 PROVIDES AIR DATA AND GPS INFORMATION TO THE GTX SO NO SEPARATE ALTITUDE ENCODER IS REQUIRED. THE GTX INPUT SHOULD BE CONFIGURED FOR REMOTE.
11. OPTIONAL INTERFACE.
12. THE GMA 240 IS SHOWN HERE FOR REFERENCE ONLY. OTHER INTERCOM/AUDIO PANEL PRODUCTS MAY BE COMPATIBLE WITH THE GDU 37X. THE ALERTS GENERATED BY THE GDU 37X CAN BE CONFIGURED TO TRANSMIT ON MONO AND STEREO AUDIO LINES OR MONO ONLY. SEE THE G3X INSTALLATION MANUAL FOR ADDITIONAL DETAILS ON CONFIGURATION OF THE GDU 37X ALERT OUTPUS.
13. INSTALLING THE CROSS-TALK CONNECTION WILL ALLOW FLIGHT PLAN SHARING BETWEEN TWO GNS 430(W)/530(W) UNITS (VIA RS-232) OR TWO GNS 6XX/7XX UNITS (VIA ETHERNET). THE G3X SYSTEM ALWAYS DISPLAYS FLIGHT PLAN INFORMATION FROM THE ACTIVE NAV SOURCE.
14. ARINC 429 OUT 2 CAN BE OPTIONALLY CONNECTED TO A GNS 400/500 SERIES UNIT FOR DISPLAY OF TIS-A. THE G3X SYSTEM WILL CONFIGURE REMOTE MOUNT GARMIN TRANSPONDERS ARINC 429 OUT 1 FOR LOW SPEED TIS DATA AND ARINC 429 OUT 2 FOR HIGH SPEED TIS DATA BY DEFAULT. GNS 400/500 SERIES UNITS REQUIRE THE DATA TO BE HIGH SPEED. PANEL MOUNT TRANSPONDERS MUST BE CONFIGURED MANUALLY.
15. A 14 CFR 91.227 CFR COMPLIANT INSTALLATION REQUIRES RS-232 ADS-B OUT FROM A GNS 400/500 SERIES WAAS UNIT WITH MAIN SOFTWARE VERSION 3.20 (OR LATER), OR A GTN 600/700 SERIES UNIT SOFTWARE VERSION 3.00 (OR LATER) TO SUPPORT ADS-B TRANSMISSIONS. FOR VFR AIRCRAFT, NON-COMPLIANT ADS-B OUT IS PROVIDED BY THE VFR GPS DATA SENT AUTOMATICALLY TO THE GTX 23ES. IF ADS-B TRANSMISSION FROM THE GTX 23ES IS NOT REQUIRED, THIS CONNECTION IS NOT REQUIRED.
16. THE GTN 6XX/7XX UNITS RECEIVE ALTITUDE ENCODER DATA FROM THE GAD 29 VIA ARINC 429 AND RELAY THAT DATA TO THE TRANSPONDER. IF TWO GTN 6XX/7XX UNITS ARE INSTALLED, RS-232 CHANNEL 2 TRANSMIT AND RECEIVE ON THE TRANSPONDER COULD BE CONNECTED TO THE SECOND GTN INSTEAD OF THE GDU 37X AND GAD 29 IF DESIRED. NOTE THIS CONFIGURATION WOULD REQUIRE AT LEAST ONE GTN UNIT TO BE OPERATING IN ORDER FOR THE TRANSPONDER TO RECEIVE PRESSURE ALTITUDE DATA.
Figure C-2.1 External Interconnect Drawing Notes
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NOTE: THIS INTERFACE EXAMPLE DRAWING IS NOT SUFFICIENT FOR INSTALLATION OF AN SL30 OR SL40. CONTACT A LOCAL GARMIN AVIONICS DEALER FOR COMPLETE INSTALLATION INFORMATION.
THIRD PARTY AUTOPILOT
SL30/GNC 255
SL30 GNC 37 PIN 255 CONN P2001
SL40 GTR GTR
SL40/GTR
200/GTR
225
15 PIN CONN
200 P2001
225 P2001
24 NA
CONFIGURATION GUIDANCE 1. GDU 37X TO SL40, GTR 200, OR GTR 225
A. ON THE GDU 37X COMM CONFIG MODE PAGE · SET CONNECTED GDU 37X RS-232 CHANNEL FORMAT TO "GARMIN VHF COMM"
B. NO GTR 200 OR SL40 CONFIGURATION REQUIRED C. CONFIGURE GTR 225 RS-232 FORMAT TO "NMEA"
2. GDU 37X TO SL30 OR GNC 255
A. ON THE GDU 37X COMM CONFIG MODE PAGE · SET CONNECTED GDU 37X RS-232 CHANNEL FORMAT TO "GARMIN VHF COMM"
B. NO SL30 CONFIGURATION REQUIRED
C. CONFIGURE GNC 255 RS-232 FORMAT TO "NMEA"
3. GDU 37X TO VERTICAL POWER VP-X OR VP-200
A. ON THE GDU 37X COMM CONFIG MODE PAGE
· SET CONNECTED GDU 37X RS-232 CHANNEL FORMAT TO "VERTICAL POWER"
B. ON THE GDU 37X EIS CONFIG MODE PAGE
· SET THE "VOLTS 1" AND "VOLTS 2" INPUTS TO ONE OF THE FOLLOWING BASED ON WHAT INPUTS
HAVE BEEN CONNECTED TO THE VP-X OR VP-200:
NONE
VERTICAL POWER MAIN BATT VOLTS
VERTICAL POWER AUX BATT VOLTS
VERTICAL POWER BUS 1 VOLTS
VERTICAL POWER BUS 2 VOLTS
· SET THE "SHUNT 1" AND "SHUNT 2" INPUTS TO ONE OF THE FOLLOWING BASED ON WHAT INPUTS
HAVE BEEN CONNECTED TO THE VP-X OR VP-200:
NONE
VERTICAL POWER MAIN BUS AMPS
VERTICAL POWER BUS 1 AMPS
VERTICAL POWER BUS 2 AMPS
C. REFERENCE VERTICAL POWER DOCUMENTATION FOR ADDITIONAL INSTALLATION AND CONFIGURATION
GUIDANCE
Figure C-2.2 GDU 37X - External LRU Interconnect Examples
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CONFIGURATION GUIDANCE 1. GNS 4XX/5XX OR GTN 6XX/7XX PROVIDING ADS-B POSITION SOURCE DATA (OPTIONAL)
A. ON THE GNS OR GTN UNIT, CONFIGURE THE RS-232 OUTPUT PROVIDING THIS
DATA TO "ADS-B OUT" ("ADS-B OUT+ IF AVAILABLE)
Figure C-2.3 GSU 25 - GTX 23ES Transponder Interconnect/Configuration Example
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GSU 25 ADAHRS 1 ONLY
CONFIGURATION GUIDANCE 1. GTX 327/328/330(ES)
A.ON THE GTX 327/328/330(ES) RS-232 CONFIG MODE PAGE FOR RS-232 CHANNEL 1 · SET CONNECTED GTX 327/328/330(ES) RS-232 CHANNEL 1 INPUT FORMAT TO "REMOTE" · SET CONNECTED GTX 330(ES) RS-232 CHANNEL 1 OUTPUT FORMAT TO "REMOTE+TIS"
B. ON THE GTX 330(ES) RS-232 CONFIG MODE PAGE FOR RS-232 CHANNEL 2 · SET RS-232 CHANNEL 2 INPUT FORMAT TO "REMOTE"
C. ON THE GTX 327/328/330(ES) SQUAT SWITCH CONFIG MODE PAGE · SET THE SQUAT SWITCH FIELD TO "NO"
D.IF REMOTE CONTROL OF THE TRANSPONDER FROM THE GDU 37X IS DESIRED · ON THE GDU 37X XPDR CONFIG MODE PAGE SET TRANSPONDER TYPE TO "GTX 327" OR "GTX 328" OR "GTX 330" OR "GTX 330ES" OR "GTX 33" AS APPROPRIATE
E.NO GSU 25 CONFIGURATION REQUIRED
2. GTX 33(ES) A.ON THE GDU 37X XPDR CONFIG MODE PAGE · SET TRANSPONDER TYPE TO "GTX 33" OR "GTX 33ES" AS APPROPRIATE B. NO GSU 25 CONFIGURATION REQUIRED
3. GTN 6XX/7XX, GNS 4XXW/5XXW (WHEN ADS-B OUT IS BEING PROVIDED TO ES TRANSPONDER) A.ON THE GTN/GNS RS-232 CONFIG MODE PAGE · SET RS-232 OUTPUT FORMAT TO ADS-B OUT(+) (FOR RS-232 PORT CONNECTED TO TRANSPONDER RS-232 IN CHANNEL 2)
Figure C-2.4 GSU 25 - Transponder Interconnect/Configuration Example
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GSU 25
CONFIGURATION GUIDANCE (IN THIS CONFIGURATION THE TRANSPONDER IS CONTROLLED BY THE GTN 6XX/7XX UNIT (NOT CONTROLLED BY THE G3X DISPLAY) 1. GTX 32
A.ON THE GTN 6XX/7XX RS-232 CONFIG PAGE · SET RS-232 CHANNEL 1 INPUT AND OUTPUT FORMATS TO "GTX MODE C #1"
B. ON THE GTN 6XX/7XX XPDR1 CONFIG PAGE · SET RS-232 CHANNEL 1 INPUT AND OUTPUT FORMATS TO "REMOTE" · SET RS-232 CHANNEL 2 INPUT FORMAT TO "REMOTE"
C.ON THE GDU 37X XPDR CONFIG MODE PAGE · SET THE TRANSPONDER TYPE TO "NONE"
D.NO GDU 37X OR GSU 25 CONFIGURATION REQUIRED
2. GTX 327 A.ON THE GTN 6XX/7XX RS-232 CONFIG PAGE · SET RS-232 CHANNEL 1 INPUT FORMAT TO "ALTITUDE FORMAT 1" · SET RS-232 CHANNEL 1 OUTPUT FORMAT TO "AVIATION OUTPUT 1" B. ON THE GTX 327 RS-232 CONFIG PAGE · SET RS-232 CHANNEL 1 INPUT FORMAT TO "GPS" · SET RS-232 CHANNEL 1 OUTPUT FORMAT TO "ICARUS ALT" · SET RS-232 CHANNEL 2 INPUT FORMAT TO "REMOTE" C.ON THE GDU 37X XPDR CONFIG PAGE · SET THE TRANSPONDER TYPE TO "NONE" D.NO GSU 25 CONFIGURATION REQUIRED
3. GTX 33(ES) A.ON THE GTN 6XX/7XX RS-232 CONFIG PAGE · SET RS-232 CHANNEL 1 INPUT AND OUTPUT FORMATS TO "GTX w/TIS #1" B. ON THE GTN 6XX/7XX XPDR1 CONFIG PAGE · SET RS-232 CHANNEL 1 INPUT FORMAT TO "REMOTE" · SET RS-232 CHANNEL 1 OUTPUT FORMAT TO "REMOTE w/TIS" · SET RS-232 CHANNEL 2 INPUT FORMAT TO "REMOTE" · SET RS-232 CHANNEL 2 OUTPUT FORMAT TO "REMOTE w/TIS" C.ON THE GDU 37X RS-232 CONFIG PAGE · SET THE CONNECTED RS-232 CHANNEL FORMAT TO "TIS IN" · SET THE CONNECTED RS-232 CHANNEL FORMAT TO "TIS_A IN" IF TIS-A TRAFFIC DATA IS DESIRED.
