Garmin | G3X Touch™ for Certificated Aircraft | Garmin G3X Touch™ for Certificated Aircraft G3X Touch EFIS Part 23 AML STC Maintenance Manual contains ICA

Garmin G3X Touch™ for Certificated Aircraft G3X Touch EFIS Part 23 AML STC Maintenance Manual contains ICA
Garmin G3X Touch
Electronic Flight Instrument System
Part 23 AML STC Maintenance Manual
Contains Instructions for Continued
Airworthiness for STC SA01899WI
190-02472-02
2019
Revision 2
© Copyright 2019
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.
Garmin International, Inc.
1200 E. 151st Street
Olathe, KS 66062 USA
Telephone: 913-397-8200
www.garmin.com
Garmin (Europe) Ltd.
Liberty House
Bulls Copse Road
Hounsdown Business Park
Southampton, SO40 9RB, UK
Phone: +44 (0) 23 8052 4000
Fax: +44 (0) 23 8052 4004
RECORD OF REVISIONS
Revision
Revision Date
Description
1
03/15/2019
Initial release
2
4/05/2019
Added interface to GPS 175 / GNX 375, limitations for
GTS 8XX and non-Garmin autopilots
ECO #
------
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
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190-02472-02
Revision 2
Page ii
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. A violation of the EAR may be subject to a penalty of up to 10
years imprisonment and a fine of up to $1,000,000 under section 2410 of the Export Administration Act of
the 1979. The preceding statement is required to be included on any and all reproductions in whole or in
part of this manual.
The information on this document is subject to change without notice. For updates and supplemental
information regarding the operation of Garmin products visit www.fly.garmin.com.
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
190-02472-02
Revision 2
Page iii
SOFTWARE LICENSE AGREEMENT FOR GARMIN AVIATION PRODUCTS
BY USING THE DEVICE, COMPONENT OR SYSTEM MANUFACTURED OR SOLD BY GARMIN (“THE
GARMIN PRODUCT’), YOU AGREE TO BE BOUND BY THE TERMS AND CONDITIONS OF THE
FOLLOWING SOFTWARE LICENSE AGREEMENT. PLEASE READ THIS AGREEMENT CAREFULLY.
Garmin Ltd. and its subsidiaries (“Garmin”) grants you a limited license to use the software embedded in
the Garmin Product (the “Software”) in binary executable form in the normal operation of the Garmin
Product. Title, ownership rights, and intellectual property rights in and to the Software remain with Garmin
and/or its third-party providers. You acknowledge that the Software is the property of Garmin and/or its
third-party providers and is protected under the United States of America copyright laws and international
copyright treaties. You further acknowledge that the structure, organization, and code of the Software are
valuable trade secrets of Garmin and/or its third-party providers. You agree not to reproduce, decompile,
disassemble, modify, reverse assemble, reverse engineer, or reduce to human readable form the
Software or any part thereof or create any derivative works based on the Software. You agree not to
export or re-export the Software to any country in violation of the export control laws of the United States
of America.
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
190-02472-02
Revision 2
Page iv
WARNING, CAUTION, and NOTE DEFINITIONS
WARNING
A warning is used to bring to the installer’s immediate attention not only
damage to the equipment, but personal injury may occur if the instruction is
disregarded.
CAUTION
A caution means damage to equipment is possible if procedural step is not followed.
NOTE
A note provides additional information.
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.
WARNING
Perchlorate Material – special handling may apply. Refer to www.dtsc.ca.gov/hazardouswaste/perchlorate.
WARNING
Failure to properly configure the EIS gauges per the POH/AFM and other approved data could result in
serious injury, damage to equipment, or death.
NOTE
All screen shots used in this document are current at the time of publication. Screen shots are intended to
provide visual reference only. All information depicted in screen shots, including software file names,
versions and part numbers, is subject to change and may not be up to date.
NOTE
Ensure no dust or grit accumulates at the bottom of the display glass. The GDU 4X0 display uses
invisible infrared beams for touch detection, this makes it very important to keep the screen clean,
especially along the edges.
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
190-02472-02
Revision 2
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TABLE OF CONTENTS
SECTION
PAGE
1. INTRODUCTION ........................................................................................................................ 1
1.1 Content, Scope, Purpose .................................................................................................... 1
1.2 Organization ........................................................................................................................ 2
1.3 Acronyms & Abbreviations .................................................................................................. 3
1.4 Publications ......................................................................................................................... 5
1.5 Revision and Distribution .................................................................................................... 5
2. SYSTEM DESCRIPTION............................................................................................................ 6
2.1 Equipment Descriptions ...................................................................................................... 7
2.2 G3X Optional Interfaces .................................................................................................... 14
2.3 G3X Touch Architecture Example..................................................................................... 15
2.4 Electrical Power Distribution ............................................................................................. 17
3. G3X CONTROL & OPERATION .............................................................................................. 18
3.1 GDU 4X0 Softkeys/Features and Control ......................................................................... 18
3.2 Display Modes................................................................................................................... 19
4. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ........................................................ 26
4.1 Airworthiness Limitations .................................................................................................. 26
4.2 Servicing Information ........................................................................................................ 27
4.3 Maintenance Intervals ....................................................................................................... 27
4.4 Visual Inspection ............................................................................................................... 29
4.5 Electrical Bonding Test ..................................................................................................... 29
4.6 GSU 25D Earth Magnetic Field Updates .......................................................................... 30
4.7 Special Inspection Requirements ..................................................................................... 30
5. TROUBLESHOOTING ............................................................................................................. 31
5.1 General Troubleshooting .................................................................................................. 31
5.2 CAN Bus Network Troubleshooting .................................................................................. 32
5.3 GDU 4X0 ........................................................................................................................... 35
5.4 GSU 25D ADAHRS and GMU 11 Magnetometer Troubleshooting .................................. 37
5.5 Engine Indication Troubleshooting.................................................................................... 44
5.6 Traffic Alert Messages ...................................................................................................... 45
5.7 Transponder Alert Messages ............................................................................................ 46
5.8 Loss of Navigation Information (External Navigators) ...................................................... 46
5.9 Garmin GFC 500 Failure Messages ................................................................................. 47
5.10 Loss of Non-Garmin Autopilot Heading and/or Course Datum ......................................... 47
5.11 Miscellaneous Alerts ......................................................................................................... 47
5.12 Aircraft Harness/LRU Connectors..................................................................................... 47
6. G3X EQUIPMENT REMOVAL & REINSTALLATION ............................................................. 61
6.1 GDU 4X0 ........................................................................................................................... 61
6.2 GSU 25D ADAHRS ........................................................................................................... 64
6.3 GMU 11 Magnetometer..................................................................................................... 65
6.4 GTP 59 Temperature Probe ............................................................................................. 66
6.5 GAD 27 Electronic Adapter Unit ....................................................................................... 67
6.6 GEA 24 Engine Indicating System .................................................................................... 68
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6.7 GAD 29B ARINC 429 Adapter .......................................................................................... 72
6.8 GDL 5XR Datalink ............................................................................................................. 73
6.9 GPS Antenna (p/n 011-04036-00) .................................................................................... 74
7. G3X EQUIPMENT CONFIGURATION & TESTING ................................................................ 76
7.1 GDU 4X0 ........................................................................................................................... 76
7.2 GSU 25D ADAHRS and GMU 11 Magnetometer ............................................................. 76
7.3 GMU 11 Magnetometer..................................................................................................... 84
7.4 GTP 59 Temperature Probe ............................................................................................. 84
7.5 GAD 27 ............................................................................................................................. 84
7.6 GEA 24 Engine and Airframe Unit .................................................................................... 84
7.7 GAD 29B ........................................................................................................................... 85
7.8 GDL 5XR ........................................................................................................................... 85
7.9 G3X Software Information ................................................................................................. 85
7.10 Activation of GDL 51R/52R SiriusXM Radio and Weather ............................................... 90
8. SYSTEM RETURN TO SERVICE PROCEDURE .................................................................... 91
8.1 Recommended Test Equipment ....................................................................................... 91
8.2 Transponder Check........................................................................................................... 92
8.3 GPS Receiver Check ........................................................................................................ 92
8.4 NAV Receiver Check ........................................................................................................ 94
8.5 ADS-B Traffic Interface Check .......................................................................................... 95
8.6 TIS-A Traffic Interface Check ............................................................................................ 95
8.7 WX-500 Stormscope Interface Check............................................................................... 96
8.8 FIS-B Weather via ADS-B In ............................................................................................. 96
8.9 GDL 51R/52R SXM Weather Check ................................................................................. 96
8.10 GDL 51R/52R SXM Audio Interface Check ...................................................................... 97
8.11 EIS Check ......................................................................................................................... 97
8.12 ADAHRS and Magnetometer Ground Checks .................................................................. 98
8.13 Garmin GFC 500 Autopilot .............................................................................................. 100
8.14 Non-Garmin Autopilot Interface ...................................................................................... 100
8.15 G5 Miscompare Check.................................................................................................... 103
8.16 EMI / RFI Check .............................................................................................................. 103
APPENDIX A
INSTALLATION SPECIFIC INFORMATION ....................................... A-1
A.1 Maintenance Records ..................................................................................................... A-1
A.2 Equipment Locations....................................................................................................... A-2
A.3 Wire Routing ................................................................................................................... A-2
APPENDIX B
EXTERNAL INTERFACE CONFIGURATION ..................................... B-1
B.1 GPS/VHF Nav Interfaces ................................................................................................ B-1
B.2 GPS NAV Interface ......................................................................................................... B-4
B.3 VHF NAV/COM Interface ................................................................................................ B-5
B.4 Traffic and Weather Source ............................................................................................ B-6
B.5 Non-Garmin Autopilot Systems ....................................................................................... B-8
B.6 Audio Panel ................................................................................................................... B-11
B.7 EIS Sensors .................................................................................................................. B-12
B.8 Antennas ....................................................................................................................... B-15
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B.9 ADS-B Antenna Interface .............................................................................................. B-16
LIST OF ILLUSTRATIONS
FIGURE
PAGE
Figure 2-1 – GDU 460 (Single Display, with EIS Optional).............................................................. 8
Figure 2-2 – GDU 470 ...................................................................................................................... 9
Figure 2-3 – GSU 25D ADAHRS ................................................................................................... 10
Figure 2-4 – GMU 11 Magnetometer ............................................................................................. 10
Figure 2-5 – GTP 59 ...................................................................................................................... 11
Figure 2-6 – GAD 29B (ARINC 429 Adapter) ................................................................................ 11
Figure 2-7 – GAD 27 ...................................................................................................................... 12
Figure 2-8 – GEA 24 Engine and Airframe Unit ............................................................................. 12
Figure 2-9 – GDL 52R Data Link ................................................................................................... 13
Figure 2-10 – GPS Antenna ........................................................................................................... 14
Figure 2-11 – G3X Architecture (Summary) .................................................................................. 15
Figure 3-1 – GDU Features and Controls ...................................................................................... 19
Figure 3-2 – Split/Full Format Buttons - GDU 460 ...................................................................... 20
Figure 3-3 – Split/Full Format Buttons - GDU 470 ...................................................................... 20
Figure 3-4 – Normal Mode, Full Format – PFD w/ EIS (Example)................................................. 20
Figure 3-5 – Normal Mode, Split Format – PFD W/ EIS (Example)............................................... 21
Figure 3-6 – Normal Mode, Full – MFD with EIS (Example) .......................................................... 22
Figure 3-7 – GDU Knob Function Example ................................................................................... 23
Figure 3-8 – Data Entry Options (Examples) ................................................................................. 23
Figure 3-9 – Configuration Mode Pages ........................................................................................ 24
Figure 5-1 – Incorrect CAN Bus Topographies .............................................................................. 33
Figure 5-2 – Correct CAN Bus Wiring Example and Node Connections ....................................... 33
Figure 5-3 – Network Error Rate (Configuration/Diagnostic Mode) ............................................... 34
Figure 5-4 – Heading Failure Indication ......................................................................................... 39
Figure 5-5 – Attitude Failure Indication .......................................................................................... 40
Figure 5-6 – Magnetometer Interference Test On-screen Instructions .......................................... 41
Figure 5-7 – Magnetometer Interference Test Progress ................................................................ 42
Figure 5-8 – Magnetometer Interference Test Status .................................................................... 42
Figure 5-9 – Engine/Airframe Failure Indications .......................................................................... 44
Figure 5-10 – View of P4X01 Connector from back of GDU ......................................................... 48
Figure 5-11 – View of P4X02 Connector from back of GDU ......................................................... 48
Figure 5-12 – View of J251 Connector on the GSU 25D ............................................................... 50
Figure 5-13 – View of J252 Connector on the GSU 25D ............................................................... 50
Figure 5-14 – View of J111 Connector on the GMU 11 ................................................................. 51
Figure 5-15 – View of J271 Connector on the GAD 27 ................................................................. 52
Figure 5-16 – View of TB273 Terminal Block on GAD 27 ............................................................. 54
Figure 5-17 – View of J241 Connector on the GEA 24.................................................................. 54
Figure 5-18 – View of J242 Connector on the GEA 24.................................................................. 55
Figure 5-19 – View of J243Connector on the GEA 24................................................................... 56
Figure 5-20 – View of J244 Connector on the GEA 24.................................................................. 57
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Figure 5-21 – View of J291 Connector on the GAD 29B ............................................................... 58
Figure 5-22 – View of J292 Connector on the GAD 29B ............................................................... 59
Figure 5-23 – View of J5X1 Connector on the GDL 5XR .............................................................. 60
Figure 6-1 – GDU 460 Shown, (GDU 470 Similar) ........................................................................ 62
Figure 6-2 – Configuration Module (PFD) ...................................................................................... 63
Figure 6-3 – GDU 460-Mounted GSU 25D (GDU 470 similar) ...................................................... 64
Figure 6-4 – Remote mounted GSU 25D....................................................................................... 65
Figure 6-5 – GMU 11 Magnetometer ............................................................................................. 66
Figure 6-6 – GTP 59 Temperature Probe ...................................................................................... 67
Figure 6-7 – GAD 27 ...................................................................................................................... 68
Figure 6-8 – GEA 24 ...................................................................................................................... 69
Figure 6-9 – Pressure Sensor, Coupling Mount Type ................................................................... 70
Figure 6-10 – Carburetor Air Temperature Sensor Mounting ........................................................ 71
Figure 6-11 – Fuel Flow Transducer Installation Example ............................................................ 72
Figure 6-12 – GAD 29B.................................................................................................................. 73
Figure 6-13 – GDL 5XR (GDL 52R Shown) ................................................................................... 74
Figure 6-14 – GPS Antenna (Screw-mounted Installation Example) ............................................ 75
Figure 6-15 – GPS Antenna (Hook and Loop Installation Example) ............................................. 75
Figure 7-1 – Aircraft Level Attitude ................................................................................................ 78
Figure 7-2 – Pitch/Roll Offset Calibration in Progress ................................................................... 79
Figure 7-3 – Pitch/Roll Offset Completion Status .......................................................................... 79
Figure 7-4 – Compass Rose Starting Position ............................................................................... 80
Figure 7-5 – Magnetometer Calibration On-Screen Instructions ................................................... 80
Figure 7-6 – Magnetometer Calibration Progress .......................................................................... 81
Figure 7-7 – Static Pressure Calibration ........................................................................................ 82
Figure 7-8 – Static Pressure Calibration Warning ......................................................................... 82
Figure 7-9 – Static Pressure Calibration Instructions .................................................................... 82
Figure 7-10 – Static Pressure Calibration in Progress ................................................................... 82
Figure 7-11 – Static Pressure Calibration Completion Status ....................................................... 83
Figure 7-12 – Update Software Window ........................................................................................ 89
Figure 7-13 – Data Link Page ........................................................................................................ 90
Figure 8-1 – Transponder Setup Page (Normal Mode) ................................................................. 92
Figure A-1– Generic Aircraft Figure ............................................................................................. A-3
LIST OF TABLES
TABLE
PAGE
Table 1-1 – Required Documents .................................................................................................... 5
Table 2-1 – G3X Touch AML STC Installed Sensors .................................................................... 12
Table 2-2 – GDL 5XR Data Link Features and Functions ............................................................. 13
Table 2-3 – G3X Touch and Supporting Equipment ...................................................................... 17
Table 2-4 – LRU Current Draw ...................................................................................................... 17
Table 3-1 – LRU Status Indicator Symbols .................................................................................... 24
Table 4-1 – Maintenance Intervals ................................................................................................. 28
Table 4-2 – Electrical Bonding Procedure ..................................................................................... 30
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G3X Touch EFIS Part 23 AML STC
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Table 5-1 – Status LED Indications ............................................................................................... 32
Table 5-2 – LED Indications Recommended Action ...................................................................... 32
Table 5-3 – CAN Network Error Values (Configuration/Diagnostic Mode) .................................... 34
Table 5-4 – Unit Communication Error Messages (Dual GDU Installations) ................................. 36
Table 5-5 – GDU Reboot During Engine Start ............................................................................... 36
Table 5-6 – ADAHRS and Magnetometer Troubleshooting........................................................... 37
Table 5-7 – Magnetometer Interference Test Sequence Example ................................................ 43
Table 5-8 – EIS Gauges Troubleshooting...................................................................................... 44
Table 5-9 – Traffic Alert Troubleshooting....................................................................................... 45
Table 5-10 – Transponder Alert Troubleshooting .......................................................................... 46
Table 5-11 – Loss of Navigation Information (External Navigators) .............................................. 46
Table 5-12 – Miscellaneous Alerts ................................................................................................. 47
Table 5-13 – P4X01/J4X01 Pin Functions ..................................................................................... 48
Table 5-14 – P4X02/J4X02 Pin Functions ..................................................................................... 49
Table 5-15 – P251/J251 Pin Functions .......................................................................................... 50
Table 5-16 – P252/J252 Pin Functions .......................................................................................... 51
Table 5-17 – P111/J111 Pin Functions .......................................................................................... 51
Table 5-18 – GTP 59 Lead Wire Functions ................................................................................... 52
Table 5-19 – P271/J271 Pin Functions .......................................................................................... 52
Table 5-20 – TB273 Terminal Functions........................................................................................ 54
Table 5-21 – P241/J241 Pin Functions .......................................................................................... 54
Table 5-22 – P242/J242 Pin Functions .......................................................................................... 55
Table 5-23 – P243/J243 Pin Functions .......................................................................................... 56
Table 5-24 – P244/J244 Pin Functions .......................................................................................... 57
Table 5-25 – P291/J291 Pin Functions .......................................................................................... 58
Table 5-26 – P292/J292 Pin Functions .......................................................................................... 59
Table 5-27 – P5X1/J5X1 Pin Functions ......................................................................................... 60
Table 6-1 – GDU Configuration Module Kit (P/N 010-12253-01) .................................................. 63
Table 7-1 – GSU 25D/GMU 11 Recalibration Criteria ................................................................... 77
Table 8-1 – LRU Status Indicators ................................................................................................. 91
Table 8-2 – Airspeed Test Points ................................................................................................... 99
Table 8-3 – Heading Verification – ADAHRS Check ................................................................... 100
Table 8-4 – EMI Victim/Source Matrix ......................................................................................... 105
Table A-1 – G3X Post-Installation Log......................................................................................... A-1
Table A-2 – G3X Equipment Locations........................................................................................ A-2
Table B-1 – Compatible Equipment – GPS/VHF Nav Interfaces ................................................. B-1
Table B-2 – Compatible Equipment – GPS NAV ......................................................................... B-4
Table B-3 – Compatible Equipment – VHF NAV/COM ................................................................ B-5
Table B-4 – Compatible Traffic and Weather Sources ................................................................ B-6
Table B-5 – Compatible Equipment – Non-Garmin Autopilots .................................................... B-8
Table B-6 – Compatible EIS Sensors ........................................................................................ B-12
Table B-7 – Supported GPS & SXM Antennas .......................................................................... B-15
Table B-8 – GPS or GPS/WAAS Antenna Minimum Requirements .......................................... B-15
Table B-9 – SXM Satellite Radio Antenna Minimum Requirements .......................................... B-16
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
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Revision 2
Page x
1.
INTRODUCTION
1.1 Content, Scope, Purpose
This document provides Instructions for Continued Airworthiness (ICA) for the Garmin G3X Touch EFIS
Part 23 AML STC as installed in Part 23 aircraft under Supplemental Type Certificate (STC) SA01899WI.
This document satisfies the requirements for continued airworthiness as defined by 14 CFR Part 23.1529
Appendix G. Information in this document is required to maintain the continued airworthiness of the G3X
Touch EFIS systems.
1.1.1 Applicability
This document applies to all aircraft with the G3X Touch system installed in accordance with AML STC
SA01899WI.
Modification of an aircraft by this STC obligates the aircraft operator to include the maintenance
information provided by this document in the operator’s Aircraft Maintenance Manual and the operator’s
Aircraft Scheduled Maintenance Program.
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
190-02472-02
Revision 2
Page 1
1.2 Organization
This manual is structured as described below:
Section 2: System Description
Provides an overview of the G3X Touch EFIS system equipment installed by this STC.
Section 3: Control & Operation
Presents basic control and operation information specifically tailored to maintenance practices. Basic
G3X Touch Configuration Mode operation is also described.
Section 4: Instructions for Continued Airworthiness
Provides maintenance instructions for Continued Airworthiness of the G3X Touch EFIS system.
Section 5: Troubleshooting
Provides troubleshooting information to aid in diagnosing and resolving potential problems with
equipment and functions installed by this STC.
Section 6: G3X Equipment Removal & Replacement
Gives instructions for the removal and replacement of G3X Touch EFIS equipment.
Section 7: G3X Equipment Configuration & Testing
Gives instructions for loading software, configuring, and testing of G3X Touch EFIS equipment.
Section 8: System Return to Service Procedure
Specifies return-to-service (checkout) procedures to be performed upon completion of maintenance of the
G3X Touch EFIS system.
Appendix A: Installation Specific Information
Provides a template to record aircraft-specific installation and configuration data for the G3X Touch EFIS
system.
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
190-02472-02
Revision 2
Page 2
1.3 Acronyms & Abbreviations
AC:
ADAHRS:
ADI:
ADS-B:
ADS-R:
AFCS:
AFM:
AHRS:
ALT:
AML:
AND:
ARINC:
AS:
ASI:
AWG:
BNC:
CAN:
CDI:
CDU:
CE:
CFR:
CHT:
CI:
COM:
CRS:
CS:
DC:
DDM:
DME:
DMM:
ECO:
EEPROM:
EFIS:
EGT:
EIS:
EMC:
EMI:
ES:
FAA:
FF:
FIS-B:
GA:
GAD:
GDL:
GDU:
GEA:
GFC:
GMU:
GNS:
GNX:
GPS:
GPSS:
GSU:
GTN:
GTP:
GTR:
GTS:
GTX:
HDG:
HSDB:
HSI:
IAS:
ICA:
ID:
IFR:
IGRF:
Advisory Circular
Air data, Attitude and Heading
Reference System.
Analog Devices, Inc.
Automatic Dependent Surveillance Broadcast
Automatic Dependent Surveillance Rebroadcast
Aircraft Flight Control System
Airplane Flight Manual
Attitude and Heading Reference System
Altitude Preselect
Approved Model List
Logical AND
Aeronautical Radio, Incorporated
Aerospace Standard
Airspeed Indicator
American Wire Gauge
Bayonet Neill–Concelman
Controller Area Network
Course Deviation Indicator
Control Display Unit
European Committee
Code of Federal Regulations
Chart Processing
Course to Intercept
Communication Radio
Course
Conducted Susceptibility
Direct Current
Difference in Depth of Modulation
Distance Measuring Equipment
Digital Multi Meter
Engineering Change Order
Electrically Erasable Programmable
Read-Only Memory
Electronic Flight Instrument System
Exhaust Gas Temperature
Engine Indication System
Electromagnetic Compatibility
ElectroMagnetic Interference
Extended Squitter
Federal Aviation Administration
Fuel Flow
Flight Information Service Broadcast
Go-Around
Garmin Adapter
Garmin Datalink LRU
Garmin Display Unit
Garmin Engine and Airframe Unit
Garmin Automatic Flight Control System
ILS:
KTS:
LCD:
LED:
LNAV:
LOC:
LRU:
METAR:
MFD:
MFR:
NEXRAD:
NMEA:
OAT:
OBS:
OR:
PFD:
POH:
RPM:
RTCA:
RX:
SAS:
SD:
STC:
SXM:
SYS:
TAS:
TAWS:
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
Garmin Magnetometer Unit
Garmin Navigation System
Garmin Navigator Transponder
Global Positioning System
GPS Roll Steering
Garmin Sensor Unit
Garmin Touch Navigator
Garmin Temperature Probe
Garmin Transmitter / Receiver
Garmin Traffic System
Garmin Transponder
Heading (mode)
High Speed Data Bus
Horizontal Situation Indicator
Indicated Air Speed
Instructions for Continued Airworthiness
Identifier
Instrument Flight Rules
International Geomagnetic Reference
Field
Instrument Landing System
Knots
Liquid Crystal display
Light Emitting Diode
Lateral Navigation
Localizer
Line-Replaceable Unit
Meteorological Terminal Aviation
Routine Weather Report
Multi-Function Display
Manufacturer
Next-Generation Radar
National Marine Electronics Association
Outside Air Temperature
Omni Bearing Selector
Logical OR
Primary Flight Display
Pilot’s Operating Handbook
Revolutions per Minute
Radio Technical Commission for
Aeronautics
Receive
Stability Augmentation System
SanDisk Memory
Supplemental Type Certificate
Sirius XM
System
Traffic Advisory System
OR
True Airspeed
Terrain Awareness and Warning System
190-02472-02
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TCAS:
TIS:
TIS-A:
TIS-B:
TIT:
TNC:
TSO:
TX:
UAT:
UHF:
VDC:
VFR:
VHF:
VLOC:
VNAV:
VOR:
WAAS:
WPT:
XM:
Traffic Collision Avoidance System
Traffic Information Service
Traffic Information Service-A
Traffic Information Service - Broadcast
Turbine Inlet Temperature
Threaded Neill–Concelman
Technical Standard Order
Transmit
Universal Access Transceiver
Ultra High Frequency
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
Volts of Direct Current
Visual Flight Rules
Very High Frequency
VOR/Localizer
Vertical Navigation
VHF Omni Directional Radio Range
Wide Area Augmentation System
Waypoint
XM Satellite Radio
190-02472-02
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1.4 Publications
The following documents are required by this maintenance manual to perform maintenance. It is the
responsibility of the owner / operator to ensure latest versions of these documents are used during
operation, servicing or maintenance of the airplane.
Table 1-1 – Required Documents
Document Number
Garmin Document Title
190-02472-00
Garmin G3X Pilot’s Guide for Certified Aircraft
190-02472-01
Garmin G3X Touch EFIS Part 23 AML STC Installation Manual
1.5 Revision and Distribution
This document is required for maintaining the continued airworthiness of the aircraft. When this document
is revised, each page will also be revised to indicate the current revision level.
Garmin Dealers may obtain the latest revision of this document on the Garmin Dealer Resource Center
website.
Owners/operators may obtain the latest revision of this document by one of the following methods:

Visit https://fly.garmin.com/support

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Maintenance Manual
G3X Touch EFIS Part 23 AML STC
190-02472-02
Revision 2
Page 5
2. SYSTEM DESCRIPTION
This section provides an overview of the line replaceable units (LRUs) installed by the G3X Touch EFIS
Part 23 AML STC.
The Garmin G3X Touch EFIS replaces the standard pneumatic instruments (altimeter, airspeed indicator
(ASI) and vacuum attitude gyro indicator) and combines primary flight instrumentation, aircraft systems
instrumentation, and navigational information, all displayed on one- or two-color Garmin Display Units
(GDU) 4X0. The following functionalities can be provided by the G3X Touch EFIS system:

Primary Flight Display (PFD)

Multi-Function Display (MFD)

Optional Engine Indicating System (EIS)

Optional Traffic and Weather Receiver (ADS-B In)
 Optional SiriusXM Weather and Radio (subscription required)
A G3X system installed per this STC may consist of one of the following display configurations:
1. Single 7-inch GDU 470 (portrait orientation) PFD with the capability to be split into a PFD/MFD
configuration but with no support for EIS.
2. Single 10.6-inch GDU 460 with PFD/MFD split capability and EIS supported.
3. Dual 7-inch GDU 470 (portrait orientation), one configured as PFD and the other as MFD, with
EIS only supported on the MFD.
4. Single 7-inch GDU 470 (portrait orientation) as PFD and a single 10.6-inch GDU 460 as MFD with
the EIS only supported on 10.6-inch MFD.
5. Single 10.6-inch GDU 460 as PFD and a single 7-inch GDU 470 (portrait orientation) as MFD,
with the EIS supported in either the PFD or MFD.
When two GDUs are installed, one as PFD and the other as an MFD, failure of one display unit will cause
the system to automatically revert to a reversionary format. In the reversionary format, primary flight
information, radio tuning information and EIS (if installed) are displayed on the remaining GDU.
Additionally, a multi-function pane can be displayed if the “split” touchscreen button is selected.
Each of the above display configurations require the following LRUs and equipment as part of the
installation:

GSU 25D Air Data Computer, Aircraft Heading and Reference System (ADAHRS)

GMU 11 Magnetometer

GTP 59 Temperature Probe

GPS Antenna

GEA 24 Engine and Airframe adaptor (Optional) (required for EIS)

GAD 27 Electronic Adapter Unit (required for 14-volt aircraft with EIS and optional for 14-volt
aircraft without EIS).
Standby attitude, airspeed, and altitude instruments are required if a G3X display unit is installed as the
primary flight display (PFD) in IFR installations. The standby instruments may be a Garmin G5 or existing
pneumatic instruments.
The G3X system is composed of several sub-units or Line Replaceable Units (LRUs). The LRUs have a
modular design and can be installed directly behind the instrument panel or mounted directly on the panel
in the case of a GDU, or in a separate location. Each LRU has a particular function, or set of functions, as
described in their applicable sections.
A GPS antenna is required for G3X installations. The GDU contains an internal WAAS GPS receiver
which supports VFR navigation only. IFR navigation requires a compatible certified navigator that can
interface to the G3X system and display flight plan and guidance on the GDU. Alternatively, navigation
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G3X Touch EFIS Part 23 AML STC
190-02472-02
Revision 2
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equipment that is not compatible with G3X can retain their separate external indicator to maintain IFR
capability. The external indicator installation is outside the scope of this STC.
G3X systems using optional SiriusXM (SXM) or ADS-B receivers require dedicated antennas which are
not installed under this STC.
2.1 Equipment Descriptions
2.1.1
GDU 460
The Garmin Display Unit (GDU) 460 provides a central display and user interface for the G3X Touch EFIS
Touch system. GDU 460 is a 10.6-inch landscape-oriented, panel mounted control and display unit with
a GPS receiver. The GDU features a high-resolution infrared touchscreen user interface augmented by a
set of dual-concentric knobs and dedicated buttons for commonly used functions. The GDU 460 is
mounted flush to the aircraft instrument panel on the left side within the pilot’s primary field of view. Below
is a list of some of the functions provided by the GDU 460.
Many of the listed functions depend on optional equipment interfaces and/or subscription services.
PFD Functions
 Primary attitude, heading, and air data information
 Slip/skid and rate-of-turn indication
 Synthetic Vision including Pathways and Flight Path Marker
 Horizontal Situation Indicator (HSI)
 Flight Director display with GFC500 autopilot modes and alerts
 Clock and timer
MFD Functions
 Moving map with VFR flight planning function
 Charts and SafeTaxi
 Traffic display and alerting
 Terrain and obstacle display and alerting
 Datalink weather

Display of flight plan and navigation from an external Garmin GPS navigator

Display of navigation from an external VOR/ILS NAV radio
 Control and display of Transponder and Com radios
System Interfaces

Display engine parameters when configured and interfaced with a Garmin Engine Adapter (GEA
24).

Wireless Bluetooth transceiver that can communicate with tablet computers and other Garmin
devices that support Connext interface protocol. Refer to G3X Touch Pilot’s Guide for Certified
Aircraft (190-02472-00) for guidance in using Connext Bluetooth connections.

CAN and RS-232 interfaces to communicate with Garmin LRUs and other devices. Refer to the
appropriate sections in G3X Touch EFIS Part 23 AML STC Installation Manual (190-02472-01)
for interconnect and configuration information.
 BNC connector for GPS antenna (only required on PFD)
One GDU 460 may be installed as a single PFD (see Figure 2-1) or with a GDU 470 in a dual display
configuration.
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Figure 2-1 – GDU 460 (Single Display, with EIS Optional)
2.1.2
GDU 470
The Garmin Display Unit (GDU) 470 provides a central display and user interface for the G3X Touch EFIS
Touch system. The Garmin Display Unit (GDU) 470 is a 7-inch LCD portrait-oriented panel mounted
control and display unit with a GPS receiver. The GDU features a high-resolution infrared touchscreen
user interface augmented by a set of dual-concentric knobs and dedicated buttons for commonly used
functions. The GDU 470 is mounted flush to the aircraft instrument panel on the left side within the pilot’s
primary field of view. Below is a list of some of the functions provided by the GDU 470.
Many of the listed functions depend on optional equipment interfaces and/or subscription services.
PFD Functions
 Primary attitude, heading, and air data information
 Slip/skid and rate-of-turn indication
 Synthetic Vision including Pathways and Flight Path Marker
 Horizontal Situation Indicator (HSI)
 Flight Director display with GFC500 autopilot modes and alerts
 Clock and timer
MFD Functions
 Moving map with VFR flight planning function
 Charts and SafeTaxi
 Traffic display and alerting
 Terrain and obstacle display and alerting
 Datalink weather
 Display of flight plan and navigation from an external Garmin GPS navigator
 Display of navigation from an external VOR/ILS NAV radio
 Control and display of Transponder and Com radios
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System Interfaces

Display engine parameters when configured and interfaced with a Garmin Engine Adapter (GEA
24).