D.ON THE GDU 37X XPDR CONFIG MODE PAGE · SET THE TRANSPONDER TYPE TO "NONE"
E. NO GSU 25 CONFIGURATION REQUIRED
4. GTX 330(ES) A.ON THE GTN 6XX/7XX RS-232 CONFIG PAGE · SET RS-232 CHANNEL 1 INPUT AND OUTPUT FORMATS TO "PANEL GTX w/TIS #1" B. ON THE GTX 330 RS-232 CONFIG PAGE · SET RS-232 CHANNEL 1 INPUT FORMAT TO "REMOTE" · SET RS-232 CHANNEL 1 OUTPUT FORMAT TO "REMOTE+TIS" · SET RS-232 CHANNEL 2 INPUT FORMAT TO "REMOTE" · SET RS-232 CHANNEL 2 OUTPUT FORMAT TO "REMOTE+TIS" C.ON THE GDU 37X RS-232 CONFIG PAGE · SET THE CONNECTED RS-232 CHANNEL FORMAT TO "TIS IN" · SET THE CONNECTED RS-232 CHANNEL FORMAT TO "TIS_A IN" IF TIS-A TRAFFIC DATA IS DESIRED.
D.ON THE GDU 37X XPDR CONFIG PAGE · SET THE TRANSPONDER TYPE TO "NONE"
E. NO GSU 25 CONFIGURATION REQUIRED
5. GTX 23ES A. THE GTX 23ES MUST BE CONNECTED AS SHOWN IN FIG C-2.3
B. CONTROL OF GTX 23ES FROM THE GTN 6XX/7XX IS NOT SUPPORTED
Figure C-2.5 GTN 6XX/7XX Transponder Interconnect/Configuration Example
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CONFIGURATION GUIDANCE 1. GNS 430W/530W
A. ON THE MAIN ARINC 429 CONFIG PAGE · SET IN 1 SPEED TO "LOW" · SET IN 1 DATA TO "EFIS/AIR DATA" · SET OUT SPEED TO "LOW" · SET OUT DATA TO "GAMA 429" · SET SDI TO "LNAV 1" · SET VNAV TO "ENABLE LABELS" FOR GNS #1 (WAAS UNITS ONLY)
B. ON THE MAIN RS-232 CONFIG PAGE · SET CHNL 1 INPUT TO "OFF" · SET CHNL 1 OUTPUT TO "MAPMX" (WAAS UNITS ONLY) OR "AVIATION" (NON-WAAS UNITS)
C. ON THE MAIN CDI/OBS CONFIG PAGE · PRESS MENU AND SELECT THE "IGNORE SEL CRS FOR VLOC?" OPTION NOTE: MENU WILL SAY "ALLOW SEL COURSE FOR VLOC?" WHEN SET CORRECTLY
D. ON THE VOR/LOC/GS ARINC 429 CONFIG PAGE · SET RX AND TX SPEED TO "LOW" · SET SDI TO "VOR/ILS 1"
2. G3X A. ON THE GDU 37X COMM CONFIG MODE PAGE · SET THE CONNECTED GDU 37X (PFD) RS-232 CHANNEL TO "MAPMX" (IF CONNECTED TO A WAAS UNIT) OR "AVIATION IN" (IF CONNECTED TO A NON-WAAS UNIT) · SET ARINC 429 TX 1 FORMAT TO "EFIS/AIRDATA" AND "NAV 1" · SET ARINC 429 RX 1 FORMAT TO "GARMIN GPS" AND "NAV 1" · SET ARINC 429 RX 2 FORMAT TO "GARMIN VOR/ILS" AND "NAV 1"
Figure C-2.6 Single GNS 430(W)/530(W) Interconnect/Configuration Example
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CONFIGURATION GUIDANCE 1. GNS #1 AND #2
A. ON THE MAIN ARINC 429 CONFIG PAGE · SET IN 1 SPEED TO "LOW" · SET IN 1 DATA TO "EFIS/AIR DATA" · SET OUT SPEED TO "LOW" · SET OUT DATA TO "GAMA 429" · SET SDI TO "LNAV 1" FOR GNS #1 AND "LNAV 2" FOR GNS #2 · SET VNAV TO "ENABLE LABELS" FOR GNS #1 AND GNS #2 (WAAS UNITS ONLY)
B. ON THE MAIN RS-232 CONFIG PAGE · SET CHNL 1 INPUT TO "OFF" · SET CHNL 1 OUTPUT TO "MAPMX" (WAAS UNITS ONLY) OR "AVIATION" (NON-WAAS UNITS)
C. ON THE MAIN CDI/OBS CONFIG PAGE · PRESS MENU AND SELECT THE "IGNORE SEL CRS FOR VLOC?" OPTION NOTE: MENU WILL SAY "ALLOW SEL COURSE FOR VLOC?" WHEN SET CORRECTLY
D. ON THE VOR/LOC/GS ARINC 429 CONFIG PAGE · SET RX AND TX SPEED TO "LOW" · SET SDI TO "VOR/ILS 1" FOR GNS #1 AND "VOR/ILS 2" FOR GNS #2
2. G3X A. ON THE GDU 37X COMM CONFIG MODE PAGE · SET THE CONNECTED GDU 37X (PFD) RS-232 CHANNEL TO "MAPMX" (IF CONNECTED TO A WAAS UNIT) OR "AVIATION IN" (IF CONNECTED TO A NON-WAAS UNIT) FOR GNS #1 · SET THE CONNECTED GDU 37X (PFD OR MFD) RS-232 CHANNEL TO "MAPMX" (IF CONNECTED TO A WAAS UNIT) OR "AVIATION IN" (IF CONNECTED TO A NON-WAAS UNIT) FOR GNS #2 · SET ARINC 429 TX 1 FORMAT TO "EFIS/AIRDATA" AND "NAV 1 + 2" · SET ARINC 429 RX 1 FORMAT TO "GARMIN GPS" AND "NAV 1" FOR GNS #1 · SET ARINC 429 RX 2 FORMAT TO "GARMIN VOR/ILS" AND "NAV 1" FOR GNS #1 · SET ARINC 429 RX 3 FORMAT TO "GARMIN GPS" AND "NAV 2" FOR GNS #2 (IF APPLICABLE) · SET ARINC 429 RX 4 FORMAT TO "GARMIN VOR/ILS" AND "NAV 2" FOR GNS #2
IMPORTANT: GNS #1 AND #2 ARE DIFFERENTIATED IN THE G3X SYSTEM BY THE GDU 37X RS-232 PORT ASSIGNMENTS. GNS #1 SHOULD ALWAYS BE CONNECTED TO A LOWER NUMBERED PORT ON THE PFD. GNS #2 CAN BE CONNECTED TO A HIGHER NUMBERED PORT ON THE PFD OR TO ANY PORT ON THE MFD.
Figure C-2.7 Dual GNS 430(W)/530(W) Interconnect/Configuration Example
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CONFIGURATION GUIDANCE
1. GTN 6XX/7XX
A. ON THE ARINC 429 CONFIG PAGE · SET IN 1 SPEED TO "LOW" · SET IN 1 DATA TO "EFIS FORMAT 2" · SET OUT 1 SPEED TO "LOW" · SET OUT 1 DATA TO "GAMA FORMAT 1" · SET SDI TO "LNAV 1"
B. ON THE RS-232 CONFIG PAGE · SET CHNL 3 INPUT TO "OFF" · SET CHNL 3 OUTPUT TO "MAPMX"
C. ON THE MAIN MAIN INDICATOR (ANALOG) CONFIG PAGE · SET SELECTED COURSE FOR VLOC TO "IGNORED"
D. ON THE VOR/LOC/GS ARINC 429 CONFIG PAGE · SET NAV RADIO TO "ENABLED" · SET TX SPEED TO "LOW" · SET SDI TO "VOR/ILS 1"
2. G3X
A. ON THE GDU 37X COMM CONFIG MODE PAGE · SET THE CONNECTED GDU 37X (PFD) RS-232 CHANNEL TO "MAPMX" · SET ARINC 429 TX 1 FORMAT TO "EFIS/AIRDATA" AND "NAV 1" · SET ARINC 429 RX 1 FORMAT TO "GARMIN GPS" AND "NAV 1" · SET ARINC 429 RX 2 FORMAT TO "GARMIN VOR/ILS" AND "NAV 1"
Figure C-2.8 Single GTN 6XX/7XX Interconnect/Configuration Example
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CONFIGURATION GUIDANCE 1. GTN 6XX/7XX #1 AND #2
A. ON THE ARINC 429 CONFIG PAGE · SET IN 1 SPEED TO "LOW" · SET IN 1 DATA TO "EFIS FORMAT 2" · SET OUT 1 SPEED TO "LOW" · SET OUT 1 DATA TO "GAMA FORMAT 1" · SET SDI TO "LNAV 1" FOR GTN #1 and "LNAV 2" FOR GTN #2
B. ON THE RS-232 CONFIG PAGE · SET CHNL 3 INPUT TO "OFF" · SET CHNL 3 OUTPUT TO "MAPMX"
C. ON THE MAIN MAIN INDICATOR (ANALOG) CONFIG PAGE · SET SELECTED COURSE FOR VLOC TO "IGNORED"
D. ON THE VOR/LOC/GS ARINC 429 CONFIG PAGE · SET NAV RADIO TO "ENABLED" · SET TX SPEED TO "LOW" · SET SDI TO "VOR/ILS 1" FOR GTN #1 AND "VOR/ILS 2" FOR GTN #2
E. ON THE INTERFACED EQUIPMENT CONFIG PAGE · SET CROSS-SIDE NAVIGATOR TO "PRESENT"
2. G3X A. ON THE GDU 37X COMM CONFIG MODE PAGE · SET THE CONNECTED GDU 37X (PFD) RS-232 CHANNEL TO "MAPMX" FOR GTN #1 · SET THE CONNECTED GDU 37X (PFD OR MFD) RS-232 CHANNEL TO "MAPMX" FOR GTN #2 · SET ARINC 429 TX 1 FORMAT TO "EFIS/AIRDATA" AND "NAV 1 + 2" · SET ARINC 429 RX 1 FORMAT TO "GARMIN GPS" AND "NAV 1" FOR GNS #1 · SET ARINC 429 RX 2 FORMAT TO "GARMIN VOR/ILS" AND "NAV 1" FOR GNS #1 · SET ARINC 429 RX 3 FORMAT TO "GARMIN GPS" AND "NAV 2" FOR GNS #2 (IF APPLICABLE) · SET ARINC 429 RX 4 FORMAT TO "GARMIN VOR/ILS" AND "NAV 2" FOR GNS #2
IMPORTANT: GTN #1 AND #2 ARE DIFFERENTIATED IN THE G3X SYSTEM BY THE GDU 37X RS-232 PORT ASSIGNMENTS. GTN #1 SHOULD ALWAYS BE CONNECTED TO A LOWER NUMBERED PORT ON THE PFD. GTN #2 CAN BE CONNECTED TO A HIGHER NUMBERED PORT ON THE PFD OR TO ANY PORT ON THE MFD.