Wireless Bluetooth transceiver that can communicate with tablet computers and other Garmin
devices that support Connext interface protocol. Refer to G3X Touch Pilot’s Guide for Certified
Aircraft (190-02472-00) for guidance in using Connext Bluetooth connections.
 CAN and RS-232 interfaces to communicate with Garmin LRUs and other devices. Refer to the
appropriate sections in the G3X Touch EFIS Part 23 AML STC Installation Manual (190-0247201) for interconnect and configuration information.
 BNC connector for GPS antenna (only required on PFD)
One GDU 470 may be installed as a single PFD configuration (see Figure 2-2) or two GDU 470s as a
dual PFD and MFD configuration. EIS is only supported on a GDU 470 configured as an MFD in a dual
display system. A GDU 470 may also be installed with a GDU 460 in a dual display configuration.
The display on a 7” GDU when configured as an MFD (in a dual display configuration) does not have split
format functionality in normal mode but is available in reversionary mode if the PFD fails.
NOTE
EIS is not supported in a single GDU 470 installation.
Figure 2-2 – GDU 470
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2.1.3
GSU 25D ADAHRS
The GSU 25D is an LRU that provides Air Data Computer and Attitude Heading Reference System
(ADAHRS) information. The GSU 25D interfaces to a remote mounted GMU 11 magnetometer for
heading information, and computes OAT and TAS from inputs provided by the GTP 59. The GSU 25D is
connected to existing primary pitot/static system. Only one GSU 25D is approved for installation and
interface by this STC.
Figure 2-3 – GSU 25D ADAHRS
2.1.4
GMU 11 Magnetometer
The Garmin GMU 11 Magnetometer is a remote mounted device that provides magnetic field
measurements to the GSU 25D to support computation of flight attitude and heading data.
Figure 2-4 – GMU 11 Magnetometer
2.1.5
GTP 59 Temperature Probe
The Garmin GTP 59 is an externally mounted temperature probe that provides raw outside air
temperature data. The device is a three-wire temperature probe interface.
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Figure 2-5 – GTP 59
2.1.6 GAD 29B ARINC 429 Adapter (Optional)
The GAD 29B allows the G3X system to interface to IFR GPS navigators such as the Garmin GPS 175,
GNX 375, GNS and GTN series. It also allows for interface to some non-Garmin autopilots.
Figure 2-6 – GAD 29B (ARINC 429 Adapter)
2.1.7
GAD 27 Electronic Adapter Unit
The GAD 27 provides a stabilized 12V power output to keep EIS online during engine start when battery
voltage drops. It is installed on airplanes with a 14-volt electrical system that install the G3X EIS option. It
may be installed on aircraft with a 14-volt electrical system that do not have EIS to prevent reboot during
temporary low battery voltage levels. Refer to Appendix A.1 for installed equipment. GAD 27 is not
installed in aircraft with 28-Volt electrical systems.
If a GAD 27 is not installed on 14-Volt aircraft and a PFD/MFD reboot is observed, troubleshoot the
aircraft per guidance in Section 5.3.5.
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Figure 2-7 – GAD 27
2.1.8
GEA 24 Engine/Airframe Unit
The Garmin Engine and Airframe (GEA) 24 is an input/output system used to monitor and power engine
and airframe sensors. The GEA 24 is used to monitor and display engine data for single engine aircraft
with up to 6 cylinders.
Figure 2-8 – GEA 24 Engine and Airframe Unit
2.1.8.1 EIS Functionality
If a GEA 24 is installed, configured engine data and airframe parameters are displayed on the GDU. This
manual only provides information for the EIS sensors that were installed by the G3X Touch EFIS Part 23
AML STC. Table 2-1 lists the sensors that are maintained in this manual. Refer to the applicable
maintenance data and/or TSO manual for other sensors that are interfaced to the EIS.
Table 2-1 – G3X Touch AML STC Installed Sensors
Function
Description
Garmin Part Number
Oil Pressure
Garmin 150 PSIG Pressure
011-04202-30
Oil Temperature
UMA T3B3-2.5G (K Type Probe)
494-70009-00
Manifold Pressure
Garmin 30 PSIA Pressure
011-04202-00
Carb Air Temperature
UMA T3B10-SG (K Type Probe)
494-70010-00
Fuel Pressure
Garmin 75 PSIG Pressure
011-04202-20
Garmin 15 PSIG Pressure
011-04202-10
EI FT-60
494-10001-00
EI FT-90
494-10001-01
Fuel Flow & Return FF
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2.1.9 GDL 5XR Data Link
GDL 5XR provides the data and functions shown in Table 2-2 via Bluetooth® wireless technology and/or
over wired connections.
Table 2-2 – GDL 5XR Data Link Features and Functions
GDL 50R
GDL 51R
GDL 52R
ADS-B Receiver (Traffic and
Weather)
Sirius XM Receiver
(Weather/audio)
ADS-B Receiver (Traffic and
Weather) and Sirius XM
Receiver (Weather/audio)
The GDL 5XR are remote mounted and require external antennas and power connections. No battery is
provided.
The GDL 50R/52R receives Traffic (ADS-B/ADS-R and TIS-B) on both Universal Access Transceiver
(UAT) and 1090 ES (Extended Squitter) frequency bands. When in range of a ground station, these units
will receive FIS-B weather over the UAT link.
The GDL 5XR products provide information to G3X Touch displays via RS-232 and to devices running
Garmin Pilot™ via a Connext® data connection (via Bluetooth®). Please see additional information in the
G3X Touch Pilot's Guide for Certified Aircraft (190-02472-00).
Figure 2-9 – GDL 52R Data Link
2.1.10 Antennas
The optional glareshield-mounted GPS antenna (Garmin part number 011-04036-00) feeds a GPS
receiver inside the GDU which provides position, velocity, and time data to support various display
functions. The GPS data is also passed on to the GSU 25D to provide improved AHRS performance.
A GPS antenna must be connected to the PFD. In a dual display G3X installation the PFD will pass GPS
data to the MFD. A second GPS antenna is not required but may optionally be installed and connected to
the MFD for redundancy.
There are other GPS antennas which are compatible with the GDUs, reference Table B-7 for more
information.
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Figure 2-10 – GPS Antenna
2.2 G3X Optional Interfaces
See APPENDIX B for equipment that may be connected to and interfaced with a G3X Touch system.
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2.3 G3X Touch Architecture Example
RS-232
GAD 27
(Opt ional)
14 V
Aircraft
Pitot
GDL 5xR
(ADS-B In and/or
SXM)
(Opt ional)
14 V
14 V
S
to
GEA24
GDU 4x0
PFD
GFC500
Aircraft
Static
GTP 59
OAT
4
A
GSA 28
Yaw Servo
(Opt ional)
(Opt ional)
P
S
GSU 25
ADAHRS
RS-232
GMC 507
A/P Controller
(Backup
ADAHRS)
P
G5
1
Standby
GSA 28
Pitch Servo
GSA 28
Roll Servo
GSA 28
Trim Servo
(Optional)
(Opt ional)
(Opt ional)
(Opt ional)
RS-232
RS-232
CAN BUS
2
RS-232
RS232
2
RS-232
RS-232
GTS 8XX
TAS/TCAS
(Opt ional)
5
GTX
Transponder
A429
(Opt ional)
RS-232
Connext
(Flt Plan
Xfer)
HSDB
Mono
Audio
RS-232
GEA 24
EIS
(Backup EIS)
GDU 4x0
MFD
Stereo
Audio
14 V from
GAD27
(Opt ional)
WX-500
Storm
scope
2
RS-232
GMU 11
(Opt ional)
RS-232
Engine/
Airframe
Sensors
RS-232
(Optional)
RS-232
(ADS-B)
MapMx
MapMx
3
No. 1 GPS/COM
A429
(NAV)
A429
(GPS)
GAD 29B
Data
Concentrator
A429
(Air Data)
(Opt ional)
A429
(NAV)
Optional)
RS-232
3,6
No. 2 GPS/COM
(Opt ional)
A429
(GPS)
KEY:
Analog
CRS & HDG
Audio Panel
Optional
G3X Equip
Non-Garmin
Autopilot
(Opt ional)
Sta ndard
G3X Equip
Garmin COM or
3,6
NAV/COM
6
Inte rfa cing
Equip
(Opt ional)
Figure 2-11 – G3X Architecture (Summary)
Notes:
(1) Backup instruments for a G3X PFD installation may be either a G5 ADI or pneumatic instruments
(vacuum AI, airspeed indicator, altimeter). If GFC500 is installed with a G3X PFD, a G5 is not
required if a Sonalert is installed.
(2) HSDB & RS232 Connext interfaces are only applicable with GNX 375 or GTX 345() to support
FIS-B weather & TIS-B traffic display on GTN & GDUs.
(3) Maximum of two (2) COM/NAV units installed.
(4) GAD 27 required for 14v airframes with EIS and may optionally be connected to PFD and GSU
25D in 14v airframes without EIS.
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(5) A GTS 8XX traffic system cannot be interfaced to the GDU if an ADS-B In transponder such as
the GTX 345(R) or GNX 375 is installed.
(6) If a non-Garmin autopilot is installed, only one external navigator (GPS and/or VHF) can be
connected to G3X. A second navigator, if installed, must use a dedicated CDI and cannot
interface to G3X.
GDU 232 Ports:
GDUs have six RS-232 ports. Except as noted below, the ports can be connected to any compatible LRU
and if multiple GDUs are installed they will share the data between them on the CAN bus. The RS-232
architecture shown above is only an example configuration.
The port on the P4x01 connector is only compatible with the GSU 25D or GEA24. The five ports on
P4x02 can be configured for any supported interface (including GSU 25D and GEA 24).
When two external navigators are connected, the #1 Nav must be connected to a lower numbered RS232 port on the PFD, and the #2 Nav connected to either a higher numbered port on the PFD or any 232
port on the MFD.
GTN Connext interface must be connected to PFD1.
Weather data is not shared between GDUs, therefore the traffic/weather receiver (GNX 375, GTX 345() or
GDL 5xR) should be connected via RS-232 to each GDU. If both SXM and ADS-B In are desired in a
fully optioned single GDU installation (PFD, EIS, and dual Garmin navigators), a GDL 52R should be
used for 232 port availability considerations (the 52R sends both SXM and FIS-B/TIS-B on one RS-232
bus). Note however that the GDL 5xR is not compatible with the GTN, so if ADS-B traffic & weather
display is desired on both G3X and GTN it must be sourced from a GNX 375 or GTX 345() per Note 2
(alternatively, the GTN could use GDL 88 or GDL 69, but these are incompatible with G3X).
GTX 335R/345R:
RS-232 port 1 on the GTX335R/345R must be used to connect to the GSU 25D.
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Table 2-3 – G3X Touch and Supporting Equipment
EQUIPMENT
GDU 4X0
GSU 25D
GMU 11
GTP 59
GAD 27
GPS Antenna (011-04036-00)
GAD 29B
GDL 5XR
GEA 24
SUPPLIER
QTY
STANDARD/
OPTIONAL
Garmin
Garmin
Garmin
Garmin
Garmin
Garmin
Garmin
Garmin
Garmin
1 or 2
1
1
1
1
1
1
1
1
Standard
Standard
Standard
Standard
Standard/Optional*
Optional
Optional
Optional
Optional
*Reference Section 2.1.7 for applicability.
2.4 Electrical Power Distribution
Electrical load information for the G3X Touch EFIS system LRUs is provided below in Table 2-4.
Appendix A of this document contains details specific to the load changes for the specific aircraft
installation.
Table 2-4 – LRU Current Draw
LRU
GAD 27
Current Draw – Maximum Amps
14V System
28V System
Typical
Max
Typical
Max
0.1A
0.1A
N/A
N/A
GAD 29B
0.1A
0.2A
0.1A
0.1A
GDL 50R
0.1A
0.3A
0.1A
0.1A
GDL 51R
0.1A
0.2A
0.1A
0.1A
GDL 52R
0.2A
0.3A
0.1A
0.2A
GDU 460
1.0A
2.0A
0.5A
1.0A
GDU 470
0.6A
1.3A
0.4A
0.7A
GEA 24
0.2A
0.4A
0.1A
0.2A
GSU 25, GMU11,
GTP 59
0.25A
0.35A
0.125A
0.175A
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3.
G3X CONTROL & OPERATION
The Garmin G3X Touch EFIS is intended for Part 23 aircraft covered by the AML STC # SA01899WI.
The following is an overview of G3X Touch panel-mounted units and display features that are provided by
the G3X Touch EFIS.
3.1 GDU 4X0 Softkeys/Features and Control
The GDU 4X0 does not have a power button and will turn ON when power is applied to the aircraft. G3X
Touch remote-mounted LRUs also do not have dedicated power buttons but will turn ON when battery
power is applied to the aircraft or the dedicated bus power (avionics power) is applied. The G3X GDU has
the following controls as shown in Figure 3-1:







Dual Concentric Knobs – Control knobs that can be used to scroll and select through various
options on the display. Pressing the knob acts as an enter or selection of the currently highlighted
information. The function of each knob on the lower bezel is context sensitive and is identified on
the screen just above the associated knob. Reference Section 3.2.2.1 for using the GDU knob in
configuration mode.
Menu Button – Used to enter configuration or configuration/diagnostic mode. Reference Garmin
G3X Touch EFIS Part 23 AML STC Installation Manual (190-02472-01) for specific functions
covered in various pages in configuration mode. In normal mode, pressing the MENU button once
brings up the “PFD options” and twice will bring up the “Main Menu”.
Back Button – Used to return to a previous section/page.
Direct to – Not used in configuration mode.
NRST Button – Used in conjunction with the MENU button to enter diagnostic mode or with
MENU and BACK buttons to reboot the GDU. No other functions in configuration mode.
Photocell – The photocell may be configured to be used by the display to automatically adjust
the display backlighting in reference to ambient light conditions.
SD Card Slot – A card slot in the display that accepts standard SD cards. The following list
shows the tasks that can be performed via the SD card slot with an SD card installed:
o Update databases
o Software updates
o Datalogging
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PHOTOCELL
SD CARD SLOT
Figure 3-1 – GDU Features and Controls
KNOB
Nearest
(NRST)
DIRECT TO
MENU
BACK
KNOB
3.1.1 GDU Reboot


To reboot GDU without turning off aircraft power, simultaneously and momentarily press the
BACK, MENU and NRST buttons. If the GDU is in configuration mode, it will reboot to normal
mode.
In configuration mode the GDU may be rebooted back to normal mode by selecting the “Save
and Reboot” page.
3.2 Display Modes
3.2.1 Normal Display Mode
PFD: Two PFD display formats are available in normal mode and controlled by the split/full touch field on
the upper portion of the display. Refer to Figure 3-2 and Figure 3-3:


Full display – occupies the entire width of the display
Split format – 50/50 percent display of PFD instrumentation and a Multi-function pane/window, or
a 20/40/40 percent display when the engine bar is present.
The location of the split/full button and the format to be displayed at power up are configured in the
Display Configuration page.
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Figure 3-2 – Split/Full Format Buttons - GDU 460
Figure 3-3 – Split/Full Format Buttons - GDU 470
The location of the split/full button and the format to be displayed at start up, are configured in the Display
Configuration page.
Figure 3-4 – Normal Mode, Full Format – PFD w/ EIS (Example)
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Figure 3-5 – Normal Mode, Split Format – PFD W/ EIS (Example)
MFD: provides a multi-function area with various pages and EIS if configured. The display on a 7” GDU
470 when configured as an MFD does not have split format functionality in normal mode but is available
in reversionary mode if the PFD fails. In its place the button is used to toggle between PFD and MFD
functionality.
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Figure 3-6 – Normal Mode, Full – MFD with EIS (Example)
3.2.1.1 Reversionary Mode
In a dual display installation, a reversionary display mode is supported in the event of GDU failure. When
two GDUs are installed, one as PFD and the other as an MFD, the system will automatically revert the
functioning GDU to a reversionary format in the event of a GDU failure. In the reversionary mode,
primary flight information, radio tuning information and EIS (if installed) are displayed on the remaining
GDU.
3.2.2 Configuration Mode Overview
Throughout this document, references are made to the GDUs being in configuration mode. The
configuration mode exists to provide the avionics technician with a means of configuring, checking, and
calibrating various G3X Touch system.
To enter configuration mode:
1. Hold down the “MENU” key on the GDU 4X0 while applying power to the aircraft, until the display
shows “Configuration Mode" text.
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2. Use the “Move Selector” knob or by touching the display panel to make selections and changes.
3. After all configuration changes have been made, use the “Save & Reboot” page to save all
changes and return to normal mode.
NOTE
For a complete description and breakdown of each Configuration Mode page, refer to the G3X
Touch EFIS Part 23 AML STC Installation Manual (190-02472-01).
3.2.2.1 GDU Knob
The GDU knob has dual concentric knobs; a small inner and a larger outer. GDU 460 has two knobs, one
on each side of the lower section, while GDU 470 has one on the right side of the lower section of the
GDU. The function of each knob on the lower bezel is context sensitive and is identified on the screen just
above the associated knob. If both inner and outer knobs have the same function, the function will be
displayed on the screen above the knob; for example, “Move Selector”, “Scroll List”, etc. may be
displayed. If the inner and outer knobs have the different functions that would be displayed on the screen.
As shown below in Figure 3-7, the outer knob is used to select a tab and the inner knob is used to scroll
down a list.
Figure 3-7 – GDU Knob Function Example
To cycle through different configuration pages:
To scroll to a particular page: Rotate either the large outer or small inner knob or use the touch
panel.
To select a page: Press/push the inner knob or touch the page on the display.
To navigate between different tabs on a page: Rotate the large outer knob or use the touch panel.
To scroll down a list/data field in a tab: Rotate the inner knob or use the touch panel.
To select a data field: Press/push the inner knob or use the touch panel.
3.2.2.2 Configuration Data Entry
To change the contents of a highlighted data field, use the either the pop-up keyboard, pop-up keypad,
pop-up slider bar or touch panel as applicable.
Figure 3-8 – Data Entry Options (Examples)
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3.2.2.3 System Status Indicators
The “System Information” page in the configuration mode of the GDU 4X0 PFD has a “Devices Online”
tab that reports the status of installed LRU’s and their currently installed software part numbers and
versions. The icon/checkbox next to each LRU reports a green checkmark, a ‘red x’ or blank checkbox to
indicate the status of each LRU as described in Table 3-1.
Table 3-1 – LRU Status Indicator Symbols
INDICATION
LRU CONDITION
The LRU is online and reports the item located next to the
indicator box is communicating.
The LRU is online, and reports the item located next to the
indicator box is not communicating, a fault, warning, or
error has been detected.
The LRU is not online.
3.2.2.4 Configuration Mode Navigation
Using the PFD knob and data entry options as described in Sections 3.2.2.1 and 3.2.2.2 a user can
navigate through different pages and page groups in the Configuration Mode. Reference the Garmin G3X
Touch EFIS Part 23 AML STC Installation Manual (190-02472-01) on how to make configuration
changes.
NOTE
Some configuration pages appear only when certain optional LRUs are installed and configured.
Figure 3-9 – Configuration Mode Pages
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3.2.3 Configuration/Diagnostic Mode
Troubleshooting and diagnostic information for CAN bus can be viewed in Configuration/Diagnostic
mode. For CAN troubleshooting information, reference section 5.2.
To enter configuration/diagnostic mode:
1. Simultaneously hold down the “MENU” and “NRST” key on the GDU 4X0 while applying power to
the aircraft, until the “Configuration/diagnostic Mode” text is displayed on the screen.
2. Use the “Move Selector” knob or touch panel to make selections as necessary.
3. After all configuration changes have been made, use the “Save & Reboot” page to save all
changes and return to normal mode.
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4.2 Servicing Information
G3X Touch EFIS LRUs maintenance is ‘on condition’ only. No component-level overhaul is required for
the G3X Touch EFIS Part 23 AML STC installation. See section 6 for equipment removal and installation.
4.2.1
On-condition Servicing
‘On Condition’ replacement and/or servicing should occur when an item exhibits conditions, symptoms,
and/or abnormalities defined in Section 5 of this manual. Replacement and/or servicing should be made
only after the technician troubleshoots the system to the extent determined necessary by using the
guidance in this manual along with common avionics maintenance practices.
NOTE
It is impossible to provide guidance for every conceivable failure scenario within the scope of this manual.
Every effort has been made to provide comprehensive guidance for possible failures. The information in
this document should always be combined with sound aviation maintenance practices and a thorough
knowledge of the system. Use sound avionics maintenance practices when working around or on G3X
equipment.
NOTE
After replacing or servicing electrical components near the GMU 11 magnetometer, the Magnetometer
Interference Test (reference Section 5) and Magnetometer Calibration Procedure (reference Section 7)
must be performed.
The remainder of this document is organized in the following fashion:

Section 4.3 lists maintenance requirements related to the G3X system.

Section 5 provides troubleshooting guidance

Section 6 gives instructions regarding the removal and replacement of physical G3X Touch EFIS
equipment and parts.

Section 7 gives configuration and testing instructions to be accomplished if G3X Touch EFIS
equipment or parts are removed or replaced.

Section 8 specifies system return-to-service procedure.
4.2.2 Required Tools
The following tools are needed to perform maintenance tasks on G3X equipment:

SanDisk brand SD card, 8GB or smaller

Calibrated Milliohm meter with Kelvin probes or equivalent

Calibrated digital level

Calibrated air data test set (pitot/static ramp tester)

Calibrated VHF NAV/COM/ILS ramp tester or equivalent

Outdoor line-of-site to GPS satellite signals or GPS indoor repeater

Headset/microphone

Ground Power Unit

Calibrated torque wrench

Standard sockets & wrenches

3/32” Hex tool
4.3 Maintenance Intervals
Table 4-1 shows systems and items installed by this STC, which must undergo tests or checks at specific
intervals.
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Table 4-1 – Maintenance Intervals
Description/Procedure
Manual
Section No.
Interval
G3X Touch System Visual
Inspections
Complete Visual Inspection of all
installed G3X system LRUs and wiring
harnesses must be performed to ensure
continued integrity of the installation.
0
12 Calendar Months
(During annual
inspection)
Electrical Bonding Check
Perform an electrical bonding check of
the G3X Touch system LRUs in
accordance with Section 4.5.
4.5
Every 2000 flight hours
or 10 years, whichever
comes first
GDU 4X0 (Qty 1 or 2)
Removal & Replacement
6.1
On Condition
Removal & Replacement
6.2
On Condition
AHRS Magnetic Field Model Update
4.6
When available (5-year
update cycle)
Removal & Replacement
6.3
On Condition
Removal & Replacement
6.4
On Condition
Special Inspection Requirements
4.6
On Condition
GAD 27
Removal & Replacement
6.5
On Condition
GEA 24
Removal & Replacement
6.6
On Condition
GAD 29B
Removal & Replacement
6.7
GDL 5XR
Removal & Replacement
6.8
G3X Alerts
Check for and troubleshoot any alerts
provided in the alert window per the
referenced manual section
GPS Antenna
Removal & Replacement
Item
GSU 25D (ADAHRS)
GMU 11
GTP 59
On Condition
5
On Condition
6.9
On Condition
6.1.1
On Condition
4.7
On Condition
6.6.1
On Condition
G3X Accessories
GDU Configuration Module
(Qty 1)
Removal & Replacement
G3X Lightning Protection
Lightning Strike to Antenna
Actual or Suspected
Inspect the GTP 59 and surrounding
installation
Engine/Airframe Sensors
Oil Pressure
Oil Temperature
Manifold Pressure
Carb Air Temp
Removal & Replacement:
Fuel Pressure
Fuel Flow
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4.4 Visual Inspection
Operation of the G3X Touch system is not permitted unless a visual inspection, as described in this
section, has been completed within the preceding 12 calendar months. Check for corrosion, damage, or
other defects for each of the G3X Touch LRUs. Replace any damaged parts as required. Inspection may
require the temporary removal of a unit or units to gain access to connectors. Follow guidance in Section
6 for equipment removal and replacement.
Conduct the following visual inspection of the G3X Touch EFIS system LRUs and associated wiring
harnesses to ensure installation integrity:
1. Inspect all units for security of attachment, including visual inspection of brackets and other
supporting structure attaching all units to the airframe.
2. Inspect all switches, annunciators, knobs, and buttons for legibility.
3. Inspect displays for legibility and acceptable brightness. Reference Section 5.3.1.
4. Visually inspect each unit’s wiring (including electrical bonding straps), overbraid, and connectors
for chafing, deterioration, damage, or wear.
5. Visually check for any signs of corrosion.
4.4.1 Aluminum Foil Tape (Non-metallic Aircraft Only)
Any aluminum foil tape if used in the G3X Touch installation for grounding of a GSU 25D, GEA 24, GAD
29B or GAD 27, (refer to Appendix A of this document) must be inspected every 12 calendar months.
The inspection must verify that the foil tape is not torn, damaged, or showing signs of corrosion. If any of
these conditions are found, the tape must be replaced in accordance with Section 4 of G3X Touch EFIS
Part 23 AML STC Installation Manual.
4.5 Electrical Bonding Test
G3X Touch EFIS LRU electrical bonding must be checked every 2,000 flight hours or 10 years, whichever
occurs first.
4.5.1 Requirements


Disconnect any cables and connectors normally attached to the LRU.
Resistance must be measured from a bare metal portion of the LRU to an airframe grounding
location.
The airframe grounding location should be as close to the LRU as possible, unless otherwise noted in
Table 4-2.
4.5.2 Test Equipment
Calibrated 4 wire Milliohm meter and Kelvin probes are required for this test.
4.5.3 Electrical Bonding Test Procedures.




Using a calibrated milliohm meter and Kelvin probes measure the resistance of each G3X Touch
LRU between the locations noted in
Table 4-2, and record the result of each installed LRU. Some equipment on the list are optional
and may not be installed.
Ensure the resistance does not exceed 10 milliohms.
If the measured resistance is greater 10 milliohms, bonding must be improved to meet applicable
requirements for a new installation in accordance with Section 4 of G3X Touch EFIS Part 23 AML
STC Installation Manual (190-02472-01).
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Table 4-2 – Electrical Bonding Procedure
Measurement Location (3)
Unit
GDU 4X0 (PFD)
GDU 4X0 (MFD) (if
installed)
GSU 25D (1)
GMU 11
GAD 29B
GAD 27
GEA 24
GDL 5XR
Notes:
J4X02 backshell to ground stud (2)
J4X02 backshell to ground stud (2)
Result
(milliohm)
mΩ
mΩ
Chassis mounting screw to adjacent aircraft ground
P251 backshell to ground stud (2)
P111 backshell to ground stud (2)
Chassis mounting screw to adjacent aircraft ground
Chassis mounting screw to adjacent aircraft ground
Chassis mounting screw to adjacent aircraft ground
P5X1 backshell to ground stud (2)
mΩ
mΩ
mΩ
mΩ
mΩ
mΩ
(1) For remote mounted – it is bonded via the chassis mounting to aircraft ground.
For GDU-mounted – it is bonded via bonding strap to a ground stud
(2) This is the ground stud that the LRU bonding strap is connected to.
(3) For remote LRUs bonded to the back of the instrument panel via an installed aluminum foil ground plane,
the bonding measurement must be taken between the remote LRU and the instrument panel.
4.6 GSU 25D Earth Magnetic Field Updates
The GSU 25D utilizes an Earth magnetic field model which is updated once every five years. The IGRF
(International Geomagnetic Reference Field) update is expected to be available from Garmin in July 2020
and every five years thereafter, as long as the GSU 25D remains a Garmin-supported product.
The IGRF model is automatically updated with a GDU software update. The G3X system alerts the
operator the magnetic field database is out of date by issuing the message “AHRS SERVICE – AHRS
Magnetic-field model needs update”. Garmin will distribute update instructions when updates are
available.
4.7 Special Inspection Requirements
After a suspected lighting strike, the following actions must be performed for the specific LRU.
GTP 59 Temperature Probe
Inspect the GTP 59 temperature probe for signs of lightning damage. Check the self-sealing washer (P/N
212-00026-00) used on the probe tip outside of the aircraft for any evidence of melting or lack of seal.
Replace the washer if damaged. If there is evidence of lightning strike to the GTP 59 temperature probe
or any lightning damage, replace the probe.
Tube-and-fabric aircraft must replace the GTP 59 bond strap (if installed) in accordance with Section 4 of
the G3X Touch EFIS Part 23 AML STC Installation Manual (190-02472-01).
G3X Equipment
All G3X equipment should be checked per Section 7. If equipment is not functioning correctly,
troubleshoot using information in Section 5. Contact Garmin Product Support before replacing G3X LRUs
to verify all troubleshooting options were exhausted.
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5.
TROUBLESHOOTING
This section provides instructions and guidance for G3X Touch EFIS troubleshooting.
Troubleshoot the G3X Touch EFIS by first identifying, then isolating the specific failure to the responsible
LRU. There are several indications the G3X Touch EFIS presents to the pilot or technician, showing overall
system condition. A course of action should be determined based on the information presented on the
display. This section shows possible scenarios likely to be encountered during normal operation and
provides troubleshooting guidance to the technician to resolve problems. Reference the interconnect
diagrams on the G3X Touch EFIS Part 23 AML STC Installation Manual (190-02472-01) and retained with
aircraft permanent records while troubleshooting the G3X system.
In this manual, the term ‘Red-X’ refers to a red “X” that appears on different areas of the display to indicate
the failure of that specific function.
IMPORTANT
Sections 6, 7 and 8 provide detailed instructions on equipment removal, replacement, configuration, and
return-to-service testing. Anytime a G3X Touch component or LRU is removed, swapped, or replaced, the
technician must follow the procedures given in Sections 6, 7, and 8 to ensure proper operation of the system.
Refer to the G3X Touch Pilot’s Guide for Certified Aircraft (190-02472-00) for a complete listing of System
Status Messages.
For additional assistance, contact a G3X Touch Dealer, or Garmin Aviation Product Support at US Toll Free
Number 1-888-606-5482, or US 1-913-397-8200.
NOTE
Any warning message indicated on the “Messages” field or anywhere on the display while onground 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.
5.1
General Troubleshooting
1. Review the airframe logbook to verify if any G3X Touch EFIS or other avionics/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. Connect an auxiliary ground power unit and apply power to the aircraft.
4. Turn ON the G3X Touch EFIS 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 Touch EFIS and remove the interior panels (as required) to gain access to the
ADAHRS. 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 could move around during flight. This condition may cause the
wire to pull on or vibrate the connector, creating intermittent connections.
4. Ensure the affected LRU is mounted securely. Check the tightness of the mounting hardware.
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5. Look in the vicinity of the affected LRU for any heavy objects that may not be securely fastened to
the structure, inducing vibration in the ADAHRS.
6. Look for evidence of water or fluid contamination in the area around the affected LRU.
7. Disconnect the affected LRU’s connector(s) 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, use data in this section before
contacting Garmin Product Support for additional assistance. A Garmin Field Service Engineer may ask the
technician to download the fault logs via an SD card and email the logs back to Garmin to help determine the
root cause.
5.2 CAN Bus Network Troubleshooting
If communication problems between LRUs are suspected, the CAN bus wiring and arrangement of devices
on the network should be examined.
1. Review the status LED of devices on the CAN bus. The GAD 29B, GEA 24, GSU 25D, GAD 27 and
GSA 28 (if GFC 500 is installed) have an LED on their outer cases that indicates the LRU’s current
status. The status indications are shown in Table 5-1:
Table 5-1 – Status LED Indications
LED Indication
Description
No light
No power
Steady Green
ON, but not communicating via the CAN Bus
Flashing Green
ON, and communicating via CAN Bus
Red
Hardware Fault
Alternating Green/Red
CAN Bus network error, two similar devices are
configured with the same unit ID
2. Use the guidance in Table 5-2 to troubleshoot LED indications.
Table 5-2 – LED Indications Recommended Action
LED Indication
No light
Description
No power
Recommended Action
Verify the circuit breaker, power and ground wiring
between the circuit breaker and the affected unit.
Replace the unit if power is available to the unit.
Contact Garmin Product Support before replacing unit to
determine all troubleshooting options have been completed.
Steady Green
ON, but not
communicating via the
CAN Bus
Inspect and verify the CAN Bus wiring between the G3X
Touch and the unit
Flashing Green
ON, and communicating
via CAN Bus
None.
Red
Hardware Fault
Contact Garmin Product Support (unit may need to be
replaced)
Alternating
Green/Red
CAN Bus network error,
two similar devices are
configured with the
same unit ID
verify the Unit ID strapping on the G3X units. Reference
the G3X Touch EFIS Part 23 AML STC Installation
Manual (190-02472-01) wiring diagrams for strapping
details
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3. Ensure proper installation of the CAN bus and that the following guidance was adhered to during
installation:
 The CAN bus backbone must be a single linear path with exactly two distinct ends. CAN bus
connections must be “daisy-chained” from device to device. Avoid “star” and “Y” topologies, and
do not use a hub device. Reference Figure 5-1.
Figure 5-1 – Incorrect CAN Bus Topographies

The overall length of the bus must not exceed 100 feet.

Ensure any existing part number M27500 wire if retained for the CAN bus wiring does not
exceed 60 feet in overall length.

Do not connect more than one device to the CAN bus backbone at the same point. Instead,
daisy-chain the CAN bus backbone from one device to the next.

Observe proper wiring, shielding, and grounding requirements as described above.

Terminate the CAN bus at the two extreme ends of the bus, as described above.

When adding a new device to the CAN bus, evaluate proposed modifications to the CAN bus
wiring connections to ensure compliance with all above requirements and the G3X Touch EFIS
Part 23 AML STC Installation Manual (190-02472-01).
4. Ensure the CAN bus is terminated in only two locations, and only at the extreme ends of the CAN
bus.
Figure 5-2 – Correct CAN Bus Wiring Example and Node Connections
5. Ensure the G5 (if installed) is not at either extreme end of the CAN bus as the terminator.
6. With power removed, remove a connector from one of the devices that is not located at either of the
extreme ends of the CAN bus.
NOTE
Do not perform this test on the G5 (if installed as a standby flight display).
a. Using an ohm meter, verify that the resistance between the CAN HI and CAN LO pins on the
connector is 60 ohms. This will verify that the CAN backbone is properly terminated at each
end (two 120 ohm terminating resistors in parallel).
b. A resistance of 120 ohms indicates that one of the two required CAN terminations is
missing.
c. A resistance of 40 ohms or less indicates that too many terminations are installed.
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d. Verify that the CAN HI and CAN LO signals are not shorted to ground (this can happen
when shielded wire is installed incorrectly).
e. Measure the resistance between CAN HI and shield ground, and CAN LO and shield
ground. Verify resistance is several hundred kilohms (KΩ) or greater.
7. Verify that the CAN HI and CAN LO signals are not swapped or open-circuited at any LRU
connector.
8. Power the G3X system and with GDUs in configuration/diagnostic mode, reference section 3.2.3.
 Using Touch Panel or a Move Selector Knob to select and view the System Information
Page.

Scroll the Device List box and the select each device and verify the value displayed for
Network Error Rate is a steady 0% (Figure 5-3).Also verify the other network counts values
listed on Table 5-3.
Figure 5-3 – Network Error Rate (Configuration/Diagnostic Mode)
NOTE
CAN issue might not be with the unit reporting CAN errors but could be anywhere in the CAN bus
system. Table 5-3 is used as a guidance for determining if CAN bus is causing errors while
troubleshooting unit or system errors.
Table 5-3 – CAN Network Error Values (Configuration/Diagnostic Mode)
CAN INFO
DESCRIPTION
VALUE
POSSIBLE CAUSE
ACTION
Network Error Rate
> 0%
CAN bus wiring problem
Troubleshoot wiring and connection
issues that might create CAN errors
Network Tx Warning
Increasing ≥ 1
per minute
CAN bus wiring problem
Troubleshoot wiring and connection
issues that might create CAN errors
Network Rx Warning
Increasing ≥ 1
per minute
CAN bus wiring problem
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CAN INFO
DESCRIPTION
VALUE
POSSIBLE CAUSE
ACTION
Network Error Passive
≥2
CAN bus wiring problem
Troubleshoot wiring and connection
issues that might create CAN errors
Network Pass Off
≥2
CAN bus wiring problem
Troubleshoot wiring and connection
issues that might create CAN errors
9. Power up only the PFD display and one CAN device at a time and verify the connection quality for
each device. Sometimes a device will only communicate with PFD when it is the only powered
device on the CAN bus, if one or more of the above issues is present. Evaluating each CAN device
in turn can help narrow down a problem.
5.3 GDU 4X0
5.3.1 Display Legibility
Degradation of the GDU 4X0 LCD or backlight may reduce legibility. Backlight brightness may also be
adversely affected by issues with an external lighting bus or the photocells in the GDU bezel. If display
elements are not easily legible under all lighting conditions encountered in the cockpit including direct
sunlight, verify that the backlight can be adjusted to an acceptable brightness level via the manual dimming
control in the PFD menu. If manual dimming adjustment results in acceptable legibility, troubleshoot the
external lighting bus input for incorrect input voltage levels. Verify photocell lenses are clean and
unobstructed. Backlight dimming configuration for lighting bus or photocell should be verified in
Configuration Mode and may be adjusted as needed. Reference the G3X Touch EFIS Part 23 AML STC
Installation Manual (190-02472-01) for further detail.
If the above steps do not result in acceptable display legibility the GDU may need to be replaced. Contact
Garmin Product Support for more information.
5.3.2 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 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 with a maximum capacity of 8 GB).
Replace any corrupted SD card that might be causing an issue.
5.3.3 Data Logging
Data logging on the G3X Touch GDU may be used to help troubleshoot issues. Operational data is gathered
from the G3X Touch during flight or on ground and is stored in *.csv log files on the SD card (if installed and
enabled).
5.3.4 Unit Communication Error Messages (Dual GDU Installations)
Error messages occur if there is a mismatch in GDU software versions. If this occurs, the GDU’s will not
communicate with each other, and a software mismatch message will be reported on the “Messages” page.
Use the touch panel to select the yellow “Messages” field
or select Main Menu > Tools >
Messages, to view the error messages. Ensure both displays are running the same software version to clear
the issue. Unit communication error related messages and recommended actions are shown on Table 5-4.
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Table 5-4 – Unit Communication Error Messages (Dual GDU Installations)
Failure Message
Possible Cause
Recommended Action
GDU software version
mismatch
The two GDU displays are
using incompatible software
versions
Update the GDU with incorrect software
version
State of a GDU's mode pins
was detected to have changed.
Check for loose connections and
reference the G3X Touch EFIS Part 23
AML STC Installation Manual (19002472-01) for information on GDU
mode pin connections
“GDU COMM ERROR –
CHECK GDU WIRING”
Indicates that more than one
GDU is configured to be the
same unit type (e.g. two
displays are configured as
PFD)
Verify and correct GDU mode pin
connections per the G3X Touch EFIS
Part 23 AML STC Installation Manual
(190-02472-01)
[Navigation/Terrain/Obstacle]
Database Missing
Indicates that a required
database is missing on the
specified GDU display.
Indicates that the GDU displays
have different versions of the
specified database.
Update databases as required.
“[UNIT]” network address
changed”
[Navigation/Terrain/Obstacle]
Database Mismatch
Update the databases in all GDU
displays to the same cycle number.
5.3.5 GDU Reboot During Engine Start in a 14-volt Aircraft
If the GDU display inadvertently reboots during engine start, troubleshoot aircraft electrical system for
anything that might result in low bus voltage during engine start, reference Table 5-5 for recommended
actions.
NOTE
Flickering and dimming during engine start are not considered rebooting. The display has to turn
off and initialize again (generally requiring 20-30 seconds) to be considered a reboot.
Table 5-5 – GDU Reboot During Engine Start
Symptom
Possible Cause
Recommended Action
Low bus voltage
Troubleshoot aircraft electrical system for:
GDU display reboots
during engine start (14-volt
aircraft only)





insufficient battery capacity
poor starter performance
insufficient wire gauge in starter circuit
high resistance through wire connections, circuit
breakers, or solenoids
other issues in the starter circuit and primary power
distribution system
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Symptom
Possible Cause
Recommended Action
Verify that the Electrical Load Analysis and Battery
Capacity Analysis have been performed with
satisfactory results per the G3X Touch EFIS Part 23
AML STC Installation Manual (190-02472-01) Sections
3.6.1 and 3.6.2.
Install a GAD 27
If troubleshooting does not reveal any anomalies in the
aircraft’s battery or electrical system, a GAD 27 may be
optionally installed per the G3X Touch EFIS Part 23
AML STC Installation Manual (190-02472-01) to
address the issue
5.4 GSU 25D ADAHRS and GMU 11 Magnetometer Troubleshooting
5.4.1 Air Data Troubleshooting
Under normal operating conditions, the ADAHRS provides the following air data information:
 Total Air Temperature is measured
 Outside Air Temperature (OAT) – A valid OAT will display a number
 Indicated Airspeed (IAS)
 True Airspeed (TAS) – A valid OAT value is required to calculate 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).
Reference Table 5-6 for troubleshooting guidance.
Table 5-6 – ADAHRS and Magnetometer Troubleshooting
Symptom or Failure
Message
Heading failure (Red X’d
intermittently or steady)
Possible Cause
Recommended Action
Improper installation of the
GMU 11 and/or GSU 25D
Verify GMU 11 and GSU 25D mounting
locations are in accordance with the G3X
Touch EFIS Part 23 AML STC Installation
Manual (190-02472-01)
Excessive magnetic
interference (determine if any
Perform the magnetic interference test in
Section 8.12.1
new equipment has been
installed on the aircraft near the
magnetometer)
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Symptom or Failure
Message
Magnetic heading not
present
AHRS not receiving
magnetometer data
Attitude failure
(Red X’d intermittently or
steady)
Possible Cause
Recommended Action
Magnetic anomaly (If 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).
If this error shows up repeatedly, conduct the
magnetic interference check in Section
8.12.1
Communication lost between
GSU 25D and GMU 11
Inspect GMU 11 wiring
Ensure the GMU 11 installation is in
accordance with the G3X Touch EFIS Part
23 AML STC Installation Manual (190-0247201)
Inspect GMU 11 wiring
Communication lost between
GSU 25D and GMU 11
ADAHRS and/or
Magnetometer not calibrated
Ensure the GMU 11 installation is in
accordance with the G3X Touch EFIS Part
23 AML STC Installation Manual (190-0247201)
Perform pitch/roll compensation offset and
magnetometer calibration as per Section 7
ADAHRS unable to compute
valid attitude data due to
insufficient or invalid sensor
information
Replace GSU 25D
OAT is unavailable

Both OAT and TAS
failure
Contact Garmin Product Support before replacing
unit to determine all troubleshooting options have
been completed.



TAS has a dashed-out
value
true airspeed being
measured is too low to be of
value (e.g. when the aircraft
is on the ground).If the TAS
Inspect GTP 59 OAT probe wiring and
connection for faults.
Replace the GTP 59 OAT probe.
Inspect GSU 25D wiring and connections
for faults
If the problem persists, replace the GSU
25D with a known good unit
None
indication remains dashed out at
speeds greater than 20 knots
and/or the OAT indication is Red
-X’d continue with recommended
action above for OAT and TAS
failure.
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Symptom or Failure
Message
Airspeed and/or Altitude
failure
Possible Cause
Recommended Action
Pressure sensor is out of
range (possibly due to
improper plumbing such as
pitot and static lines
reversed)

No power to GSU 25D (if
Heading, Attitude and OAT
are also red-x’d)



GSU 25D has failed (installed
with a G5 standby).