Figure C-2.9 Dual GTN 6XX/7XX Interconnect/Configuration Example
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CONFIGURATION GUIDANCE
1. GNS 480
A. ON THE MAIN ARINC 429 SETUP PAGE · SET IN 2 SEL TO "EFIS" · SET IN 2 SPEED TO "LOW" · SET IN 2 SDI TO "SYS1" · SET OUT 1 SEL TO "GAMA 429" · SET OUT 1 SPEED TO "LOW" · SET OUT 1 SDI TO "SYS1" · SET OUT 2 SEL TO "VOR/ILS" · SET OUT 2 SPEED TO "LOW" · SET OUT 2 SDI TO "SYS1"
B. ON THE SERIAL SETUP PAGE · SET CHNL 1 OUTPUT TO "MAPMX"
C. ON THE RESOLVER INTERFACE PAGE SET RESOLVER TO "NOT INSTALLED"
D. ON THE MISCELLANEOUS SETUP PAGE SET CDI SELECT TO "USE"
2. G3X
A. ON THE GDU 37X COMM CONFIG MODE PAGE · SET THE CONNECTED GDU 37X (PFD) RS-232 CHANNEL TO "MAPMX" · SET ARINC 429 TX 1 FORMAT TO "EFIS/AIRDATA" AND "NAV 1" · SET ARINC 429 RX 1 FORMAT TO "GARMIN GPS" AND "NAV 1" · SET ARINC 429 RX 2 FORMAT TO "GARMIN VOR/ILS" AND "NAV 1"
Figure C-2.10 GNS 480 Interconnect/Configuration Example
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NON-GARMIN AUTOPILOT INTERCONNECTS SHOWN FOR REFERENCE ONLY. AUTOPILOT VENDOR DOCUMENTATION SHOULD BE CONSULTED FOR PROPER PIN CONNECTIONS.
GAD 29
P292
GAD 29
P292
CONFIGURATION GUIDANCE 1. TRUTRAK GX PILOT / SORCERER
A.ON THE GDU 37X COMM CONFIG MODE PAGE · SET CONNECTED GDU 37X RS-232 CHANNEL FORMAT TO "INTEGRATED AUTOPILOT" · SET ARINC 429 TX 2 FORMAT TO "AUTOPILOT"
2. TRUTRAK DIGIFLIGHT II SERIES A.ON THE GDU 37X COMM CONFIG MODE PAGE · SET CONNECTED GDU 37X RS-232 CHANNEL FORMAT TO "NMEA OUT" · SET ARINC 429 TX 2 FORMAT TO "AUTOPILOT"
3. TRUTRAK DIGITRAK / PICTORIAL PILOT / ADI OR TRIO AVIONICS EZ PILOT A.ON THE GDU 37X COMM CONFIG MODE PAGE · SET CONNECTED GDU 37X RS-232 CHANNEL FORMAT TO "NMEA OUT"
4. TRIO GX PRO / PROPILOT A.ON THE GDU 37X COMM CONFIG MODE PAGE · SET CONNECTED GDU 37X RS-232 CHANNEL FORMAT TO "INTEGRATED AUTOPILOT"
Figure C-2.11 Non-Garmin Auto Pilot Interconnect/Configuration Example
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THIS DRAWING IS ONLY APPLICABLE TO "INTEGRATED" AUTOPILOTS SHOWN IN FIGURE C-2.11
Figure C-2.12 Non-Garmin Auto Pilot Interconnect/Configuration Example w/GMC 305
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CONFIGURATION GUIDANCE 1. GTS 8XX
A.USE GTS 8XX SOFTWARE VERSION 2.02 OR HIGHER B. CONFIGURE "TRAFFIC DISPLAY DESTINATION" TO THE APPROPRIATE RS-232 PORT C.CONFIGURE "BAROMETRIC ALTITUDE SOURCE" AND "MAGNETIC HEADING SOURCE" TO THE APPROPRIATE
A429 INPUT PORT, AND UNCHECK THE ASSOCIATED "HIGH" SPEED CHECKBOXES 2. GDU 37X
A.ON THE GDU 37X COMM CONFIG MODE PAGE · SET CONNECTED GDU 37X RS-232 CHANNEL FORMAT TO "GARMIN HSDB" · SET THE APPROPRIATE ARINC 429 OUT FORMAT TO "EFIS/AIRDATA" · CONFIGURE THE "NAV 1/2" SETTING AS REQUIRED FOR THE EXTERNAL GPS NAVIGATOR(S), IF APPLICABLE
B. ON THE GDU 37X XPDR CONFIG MODE PAGE · IF A REMOTE TRANSPONDER IS CONFIGURED, SET "TIS-A TRAFFIC DATA" TO "DISABLED"
C.ON THE GDU 37X SOUND CONFIG MODE PAGE · SET "TRAFFIC AUDIO" AND "TRAFFIC N/A ALERT" TO "OFF"
Figure C-2.13 GTS 8XX Interconnect/Configuration Example
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Figure C-2.14 GDL 39/GDL 39R Interconnect/Configuration Example
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APPENDIX D G3X W/GSU 73 INTERCONNECT DRAWINGS D.1 Core Interconnect Drawings
Figure D-1.1 Core (w/GSU 73) Interconnect Notes and 2 Display CAN Bus Interconnect Drawing
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G3X Installation Manual - G3X w/GSU 73 Interconnect Drawings Page D-1
Figure D-1.2 GDU 37X/GMU 22/GSU 73 Interconnect Drawing
G3X Installation Manual -G3X w/GSU 73 Interconnect Drawings Page D-2
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Figure D-1.3 Power, Backup Power, and Antennas Interconnect Drawing w/GSU 73
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G3X Installation Manual - G3X w/GSU 73 Interconnect Drawings Page D-3
SERVO POWER
SERVO POWER GND
9
TO ROLL TRIM MOTOR TO ROLL TRIM MOTOR
TO PITCH TRIM MOTOR TO PITCH TRIM MOTOR
GSU 73 CONNECTOR J731 DISCRETE IN*1 9
OR DISCRETE IN*2 10 OR DISCRETE IN*3 11 OR DISCRETE IN*4 12
CONFIGURED FOR "AFCS TO/GA"
TO YAW TRIM SWITCH TO YAW TRIM SWITCH TO YAW TRIM MOTOR TO YAW TRIM MOTOR
CONFIGURATION GUIDANCE 1. G3X
A. ON THE GDU 37X CONFIG MODE COM PORT CONFIGURATION PAGE SET COM PORT CONNECTED TO GMC 305 TO "GARMIN INSTRUMENT DATA"
B. ON THE GDU 37X CONFIG MODE LRU EQUIPMENT CONFIGURATION PAGE SET AUTOPILOT SERVOS TO ONE OF THE FOLLOWING: "ROLL ONLY", "PITCH + ROLL", OR "PITCH + YAW"
Figure D-1.4 GMC 305/GSA 28 Interconnect Drawing w/GSU 73
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D.2 External Interconnect Drawings w/GSU 73
FIG D-2.9
A 14 CFR 91.227 COMPLIANT INSTALLATION REQUIRES RS-232 ADS-B OUT FROM A GNS 400/500 SERIES WAAS UNIT WITH MAIN SOFTWARE VERSION 3.20 (OR LATER), OR A GTN 600/700 SERIES UNIT SOFTWARE VERSION 3.00 (OR LATER) TO SUPPORT ADS-B TRANSMISSIONS. FOR VFR AIRCRAFT, NON-COMPLIANT ADS-B OUT IS PROVIDED BY THE VFR GPS DATA SENT AUTOMATICALLY TO THE GTX 23ES. IF ADS-B TRANSMISSION FROM THE GTX 23ES IS NOT REQUIRED, THIS CONNECTION IS NOT REQUIRED.