Ensure GSU 25D circuit breaker is not open.
Inspect wiring and electrical connections

If problem persists, replace the GSU 25D
with a known good unit.
Inspect ADAHRS pitot/static plumbing
integrity.
 Inspect pitot/static ports and associated
equipment.
 If a periodic altimeter test, performed
with properly calibrated static system test
set, indicates that the ADAHRS static
pressure sensor needs to be recalibrated, follow the procedures
described in Section 7.2.1.3.
 If the problem persists, replace the GSU
25D with a known good unit
Ensure GSU 25D circuit breaker is not open.
Inspect wiring and electrical connections
If problem persists, replace the GSU 25D
with a known good unit.
5.4.2 Heading Red-X
Figure 5-4 – Heading Failure Indication
If a Red-X (steady or intermittent) or a yellow (degraded) is displayed on the heading (Figure 5-4), use
guidance in Table 5-6 and 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 or its
calibration.
2. When the aircraft is taxiing on the ground with a yaw rate of less than 2.5 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.
5.4.3 Attitude/Heading Failure Troubleshooting
The ADAHRS may not be able to provide valid heading/pitch/roll data for the following reasons:
1. If an “ADAHRS not Calibrated” message is displayed, the external installation configuration
parameters are not calibrated and the ADAHRS pitch/roll compensation offset (Section 7.2.1.1)
and/or Magnetometer calibration (Section 7.2.1) need to be performed. If either of these is not
calibrated, the ADAHRS heading, pitch, and roll may all be flagged as invalid. Calibrate the unit to
the installation.
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2. The ADAHRS is unable to compute valid attitude information due to insufficient or invalid sensor
information being provided.
Figure 5-5 – Attitude Failure Indication
If the attitude is failed and shows a Red-X condition, follow the troubleshooting steps in the Section 5.1. If
this does not resolve the issue, use guidance in Table 5-6, before gathering answers to the following
questions. This information may be helpful to the customer, the avionics 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 "ADAHRS Align: Keep
Wings Level" message (which is indicative of an ADAHRS reset), or the "Attitude Fail" message
(which is indicative of either ADAHRS 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 hangar 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 on the display or messages field within
an hour of the occurrence of the problem?
 ADAHRS not receiving airspeed
 ADAHRS not receiving any GPS information
 ADAHRS magnetic-field model out of date
 ADAHRS extended operation in no-GPS mode
8. Did the onset of the problem occur shortly after a software upload to the G3X Touch system, or
shortly after a repeat of the magnetometer calibration procedure? Were there any GPS Alert
messages or loss of position lock?
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190-02472-02
Revision 2
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5.4.4 Magnetometer Interference Test
NOTE
The Magnetic Interference Test is only required for initial installation verification. This test should also be
repeated to verify all subsequent electrical changes associated with devices within 10 feet of the GMU
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 magnetometer unit.
Likewise, this test should also be repeated to verify all subsequent changes to materials within 10 feet of
the GMU magnetometer. 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 magnetometer unit.
This procedure validates that no electronic device is interfering with the operation of the GMU
magnetometer which directly impacts the determination of attitude and heading by the GSU 25D. The
ADAHRS Unit Orientation and Pitch/Roll Offset Compensation are not required prior to this execution of
this procedure. A sequence of activities to be performed during a magnetometer interference test is
shown in Table 5-7 below. This is an example to help guide a technician through an aircraft’s functions
that may create interference with an installed GMU 11 magnetometer.
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.
1.
2.
3.
4.
Power on PFD in configuration mode (Section 3.2.2).
Select the Magnetometer Calibration Page.
Select Magnetic Interference Test.
Ensure that the aircraft has been properly prepared per the on-screen instructions. See Table 5-7 for
a sample test sequence. Press the Start button to begin the test.
Figure 5-6 – Magnetometer Interference Test On-screen Instructions
5. The actions must be carried out as 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.
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Figure 5-7 – Magnetometer Interference Test Progress
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.
6. 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 Magnetometer Page.
Figure 5-8 – Magnetometer Interference Test Status
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Table 5-7 – Magnetometer Interference Test Sequence Example
Elapsed Time (From Start of Test)
(min:secs)
Action
0:00
Test Begins
0:10
Aileron Full Right
0:20
Aileron Full Left
0:30
Aileron Level
0:40
Elevator Up
0:50
Elevator Down
1:00
Elevator Level
1:20
Rudder Left
1:40
Rudder Right
1:50
Rudder Center
2:00
Flaps Down
2:10
Flaps Up
2:20
Autopilot On
2:30
Autopilot Off
2:40
Electric Trim (GFC 500)
2:50
Landing Gear Up
3:00
Landing Gear Down
3:10
Speed Brake Up
3:20
Speed Brake Down
3:30
Navigation Lights On
3:40
Navigation Lights Off
3:50
Landing Lights On
4:00
Landing Lights Off
4:10
Taxi Lights On
4:20
Taxi Lights Off
4:30
Landing + Taxi Lights On
4:40
Landing + Taxi Lights Off
4:50
Strobes On
5:00
Strobes Off
5:10
Recognition Lights On
5:20
Recognition Lights Off
5:30
All Wing-Tip Lights On (simultaneous)
5:40
All Wing-Tip Lights Off (simultaneous)
5:50
Beacon On
6:00
Beacon Off
6:10
Pitot Heat On
6:20
Pitot Heat Off
6:30
Test Complete
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If the magnetic interference 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 magnetometer maximum deviation
values, and the 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:

new equipment is installed in close proximity to the GMU magnetometer or

An existing or new electronic device has become grounded through the aircraft structure instead
of by proper ground wire in a twisted shielded pair, or

Use of magnetized tools in close proximity to the GMU 11.
5.5 Engine Indication Troubleshooting
EIS indication failures may be presented as red x’s on the gauges as shown in Figure 5-9, or as operation
anomalies. Reference Table 5-8 below for troubleshooting guidance.
Figure 5-9 – Engine/Airframe Failure Indications
Table 5-8 – EIS Gauges Troubleshooting
Symptom or Failure
Message
Possible Cause
Recommended Action
Power removed from GEA
24
Ensure GEA 24circuit breaker is not open.
Defective or failed GEA 24
Engine Indications Red
X’d
EGT/CHT only Red X’d
Inspect wiring and electrical connections.
If problem persists, replace the GEA 24 with a
known good unit.
Power interrupted during
initialization
Cycle power and permit time for initialization
Software and configuration
load error
Reload software
Temperature probe is
shorted (typically where the
Inspect temperature probe(s) and wiring
bayonet is crimped)
EGT temperature slowly
drift up and eventually
flag
Electrical open in the probe
or wiring
Inspect EGT probes and wiring
Resistor failure
Disconnect P-Lead signal wires at
both ends. Verify wire is more than 400 KΩ.

Unstable RPM
Replace wire and parallel resistors if less than
400 KΩ
Poor connection
Verify wiring and connections
Interference
Route signal wires away from spark plug
leads and power wires
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Symptom or Failure
Message
Possible Cause
Recommended Action
Resistor failure
Disconnect P-Lead signal wires at
both ends. Verify wire is more than 400 KΩ.
Unstable RPM during
magneto check
RPM is erratic during
engine start/cranking
Fuel quantity gauge is
inaccurate
Fuel totalizer inaccurate
Fuel flow indication is
unstable

Replace wire and parallel resistors if less than
400 KΩ
Poor connection
Verify wiring and connections
Starting vibrator is installed.
Normal operation with p-lead
RPM input
None
Poor connection
Verify wiring and connections
Fuel probe malfunction
Replace fuel probe
Probe out of calibration
Recalibrate fuel tank probes
Fuel flow requires calibration
Calibrate fuel flow. (1)
Replace fuel flow transducer
Poor connection
Verify wiring and connections
Air/contamination in the
sensor
Purge fuel lines of air, verify sensor
orientation and clean the sensor
Interference
Route wires away from spark plug leads and
power wires. Install EMI shield

Pressure line drain plugged
Manifold pressure
unstable
Verify fuel is not trapped in the manifold
pressure line.
Replace manifold pressure sensor
Sensor failure
Manifold pressure
inaccurate
Replace fuel flow transducer if symptoms
persist
Verify manifold pressure line vent (if installed)
is clear.
Pressure line blocked
Sensor failure
Verify manifold pressure line is clear of
obstructions.
Replace pressure manifold sensor
Notes:
(1) Reference the G3X Touch EFIS Part 23 AML STC Installation Manual (190-02472-01)
5.6 Traffic Alert Messages
Table 5-9 – Traffic Alert Troubleshooting
Failure Message
Possible Cause
Recommended Action
 Interface to the G3X has
failed
Inspect unit wiring and connections for faults
 Traffic device has failed
Troubleshoot the device failure in accordance
with the LRU maintenance manual
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190-02472-02
Revision 2
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5.7 Transponder Alert Messages
Table 5-10 – Transponder Alert Troubleshooting
Failure Message
Possible Cause
Recommended Action
GPS data connection from
external navigator lost
Verify ADS-B sourced GPS receiver has a
GPS signal
Verify external navigator has power and is
functioning properly
Transponder failure
Verify the transponder is powered on and
functional.
Communication lost
between transponder and
GSU 25D
Verify the GSU 25D is powered on and
functional (the transponder communicates
to G3X via the GSU).
XPDR Fault
Hardware fault
Contact Garmin Product Support
XPDR CONFIG ERROR
Transponder configuration
fault
Check transponder configuration
Flight ID is not defined
correctly.

“Red X’d” XPDR
NO ID

if “Set by Pilot” is configured, ensure
the flight ID is an alpha numeric with 8
or less characters.
If the flight ID was entered via GTX tool,
correct it.
5.8 Loss of Navigation Information (External Navigators)
If VHF/GPS Navigation information is removed from the G3X Touch GDU and “GPS” (in magenta) and “VFR”
and “REV” (both in yellow) are displayed on the PFD HSI:
Table 5-11 – Loss of Navigation Information (External Navigators)
Failure Message
Possible Cause
Recommended Action
Communication with
external GPS lost. PFD
automatically reverted to
internal GPS
 Complete troubleshooting as directed and
applicable in Sections 5.1 (General
Troubleshooting) and 5.2 (CAN bus
troubleshooting).
 Inspect and verify the ARINC 429 wiring
between GPS navigator and GAD 29B.
 Verify the G3X Touch and GPS navigator
configurations have not changed.
Reference APPENDIX B
 Verify navigator is functioning properly.
Reference the navigator manufacturer’s
troubleshooting procedures.
 If problem persists, replace the GAD 29B
or navigator as applicable with a known
good unit.
Contact Garmin Product Support before replacing
unit to determine all troubleshooting options have
been accomplished.
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190-02472-02
Revision 2
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5.9 Garmin GFC 500 Failure Messages
During operation of the GFC 500 AFCS, the G3X Touch GDU may annunciate a failure or fault that is
specific to the GFC 500 Autopilot system. Refer to the GFC 500 Autopilot with Electronic Stability Protection
Part 23 AML STC Maintenance Manual with Instructions for Continued Airworthiness (190-02291-01), for
assistance in troubleshooting the problem.
5.10 Loss of Non-Garmin Autopilot Heading and/or Course Datum
If a Non-Garmin autopilot loses the capability to couple and track Heading and/or Course Datum:
1. Complete troubleshooting as directed and applicable in Sections 5.1, 5.2 (CAN bus troubleshooting),
5.4.2 (for loss of heading datum) and 5.7 (for loss of course and GPSS datum).
2. Inspect and verify the ARINC 429 wiring between GPS navigator, GAD 29B and the autopilot
computer.
3. Inspect the analog wiring between the GAD29B and the autopilot computer.
4. Verify the G3X Touch and GPS navigator configurations have not changed. Reference APPENDIX B
5. Verify autopilot computer is functioning properly. Reference the autopilot manufacturer’s
troubleshooting procedures.
6. If problem persists, replace the GAD 29B with a known good unit.
5.11 Miscellaneous Alerts
Table 5-12 – Miscellaneous Alerts
Alert Message
TAWS FAIL
Possible Cause
Recommended Action
Database error
Verify databases are up to date
Loss of GPS position
Verify GPS signal is available
Power removed from GAD 27
Ensure GAD 27 circuit breaker is not open.
Defective or failed GAD 27
Inspect wiring and electrical connections.
If problem persists, replace the GAD 27
with a known good unit.
GDU 470 display is in split
screen mode and CAUTION
annunciations are not
displayed.


Select full screen format to view
messages
Select
on the lower section of
the display
GDU 470 display is in split
screen mode and WARNING
annunciations are not
displayed.
5.12
Aircraft Harness/LRU Connectors
This section describes the aircraft harness connectors and associated LRU connectors. The pin
arrangement for each LRU connector is shown and the LRU connector arrangement for units with more than
one connector will be shown in the following sections. LRU connector arrangements will show the aircraft
harness connector designations. Reference the G3X Touch EFIS Part 23 AML STC Installation Manual (19002472-01) for further detail.
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
190-02472-02
Revision 2
Page 47
5.12.1 GDU 4X0 Aircraft Harness/LRU Connectors
This section describes the GDU 4X0 aircraft harness and interface connectors on the GDU. The GDU
connector designation is P4X01 and P4X02 and the aircraft harness connectors are designated as J4X01
and J4X02 respectively. GDU connector P4X03 is not used. The GDU connectors are clearly marked on the
back of the GDU as P4601, P4602 and P4603 for GDU 460 and P4701, P4702, and P4703 for GDU 470.
5.12.1.1 Aircraft Harness Connector J4X01
The aircraft harness connector J4X01 is a 9-socket D-sub plug connector and interfaces to the GDU P4X01
connector. A pinout arrangement of P4X01 is shown in Figure 5-10. Connector pin functions are shown in
Table 5-13.
Figure 5-10 – View of P4X01 Connector from back of GDU
Table 5-13 – P4X01/J4X01 Pin Functions
PIN
1
2
3
4
5
6
7
8
9
PIN NAME
RESERVED
RESERVED
RESERVED
RS-232 TX
RS-232 RX
RESERVED
RESERVED
RESERVED
RS-232 GROUND
I/O
---OUT
IN
-----
5.12.1.2 Aircraft Harness Connector J4X02
The aircraft harness connector J4X02 is a 50-pin D-sub plug connector and interfaces to the GDU P4X02
connector. A pinout arrangement of P4X02 is shown in Figure 5-11 and connector pin functions are shown in
Table 5-14
Figure 5-11 – View of P4X02 Connector from back of GDU
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G3X Touch EFIS Part 23 AML STC
190-02472-02
Revision 2
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Table 5-14 – P4X02/J4X02 Pin Functions
PIN
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
44
45
46
47
48
49
50
PIN NAME
ALERT AUDIO OUT HI
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
CDU SYSTEM ID PROGRAM 1
RESERVED
RESERVED
RS-232 TX 3
RS-232 RX 2
RESERVED
POWER GROUND 1
CONFIG MODULE POWER OUT
ALERT AUDIO OUT LO
RESERVED
RESERVED
RESERVED
RESERVED
RS-232 RX 4
RS-232 RX 5
RESERVED
28V LIGHTING BUS HI
SYSTEM PROGRAM GROUND
CAN BUS TERMINATION
RS-232 RX 3
RS-232 TX 2
AIRCRAFT POWER 2
AIRCRAFT POWER 1
CONFIG MODULE CLOCK
RS-232 GROUND 1
RS-232 GROUND 2
RS-232 GROUND 3
RS-232 GROUND 4
RESERVED
RESERVED
RS-232 TX 4
RS-232 TX 5
RESERVED
14V LIGHTING BUS HI
RS-232 GROUND 5
CAN-L
CAN-H
RS-232 RX 1
RS-232 TX 1
CONFIG MODULE GROUND
CONFIG MODULE DATA
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
I/O
OUT
-----------OUT
IN
--OUT
OUT
----IN
IN
-IN
--IN
OUT
--I/O
------OUT
OUT
-IN
-I/O
I/O
IN
OUT
-I/O
190-02472-02
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5.12.2 GSU 25D Aircraft Harness/LRU Connectors
This section describes the GSU 25D aircraft harness and interface connectors on the GSU. The GSU
connector designation is J251 and J252 and the aircraft harness connectors are designated as P251 and
P252 respectively.
5.12.2.1 Aircraft Harness Connector P251
The aircraft harness connector P251 is a 9-socket D-sub plug connector and interfaces to the J251
connector on the GSU. A pinout arrangement of J251 is shown in Figure 5-12 and connector pin functions
are shown in Table 5-15.
Figure 5-12 – View of J251 Connector on the GSU 25D
Table 5-15 – P251/J251 Pin Functions
Pin
1
2
3
4
5
6
7
8
9
Pin Name
CAN-H
CAN-L
RESERVED
RS-232 RX 1
RS-232 TX 1
POWER GROUND
AIRCRAFT POWER 1
AIRCRAFT POWER 2
RS-232 GROUND
I/O
I/O
I/O
-IN
OUT
-IN
IN
--
5.12.2.2 Aircraft Harness Connector P252
The aircraft harness connector P251 is a 15-socket D-sub plug connector and interfaces to the J251
connector on the GSU. A pinout arrangement of J251 is shown in Figure 5-13 and connector pin functions
are shown in Table 5-16.
Figure 5-13 – View of J252 Connector on the GSU 25D
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190-02472-02
Revision 2
Page 50
Table 5-16 – P252/J252 Pin Functions
PIN
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
PIN NAME
TEMP PROBE POWER OUT
TEMP PROBE IN HI
TEMP PROBE IN LO
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RS-232 TX 3
RS-232 RX 3
RS-232 GROUND 3
RESERVED
RESERVED
RS-232 GROUND 2
RS-232 TX 2
I/O
OUT
IN
IN
-----OUT
IN
----OUT
5.12.3 GMU 11 Aircraft Harness/LRU Connector
This section describes the GMU 11 aircraft harness and interface connector. The GMU LRU connector
designation is J111 and he aircraft harness connector is designated as P111.
The aircraft harness connector P111 is a 9-socket D-sub plug connector and interfaces to the J111
connector on the GMU. A pinout arrangement of J111 is shown in Figure 5-14 and connector pin functions
are shown in Table 5-17.
Figure 5-14 – View of J111 Connector on the GMU 11
Table 5-17 – P111/J111 Pin Functions
Pin
1
2
3
4
5
6
7
8
9
Pin Name
CAN-H
CAN-L
RESERVED
RESERVED
RESERVED
RESERVED
AIRCRAFT POWER 1
RESERVED
POWER GROUND
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I/O
I/O
I/O
----IN
---
190-02472-02
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5.12.4 GTP 59 Harness
The GTP59 is an OAT sensing device. The connection to this LRU is made via pre-installed lead wires and it
is acceptable to use crimp splices to extend the lead wire harness to the GSU. The pre-installed lead wires
are ten feet in length. Reference Table 5-18 for lead wire functions. For specific wiring information refer to
G3X Touch EFIS Part 23 AML STC Installation Manual (190-02472-01).
Table 5-18 – GTP 59 Lead Wire Functions
PIN
WHITE
BLUE
ORANGE
WIRE
TEMP PROBE POWER IN
TEMP PROBE OUT HI
TEMP PROBE OUT LO
I/O
IN
OUT
OUT
5.12.5 GAD 27 Aircraft Harness/LRU Connectors
This section describes the GAD 27 aircraft harness and the interface connectors on the GAD 27. The GAD
27 connector designation is J271 and the aircraft harness connector is designated as P271. GAD 27
connector J272 is not used. GAD 27 also has a terminal block TB273.
5.12.5.1 Aircraft Harness Connector P271
The aircraft harness connector P271 is a 50-socket D-sub plug connector and interfaces to the GAD 27
connector J271. A pinout arrangement of J271 is shown in Figure 5-15 and connector pin functions are
shown in Table 5-19.
Figure 5-15 – View of J271 Connector on the GAD 27
Table 5-19 – P271/J271 Pin Functions
PIN
1
2
3
4
5
6
7
8
9
10
11
12
PIN NAME/FUNCTION
CAN HI
CAN LO
CAN BUS TERM
GAD 27 POWER GND
RESERVED
RESERVED
RESERVED
GAD 27 POWER GROUND
RESERVED
RESERVED
RESERVED
RESERVED
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
I/O
I/O
I/O
----------190-02472-02
Revision 2
Page 52
PIN
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
44
45
46
47
48
49
50
PIN NAME/FUNCTION
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
GAD 27 POWER GROUND
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
I/O
---------------------------------------
5.12.5.2 Terminal Block TB273
This connection is only required for 14 VDC aircraft using p/n 235-00094-00 ring terminal. A terminal
arrangement of TB273 is shown in Figure 5-16 and connector terminal functions are shown in Table 5-20
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
190-02472-02
Revision 2
Page 53
Figure 5-16 – View of TB273 Terminal Block on GAD 27
Table 5-20 – TB273 Terminal Functions
TERMINAL
1
2
3
4
5
6
7
8
9
10
TERMINAL NAME/FUNCTION
KEEP ALIVE POWER IN
KEEP ALIVE POWER V OUT
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
I/O
IN
OUT
---------
5.12.6 GEA 24 Aircraft Harness/LRU Connectors
This section describes the GEA 24 aircraft harness and LRU interface connectors. The GEA connector
designations are J241, J242, J243 and J244 and the aircraft harness connectors are designated as P241,
P242, P243 and P244 respectively.
5.12.6.1 Aircraft Harness Connectors P241
The aircraft harness connector P241 is a 9-socket D-sub plug connector and interfaces to the J241
connector on the GEA. A pinout arrangement of J241 is shown in Figure 5-17 and connector pin functions
are shown in Table 5-21.
Figure 5-17 – View of J241 Connector on the GEA 24
Table 5-21 – P241/J241 Pin Functions
PIN
1
2
3
PIN NAME
CAN HI
CAN LO
RESERVED
I/O
I/O
I/O
--
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Page 54
PIN
4
5
6
7
8
9
PIN NAME
RS-232 RX 1
RS-232 TX 1
POWER GROUND
AIRCRAFT POWER 1
AIRCRAFT POWER 2
RS-232 GROUND
I/O
IN
OUT
-----
5.12.6.2 Aircraft Harness Connectors P242
The aircraft harness connector P242 is a 25-pin D-sub plug connector and interfaces to the J242 connector
on the GEA. A pinout arrangement of J242 is shown in Figure 5-18 and connector pin functions are shown in
Table 5-22
Figure 5-18 – View of J242 Connector on the GEA 24
Table 5-22 – P242/J242 Pin Functions
PIN
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
PIN NAME
RESERVED
CHT CYL 6 LO
EGT CYL 6 LO
CHT CYL 5 LO
EGT CYL 5 LO
CHT CYL 4 LO
EGT CYL 4 LO
CHT CYL 3 LO
EGT CYL 3 LO
CHT CYL 2 LO
EGT CYL 2 LO
CHT CYL 1 LO
EGT CYL 1 LO
CHT CYL 6 HI
EGT CYL 6 HI
CHT CYL 5 HI
EGT CYL 5 HI
CHT CYL 4 HI
EGT CYL 4 HI
CHT CYL 3 HI
EGT CYL 3 HI
CHT CYL 2 HI
EGT CYL 2 HI
CHT CYL 1 HI
EGT CYL 1 HI
I/O
-IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
OUT
OUT
OUT
OUT
OUT
OUT
OUT
OUT
OUT
OUT
OUT
OUT
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5.12.6.3 Aircraft Harness Connector P243
The aircraft harness connector P243 is a 37-socket D-sub plug connector and interfaces to the J243
connector on the GEA. A pinout arrangement of J243 is shown in Figure 5-19 and connector pin functions
are shown in Table 5-23.
Figure 5-19 – View of J243Connector on the GEA 24
Table 5-23 – P243/J243 Pin Functions
PIN
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
PIN NAME
FUEL PRESS GND
FUEL PRESS RX
FUEL PRESS XDCR +12V
FUEL PRESS XDCR +5V
RPM 2 GND
RPM 2
RPM 1 GND
RPM 1
RPM 1 +12V
RPM 2 +12V
RESERVED
MANIFOLD PRESS GND
MANIFOLD PRESS RX
MANIFOLD PRESS XDCR +12V
MANIFOLD PRESS XDCR +5V
OIL PRESS GND
OIL PRESS RX
OIL PRESS XDCR +12V
OIL PRESS XDCR +5V
FUEL FLOW 1 GND
FUEL FLOW 2 RX
FUEL FLOW 2 GND
FUEL FLOW 1 RX
FUEL FLOW 1 XDCR +12V
FUEL FLOW 2 XDCR +12V
RESERVED
RESERVED
TIT 2 LO
TIT 2 HI
TIT 1 LO or CARBURETOR TEMP LO
TIT 1 HI or CARBURETOR TEMP HI
OIL TEMP LO
OIL TEMP HI
BUS 2 AMPS LO
BUS 2 AMPS HI
BUS 1 AMPS LO
BUS 1 AMPS HI
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G3X Touch EFIS Part 23 AML STC
I/O
-IN
OUT
OUT
-IN
-IN
OUT
OUT
--IN
OUT
OUT
-IN
OUT
OUT
-IN
-IN
OUT
OUT
--IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
190-02472-02
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5.12.6.4 Aircraft Harness Connector P244
The aircraft harness connector P244 is a 50-socket D-sub plug connector and interfaces to the J244
connector on the GEA. A pinout arrangement of J244 is shown in Figure 5-20 and connector pin functions
are shown in Table 5-24
Figure 5-20 – View of J244 Connector on the GEA 24
Table 5-24 – P244/J244 Pin Functions
PIN
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
PIN NAME
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
FUEL QTY 1
RESERVED
RESERVED
FUEL QTY 2
RESERVED
RESERVED
FUEL QTY 3
RESERVED
RESERVED
FUEL QTY 4
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
VOLTS 1
RESERVED
RESERVED
VOLTS 2
RESERVED
RESERVED
RESERVED
I/O
-----IN
--IN
--IN
--IN
---------IN
--IN
----
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PIN
32
33
34
35
36
37
38
39
40
41
42
43
44
45
46
47
48
49
50
PIN NAME
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
I/O
--------------------
5.12.7 GAD 29B Aircraft Harness/LRU Connectors
This section describes the GAD 29B aircraft harness and LRU interface connectors. The GAD 29 connector
designations are J291 and J292 and the aircraft harness connectors are designated as P291 and P292
respectively.
5.12.7.1 Aircraft Harness Connector P291
The aircraft harness connector P291 is a 9-socket D-sub plug connector and interfaces to the J291
connector on the GAD29B. A pinout arrangement of J291 is shown in Figure 5-21 and connector pin
functions are shown in Table 5-25.
Figure 5-21 – View of J291 Connector on the GAD 29B
Table 5-25 – P291/J291 Pin Functions
PIN
1
2
3
4
5
6
7
8
9
PIN NAME
CAN-H
CAN-L
RESERVED
RESERVED
RESERVED
POWER GROUND
AIRCRAFT POWER 1
RESERVED
GROUND
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I/O
I/O
I/O
----IN
--190-02472-02
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5.12.7.2 Aircraft Harness Connector P292
The aircraft harness connector P292 is a 25-pin D-sub plug connector and interfaces to the J291 connector
on the GAD29B. A pinout arrangement of J292 is shown in Figure 5-22 and connector pin functions are
shown in Table 5-26.
Figure 5-22 – View of J292 Connector on the GAD 29B
Table 5-26 – P292/J292 Pin Functions
PIN
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
PIN NAME
AC REFERENCE HI
AC REFERENCE LO
HDG/CRS VALID
ARINC 429 RX 4B
ARINC 429 RX 3B
ARINC 429 TX 2B
ARINC 429 TX 2B
HEADING ERROR HI
CAN TERM 1
ARINC 429 RX 2B
ARINC 429 RX 1B
ARINC 429 TX 1B
ARINC 429 TX 1B
HEADING ERROR LO
COURSE ERROR HI
ARINC 429 RX 4A
ARINC 429 RX 3A
ARINC 429 TX 2A
ARINC 429 TX 2A
COURSE ERROR LO
CAN TERM 2
ARINC 429 RX 2A
ARINC 429 RX 1A
ARINC 429 TX 1A
ARINC 429 TX 1A
I/O
IN
IN
OUT
IN
IN
OUT
OUT
OUT
-IN
IN
OUT
OUT
IN
OUT
IN
IN
OUT
OUT
IN
-IN
IN
OUT
OUT
5.12.8 GDL 5XR Aircraft Harness/LRU Connectors
This section describes the GDL 5XR aircraft harness and interface connector. The GDL LRU connector
designation is J5X1 and the aircraft harness connector is designated as P5X1.
The aircraft harness connector P5X1 is a 15-socket D-sub plug connector and interfaces to the J5X1
connector on the GMU. A pinout arrangement of J5X1 is shown in Figure 5-23 and connector pin functions
are shown in Table 5-27.
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G3X Touch EFIS Part 23 AML STC
190-02472-02
Revision 2
Page 59
Figure 5-23 – View of J5X1 Connector on the GDL 5XR
Table 5-27 – P5X1/J5X1 Pin Functions
PIN
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
PIN NAME
RESERVED
RESERVED
RESERVED
RESERVED
RS-232 TX 2
RS-232 RX 2
RS-232 TX 1
RS-232 RX 1
POWER GROUND
AIRCRAFT POWER
RS-232 GROUND 1
RS-232 GROUND 2
MUSIC OUT LEFT
AUDIO COMMON
MUSIC OUT RIGHT
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I/O
----OUT
IN
OUT
IN
-IN
--OUT
-OUT
190-02472-02
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6.
G3X EQUIPMENT REMOVAL & REINSTALLATION
This section contains basic procedures for removing and reinstalling G3X LRUs.
The G3X Touch EFIS equipment part numbers approved by STC SA01899WI are in the G3X Touch EFIS
Part 23 AML STC Installation Manual (190-02472-01).
NOTE
Once an LRU is replaced, software loading and testing is required. See Section 7 for the software
loading and testing procedures for a replacement LRU.
CAUTION
Always ensure aircraft power is off or LRU circuit breaker is open when removing and/or replacing an
LRU. Unplug any auxiliary power supplies
NOTE
Ensure all LRU mounting hardware removed is retained for reinstallation. If hardware needs to be
replaced, reference G3X Touch EFIS Part 23 AML STC Installation Manual (190-02472-01) appropriate
hardware part numbers.
6.1 GDU 4X0
Removal:
1.
2.
3.
4.
Power OFF the aircraft to remove power from the GDU and other LRUs.
Using a 3/32” hex tool, rotate all four fasteners counter-clockwise to remove them.
Carefully remove the display from the panel.
While supporting the display, disconnect all connectors and the GSU 25D without disconnecting the
pitot/static lines (if installed on back of GDU, as defined in Section 6.2).
Reinstallation:
1. Inspect the connector and pins (on the unit) for signs of damage.
2. While supporting the display, connect the connectors to the rear of the unit and GSU 25D if installed
on the back of GDU (as defined in Section 6.2).
3. Carefully insert the display into the panel cutout and align fasteners with the corresponding holes.
Do not use excessive force while inserting the display.
4. Using a 3/32” hex tool, insert screws and rotate clockwise to tighten and torque to 8 ±1 in-lbs. to
secure display to the instrument panel.
5. Continue to section 7.1 for configuration and checkout procedures.
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Page 61
Figure 6-1 – GDU 460 Shown, (GDU 470 Similar)
6.1.1 PFD Configuration Module
The GDU 4X0 PFD 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 such as the GSU 25D. This allows critical data to
be retained with the airframe even if the PFD display is replaced.
NOTE
All item numbers (in parenthesis) in this procedure reference Figure 6-2.
Removal:
1. Remove the PFD in accordance with Section 6.1 to gain access to connector J4X02.
2. Remove the backshell cover (8) from connector J4X02 by removing the two screws (7).
3. Remove the screw (4) securing the configuration module (1) to the backshell (6).
4. Lift the configuration module (1) out of the backshell (6) and disconnect the wiring harness (3) from
the module.
5.
Inspect the wiring harness (3) and connector pins (2) for damage, loose wiring, or corrosion. Repair
any defects or replace components as necessary.
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Reinstallation:
1. Inspect the connectors to ensure there are no bent or damaged pins. Repair any damage.
2. Connect the wiring harness (3) to the new configuration module (1).
3. Install the new configuration module in the connector backshell (6) and secure with screw (4)
4. Reinstall the backshell cover (8) using the two screws (7).
5. Reconnect the J4X02 connector on the back of the GDU.
6. Reinstall the PFD in accordance with Section 6.1.
Figure 6-2 – Configuration Module (PFD)
Table 6-1 – GDU Configuration Module Kit (P/N 010-12253-01)
Item
1
2
3
4
Description
Potted Module (w/EEPROM)
Contact, Socket, Size 20, 26-30 AWG
4 conductor Config. Module harness
Pan head screw
Qty. Required
1
4
1
1
Part Number
011-03702-00
336-00022-01
325-00122-00
211-60232-07
NOTE
System configuration will be automatically copied to the module by the PFD upon the first power ON after
replacement. If the PFD was also replaced in conjunction with the module, system configuration and
calibration will be required.
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6.2 GSU 25D ADAHRS
Removal:
GDU-mounted GSU 25D:
1. Remove the GDU in accordance with Section 6.1.
2. Disconnect the GSU 25D electrical connectors.
3. Disconnect the pitot static lines as required and install plugs or covers to protect the system.
4. While supporting the GSU 25D, remove the four bolts that attach the GSU 25D to the back of the
GDU.
Figure 6-3 – GDU 460-Mounted GSU 25D (GDU 470 similar)
Remote mounted GSU 25D:
1. Gain access to the GSU 25D. Refer to the location information recorded in APPENDIX A of this
document and maintained with the aircraft records.
2. Disconnect the GSU 25D electrical connectors.
3. Disconnect the pitot and static lines as required and install plugs or covers to protect the system.
4. Unscrew the four bolts or screws that secure the GSU 25D to the mounting location. Note the
mounting orientation for reinstallation.
5. Lift the GSU 25D off the mounting location.
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Revision 2
Page 64
Figure 6-4 – Remote mounted GSU 25D
Reinstallation:
GDU-mounted GSU 25D:
1. Place the GSU 25D on the back of the GDU in the same mounting orientation as it was when
removed. Align GSU holes with the mounting holes on the back of the GDU.
2. Insert the four mounting bolts and secure the GSU 25D on the back of the GDU.
3. Connect the pitot and static lines.
4. Inspect the electrical connector to ensure there are no bent or damaged pins. Repair any damage.
5. Connect the electrical connectors to the GSU 25D.
6. Reinstall the GDU as noted in Section 6.1.
7. Continue to section 7.2 for configuration and checkout procedures.
Remote mounted GSU 25D:
1. Place the GSU 25D on the mounting location in the same mounting orientation as it was when
removed. Align GSU holes with the holes on the mounting location. Connect the electrical connectors
to the GSU 25D.
2. Insert the four mounting bolts or screws and secure the GSU 25D to the mounting location with
washers and nuts (as applicable).
3. Connect the pitot and static lines.
4. Inspect the electrical connector to ensure there are no bent or damaged pins. Repair any damage.
5. Connect the electrical connectors to the GSU 25D.
6. Continue to section 7.2 for configuration and checkout procedures.
6.3 GMU 11 Magnetometer
Removal:
1. Gain access to the GMU 11. Refer to the location information recorded in APPENDIX A of this
document and maintained with the aircraft records.
2. Disconnect the electrical connector.
3. Remove the 4 fasteners that secure the GMU 11 to the mounting location.
4. Lift the GMU 11 off the mounting location.
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Reinstallation:
1. Place the GMU 11 in its mounting location and align its holes with the mounting holes.
2. Insert the four mounting screws and secure the GMU 11 in place with washers and nuts. Tighten
screws until snug, plus 1/4 turn.
3. Inspect the electrical connector to ensure there are no bent or damaged pins. Repair any damage.
4. Connect the electrical connector to the GMU 11.
5. Continue to section 7.2 for configuration/calibration and checkout procedures.
Figure 6-5 – GMU 11 Magnetometer
6.4 GTP 59 Temperature Probe
Removal:
1. Ensure power is removed from the GSU 25D.
2. Remove the mounting nut and washer from the GTP 59 probe.
3. Pull the GTP 59 from the mounting hole.
Reinstallation:
1. Place the GTP 59 on the previous installation location.
2. Install the washer and nut.
3. Torque nut to 100 +/- 20 in-lbs.
4. Continue to section 7.4 for checkout procedures.
NOTE
Reference the G3X Touch EFIS Part 23 AML STC Installation Manual (190-02472-01) for installation of
new GTP 59.
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
190-02472-02
Revision 2
Page 66
Figure 6-6 – GTP 59 Temperature Probe
6.5 GAD 27 Electronic Adapter Unit
Removal:
1. Gain access to the GAD 27. Refer to the location information recorded in APPENDIX A of this
document and maintained with the aircraft records.
2. Disconnect the GAD 27 connector and ring terminals from the terminal block. Note the location of
each ring terminal on the terminal block for proper reinstallation.
3. Remove the four screws and washers and nuts (as applicable) that secure the GAD 27 to the
mounting location.
4. Lift the GAD 27 off the mounting location.
Reinstallation:
1. Place the GAD 27 in its mounting location and align its holes with the mounting holes.
2. Insert the four mounting screws and secure the GAD 27 in place with washers and nuts or on
nutplates as applicable.
3. Inspect the electrical connector to ensure there are no bent or damaged pins. Repair any damage.
4. For a newly installed GAD 27, install the d-sub cover plate on unused connector.
5. Connect the connector and ring terminals to the GAD 27.
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6. Continue to section 7.5 for configuration and checkout procedures
Figure 6-7 – GAD 27
6.6 GEA 24 Engine Indicating System
Removal:
1. Gain access to the GEA 24. Refer to the location information recorded in APPENDIX A of this
document and maintained with the aircraft records.
2. Disconnect the GEA 24 electrical connectors.
3. Remove the four screws that hold the GEA to the mounting location.
4. Lift the GEA 24 off its mounting location.
Reinstallation:
1. Place the GEA 24 in its mounting location and align its holes with the mounting holes.
2. Insert the four mounting screws and secure the GEA 24 in place.
3. Inspect the electrical connectors and pins for signs of damage. Repair any damage.
4. Connect the wiring harness connectors to the GEA 24.
5. Continue to section 7.6 for configuration and checkout procedures.
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
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Figure 6-8 – GEA 24
6.6.1 EIS Sensors
In addition to the data in this manual and the G3X Touch EFIS Part 23 AML STC Installation Manual (19002472-01), replacement or re-installation of each probe/sensor and wire must be accomplished in
accordance with the sensor manufacturer instructions or as recommended by the engine manufacturer. Wire
routing and clamping must follow procedures defined in the aircraft maintenance manual, standard practices
manual, or practices defined in Chapter 11, Electrical Systems, of advisory circular AC 43.13-1B, Aircraft
Inspection and Repair.
Sensors must be connected using hoses and fittings approved as part of aircraft or engine type certificated
design or standard aircraft parts (AN/MS) or the G3X Touch EFIS Part 23 AML STC Installation Manual
(190-02472-01).
After removing or replacing any EIS sensor, perform the EIS ground checkout procedure for the specific
sensor that was affected in Section 8.11
6.6.1.1 Pressure Sensors (Oil, Manifold and Fuel)
Manifold pressure, oil pressure, and fuel pressure sensor installations are similar.
When replacing existing sensors:


Do not remove engine and fuel fittings with an intentionally reduced orifice. It may limit fluid loss and
fire damage in the event of a hose failure
Inspect the condition of all existing tubes, hoses, and fittings that are being reused; replace if
necessary.
Install pressure sensors as described in Figure 6-9. When installing pressure sensors:
1. New fuel and oil hoses in the engine compartment must meet TSO-C53a Type C or D (fire
resistant).
2. Do not install sensors directly below fittings or components that may leak flammable fluid.
3. Thread sealant or tape must be used for the NPT threads. To reduce the risk of system
contamination, a minimal amount of sealant should be applied leaving at least two threads at the
end of the fitting clear of sealant/tape.
4. Sensors must be routed as far away from the aircraft exhaust system as practical and no closer
than 6 inches.
Maintenance Manual
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190-02472-02
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Page 69
Figure 6-9 – Pressure Sensor, Coupling Mount Type
6.6.1.2 Oil Temperature
When installing the oil temperature sensor, the unbroken side of the crush washer must face the sensor
flange. The sensor is torqued finger tight plus one-half turn and safety wired in accordance with practices
defined in Section 7, Safetying, of Chapter 7, Aircraft Hardware, Control Cables and Turnbuckles, of advisory
circular AC 43.13-1B, Aircraft Inspection and Repair.
6.6.1.3 Carburetor Air Temperature
The sensor location will vary for different carburetors. Reinstall the carburetor temperature sensor as
described in Figure 6-10.
CAUTION
Fuel and air passages must remain free of contaminants during work near and around the
carburetor.
Maintenance Manual
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Figure 6-10 – Carburetor Air Temperature Sensor Mounting
6.6.1.4 Fuel Flow
The fuel flow transducer may be mounted with a bracket or clamps on the hoses. Reinstall the fuel flow
transducer as follows:

Install the mounting clamps (if used) within 6 inches of the nearest face of the transducer.

Install it with the fuel flow direction matching the direction marked on the ports and the wires are not
pointing downward.

Ensure the hose connected to the IN port are straight for a minimum of 4 inches.