Figure D-2.1 External Interconnect w/GSU 73 Drawing Notes
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GSU 73 ADAHRS 1 ONLY
CONFIGURATION GUIDANCE 1. GTX 327/328/330(ES)
A.ON THE GTX 327/328/330(ES) RS-232 CONFIG MODE PAGE FOR RS-232 CHANNEL 1 · SET CONNECTED GTX 327/328/330(ES)RS-232 CHANNEL 1 INPUT FORMAT TO "REMOTE" · SET CONNECTED GTX 330(ES) RS-232 CHANNEL 1 OUTPUT FORMAT TO "REMOTE+TIS"
B. ON THE GTX 330(ES) RS-232 CONFIG MODE PAGE FOR RS-232 CHANNEL 2 · SET RS-232 CHANNEL 2 INPUT FORMAT TO "REMOTE"
C. ON THE GTX 327/328/330(ES) SQUAT SWITCH CONFIG MODE PAGE · SET THE SQUAT SWITCH FIELD TO "NO"
D.IF REMOTE CONTROL OF THE TRANSPONDER FROM THE GDU 37X IS DESIRED · ON THE GDU 37X XPDR CONFIG MODE PAGE SET TRANSPONDER TYPE TO "GTX 327" OR "GTX 328" OR "GTX 330" OR "GTX 330ES" OR "GTX 33" AS APPROPRIATE
E.NO GSU 73 CONFIGURATION REQUIRED
2. GTX 33(ES) A.ON THE GDU 37X XPDR CONFIG MODE PAGE · SET TRANSPONDER TYPE TO "GTX 33" OR "GTX 33ES" AS APPROPRIATE
B. NO GSU 73 CONFIGURATION REQUIRED 3. GTX 23ES
A.ON THE GDU 37X XPDR CONFIG MODE PAGE · SET TRANSPONDER TYPE TO "GTX 23ES"
B. NO GSU 73 CONFIGURATION REQUIRED
4. GTN 6XX/7XX, GNS 4XXW/5XXW (WHEN ADS-B OUT IS BEING PROVIDED TO ES TRANSPONDER) A.ON THE GTN/GNS RS-232 CONFIG MODE PAGE · SET RS-232 OUTPUT FORMAT TO ADS-B OUT(+) (FOR RS-232 PORT CONNECTED TO TRANSPONDER RS-232 IN CHANNEL 2)
Figure D-2.2 G3X w/GSU 73 - Transponders Interconnect/Configuration Example
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CONFIGURATION GUIDANCE 1. GTX 32
A.ON THE GTN 6XX/7XX RS-232 CONFIG PAGE · SET RS-232 CHANNEL 1 INPUT AND OUTPUT FORMATS TO "GTX MODE C #1"
B. ON THE GTN 6XX/7XX XPDR1 CONFIG PAGE · SET RS-232 CHANNEL 1 INPUT AND OUTPUT FORMATS TO "REMOTE" · SET RS-232 CHANNEL 2 INPUT FORMAT TO "REMOTE"
C.ON THE GDU 37X XPDR CONFIG MODE PAGE · SET THE TRANSPONDER TYPE TO "NONE"
D.NO GDU 37X OR GSU 73 CONFIGURATION REQUIRED
2. GTX 327 A.ON THE GTN 6XX/7XX RS-232 CONFIG PAGE · SET RS-232 CHANNEL 1 INPUT FORMAT TO "ALTITUDE FORMAT 1" · SET RS-232 CHANNEL 1 OUTPUT FORMAT TO "AVIATION OUTPUT 1" B. ON THE GTX 327 RS-232 CONFIG PAGE · SET RS-232 CHANNEL 1 INPUT FORMAT TO "GPS" · SET RS-232 CHANNEL 1 OUTPUT FORMAT TO "ICARUS ALT" · SET RS-232 CHANNEL 2 INPUT FORMAT TO "REMOTE" C.ON THE GDU 37X XPDR CONFIG PAGE · SET THE TRANSPONDER TYPE TO "NONE" D.NO GSU 73 CONFIGURATION REQUIRED
3. GTX 33(ES) A.ON THE GTN 6XX/7XX RS-232 CONFIG PAGE · SET RS-232 CHANNEL 1 INPUT AND OUTPUT FORMATS TO "GTX w/TIS #1" B. ON THE GTN 6XX/7XX XPDR1 CONFIG PAGE · SET RS-232 CHANNEL 1 INPUT FORMAT TO "REMOTE" · SET RS-232 CHANNEL 1 OUTPUT FORMAT TO "REMOTE w/TIS" · SET RS-232 CHANNEL 2 INPUT FORMAT TO "REMOTE" · SET RS-232 CHANNEL 2 OUTPUT FORMAT TO "REMOTE w/TIS" C.ON THE GDU 37X RS-232 CONFIG PAGE · SET THE CONNECTED RS-232 CHANNEL FORMAT TO "TIS-A IN" IF TIS-A TRAFFIC IS DESIRED D.ON THE GDU 37X XPDR CONFIG MODE PAGE · SET THE TRANSPONDER TYPE TO "NONE" E. NO GSU 73 CONFIGURATION REQUIRED
4. GTX 330(ES) A.ON THE GTN 6XX/7XX RS-232 CONFIG PAGE · SET RS-232 CHANNEL 1 INPUT AND OUTPUT FORMATS TO "PANEL GTX w/TIS #1" B. ON THE GTX 330 RS-232 CONFIG PAGE · SET RS-232 CHANNEL 1 INPUT FORMAT TO "REMOTE" · SET RS-232 CHANNEL 1 OUTPUT FORMAT TO "REMOTE+TIS" · SET RS-232 CHANNEL 2 INPUT FORMAT TO "REMOTE" · SET RS-232 CHANNEL 2 OUTPUT FORMAT TO "REMOTE+TIS" C.ON THE GDU 37X RS-232 CONFIG PAGE · SET THE CONNECTED RS-232 CHANNEL FORMAT TO "TIS-A IN" IF TIS-A TRAFFIC IS DESIRED D.ON THE GDU 37X XPDR CONFIG PAGE · SET THE TRANSPONDER TYPE TO "NONE" E. NO GSU 73 CONFIGURATION REQUIRED
5. GTX 23ES A.THE GTX 23ES MUST BE CONNECTED AS SHOWN IN FIG D-2.2
B. CONTROL OF GTX 23ES FROM THE GTN 6XX/7XX IS NOT SUPPORTED
Figure D-2.3 GTN 6XX/7XX - Transponder Interconnect/Configuration Example w/GSU 73
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G3X Installation Manual - G3X w/GSU 73 Interconnect Drawings Page D-7
CONFIGURATION GUIDANCE 1. GNS 430W/530W
A. ON THE MAIN ARINC 429 CONFIG PAGE · SET IN 1 SPEED TO "LOW" · SET IN 1 DATA TO "EFIS/AIR DATA" · SET OUT SPEED TO "LOW" · SET OUT DATA TO "GAMA 429" · SET SDI TO "LNAV 1" · SET VNAV TO "ENABLE LABELS" FOR GNS #1 (WAAS UNITS ONLY)
B. ON THE MAIN RS-232 CONFIG PAGE · SET CHNL 1 INPUT TO "OFF" · SET CHNL 1 OUTPUT TO "MAPMX" (WAAS UNITS ONLY) OR "AVIATION" (NON-WAAS UNITS)
C. ON THE MAIN CDI/OBS CONFIG PAGE · PRESS MENU AND SELECT THE "IGNORE SEL CRS FOR VLOC?" OPTION NOTE: MENU WILL SAY "ALLOW SEL COURSE FOR VLOC?" WHEN SET CORRECTLY
D. ON THE VOR/LOC/GS ARINC 429 CONFIG PAGE · SET RX AND TX SPEED TO "LOW" · SET SDI TO "VOR/ILS 1"
2. G3X A. ON THE GDU 37X COMM CONFIG MODE PAGE · SET THE CONNECTED GDU 37X (PFD) RS-232 CHANNEL TO "MAPMX" (IF CONNECTED TO A WAAS UNIT) OR "AVIATION IN" (IF CONNECTED TO A NON-WAAS UNIT) · SET ARINC 429 TX 1 FORMAT TO "EFIS/AIRDATA" AND "NAV 1" · SET ARINC 429 RX 1 FORMAT TO "GARMIN GPS" AND "NAV 1" · SET ARINC 429 RX 2 FORMAT TO "GARMIN VOR/ILS" AND "NAV 1"
Figure D-2.4 Single GNS 430(W)/530(W) Interconnect/Configuration Example w/GSU 73
G3X Installation Manual -G3X w/GSU 73 Interconnect Drawings Page D-8
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CONFIGURATION GUIDANCE 1. GNS #1 AND #2
A. ON THE MAIN ARINC 429 CONFIG PAGE · SET IN 1 SPEED TO "LOW" · SET IN 1 DATA TO "EFIS/AIR DATA" · SET OUT SPEED TO "LOW" · SET OUT DATA TO "GAMA 429" · SET SDI TO "LNAV 1" FOR GNS #1 AND "LNAV 2" FOR GNS #2 · SET VNAV TO "ENABLE LABELS" FOR GNS #1 AND GNS #2 (WAAS UNITS ONLY)
B. ON THE MAIN RS-232 CONFIG PAGE · SET CHNL 1 INPUT TO "OFF" · SET CHNL 1 OUTPUT TO "MAPMX" (WAAS UNITS ONLY) OR "AVIATION" (NON-WAAS UNITS)
C. ON THE MAIN CDI/OBS CONFIG PAGE · PRESS MENU AND SELECT THE "IGNORE SEL CRS FOR VLOC?" OPTION NOTE: MENU WILL SAY "ALLOW SEL COURSE FOR VLOC?" WHEN SET CORRECTLY
D. ON THE VOR/LOC/GS ARINC 429 CONFIG PAGE · SET RX AND TX SPEED TO "LOW" · SET SDI TO "VOR/ILS 1" FOR GNS #1 AND "VOR/ILS 2" FOR GNS #2
2. G3X A. ON THE GDU 37X COMM CONFIG MODE PAGE · SET THE CONNECTED GDU 37X (PFD) RS-232 CHANNEL TO "MAPMX" (IF CONNECTED TO A WAAS UNIT) OR "AVIATION IN" (IF CONNECTED TO A NON-WAAS UNIT) FOR GNS #1 · SET THE CONNECTED GDU 37X (PFD OR MFD) RS-232 CHANNEL TO "MAPMX" (IF CONNECTED TO A WAAS UNIT) OR "AVIATION IN" (IF CONNECTED TO A NON-WAAS UNIT) FOR GNS #2 · SET ARINC 429 TX 1 FORMAT TO "EFIS/AIRDATA" AND "NAV 1 + 2" · SET ARINC 429 RX 1 FORMAT TO "GARMIN GPS" AND "NAV 1" FOR GNS #1 · SET ARINC 429 RX 2 FORMAT TO "GARMIN VOR/ILS" AND "NAV 1" FOR GNS #1 · SET ARINC 429 RX 3 FORMAT TO "GARMIN GPS" AND "NAV 2" FOR GNS #2 (IF APPLICABLE) · SET ARINC 429 RX 4 FORMAT TO "GARMIN VOR/ILS" AND "NAV 2" FOR GNS #2
IMPORTANT: GNS #1 AND #2 ARE DIFFERENTIATED IN THE G3X SYSTEM BY THE GDU 37X RS-232 PORT ASSIGNMENTS. GNS #1 SHOULD ALWAYS BE CONNECTED TO A LOWER NUMBERED PORT ON THE PFD. GNS #2 CAN BE CONNECTED TO A HIGHER NUMBERED PORT ON THE PFD OR TO ANY PORT ON THE MFD.
Figure D-2.5 Dual GNS 430(W)/530(W) Interconnect/Configuration Example w/GSU 73
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G3X Installation Manual - G3X w/GSU 73 Interconnect Drawings Page D-9
CONFIGURATION GUIDANCE
1. GTN 6XX/7XX
A. ON THE ARINC 429 CONFIG PAGE · SET IN 1 SPEED TO "LOW" · SET IN 1 DATA TO "EFIS FORMAT 2" · SET OUT 1 SPEED TO "LOW" · SET OUT 1 DATA TO "GAMA FORMAT 1" · SET SDI TO "LNAV 1"
B. ON THE RS-232 CONFIG PAGE · SET CHNL 3 INPUT TO "OFF" · SET CHNL 3 OUTPUT TO "MAPMX"
C. ON THE MAIN MAIN INDICATOR (ANALOG) CONFIG PAGE · SET SELECTED COURSE FOR VLOC TO "IGNORED"
D. ON THE VOR/LOC/GS ARINC 429 CONFIG PAGE · SET NAV RADIO TO "ENABLED" · SET TX SPEED TO "LOW" · SET SDI TO "VOR/ILS 1"
2. G3X
A. ON THE GDU 37X COMM CONFIG MODE PAGE · SET THE CONNECTED GDU 37X (PFD) RS-232 CHANNEL TO "MAPMX" · SET ARINC 429 TX 1 FORMAT TO "EFIS/AIRDATA" AND "NAV 1" · SET ARINC 429 RX 1 FORMAT TO "GARMIN GPS" AND "NAV 1" · SET ARINC 429 RX 2 FORMAT TO "GARMIN VOR/ILS" AND "NAV 1"
Figure D-2.6 Single GTN 6XX/7XX Interconnect/Configuration Example w/GSU 73
G3X Installation Manual -G3X w/GSU 73 Interconnect Drawings Page D-10
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CONFIGURATION GUIDANCE 1. GTN 6XX/7XX #1 AND #2
A. ON THE ARINC 429 CONFIG PAGE · SET IN 1 SPEED TO "LOW" · SET IN 1 DATA TO "EFIS FORMAT 2" · SET OUT 1 SPEED TO "LOW" · SET OUT 1 DATA TO "GAMA FORMAT 1" · SET SDI TO "LNAV 1" FOR GTN #1 and "LNAV 2" FOR GTN #2
B. ON THE RS-232 CONFIG PAGE · SET CHNL 3 INPUT TO "OFF" · SET CHNL 3 OUTPUT TO "MAPMX"
C. ON THE MAIN MAIN INDICATOR (ANALOG) CONFIG PAGE · SET SELECTED COURSE FOR VLOC TO "IGNORED"
D. ON THE VOR/LOC/GS ARINC 429 CONFIG PAGE · SET NAV RADIO TO "ENABLED" · SET TX SPEED TO "LOW" · SET SDI TO "VOR/ILS 1" FOR GTN #1 AND "VOR/ILS 2" FOR GTN #2
E. ON THE INTERFACED EQUIPMENT CONFIG PAGE · SET CROSS-SIDE NAVIGATOR TO "PRESENT"
2. G3X A. ON THE GDU 37X COMM CONFIG MODE PAGE · SET THE CONNECTED GDU 37X (PFD) RS-232 CHANNEL TO "MAPMX" FOR GTN #1 · SET THE CONNECTED GDU 37X (PFD OR MFD) RS-232 CHANNEL TO "MAPMX" FOR GTN #2 · SET ARINC 429 TX 1 FORMAT TO "EFIS/AIRDATA" AND "NAV 1 + 2" · SET ARINC 429 RX 1 FORMAT TO "GARMIN GPS" AND "NAV 1" FOR GNS #1 · SET ARINC 429 RX 2 FORMAT TO "GARMIN VOR/ILS" AND "NAV 1" FOR GNS #1 · SET ARINC 429 RX 3 FORMAT TO "GARMIN GPS" AND "NAV 2" FOR GNS #2 (IF APPLICABLE) · SET ARINC 429 RX 4 FORMAT TO "GARMIN VOR/ILS" AND "NAV 2" FOR GNS #2
IMPORTANT: GTN #1 AND #2 ARE DIFFERENTIATED IN THE G3X SYSTEM BY THE GDU 37X RS-232 PORT ASSIGNMENTS. GTN #1 SHOULD ALWAYS BE CONNECTED TO A LOWER NUMBERED PORT ON THE PFD. GTN #2 CAN BE CONNECTED TO A HIGHER NUMBERED PORT ON THE PFD OR TO ANY PORT ON THE MFD.
Figure D-2.7 Dual GTN 6XX/7XX Interconnect/Configuration Example w/GSU 73
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G3X Installation Manual - G3X w/GSU 73 Interconnect Drawings Page D-11
CONFIGURATION GUIDANCE
1. GNS 480
A. ON THE MAIN ARINC 429 SETUP PAGE · SET IN 2 SEL TO "EFIS" · SET IN 2 SPEED TO "LOW" · SET IN 2 SDI TO "SYS1" · SET OUT 1 SEL TO "GAMA 429" · SET OUT 1 SPEED TO "LOW" · SET OUT 1 SDI TO "SYS1" · SET OUT 2 SEL TO "VOR/ILS" · SET OUT 2 SPEED TO "LOW" · SET OUT 2 SDI TO "SYS1"
B. ON THE SERIAL SETUP PAGE · SET CHNL 1 OUTPUT TO "MAPMX"
C. ON THE RESOLVER INTERFACE PAGE SET RESOLVER TO "NOT INSTALLED"
D. ON THE MISCELLANEOUS SETUP PAGE SET CDI SELECT TO "USE"
2. G3X
A. ON THE GDU 37X COMM CONFIG MODE PAGE · SET THE CONNECTED GDU 37X (PFD) RS-232 CHANNEL TO "MAPMX" · SET ARINC 429 TX 1 FORMAT TO "EFIS/AIRDATA" AND "NAV 1" · SET ARINC 429 RX 1 FORMAT TO "GARMIN GPS" AND "NAV 1" · SET ARINC 429 RX 2 FORMAT TO "GARMIN VOR/ILS" AND "NAV 1"
Figure D-2.8 GNS 480 Interconnect/Configuration Example w/GSU 73
G3X Installation Manual -G3X w/GSU 73 Interconnect Drawings Page D-12
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NON-GARMIN AUTOPILOT INTERCONNECTS SHOWN FOR REFERENCE ONLY. AUTOPILOT VENDOR DOCUMENTATION SHOULD BE CONSULTED FOR PROPER PIN CONNECTIONS.
CONFIGURATION GUIDANCE 1. TRUTRAK GX PILOT / SORCERER
A.ON THE GDU 37X COMM CONFIG MODE PAGE · SET CONNECTED GDU 37X RS-232 CHANNEL FORMAT TO "INTEGRATED AUTOPILOT" · SET ARINC 429 TX 2 FORMAT TO "AUTOPILOT"
2. TRUTRAK DIGIFLIGHT II SERIES A.ON THE GDU 37X COMM CONFIG MODE PAGE · SET CONNECTED GDU 37X RS-232 CHANNEL FORMAT TO "NMEA OUT" · SET ARINC 429 TX 2 FORMAT TO "AUTOPILOT"
3. TRUTRAK DIGITRAK / PICTORIAL PILOT / ADI OR TRIO AVIONICS EZ PILOT A.ON THE GDU 37X COMM CONFIG MODE PAGE · SET CONNECTED GDU 37X RS-232 CHANNEL FORMAT TO "NMEA OUT"
4. TRIO GX PRO / PROPILOT A.ON THE GDU 37X COMM CONFIG MODE PAGE · SET CONNECTED GDU 37X RS-232 CHANNEL FORMAT TO "INTEGRATED AUTOPILOT"
Figure D-2.9 Non-Garmin Auto Pilot Interconnect/Configuration Example w/GSU 73
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G3X Installation Manual - G3X w/GSU 73 Interconnect Drawings Page D-13
CONFIGURATION GUIDANCE 1. GTS 8XX
A.USE GTS 8XX SOFTWARE VERSION 2.02 OR HIGHER B. CONFIGURE "TRAFFIC DISPLAY DESTINATION" TO THE APPROPRIATE RS-232 PORT C.CONFIGURE "BAROMETRIC ALTITUDE SOURCE" AND "MAGNETIC HEADING SOURCE" TO THE APPROPRIATE
A429 INPUT PORT, AND UNCHECK THE ASSOCIATED "HIGH" SPEED CHECKBOXES 2. GDU 37X
A.ON THE GDU 37X COMM CONFIG MODE PAGE · SET CONNECTED GDU 37X RS-232 CHANNEL FORMAT TO "GARMIN HSDB" · SET THE APPROPRIATE ARINC 429 OUT FORMAT TO "EFIS/AIRDATA" · CONFIGURE THE "NAV 1/2" SETTING AS REQUIRED FOR THE EXTERNAL GPS NAVIGATOR(S), IF APPLICABLE
B. ON THE GDU 37X XPDR CONFIG MODE PAGE · IF A REMOTE TRANSPONDER IS CONFIGURED, SET "TIS-A TRAFFIC DATA" TO "DISABLED"
C.ON THE GDU 37X SOUND CONFIG MODE PAGE · SET "TRAFFIC AUDIO" AND "TRAFFIC N/A ALERT" TO "OFF"
Figure D-2.10 G3X w/GSU 73 - GTS 8XX Interconnect/Configuration Example
G3X Installation Manual -G3X w/GSU 73 Interconnect Drawings Page D-14
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APPENDIX E SENSOR WIRING EXAMPLES
THIS NOTE IS NO LONGER APPLICABLE AND HAS BEEN REMOVED.
Figure E-1.1 Notes for Sensor Wiring Example Drawings (for all Appdx E drawings)
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G3X Installation Manual - Sensor Wiring Examples Page E-1
E.1 Sensor Wiring Examples w/GEA 24
GEA 24
P244
FUEL QTY +5V_1 5 FUEL QTY 1 GND 7
FUEL QTY 1 6
S
FUEL QTY +5V_2 8 FUEL QTY 2 GND 10
FUEL QTY 2 9
S
FUEL QTY 1
6
FUEL QTY 2 9
FUEL QTY +5V_1 5 FUEL QTY 1 GND 7
FUEL QTY 1 6
S
FUEL QTY +5V_2 8 FUEL QTY 2 GND 10
FUEL QTY 2 9
S
Figure E-2.1 Page 1 of 2 Fuel Quantity and Fuel Flow Examples (w/GEA 24)
G3X Installation Manual - Sensor Wiring Examples Page E-2
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GEA 24
P243
FUEL XDCR +12V_1 24 FUEL FLOW 23
FUEL XDCR GND_1 20
FUEL XDCR +12V_2 25 FUEL RETURN 21
FUEL XDCR GND_2 22
GEA 24
P244
FUEL QTY +5V_1 5 FUEL QTY 1 6
FUEL QTY 1 GND 7
S
POS 3 / GP 3 / FUEL QTY 3 12
POS 4 / GP 4 / FUEL QTY 4 15
FUEL XDCR +12V_3 34 POS 3 LO / GND 13
POS 3 / GP 3 / FUEL QTY 3 12
S
FUEL XDCR +12V_4 35 POS 4 LO / GND 16
POS 4 / GP 4 / FUEL QTY 4 15
S
Figure E-2.1 Page 2 of 2 Fuel Quantity and Fuel Flow Examples (w/GEA 24)
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G3X Installation Manual - Sensor Wiring Examples Page E-3
GEA 24
P244
VOLTS 1 25
THESE CONNECTIONS ARE OPTIONAL, BUS VOLTAGE CAN BE MONITORED FROM THE GEA 24 POWER SUPPLY INPUTS. SEE SECTION 18 FOR CONFIGURATION INFO.
VOLTS 2 28
GEA 24
P244
POS 3 HI / +5V_3 11 POS 3 / GP 3 / FUEL QTY 3 12
POS 3 LO / GND 13
POS 4 HI / +5V_4 14 POS 4 / GP 4 / FUEL QTY 4 15
POS 4 LO / GND 16
GEA 24
P243
SHUNT 1 HI 37 SHUNT 1 LO 36
SHUNT 2 HI 35 SHUNT 2 LO 34
Figure E-2.2 Page 1 of 2 Electrical and Discrete Input/Output Examples (w/GEA 24)
G3X Installation Manual - Sensor Wiring Examples Page E-4
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GEA 24
P244 40 41 42 43
DISCRETE OUT 1/ 44 MASTER WARNING
DISCRETE OUT 2/ 45 MASTER CAUTION
Figure E-2.2 Page 2 of 2 Electrical and Discrete Input/Output Examples (w/GEA 24)
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G3X Installation Manual - Sensor Wiring Examples Page E-5
GEA 24
P244
GP1 HI / +5 18 GP1 / POS 1 19 GP1 LO / GND 20
GP2 HI / +5 21 GP2 / POS 2 22 GP2 LO / GND 23
POS 3 HI / +5V_3 11 POS 3 / GP 3 / FUEL QTY 3 12
POS 3 LO / GND 13
POS 5 HI / +5V 30 POS 5 / MISC PRESS 31
POS 5 LO / GND 32
GEA 24
P243
FUEL PRESS XDCR +12V 3 FUEL PRESS 2
FUEL PRESS GND 1
MANIFOLD PRESS XDCR +12V 14 MANIFOLD PRESS 13
MANIFOLD PRESS GND 12
OIL PRESS XDCR +12V 18 OIL PRESS HI 17
OIL PRESS GND 16
Figure E-2.3 Flaps/Trim and UMA Pressure Transducer Examples (w/GEA 24)
G3X Installation Manual - Sensor Wiring Examples Page E-6
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E.2 Sensor Wiring Examples w/GSU 73
S S
S S
Figure E-3.1 Page 1 of 2 Fuel Quantity and Fuel Flow Examples (w/GSU 73)
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G3X Installation Manual - Sensor Wiring Examples Page E-7
S
S
S
Figure E-3.1 Page 2 of 2 Fuel Quantity and Fuel Flow Examples (w/GSU 73)
G3X Installation Manual - Sensor Wiring Examples Page E-8
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THESE CONNECTIONS ARE OPTIONAL, BUS VOLTAGE CAN BE MONITORED FROM THE GSU 73 POWER SUPPLY INPUTS. SEE SECTION 18 FOR CONFIGURATION INFO.