Ensure the length of hose connected to the OUT port should be level or slope up. It must not slope
down more than 4 inches per foot.
The hoses and fittings connected to fuel flow transducer must meet the following requirements:

Fuel hoses must not be subject to engine or other movement that could loosen the fittings.

Replacement hoses must have the same internal diameter as the hose being replaced and meet
TSO-C53a Type C or D fire resistant specifications.

Use fuel compatible thread sealant or tape for the NPT threads. To reduce the risk of fuel system
contamination, a minimal amount of sealant should be applied, leaving at least two threads at the
end of the fitting clear of sealant/tape. Before connecting any hoses, thoroughly clean and flush the
transducer and hoses to insure they are free of any loose material.

Fitting torque must not exceed 12 ft-lbs, or two full turns past finger tight, whichever occurs first.
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
Install the transducer and fuel hoses routed as far away from the aircraft exhaust system as
practical. Securely wrap and the transducer with Aeroquip AE102-( ) fire-sleeve if within six inches
of any exhaust component.

Line fittings, routing, alignment, bonding, and support spacing must be installed as defined in the
aircraft maintenance manual or section 8-31 of AC 43.13-1B, “Aircraft Inspection and Repair”.
WARNING
Ensure the fuel flow transducer installation does not introduce thread sealant or debris into the fuel system.
CAUTION
Do not blow pressurized air through the flow transducer.
Figure 6-11 – Fuel Flow Transducer Installation Example
6.7 GAD 29B ARINC 429 Adapter
Removal:
1. Gain access to the GAD 29B. Refer to the location information recorded in APPENDIX A of this
document and maintained with the aircraft records.
2. Disconnect the GAD 29B connectors.
3. Remove the four screws that hold the GAD 29B to the mounting location.
4. Lift the GEA 24 off its mounting location.
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Reinstallation:
1.
2.
3.
4.
5.
Place the GAD 29B in its mounting location and align its holes with the mounting holes.
Insert the four mounting screws and secure the GAD 29B in place.
Inspect the electrical connectors and pins for signs of damage. Repair any damage.
Connect the wiring harness to the GAD 29B.
Continue to section 7.7 for configuration and checkout procedures.
Figure 6-12 – GAD 29B
6.8 GDL 5XR Datalink
Removal:
1. Gain access to the GDL 5XR. Refer to the location information recorded in APPENDIX A of this
document and maintained with the aircraft records.
2. Disconnect the GDL 5XR electrical and coax cable connectors as applicable.
3. Remove the four screws that secure the GDL 5XR to the mounting location.
4. Lift the GDL 5XR off the mounting location.
Reinstallation:
1. Place the GDL 5XR in its mounting location and align its holes with the mounting holes.
2. Insert the four mounting screws and secure the GDL 5XR in place with washers and nuts (as
appropriate).
3. Inspect the electrical connector to ensure there are no bent or damaged pins. Repair any damage.
4. Connect the electrical and coax connectors as applicable to the GDL 5XR.
5. Continue to Section 7.8 for configuration and checkout procedures.
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Figure 6-13 – GDL 5XR (GDL 52R Shown)
6.9 GPS Antenna (p/n 011-04036-00)
Removal:
1. Remove power from the aircraft.
2. Disconnect the GPS antenna coax cable the back of the PFD.
3. Remove the screws (if applicable) or pull on antenna to separate the fastener tape (hook & loop
material) securing the antenna on the glareshield.
4. Lift up on the GPS antenna from the glareshield to remove it.
Reinstallation:
1. Place the antenna on the mounting location on the glareshield.
2. Secure the antenna as applicable with screws or hook & loop material.
3. Connect the GPS antenna coax cable to the back of the PFD.
4. Coil any excess coax cable and secure with cable ties.
5. Conduct return to service procedures in Section 8 as applicable.
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Figure 6-14 – GPS Antenna (Screw-mounted Installation Example)
Figure 6-15 – GPS Antenna (Hook and Loop Installation Example)
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7.
G3X EQUIPMENT CONFIGURATION & TESTING
This section provides procedures to be performed after a G3X unit is removed and reinstalled or
replaced. At the beginning of each LRU section, instructions are given to guide the technician for various
removal/replacement scenarios. These instructions define necessary procedures to be followed for
situations where original equipment was reinstalled as well as for situations where new equipment (new
serial number) is installed.
7.1 GDU 4X0
Original GDU 4X0 is Reinstalled
No software or configuration loading is required if an original GDU 4X0 is reinstalled. This does not
include units that were returned for repair as their software and configuration files are deleted during the
repair testing process. Continue to Section 7.1.3.
New, Repaired, or Exchanged GDU 4X0 is Installed
If a new, repaired, or exchange GDU 4X0 is installed, the correct software must be loaded to the unit.
Continue to Section 7.1.2.
7.1.1
New PFD Configuration Module Installed
If a new configuration module is installed and no change is made to the PFD, the required configuration
information will be written to the new module by the PFD. If both the PFD and configuration module are
replaced with new modules, configuration of the system is required. Reference Section 5 of G3X Touch
EFIS Part 23 AML STC Installation Manual (190-02472-00) for configuration information.
NOTE
Do not use a used GDU configuration module as a replacement. Data that may reside on a used
configuration module may cause system configuration errors.
7.1.2
GDU Software Loading
Continue to section 7.9 for GDU software loading procedures.
7.1.3
GDU Display Testing
1. Apply power to the aircraft and allow the displays to initialize for approximately one minute. Verify
proper display of data and no red-x’s.
2. If no other service is to be performed, continue to the return-to-service procedures in Section 8.
7.2 GSU 25D ADAHRS and GMU 11 Magnetometer
Original GSU 25D is Reinstalled
No software or configuration loading is required if the removed GSU 25D is reinstalled.
New, Repaired or Exchange GSU 25D is Installed
If a new, repaired or exchange GSU 25D is installed, the correct software will be loaded automatically by
the G3X GDU when power is applied to the system.
Original GMU 11 is Reinstalled
No software or configuration loading is required if the removed GMU 11 is reinstalled. Continue to
Section 7.2.1.
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New, Repaired, or Exchange GMU 11 is Installed
If a new, repaired, or exchange GMU 11 is installed, the correct software will be loaded automatically by
the G3X GDU when power is applied to the system. Continue to Section 7.2.1.
7.2.1
GSU 25D/GMU 11 Testing and Calibration
Table 7-1 describes the calibration procedures to be performed for GSU 25D and/or GMU 11 units after
maintenance is performed.
For new GSU 25D and/or GMU 11, or if the mounting bracket/shelf and/or pitot and static lines have been
disturbed, perform the following tests/procedures.
1. Perform a pitot-static leak check in accordance with the aircraft manufacturer’s specification
and/or applicable regulations.
2. Pitch/Roll Offset Compensation by Aircraft Leveling (Section 7.2.1.1)
3. Magnetometer Calibration (Section 7.2.1.2).
4. Magnetometer interference test (Section 8.12.1)
 The addition, removal, or modification of components that are ferrous (magnetic), or
electrical changes to the installation that affect components within 10 feet of the GMU 11
magnetometer location after the Magnetometer Interference Test (Section 8.12.1) or
Magnetometer Calibration (Section 7.2.1.2) were completed, requires a repeat of the
Magnetometer interference test procedures. If new magnetic interference is detected, it
must be resolved, then the Magnetometer Calibration (Section 7.2.1.2) must be repeated.
5. Altimeter Check (Section 8.12.1).
 If the altimeter check (Section 8.12.1) fails, ADAHRS Static Pressure Calibration (Section
7.2.1.3) must be performed.
6. Engine run-up vibration test (Section 7.2.1.4).
7. Compass swing (Section 8.12.3). Must be performed after magnetometer calibration to verify the
ADAHRS/GMU 11 heading accuracy.
NOTE
For a new GSU 25D or GMU 11 and if the mounting screws that secure the mounting rack is loosened for
any reason affecting the orientation of the unit, ADAHRS Unit Orientation and Magnetometer Orientation
respectively, must be repeated in accordance with the G3X Touch EFIS Part 23 AML STC Installation
Manual (190-02472-01).
Table 7-1 – GSU 25D/GMU 11 Recalibration Criteria
Calibrations Required
Condition
GMU 11 was removed and reinstalled. (no
change in serial number)
GSU Pitch/Roll
Offset
Calibration
GSU 25D/GMU 11
Magnetometer
Calibration
Engine Runup
Vibration
Test
None Required.
Continue to GSU 25D/GMU 11 Checkout Procedures
GMU 11 was replaced with new unit.
(New serial number)
X
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Calibrations Required
GSU Pitch/Roll
Offset
Calibration
Condition
GSU 25D was removed and reinstalled.
The mounting bracket was NOT removed,
and the mounting bracket bolts were NOT
loosened. (same serial number)
GSU 25D was removed and reinstalled.
The mounting bracket WAS removed
and/or mounting bracket bolts WERE
loosened.
GSU 25D was replaced with new unit.
(New serial number)
GSU 25D/GMU 11
Magnetometer
Calibration
Engine Runup
Vibration
Test
None Required.
Continue to GSU 25D/GMU 11 Checkout Procedures
X
X
X
X
X
X
7.2.1.1 Pitch/Roll Offset Compensation by Aircraft Leveling
NOTE
Prior to performing the following procedure, the aircraft must be leveled using the procedures in the
aircraft maintenance manual.
Figure 7-1 – Aircraft Level Attitude
Use the following procedure to set GSU 25D pitch and roll compensation on the aircraft;
1.
2.
3.
4.
Select the ADAHRS Calibration Page.
Ensure that all the required status boxes are checked.
Select Pitch/Roll Offset.
Ensure that aircraft and ADAHRS comply with all on-screen instructions, then select the START
button.
5. “Pitch/roll offset calibration in progress” will appear on the display along with calibration
information.
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Figure 7-2 – Pitch/Roll Offset Calibration in Progress
NOTE
The GSU 25D pitch/roll offset procedure has a 30 second countdown timer that resets if the aircraft
moves.
6. When the calibration has completed “Success” or “Failure” will be displayed; select the DONE
softkey to return to the ADAHRS Calibration screen.
Figure 7-3 – Pitch/Roll Offset Completion Status
NOTE
Magnetometer Calibration must be completed after each ADAHRS pitch/roll offset calibration.
NOTE
The subsequent ADAHRS and magnetometer procedures are carried out with the aircraft engine
running. Start and operate the aircraft engines in accordance with Pilot’s Operating Handbook (POH) or
Aircraft Flight Manual (AFM).
7.2.1.2 Magnetometer Calibration
NOTE
The Pitch/Roll Offset Compensation procedure in section 7.2.1.1 must be completed prior to performing
this procedure.
Use a compass rose or calibrated magnetic sight compass to calibrate the magnetometer. Ensure that
the aircraft and compass are located away from magnetic interference sources including buildings. The
accuracy of the ADAHRS cannot be guaranteed if the calibration is not performed in an area that is free
of metallic structure or objects.
With the aircraft stationary, initiate the magnetometer calibration procedure as follows:
1. Start the aircraft engine per the POH/AFM.
2. Taxi the aircraft to a desired calibration area.
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NOTE
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 20 feet of such objects. Ensure
that vehicles or other aircraft are a minimum of 40 feet away from the aircraft during this procedure.
3. 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 below.
Figure 7-4 – Compass Rose Starting Position
4.
5.
6.
7.
Power on the display(s) in Configuration Mode.
Select the Magnetometer Calibration Page.
Select Magnetometer Calibration.
Ensure that all on-screen instructions have been complied with and select the Start button to
begin the calibration.
Figure 7-5 – Magnetometer Calibration On-Screen Instructions
8. Follow the on-screen instructions, the dots at the end of the text will be removed as the test
progresses.
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Figure 7-6 – Magnetometer Calibration Progress
9. 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 dots have been removed,
and the text changes to ‘Hold Position’, stop turning the aircraft, and wait for further instructions.
10. 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.
11. When the calibration is finished, ensure that a Calibration Status of “Success” is displayed, then
press the Done softkey to return to the Magnetometer Configuration Page.
NOTE
If smooth accurate turns are not made, the ADAHRS may incorrectly interpret a station and instruct to
“Hold current position…” prior to or after completion of the heading change. If this scenario is
encountered, it is best for the operator to temporarily ignore the “Hold current position…” command and
instead use compass rose references to complete the heading change. Dwelling at these 30° increments
for the time recommended by the ADAHRS should result in successful calibration.
7.2.1.3
ADAHRS Static Pressure Calibration
The ADAHRS Calibration page, in configuration mode, has a selection for ADAHRS Static Pressure
Calibration. This procedure is used to perform an altimeter re-calibration.
NOTE
This calibration is only used when an ADAHRS fails a periodic altimeter test and should only rarely, if
ever, be used
The static pressure calibration requires the use of a pressure control system (test set) with an altitude
accuracy of at least +/- 5 ft at sea level and +/- 20 ft at 30,000 ft. It is necessary to re-calibrate to sea
level (0 ft), 10,000 ft, 20,000 ft, and optionally to 30,000 ft. Calibration to 30,000 ft is only required for
aircraft that may reach that displayed altitude.
CAUTION
To avoid damaging the ADAHRS pressure sensors, the pitot and static ports must be connected
to the test set.
1.
2.
3.
4.
Connect the pressure test set to the pneumatic ports on the aircraft skin.
Power on the PFD in configuration mode if it is not already in configuration mode.
Select the ADAHRS Calibration Page.
Select Static Pressure Calibration.
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Figure 7-7 – Static Pressure Calibration
5. Select “OK” to continue the calibration.
Figure 7-8 – Static Pressure Calibration Warning
6. Ensure that all on-screen instructions have been complied with and all information displayed is
correct, then select the “Start” button to begin the calibration.
Figure 7-9 – Static Pressure Calibration Instructions
7. At each calibration point (sea level, 10K, 20K, and optionally 30K ft), the display will present a
screen that allows time to establish the calibration pressure before continuing.
Figure 7-10 – Static Pressure Calibration in Progress
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8. Select “Next” to continue and calibrate each pressure.
9. During the calibration at each pressure, the pressure must be held constant for 30 seconds for
the calibration step to be successful. The calibration may be cancelled at any point should the
test setup require adjustment before repeating.
10. When the static pressure calibration is complete, a status screen will show that the procedure
was successful.
Figure 7-11 – Static Pressure Calibration Completion Status
7.2.1.4 Engine Run-up Vibration Test
NOTE
The Engine Run-Up Vibration Test is required for all installations to validate the vibration characteristics of
the installation. The ADAHRS Unit Orientation and Pitch/Roll Offset Compensation (Section 7.2.1.1) 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 25D.
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 does not account for all possible
vibration profiles that may be encountered during normal aircraft operation.
1.
2.
3.
4.
5.
Power on the PFD in configuration mode if it is not already in configuration mode.
Select the ADAHRS Calibration Page.
Ensure that all the required status boxes are checked.
Select Engine Run-Up Test.
Ensure that the aircraft has been properly positioned per the on-screen instructions, then select
the Start button to begin the test.
6. Gradually increase power from idle to full-throttle and back to idle over the course of one to two
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. Select the Done softkey when engine run-up has been completed; the test results will be
displayed.
8. Ensure that test results indicate Passed, then select the Done button to return to the ADAHRS
page.
The following are potential causes for failure of the engine run-up test:

Excessive flexing of GSU 25D with respect to airframe.

Vibration or motion of the GSU 25D caused by neighboring equipment and/or supports.

Mounting of GSU 25D at a location that is subject to severe vibrations such as near engine
mounts.

Mounting screws and other hardware for GSU 25D and/or GMU magnetometer not properly
attached.
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
GSU 25D connector not firmly attached to unit.

Absence of recommended mounting support.

Cabling leading to the GSU 25D not firmly secured to supporting structure.