Figure E-3.2 Page 1 of 2 Electrical and Discrete Input/Output Examples (w/GSU 73)
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G3X Installation Manual - Sensor Wiring Examples Page E-9
Figure E-3.2 Page 2 of 2 Electrical and Discrete Input/Output Examples (w/GSU 73)
G3X Installation Manual - Sensor Wiring Examples Page E-10
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Figure E-3.3 Flaps/Trim and UMA Pressure Transducer Examples (w/GSU 73)
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G3X Installation Manual - Sensor Wiring Examples Page E-11
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APPENDIX F LYCOMING/CONTINENTAL SENSOR WIRING EXAMPLES
NOTES
7. GROUNDING METHODS FOR ELECTRONIC TACH SIGNALS MAY VARY BASED ON THE MANUFACTURER. CONSULT THE ELECTRONIC IGNITION MANUFACTURER DOCUMENTATION FOR SPECIFIC GROUNDING GUIDANCE. THE CAP FUEL 1/ RPM 2 INPUT (GSU 73) OR RPM 2 (GEA 24) INPUT CAN BE OPTIONALLY USED ON AIRCRAFT WITH DUAL ELECTRONIC IGNITION.
9. PINOUT SHOWN FOR PACKARD CONNECTOR SUPPLIED WITH KAVLICO PRESSURE TRANSDUCERS. WIRE COLORS ARE SHOWN FOR REFERENCE ONLY, ALWAYS CONFIRM CORRECT SENSOR CONNECTIONS USING SENSOR MANUFACTURER DOCUMENTATION BEFORE CONNECTING WIRES.
Figure F-1.1 Notes for Lycoming/Continental Sensor Drawings (for all Appdx F drawings)
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G3X Installation Manual - Lycoming/Continental Sensor Wiring Examples Page F-1
F.1 GEA 24 - Lycoming/Continental Sensor Drawings
Figure F-2.1 GEA 24 - 4/6 Cylinder Lycoming/Continental Sensor Wiring Examples, Page 1 of 3
G3X Installation Manual - Lycoming/Continental Sensor Wiring Examples Page F-2
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RED GRN BLK
VOLTAGE IN (PIN B) OUTPUT (PIN C) GROUND (PIN A)
RED GRN BLK
VOLTAGE IN (PIN B) OUTPUT (PIN C) GROUND (PIN A)
RED GRN BLK
VOLTAGE IN (PIN B) OUTPUT (PIN C) GROUND (PIN A)
Figure F-2.1 GEA 24 - 4/6 Cylinder Lycoming/Continental Sensor Wiring Examples, Page 2 of 3
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G3X Installation Manual - Lycoming/Continental Sensor Wiring Examples Page F-3
Figure F-2.1 GEA 24 - 4/6 Cylinder Lycoming/Continental Sensor Wiring Examples, Page 3 of 3
G3X Installation Manual - Lycoming/Continental Sensor Wiring Examples Page F-4
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F.2 GSU 73 - Lycoming/Continental Sensor Drawings
10 K
Figure F-3.1 GSU 73 - 4/6 Cylinder Lycoming/Continental Sensor Wiring Examples, Page 1 of 3
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G3X Installation Manual - Lycoming/Continental Sensor Wiring Examples Page F-5
RED GRN BLK
VOLTAGE IN (PIN B) OUTPUT (PIN C) GROUND (PIN A)
RED GRN BLK
VOLTAGE IN (PIN B) OUTPUT (PIN C) GROUND (PIN A)
RED GRN BLK
VOLTAGE IN (PIN B) OUTPUT (PIN C) GROUND (PIN A)
Figure F-3.1 GSU 73 - 4/6 Cylinder Lycoming/Continental Sensor Wiring Examples, Page 2 of 3
G3X Installation Manual - Lycoming/Continental Sensor Wiring Examples Page F-6
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Figure F-3.1 GSU 73 - 4/6 Cylinder Lycoming/Continental Sensor Wiring Examples, Page 3 of 3
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APPENDIX G ROTAX SENSOR WIRING EXAMPLES
NOTES:
1. UNLESS OTHERWISE NOTED, ALL STRANDED WIRE MUST CONFORM TO MIL-W-22759/16 OR EQUIVALENT 2. UNLESS OTHERWISE NOTED, ALL SHIELDED WIRE MUST CONFORM TO MIL-C-27500 OR EQUIVALENT 3. UNLESS OTHERWISE NOTED, ALL WIRES ARE 24 GAUGE MINIMUM 4. SYMBOL DESIGNATIONS:
TWISTED SHIELDED SINGLE CONDUCTOR SHIELD TERMINATED TO GROUND
TWISTED SHIELDED SINGLE CONDUCTOR SHIELD FLOATS
TWISTED SHIELDED 4 CONDUCTOR SHIELD TERMINATED TO GROUND
W HT TWISTED SHIELDED PAIR BLU SHIELD TERMINATED TO GROUND
W HT TWISTED SHIELDED PAIR BLU SHIELD FLOATS
W HT BLU ORN
TWISTED SHIELDED 3 CONDUCTOR SHIELD TERMINATED TO GROUND
TWISTED SHIELDED 4 CONDUCTOR SHIELD FLOATS
AIRCRAFT GROUND
GARMIN SHIELD BLOCK GROUND
S
(REFER TO 190-00313-09)
WIRE SPLICE CONNECTION
W HT BLU ORN
TWISTED SHIELDED 3 CONDUCTOR SHIELD FLOATS
COAXIAL CABLE N/C = NO CONNECTION
5. UNLESS OTHERWISE NOTED, ALL SHIELD GROUNDS MUST BE MADE TO THE RESPECTIVE UNIT BACKSHELLS. ALL OTHER GROUNDS SHOULD BE TERMINATED TO AIRCRAFT GROUND AS CLOSE TO THE RESPECTIVE UNIT AS POSSIBLE.
6. SENSOR SUPPLIED WITH THE ENGINE. 7. SENSORS SUPPLIED WITH THE GARMIN ROTAX 912 SENSOR KIT P/N K00-00514-00. 8. ROTAX P/N 956413 OR 956415 MAY BE CONFIGURED. 9. PINOUT SHOWN FOR PACKARD CONNECTOR SUPPLIED WITH KAVLICO PRESSURE TRANSDUCERS. WIRE COLORS ARE SHOWN
FOR REFERENCE ONLY, ALWAYS CONFIRM CORRECT SENSOR CONNECTIONS USING SENSOR MANUFACTURER DOCUMENTATION BEFORE CONNECTING WIRES. 10. IF MEASURING BATTERY CURRENT, PLACE THE SHUNT BETWEEN THE BATTERY POSITIVE TERMINAL AND THE BATTERY CONTACTOR. IF MEASURING ALTERNATOR CURRENT, PLACE THE SHUNT BETWEEN THE ALTERNATOR B LEAD AND THE POWER DISTRIBUTION BUS.
11. NOT INCLUDED IN THE GARMIN ROTAX 912 SENSOR KIT P/N K00-00514-00. THE KAVLICO P4055-50G-E4A CAN BE PURCHASED THROUGH A GARMIN G3X DEALER.
12. USE GARMIN P/N 682-00011-00 BI-DIRECTIONAL DIODE ON RPM 1 INPUT AND 300 RESISTOR BETWEEN PINS 7 AND 8 AS SHOWN IN FIGURE G-2.2.
13. USE THE KAVLICO P4055-15G FUEL PRESSURE SENSOR WITH THE ROTAX 912 ENGINE. USE THE UMA N1EU07D FUEL PRESSURE SENSOR WITH THE ROTAX 914 ENGINE
Figure G-1.1 Notes for Rotax 912/914 Sensor Drawings (for all Appdx G drawings)
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G3X Installation Manual - Rotax Sensor Wiring Examples Page G-1
G.1 GEA 24 - Rotax Sensor Drawings
RED GRN BLK
VOLTAGE IN (PIN B) OUTPUT (PIN C) GROUND (PIN A)
KAVLICO P4055-15G (912) UMA N1EU07D (914) RED VOLTAGE IN (PIN B) GRN OUTPUT (PIN C) BLK GROUND (PIN A)
NOTE 13
RED GRN BLK
VOLTAGE IN (PIN B) OUTPUT (PIN C) GROUND (PIN A)
Figure G-2.1 GEA 24 - Rotax 912/914 Sensor Wiring Examples, Page 1 of 2
G3X Installation Manual - Rotax Sensor Wiring Examples Page G-2
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40
1%
NOTE 12
300
1%
Figure G-2.2 GEA 24 - Rotax 912/914 Sensor Wiring Examples, Page 2 of 2
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G3X Installation Manual - Rotax Sensor Wiring Examples Page G-3
G.2 GSU 73 - Rotax Sensor Drawings
GSU 73
J732
SEE NOTE 6
OIL TEMP HI 34 OIL TEMP LO 14
S
SEE NOTE 8
+12 VDC TRANSDUCER POWER 55 POS 3/GP 3/FUEL FLOAT 3 HI 27 S
40
1%
POS 3/GP 3/FUEL FLOW 3 LO
7
OR
POS 3/GP 3/FUEL FLOAT 3 HI 27
POS 3/GP 3/FUEL FLOAT 3 LO
7
S
XDCR PWR OUT LO (GROUND) 74 RPM 17 S
300
1%
POS 1/GP 1/TIT 1 HI 47 POS 1/GP 1/TIT 1 LO 67
S
POS 2/GP 2/TIT 2 HI 28 POS 2/GP 2/TIT 2 LO 8
S
OIL TEMP SENSOR
ROTAX P/N 965531 OR ROTAX P/N 966385
C RED A WHT B
OIL PRESSURE SENSOR ROTAX P/N 956413
COMMON + EXCITATION OUTPUT
OIL PRESS SENSOR ROTAX P/N 956415
OUTPUT GROUND
ROTAX TRIGGER COIL
OUT LO/GROUND OUT HI
CHT #1 ROTAX P/N 965531 OR ROTAX P/N 966385
CHT #2 ROTAX P/N 965531 OR ROTAX P/N 966385
EGT 1 HI 63 EGT 1 LO 43
EGT 2 HI 23 EGT 2 LO 3
YEL RED
YEL RED
+5 VDC TRANSDUCER POWER 75
FUEL PRESS HI 26
FUEL PRESS LO 45
XDCR PWR OUT LO (GROUND) 57
S
SEE NOTE 7 SEE NOTE 9
MANIFOLD PRESS HI 65
MANIFOLD PRESS LO
6
S
SHUNT 1 HI 70
SHUNT 1 LO 50 S
SEE NOTE 10 1A 1A
YEL RED
YEL RED
EGT SENSORS TYPE K THERMOCOUPLES
OUT #1 HI OUT #1 LO
OUT #2 HI OUT #2 LO
FUEL PRESS SENSOR KAVLICO P4055-15G (912) UMA N1EU07D (914) B SUPPLY VOLTAGE C OUTPUT A GROUND
NOTE 13
MANIFOLD PRESS SENSOR KAVLICO P4055-30A-E4A OR KAVLICO P500-30A-E4A B SUPPLY VOLTAGE C OUTPUT A GROUND
AMPS 1, UMA 1C4 VARIES W/ TYPE
BATTERY POSITIVE / ALTERNATOR B LEAD
BATTERY CONTACTOR / POWER DISTRIBUTION BUS
Figure G-3.1 GSU 73 - Rotax 912/914 Sensor Wiring Examples, Page 1 of 2
G3X Installation Manual - Rotax Sensor Wiring Examples Page G-4
190-01115-01 Rev. K
GSU 73
J732
POS 5 / TEMP 1
72
POS 5 / TEMP 1
52
S
+5 VDC TRANSDUCER POWER
75
EGT 6 / MISC 1 HI
31
EGT 6 / MISC 1 LO
11
XDCR PWR OUT LO (GROUND)
56
S
SEE NOTE 11
CARB/COOLANT TEMPERATURE ROTAX P/N 965531
COOLANT PRESS SENSOR KAVLICO P4055-50G-E4A B SUPPLY VOLTAGE C OUTPUT A GROUND
Figure G-3.2 GSU 73 - Rotax 912/914 Sensor Wiring Examples, Page 2 of 2
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G3X Installation Manual - Rotax Sensor Wiring Examples Page G-6
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APPENDIX H JABIRU SENSOR WIRING EXAMPLES
NOTES:
1. UNLESS OTHERWISE NOTED, ALL STRANDED WIRE MUST CONFORM TO MIL-W-22759/16 OR EQUIVALENT
2. UNLESS OTHERWISE NOTED, ALL SHIELDED WIRE MUST CONFORM TO MIL-C-27500 OR EQUIVALENT
3. UNLESS OTHERWISE NOTED, ALL WIRES ARE 24 GAUGE MINIMUM.
4. SYMBOL DESIGNATIONS TWISTED SHIELDED SINGLE CONDUCTOR SHIELD TERMINATED TO GROUND
TWISTED SHIELDED SINGLE CONDUCTOR SHIELD FLOATS
TWISTED SHIELDED 4 CONDUCTOR SHIELD TERMINATED TO GROUND
TWISTED SHIELDED PAIR SHIELD TERMINATED TO GROUND
TWISTED SHIELDED PAIR SHIELD FLOATS
TWISTED SHIELDED 4 CONDUCTOR SHIELD FLOATS
S
GARMIN SHIELD BLOCK GROUND
TWISTED SHIELDED 3 CONDUCTOR SHIELD TERMINATED TO GROUND
AIRCRAFT GROUND WIRE SPLICE CONNECTION
TWISTED SHIELDED 3 CONDUCTOR SHIELD FLOATS
COAXIAL CABLE
N/C = NO CONNECTION
5. UNLESS OTHERWISE NOTED, ALL SHIELD GROUNDS MUST BE MADE TO THE RESPECTIVE UNIT BACKSHELLS. ALL OTHER GROUNDS SHOULD BE TERMINATED TO AIRCRAFT GROUND AS CLOSE TO THE RESPECTIVE UNIT AS POSSIBLE.
6. PINOUT SHOWN FOR PACKARD CONNECTOR SUPPLIED WITH KAVLICO PRESSURE TRANSDUCERS. WIRE COLORS ARE SHOWN FOR REFERENCE ONLY, ALWAYS CONFIRM CORRECT SENSOR CONNECTIONS USING SENSOR MANUFACTURER DOCUMENTATION BEFOR CONNECTING WIRES.
7. RESERVED.
8. IN THIS DOCUMENT, AN ASTERISK (*) IS USED FOR SIGNALS THAT ARE ACTIVE LOW (GROUND TO ACTIVATE). ON INSTALLATION WIRING DIAGRAMS, THE MORE TRADITIONAL OVERLINE SYMBOLOGY IS USED.
9. OPTIONAL INSTALLATION.
10. IF INSTALLING UNGROUNDED THERMOCOUPLES, THE LO SIDE MUST BE TAKEN TO A GSU SIGNAL GROUND.
11. THE RPM SIGNAL FOR THE JABIRU 3300 IS TYPICALLY OBTAINED BY TYING INTO ONE OF THE TWO WIRES RUNNING BETWEEN THE ALTERNATOR AND THE ALTERNATOR REGULATOR. ONE OF THE TWO WHITE WIRES ON THE ALTERNATOR SIDE OR ONE OF THE TWO PALE BLUE WIRES ON THE REGULATOR SIDE CAN BE USED FOR THE SIGNAL.
12. IF MEASURING BATTERY CURRENT, PLACE THE SHUNT BETWEEN THE BATTERY POSITIVE TERMINAL AND THE BATTERY CONTACTOR. IF MEASURING ALTERNATOR CURRENT, PLACE THE SHUNT BETWEEN THE ALTERNATOR B LEAD AND THE POWER DISTRIBUTION BUS.
Figure H-1.1 Notes for Jabiru Sensor Drawings (for all Appdx H drawings)
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G3X Installation Manual - Jabiru Sensor Wiring Examples Page H-1
H.1 GEA 24 - Jabiru Sensor Drawings
GEA 24
J243
OIL TEMP HI 33 OIL TEMP LO 32
S
OIL PRESS HI 17 OIL PRESS LO 16
S
RPM 1 8 S
SHUNT 1 HI 37 SHUNT 1 LO 36
WHT BLU S
SEE NOTE 11
SEE NOTE 12
WHT
1A
BLU
1A
FUEL XDCR +12V_1 24 FUEL FLOW 23
FUEL XDCR GND_1 20 S
FUEL PRESS XDCR +5V 3 FUEL PRESS 2
FUEL PRESS GND 1 S
MANIFOLD PRESS XDCR +5V 15 MANIFOLD PRESS 13
MANIFOLD PRESS GND 12 S
SEE NOTE 6
OIL TEMP SENSOR VDO P/N 320021
OIL PRESS SENSOR VDO P/N 360001 OR ELO P/N 206.252.035 OUTPUT GROUND
JABIRU ALTERNATOR PICK-OFF
AMPS 1, UMA 1C4 .0005 OHM
BATTERY POSITIVE / ALTERNATOR B LEAD
BATTERY CONTACTOR / POWER DISTRIBUTION BUS
FUEL FLOW TRANSDUCER EI FT-60 (RED CUBE) OR
FLOSCAN 201B-6
RED WHT BLK
EXCITATION INPUT OUT HI OUT LO/GND
FUEL PRESS SENSOR KAVLICO P4055-15G-E4A
RED GRN BLK
VOLTAGE IN (PIN B) OUTPUT (PIN C) GROUND (PIN A)
MANIFOLD PRESS SENSOR KAVLICO P4055-30A-E4A OR KAVLICO P500-30A-E4A
RED GRN BLK
VOLTAGE IN (PIN B) OUTPUT (PIN C) GROUND (PIN A)
Figure H-2.1 GEA 24 - Jabiru Sensor Wiring Examples, Page 1 of 2
G3X Installation Manual - Jabiru Sensor Wiring Examples Page H-2
190-01115-01 Rev. K
GEA 24
J242
CHT 1 HI 24 CHT 1 LO 12
CHT 2 HI 22 CHT 2 LO 10
CHT 3 HI 20 CHT 3 LO 8
CHT 4 HI 18 CHT 4 LO 6
CHT 5 HI 16 CHT 5 LO 4
CHT 6 HI 14 CHT 6 LO 2
YEL RED
YEL RED
YEL RED
YEL RED
YEL RED
YEL RED
EGT 1 HI 25 EGT 1 LO 13
EGT 2 HI 23 EGT 2 LO 11
EGT 3 HI 21 EGT 3 LO 9
EGT 4 HI 19 EGT 4 LO 7
EGT 5 HI 17 EGT 5 LO 5
EGT 6/MISC 1 HI 15 EGT 6/MISC 1 LO 3
YEL RED
YEL RED
YEL RED
YEL RED
YEL RED
YEL RED
SEE NOTE 10
YEL RED YEL RED YEL RED YEL RED YEL RED YEL RED
YEL RED YEL RED YEL RED YEL RED YEL RED YEL RED
CHT SENSORS TYPE J THERMOCOUPLES
OUT #1 HI OUT #1 LO OUT #2 HI OUT #2 LO OUT #3 HI OUT #3 LO OUT #4 HI OUT #4 LO OUT #5 HI OUT #5 LO OUT #6 HI OUT #6 LO
EGT SENSORS TYPE K THERMOCOUPLES
OUT #1 HI OUT #1 LO OUT #2 HI OUT #2 LO OUT #3 HI OUT #3 LO OUT #4 HI OUT #4 LO OUT #5 HI OUT #5 LO OUT #6 HI OUT #6 LO
Figure H-2.1 GEA 24 - Jabiru Sensor Wiring Examples, Page 2 of 2
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G3X Installation Manual - Jabiru Sensor Wiring Examples Page H-3
H.2 GSU 73 - Jabiru Sensor Drawings
GSU 73
J732
OIL TEMP HI 34 OIL TEMP LO 14
S
POS 3/GP 3/FUEL FLOAT 3 HI
27
POS 3/GP 3/FUEL FLOAT 3 LO
7
S
RPM 17 S
SHUNT 1 HI 70 SHUNT 1 LO 50
WHT BLU S
SEE NOTE 11
SEE NOTE 12
WHT
1A
BLU
1A
+12V TRANSDUCER POWER
55
FUEL FLOW 1 19
XDCR PWR OUT LO (GROUND)
56
S
+5 VDC TRANSDUCER POWER
75
FUEL PRESS HI
26
FUEL PRESS LO
45
XDCR PWR OUT LO (GROUND)
57
S
SEE NOTE 6
MANIFOLD PRESS HI
65
MANIFOLD PRESS LO
6
S
OIL TEMP SENSOR VDO P/N 320021
OIL PRESS SENSOR VDO P/N 360001 OR ELO P/N 206.252.035 OUTPUT GROUND
JABIRU ALTERNATOR PICK-OFF
AMPS 1, UMA 1C4 .0005 OHM
BATTERY POSITIVE / ALTERNATOR B LEAD
BATTERY CONTACTOR / POWER DISTRIBUTION BUS
FUEL FLOW TRANSDUCER EI FT-60 (RED CUBE) OR
FLOSCAN 201B-6
RED WHT BLK
EXCITATION INPUT OUT HI OUT LO/GND
FUEL PRESS SENSOR KAVLICO P4055-15G-E4A
RED GRN BLK
VOLTAGE IN (PIN B) OUTPUT (PIN C) GROUND (PIN A)
MANIFOLD PRESS SENSOR KAVLICO P4055-30A-E4A OR KAVLICO P500-30A-E4A
RED GRN BLK
VOLTAGE IN (PIN B) OUTPUT (PIN C) GROUND (PIN A)
Figure H-3.1 GSU 73 - Jabiru Sensor Wiring Examples, Page 1 of 2
G3X Installation Manual - Jabiru Sensor Wiring Examples Page H-4
190-01115-01 Rev. K
GSU 73
J732
CHT 1 HI 61 CHT 1 LO 41
CHT 2 HI 21 CHT 2 LO 1
CHT 3 HI 2 CHT 3 LO 22
CHT 4 HI 60 CHT 4 LO 40
CHT 5 HI 73 CHT 5 LO 53
CHT 6 HI 33 CHT 6 LO 13
YEL RED
YEL RED
YEL RED
YEL RED
YEL RED
YEL RED
EGT 1 HI 63 EGT 1 LO 43
EGT 2 HI 23 EGT 2 LO 3
EGT 3 HI 24 EGT 3 LO 4
EGT 4 HI 62 EGT 4 LO 42
EGT 5 HI 30 EGT 5 LO 29
EGT 6/MISC 1 HI 31 EGT 6/MISC 1 LO 11
YEL RED
YEL RED
YEL RED
YEL RED
YEL RED
YEL RED
SEE NOTE 10
YEL RED YEL RED YEL RED YEL RED YEL RED YEL RED
YEL RED YEL RED YEL RED YEL RED YEL RED YEL RED
CHT SENSORS TYPE J THERMOCOUPLES
OUT #1 HI OUT #1 LO OUT #2 HI OUT #2 LO OUT #3 HI OUT #3 LO OUT #4 HI OUT #4 LO OUT #5 HI OUT #5 LO OUT #6 HI OUT #6 LO
EGT SENSORS TYPE K THERMOCOUPLES
OUT #1 HI OUT #1 LO OUT #2 HI OUT #2 LO OUT #3 HI OUT #3 LO OUT #4 HI OUT #4 LO OUT #5 HI OUT #5 LO OUT #6 HI OUT #6 LO
Figure H-3.1 GSU 73 - Jabiru Sensor Wiring Examples, Page 2 of 2
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G3X Installation Manual - Jabiru Sensor Wiring Examples Page H-6
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APPENDIX I RS-232 Text Output Format
This data is output from a GDU 37X RX-232 port that has been configured to the "Text Out" format.
I.1 Electrical Interface
The output signals are compatible with RS-232C. Data is generated at 115,200 baud with a word length of 8 bits, one stop bit, and no parity.
I.2 Message Output Selection
Individual text output messages may be enabled or disabled in configuration mode. Enabling or disabling a particular text output message has no effect on other text output messages.
I.3 General Message Output Format
Most text output messages have the following general format:
· Escape character ('=' symbol, 0x3D hex) · ID character · Version character · Data characters (length determined by message ID) · Checksum - 2-character (1-byte) ASCII hex value that is the simple sum of all previous
bytes, including the escape character · Carriage return (0x0D hex) · Line feed (0x0A hex)
An exception to the above is the GPS Data message, which is backwards compatible with the Garmin Simple Text Output format described at:http://www8.garmin.com/support/text_out.html. The GPS Data Message has the following general format:
· Escape character ('@' symbol, 0x40 hex) · Data characters · Carriage return (0x0D hex) · Line feed (0x0A hex)
All text output messages use only printable ASCII characters. For all messages, a value that is out of range, missing, not configured, uncalibrated, or otherwise invalid is indicated by replacing the corresponding bytes within the message with the underscore character ('_', 0x5F hex).
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G3X Installation Manual - RS-232 Text Output Format Page I-1
I.4 Attitude/Air Data Message Format
The Attitude/Air Data message is transmitted approximately 10 times per second.
Table I-1 Attitude/Air Data Message Format
Field Name Escape character Sentence ID Sentence version UTC hour UTC minute UTC second UTC second fraction Pitch Roll Heading Airspeed Pressure altitude
Rate of turn
Lateral acceleration Vertical acceleration
Offset 0 1 2 3 5 7 9 11 15 20 23 27
33
37 40
Width 1 1 1 2 2 2 2 4 5 3 4 6
4
3 3
Units
hours minutes seconds 10 ms 0.1 degree 0.1 degree 1 degree 0.1 knots 1 foot 0.1 degree/ sec 0.01 G 0.1 G
AOA (Angle of Attack) 43
2
Vertical speed Outside air temperature Altimeter setting
Checksum
CR/LF Total length
45
4
49
3
52
3
55
2
57
2
59
10 fpm 1 degree C 0.01 inHg ASCII hex
Notes '=' '1' Currently '1'
positive = up positive = right magnetic
Min
Max
00 00 00 00 -900 -1800 000 0000 -01000
23 59 59 99 +900 +1800 359 9999 +60000
positive = right
-999
+999
positive = leftward
positive = upward
00 = AOA below minimum calibrated value 60 = AOA at calibrated warning threshold value 99 = AOA at or above calibrated stall value Min = 00, Max = 99
positive = up
-99 -99
0
-999
+99 +99
+99
+999
-99
+99
offset from 27.50"
sum of all previous bytes
0x0D / 0x0A
000
400
G3X Installation Manual - RS-232 Text Output Format Page I-2
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I.5 Engine Data Message Format
The Engine Data message is transmitted approximately 5 times per second.
Table I-2 Engine Data Message Format
Field Name Escape character Sentence ID Sentence version UTC hour UTC minute UTC second UTC second fraction Oil pressure Oil temperature RPM Unused Manifold pressure
Fuel flow
Unused Fuel pressure Fuel quantity 1 Fuel quantity 2 Calculated fuel remaining Volts 1 Volts 2 Amps 1 Total aircraft time Engine time CHT6 EGT6 CHT5 EGT5 CHT4 EGT4 CHT3 EGT3 CHT2 EGT2 CHT1 EGT1
Offset 0 1 2 3 5 7 9 11 14 18 22 26
29
32 35 38 41
44
47 50 53 57 62 67 71 75 79 83 87 91 95 99 103 107 111
Width 1 1 1 2 2 2 2 3 4 4 4 3
3
3 3 3 3
Units
hours minutes seconds 10 ms 1 PSI 1 degree C 1 RPM
0.1 inHg 0.1 gallon/ hour
0.1 PSI 0.1 gallon 0.1 gallon
3
0.1 gallon
3
0.1 V
3
0.1 V
4
0.1 A
5
0.1 hour
5
0.1 hour
4
1 degree C
4
1 degree C
4
1 degree C
4
1 degree C
4
1 degree C
4
1 degree C
4
1 degree C
4
1 degree C
4
1 degree C
4
1 degree C
4
1 degree C
4
1 degree C
Notes '=' '3' Currently '1'
calculated from fuel computer
Min Max
00 00 00 00 000 -999 0000
23 59 59 99 999 +999 9999
000 600 000 999
000 999 000 999 000 999
000 999
000 000 -999 00000 00000 -999 -999 -999 -999 -999 -999 -999 -999 -999 -999 -999 -999
320 320 +999 99999 99999 +999 +999 +999 +999 +999 +999 +999 +999 +999 +999 +999 +999
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G3X Installation Manual - RS-232 Text Output Format Page I-3
Field Name TIT1 TIT2
Elevator trim position
Units indicator Flap position Units indicator Carb temp Units indicator Coolant pressure Units indicator Coolant temperature Units indicator Amps 2 Units indicator
Aileron trim position
Units indicator
Rudder trim position
Units indicator Fuel quantity 3 Units indicator Fuel quantity 4 Units indicator Unused Discrete input 1 Discrete input 2 Discrete input 3 Discrete input 4 Unused
Checksum
CR/LF Total length
Table I-2 Engine Data Message Format
Offset 115 119
Width 4 4
159
5
164
1
177
5
182
1
123
5
128
1
153
5
158
1
147
5
152
1
129
5
134
1
165
5
170
1
171
5
176
1
135
5
140
1
141
5
146
1
183
18
201
1
202
1
203
1
204
1
205
12
217
2
219
2
221
Units 1 degree C 1 degree C 1% of travel 1 degree 0.1 degree C 0.01 PSI 0.1 degree C 0.1 A 1% of travel 1% of travel 0.1 gallon 0.1 gallon
ASCII hex
Notes
0 = up, 50 = neutral, 100 = down 'T'
'T'
'C'
'P'
'C'
'A' 0 = left, 50 = neutral, 100=right 'T' 0 = left, 50 = neutral, 100=right 'T'
'G'
'G'
Min -999 -999 +0000
-0090 -9999 +0000 -9999 -9999
+0000
+0000
+0000 +0000
Max +999 +999 +0100
+0090 +9999 +9999 +9999 +9999
+0100
+0100
+9999 +9999
1 = active, 0 = inactive 1 = active, 0 = inactive 1 = active, 0 = inactive 1 = active, 0 = inactive
sum of all previous bytes
0x0D / 0x0A
G3X Installation Manual - RS-232 Text Output Format Page I-4
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I.6 GPS Data Message Format
The GPS Data message is transmitted once per second.
Table I-3 GPS Data Message Format
Field Name Escape character UTC year UTC month UTC day UTC hour UTC minute UTC second Latitude hemisphere Latitude degrees Latitude minutes Longitude hemisphere Longitude degrees Longitude minutes
Position status
Horizontal position error Altitude East/west velocity direction East/west velocity magnitude North/south velocity direction North/south velocity magnitude Vertical velocity direction
Offset 0 1 3 5 7 9 11 13 14 16 21 22 25
30
31 34 40 41 45 46 50
Width 1 2 2 2 2 2 2 1 2 5 1 3 5
1
3 6 1 4 1 4 1
Units
years months days hours minutes seconds
degrees 0.001 minutes
Notes '@' last two digits of UTC year
'N' for north or 'S' for south minutes x 1000
degrees 0.001 minutes
meters meters
'E' for east or 'W' for west
minutes x 1000
'g' = 2D GPS position 'G' = 3D GPS position 'd' = 2D differential GPS position 'D' = 3D differential GPS position 'S' = simulated position '_' = invalid position
height above or below MSL
'E' for east or 'W' for west
0.1 meters/sec
'N' for north or 'S' for south
0.1 meters/sec
'U' for up or 'D' for down
Min
Max
00
99
01
12
01
31
0
23
0
59
0
59
0
90
0
59999
0
180
0
59999
000
999
-99999 +99999
0000 9999
0000 9999
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G3X Installation Manual - RS-232 Text Output Format Page I-5
Field Name
Vertical velocity magnitude
CR/LF
Total length
Table I-3 GPS Data Message Format
Offset 51 55 57
Width 4 2
Units
Notes
0.01 meters/sec
0x0D / 0x0A
Min 0000
Max 9999
For more information on the GPS Data message, see http://www8.garmin.com/support/text_out.html
G3X Installation Manual - RS-232 Text Output Format Page I-6
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