An engine/propeller combination that is significantly out of balance.
NOTE
Some aircraft may have difficulty passing this test if performed in windy conditions. Windy conditions do
not provide evidence that the test would otherwise pass successfully; an actual pass is required before
the installation can be considered adequate.
7.3 GMU 11 Magnetometer
Reference Section 7.2.
7.4 GTP 59 Temperature Probe
Original GTP 59 Reinstalled
No software or configuration loading is required when an original GTP 59 is reinstalled.
New, Repaired, or Exchange GTP 59 Installed
If a new, repaired, or exchange GTP 59 is installed, no software or configuration required.
7.4.1 GTP 59 Testing
1. Verify OAT operation by observing the PFD for a valid value for OAT.
2. Apply heat to the GTP 59 probe and observe OAT value rises by at least 5º Celsius.
7.5 GAD 27
Original GAD 27 Reinstalled
No software or configuration loading is required if the removed GAD 27 is reinstalled. Continue to
Section 7.5.1.
New, Repaired, or Exchange Display(s) Installed
If a new, repaired or exchange GAD 27 is installed, the correct software will be loaded automatically by
the G3X GDU when power is applied to the system.
7.5.1 GAD 27 Testing
Apply power to the aircraft and with all the circuit breakers closed, ensure
the GDU.
is not displayed on
7.6 GEA 24 Engine and Airframe Unit
Original GEA 24 Reinstalled
No software or configuration loading is required if the removed GEA 24 is reinstalled. Continue to Section
7.6.1
New, Repaired, or Exchange GEA 24 Installed
If a new, repaired or exchange GEA 24 is installed, the correct software version and EIS configuration will
be loaded automatically by the G3X GDU when power is applied to the system. Continue to Section
7.6.1.
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7.6.1
GEA 24 Test
Verify all engine instruments are displayed and indicate valid values and markings. Reference Section
8.11 for checkout procedures.
7.7 GAD 29B
Original GAD 29B Reinstalled
No software or configuration loading is required if the removed GAD 29B is reinstalled. Continue to
Section 7.7.1.
New, Repaired, or Exchange GAD 29B Installed
If a new, repaired or exchange GAD 29B is installed, the correct software version will be loaded
automatically by the G3X GDU when power is applied to the system. Continue to Section 7.7.1.
7.7.1 GAD 29B Testing
Verify external LRUs that are connected to the GAD 29B such as compatible navigators and non-Garmin
autopilots are operating as intended:
1. GPS receiver check (Section 8.3)
2. Nav receiver check (Section 8.4)
3. Non-Garmin Autopilot interface check (Section 8.14)
7.8 GDL 5XR
Original GDL 5XR Reinstalled
No software or configuration loading is required if the removed GDL 5XR is re-installed. Continue to
Section 7.8.1
New Repaired or Exchange GDL 5XR Installed
If a new repaired or exchange GDL 5XR is installed, the software will be loaded to the unit automatically
by the G3X GDU when power is applied to the system. Continue to Section 7.8.1
7.8.1
GDL 5XR Functional Check
Perform functional tests as applicable in Section 8.
1.
2.
3.
4.
Activate SiriusXM Radio and Weather (Section 7.10) – for newly installed GDL 51R/52R.
ADS-B Traffic interface check (Section 8.5) (GDL 50R/52R).
GDL 51R/52R SXM weather check (Section 8.9).
GDL 51R/52R SXM audio interface check (Section 8.10).
7.9 G3X Software Information
All software files are certified by Garmin and are considered part of FAA-approved Type Design data.
System software version 8.00 and later are approved for this STC.
The installer shall create this software loader card by downloading the approved software image in
accordance with Section 7.9.1.
NOTE
Only SanDisk brand 8GB SD cards or smaller are recommended for use with the G3X
system. If another brand of card is used and software loading problems occur, replace the
card with a SanDisk brand card and reattempt the software load.
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7.9.1 Software Loader Card Creation
The software image is an executable self-extracting file which builds the correct file structure onto an SD
card for use in loading software to the G3X. To obtain the current file, follow the procedures outlined
below.
1. Go to www.garmin.com/G3XTouchCertified and click on the ‘Software’ link. Do not download
software from the Experimental Aircraft web page.
2. Insert a FAT32-formatted (empty) SD card in to the card reader.
3. Double-click the .exe file to download the self-extracting update file onto the hard drive. A window
similar to the image below will pop-up while extracting.
NOTE
When the extraction begins, the program automatically deletes all current files on the SD
card and copies the selected files to it, regardless of the file format on the SD card. Ensure
files are not necessary or card is empty before proceeding.
4. When extraction is complete, a window similar to one below will appear on the screen. Verify
“GDU 4xx” is correct and an SD card is in the card reader, and then select “Next”. Follow
instructions provided by the installer application.
5. Select from the drop-down list the correct drive letter of the SD card to be used for the update.
Click next.
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Select drive
6. A window will pop-up on the screen to indicating file progress.
7. Once successfully completed, a message/window similar to below will pop-up. Click Finish to
finalize SD card.
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8. Remove SD card from card reader.
NOTE
If necessary, ‘eject’ or un-mount the SD card prior to removal.
7.9.2
Software Loading Procedure
Software loading is performed in normal mode. Obtain the software loader card as formatted and loaded
with software per section 7.9.1. This section describes the procedures needed to load software to Garmin
LRUs as part of configuring the G3X system for use.
NOTE
Perform software updates on the ground only and remain on the ground while a software update is in
progress
7.9.2.1 GDU Software Loading Procedure
1. Connect external power to the aircraft to energize the aircraft and avionics electrical busses.
CAUTION
DO NOT RELY ON THE AIRCRAFT BATTERY TO LOAD SOFTWARE. DO NOT USE A BATTERY
CHARGER AS AN EXTERNAL POWER SOURCE. Power loss during a software upgrade may cause an
LRU to become corrupted and unresponsive requiring replacement.
2. Power on the PFD 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.
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3. A Software update window will appear on the screen; use the Touch Panel or a Move Selector
Knob to select YES to begin the update.
Figure 7-12 – Update Software Window
4. The unit will reboot, then GDU software update will begin automatically.
5. Ensure power is not removed while the update is being performed. The screen will display
progress of the software load.
6. The unit will reboot after the update is complete.
NOTE
When the PFD screen goes blank during reboot, hold the MENU button down until the screen indicates
Configuration Mode. Select the System Information page to see the software load status of other G3X
LRUs. Once all LRUs have been updated it is safe to remove power or reboot the display to normal
mode.
7. Repeat steps 1 through 5 on the MFD (if installed).
7.9.2.2 LRU Software Loading Information
G3X LRUs, (except for GDUs) will automatically receive software updates from the PFD following a GDU
software update. This process may take up to ten minutes for all LRUs connected to the high-speed CAN
bus. The GDL 5XR is connected via RS-232 and may take up to 30 minutes to update software.
Progress of LRU software updates can be monitored using the System Information page in configuration
mode. Functionality provided by an LRU will be unavailable during a software update, therefore, all LRU
software updates should be allowed to complete before flight after a GDU software update.
The current LRU software versions included with a GDU software update can be found in the change
notes on the software download page.
7.9.3 Software Load Confirmation
Perform software load confirmation after the software has been loaded to the G3X GDU(s) and LRUs.
1. Start the G3X GDUs in configuration mode (reference Section 3.2.2) as required.
2. Use the Touch Panel or a Move Selector Knob to select and view the System Information Page.
3. Ensure there is a green checkmark
next to all installed G3X LRUs.
4. Scroll the Device List box and select device’s info by using the Touch Panel or a Move Selector
Knob as necessary to verify the software and version numbers installed in the system.
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7.10 Activation of GDL 51R/52R SiriusXM Radio and Weather
Before SiriusXM Weather and Radio is accessed, service must be activated by SiriusXM. Service is
activated by providing SiriusXM with a Radio ID. Following the following activation steps.
Activation Steps
1. Contact SiriusXM at 1-855-796-9847 or at www.siriusxm.com/sxmaviation to activate.
2. Obtain the Radio ID from the data tag on the unit or from the Datalink page in normal mode. To
access the datalink page on the GDU, press “MENU” key twice for the main menu, then select
Data Link.
3. Position the aircraft in an area with an unobstructed view of the southern sky. It is highly
recommended that the aircraft be positioned outside and at least 25 feet away from the hangar.
4. Connect an external power unit and apply power to the aircraft and avionics.
5. Navigate to the Data Link page in the main menu section and verify signal quality has green bars.
6. When the subscribed product is displayed by “Service Level”, the activation is complete. For
example, in the screenshot below “Pilot Pro” is the subscribed product.
NOTE
Do not remove power from the aircraft during the activation process.
Figure 7-13 – Data Link Page
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8.
SYSTEM RETURN TO SERVICE PROCEDURE
This section provides checkout procedures to be completed after maintenance and/or repair has been
performed in accordance to this manual, in order to verify the proper operation and function of G3X Touch
systems.
Perform the procedures as applicable to the specific installation. Procedures not applicable may be
skipped.
8.1
Recommended Test Equipment
The following test equipment is recommended to conduct and complete all post installation checkout
procedures in this section:

Ground power cart (capable of supplying power to the aircraft systems and avionics)

Calibrated Air data test set

Calibrated VHF NAV test set

Low resistance ohmmeter

Calibrated Digital Level

Digital Multi-Meter (DMM)

Calibrated Optical Tachometer
8.1.1 LRU Status and Software Check
Perform LRU status and software check. The “System Information” page in the configuration mode of the
GDU 4X0 PFD has a “Devices Online” tab that reports the status of installed LRU’s and their currently
installed software part numbers and versions. The icon/checkbox next to each LRU reports a green
checkmark, a ‘red x’ or blank checkbox to indicate the status of each LRU as described in Table 8-1.
To access the System Information Page, perform the following steps on the primary GDU:
1. In configuration mode, select the System Information Page. Scroll the Device List box and the
selected device’s info by using the Touch Panel or a Move Selector Knob.
2. Verify that all LRUs connected or configured to each display have a green indicator and correct
software part numbers and version numbers are reported.
3. Press the Back key to return to the Configuration Mode page when finished. Return the GDU to
normal mode.
Table 8-1 – LRU Status Indicators
Color
LRU Condition
Green
The LRU is online & no faults found.
Red ‘X’
The LRU is online & a fault, warning, or error has been detected.
Blank
The LRU is not online.
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8.2 Transponder Check
The GNX 375, all GTX 335(R)/345 (R) transponders, and GTX 33/33ES/330/330ES transponders with
software version 8.00 or later are compliant with RTCA/DO-181D, which specifies that the selection of
transponder ALT and GND modes may not be controlled by the pilot. To allow the transponder to be
operated in ALT mode while on the ground, for the purposes of performing periodic testing in accordance
with the requirements of 14 CFR Part 91.413, a special transponder ground maintenance test mode is
provided.
To access ground maintenance mode in a G3X Touch system:
1.
2.
3.
4.
Access the Transponder page, press the Menu key twice to access the main menu.
On the Main menu, select Setup to access setup page.
On the Setup page, select XPDR to access the transponder page.
On the transponder page, select “Enabled” under Ground Maintenance Test to force the
transponder into ALT mode.
Figure 8-1 – Transponder Setup Page (Normal Mode)
Transponder ground maintenance mode will be cancelled following a power cycle, or if the aircraft is
determined to be airborne.
8.3 GPS Receiver Check
8.3.1
GPS Receiver Signal Acquisition Test
The following steps constitute a simple test of the GPS receiver’s ability to acquire a GPS signal from
satellites. This test needs to be performed outside, away from obstructions such as buildings, unless a
known working GPS signal repeater has been installed in the hangar for this type of testing.
1. Power on unit in normal mode and select the Info Page.
2. Verify that the GPS receiver is functional and able to calculate its present position
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8.3.2 GPS Receiver COM Interference Test
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.
This test must be conducted outside, as the use of a GPS repeater inside a hangar may result in a failed
test. After the preceding signal acquisition test has been completed successfully, perform the following
steps:
1. Apply power to the aircraft and G3X system and allow systems to initialize and the G3X system
and/or GPS navigator (if installed) to acquire sufficient satellites for a GPS solution.
2. On the MFD (in dual GDU installations) or on the multi-function pane in split format mode (in a
single GDU (PFD) installation); navigate to the info page to view the GPS status.
3. 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
3D Differential*
*Indicates valid GPS position fix for this test
4. Select 121.150 MHz on the COM transceiver.
5. Transmit for a period of 30 seconds while monitoring GPS status.
6. During the transmit period, verify that GPS status does not lose a valid GPS position fix on the
Main Page in configuration mode.
7. Repeat steps 3 through 5 for the following frequencies:

121.175 MHz

121.200 MHz

131.250 MHz

131.275 MHz

131.300 MHz
8. Repeat steps 3 through 6 for other installed COM transceivers if applicable.
9. 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

131.290 MHz
10. Repeat step 8 for other installed COM transceivers supporting 8.33 MHz channel spacing if
applicable.
This COM interference test should be repeated if a second GDU is installed in the aircraft and paired with
GPS antenna.
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8.3.3 GPS Receiver Interface Check
NOTE
GPS satellite reception is required for the following steps. Perform the test in an outdoor area
with a clear view of the sky. The check may also be performed in a hangar with a good known
GPS repeater.
1. Verify the PFD is in Normal mode.
2. On the PFD options page under FPL Source, select “External GPS”.
3. On the PFD options page under CDI Source, select “GPS” (or “GPS1”) as the navigation source.
4. Verify the external GPS1 Navigator is powered on and if dual GPS navigators are installed,
ensure the second GPS navigator (GPS2) is powered off.
a. For a GPS 175, GNX 375, GNS 4XXW/5XXW series or GTN 6XX/7XX series navigator,
while on the power-up self-test page, verify that the PFD CDI displays the correct lateral
and vertical deviation information.
b. For a GNS 480 unit, while it is going through its power-up sequence, verify that the PFD
CDI displays the correct lateral and vertical deviation information.
5. Continue in normal mode after self-test and wait until the navigator acquires a position before
proceeding.
6. Review the active alerts on the PFD (if any) and verify that there are no alerts, service soon, or
service required alerts associated with the GPS unit.
7. Create or activate a flight plan on the GPS navigation source.
8. Verify that the active waypoint displayed in the PFD WPT field of the GDU 4X0 is the same as the
active waypoint displayed on the navigator.
9. On the GPS navigator, enter OBS mode.
10. When OBS mode is entered on navigator, the course (CRS) field
activate and change to OBS on a lighter background
configured for course will be activated to change the course.
on the GDU will
, and knob that has been
11. Adjust the course (OBS) using the configured PFD knob. Course may also be changed using the
touch screen by pressing the OBS/CRS field and entering the value using the pop-up keypad.
12. Verify that the course to the active waypoint changes on the navigator as the PFD course pointer
is rotating.
13. Exit OBS mode on the navigator.
14. If dual GPS receivers are installed power off GPS 1 and power on GPS 2. Select GPS2 on the
CDI and repeat the GPS interface check (Steps 1-13).
8.4 NAV Receiver Check
1. Verify the external NAV1 receiver is powered on and if dual NAV receivers are installed, ensure
the second NAV receiver (NAV2) is powered off.
2. Tune the NAV receiver to a localizer frequency (it is not necessary that a valid localizer signal is
being received).
3. Verify that the CDI on the PFD displays “LOC” (or “LOC1”/“LOC2” for installations with dual
navigators). The CDI source field in PFD options page should also display “LOC” (or
“LOC1”/“LOC2”.
4. If dual navigation receivers are installed, power off NAV 1 and power on NAV 2.
5. Repeat the steps 2 through 4 above.
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8.5 ADS-B Traffic Interface Check
NOTE
The following steps may be performed as a ground check as long as the aircraft is within range
of an FAA ground station with available targets of opportunity. If this is not the case, it is
recommended that these checks be performed in flight within range of an FAA ground station.
If the installed system is configured to receive ADS-B In data through an interface with an ADS-B In
capable unit (GNX 375, GTX 3X5 or GDL 50R/52R), the interface is verified as follows:
1. Verify the GDU is in normal mode.
2. Select the Traffic page on the home screen of the MFD or the multi-function pane on the PFD.
3. Turn on the interfacing ADS-B In capable equipment.
a. If the installation includes TAS/TCAS correlated traffic, turn on the TAS/TCAS source.
4. Make sure an amber NO DATA or TRAFFIC FAIL messages are not displayed over or below the
“ownship” icon.
5. Make sure there are no FAIL annunciations in the upper left-hand corner of the traffic status
window. Depending on installation either
or
should be displayed if ADS-B
Interface is correct.
a. If the installation includes TAS/TCAS correlated traffic, verify that the TAS/TCAS status is
either OPER or STBY.
6. Observe targets of opportunity from ADS-B equipped aircraft, or an FAA ground station.
7. Apply power to any installed L-band equipment such as transponders, DME or TCAS, ensure
there is no interference with ADS-B data reception.
8.5.1 TCAS Traffic Interface Check
1. Verify the GDU is in normal mode.
2. Select the Traffic page on the home screen of the MFD or the multi-function pane on the PFD.
3. Verify that no TAS/TCAS failure annunciations (“NO DATA”, “TRFC FAIL”, “NO TRFC DATA”,
“DATA FAILED”, “FAILED”) are shown on the traffic map.
4. In the upper left corner of the Traffic Map page, verify that the Traffic Status is either TAS/TCAS:
OPER or TAS/TCAS: STBY (“TIS: FAIL” or “TAS/TCAS: FAIL” must not be displayed).
5. Select the Traffic Status button and change the mode between Operate and Standby.
6. Verify that the mode of the traffic system is updated accordingly.
7. Put the traffic system in Standby mode.
8. Initiate a traffic system self-test by selecting the Test button at the bottom of the page. Note: The
Self-Test button will not be selectable if the traffic system is not powered on or is in a failed
status.
9. Verify that the traffic system runs a self-test and the self-test traffic pattern is displayed.
8.6 TIS-A Traffic Interface Check
If a Garmin GTX 3X5 transponder is connected to the G3X Touch system and no other traffic systems
covered in this manual is installed, the traffic interface is verified as follows:
1. Verify the PFD is in normal mode. For a dual GDU installation verify both are in normal mode,
and test is performed on the MFD.
2. For single GDU installations, select the Traffic page in split screen format on PFD.
3. Turn on the GTX 3X5 by pressing ALT on the GTX.
4. Verify that the Traffic Status is not TIS Fail.
5. Verify that the amber NO DATA is not displayed over the “ownship” symbol.
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6. Verify that the Traffic Status is in Standby mode. (i.e., TAS should not be displayed).
7. Attempt to place the system in Operate mode, if the aircraft is within TIS-A coverage, the system
will display Operate, if the aircraft is not within TIS-A coverage, the unit will display ‘Unavailable’.
8.7 WX-500 Stormscope Interface Check
1. Verify the GDU is in normal mode. For a dual GDU installation verify both are in normal mode.
2. Allow up to five minutes for the system to obtain a GPS position fix.
NOTE
If no other weather source is configured, the Stormscope button will be present instead of the Weather
button.
3.
4.
5.
6.
On the MFD, select the Weather button and then select the Stormscope Button.
Verify there are no warnings displayed.
On one MFD, press Menu.
Toggle between Cell and Strike modes and verify that the corresponding mode is displayed in the
bottom right corner of the MFD.
7. Toggle between 360° and Arc views and verify the image switches between a 360° view
surrounding the aircraft icon to an arc placed in front of the aircraft icon.
8.8 FIS-B Weather via ADS-B In
NOTE
The following steps may be performed as a ground check as long as the aircraft is within range of an FAA
ground station. If this is not the case, it is recommended that these checks be performed in flight within
range of an FAA ground station.
1.
2.
3.
4.
Verify the G3X Touch EFIS is in normal mode.
Verify the GPS and FIS-B source is in normal mode.
Allow up to five minutes for the system to obtain a GPS position fix.
On each installed GDU, select navigate to the Weather page, and press MENU then select the
FIS-B under the “Data Source” field.
NOTE
It may take up to 10 minutes after power-on for the system to begin receiving FIS-B weather products.
5.
6.
7.
8.
Verify there are no warnings displayed.
Press MENU button and then select several FIS-B weather products to display.
Verify at least one of the selected products displays a valid time stamp.
Verify there are no status fail messages regarding FIS-B weather.
8.9 GDL 51R/52R SXM Weather Check
SiriusXM weather and radio activation is required for this check, reference Section 7.10 for instructions.
Position the aircraft where there is a clear view of the southeastern or southwestern sky. XM Satellite
Radio satellites are located above the equator over the eastern and western coasts of the continental
United States.
1. Verify the G3X Touch system is in normal mode.
2. Allow up to five minutes for the system to obtain a GPS position fix and the GDL 5XR to obtain
data.
3. On each GDU, select the Weather page from the multi-function pane.
4. Verify there are no warnings displayed.
5. Push the GDU knob to display weather data page.
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6. Verify weather data associated with the subscribed service level is available. Examples of
weather data available are “NEXRAD, METAR, Winds Aloft, Lightning etc.
8.10 GDL 51R/52R SXM Audio Interface Check
This procedure only verifies correct installation and activation of G3X Touch system functions. It does not
activate the GDL 5XR Series XM data link radio. SiriusXM weather and radio activation is required for this
check, reference Section 7.10 for instructions.
1. Position the aircraft where there is a clear view of the southeastern or southwestern sky. (XM
Satellite Radio satellites are located above the equator over the eastern and western coasts of
the continental United States.)
2. Verify the G3X Touch system is in normal mode.
3. Allow up to five minutes for the system to obtain a GPS position fix and the GDL 5XR to obtain
data.
4. On each GDU’s Multi-function pane, select the SXM page.
5. Verify Audio signal bars are in the Green and that the displayed subscription level is accurate.
6. Verify that under Artist “XM DATA LINK FAIL” is not displayed.
7. Using the inner knob, scroll the channels.
8. Verify that music plays on multiple channels.
8.11 EIS Check
This section contains procedures to verify proper installation, operation, and gauge markings of the EIS.
Complete the following applicable checkouts if EIS sensor or gauge settings may have been affected by
maintenance.
CAUTION
Check hose routing for sharp bends. Check sensors and fittings for leaks during and after engine run-up
and correct prior to flight.
8.11.1 EIS Ground Check
Conducted with the engine off and at ambient temperature.
1.
2.
3.
4.
Verify the G3X Touch system in normal mode.
Navigate to the engine page on the MFD or multi-function pane of the PFD in split format.
Verify that no red or amber X marks are present on any EIS gauge.
EGT/CHT- Apply heat to each EGT/CHT sensor to verify the corresponding cylinder is connected
correctly.
NOTE
If the temperature decreases when heat is applied, the wire polarity may be reversed.
5. Manifold, oil, or fuel pressure(s)- Verify the corresponding gauge(s) display the ambient
condition(s).
NOTE
Estimate the ambient manifold pressure by subtracting 1 inHg for every 1,000 ft of field elevation from the
current barometric pressure.
6. Current or Voltage- Verify the corresponding gauge(s) display the correct measurement(s).
7. Fuel Quantity- Verify the indicated fuel quantities are accurate for each tank when the aircraft is
leveled in accordance with the aircraft manufacturers instructions.
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8.11.2 EIS Engine Run-Up Check
Always follow engine startup procedures as described in the Aircraft POH.
CAUTION
If the engine indications are not within operating specifications shortly after starting, IMMEDIATELY shut
down the engine and troubleshoot the problem. Failure to do so may cause engine damage.
Obtain an optical tachometer to monitor propeller RPM.
1. Place the aircraft in an open and clear area appropriate for an extended engine run-up.
2. Follow the engine start-up procedure as outlined in the aircraft POH. Adhere to the required
observations immediately following the start such as oil pressure within 30 seconds.
3. Verify the EIS RPM gauge(s) match the optical tachometer reading +/- 50 RPM.
4. Allow the engine to warm up and oil temperature to increase to at least 100°F.
5. Verify the alternator load meter (if installed) and battery charge/discharge ammeter (if installed)
indicate a positive load.
6. Perform individual magneto checks as specified by the aircraft POH. If the RPM does not drop as
expected when switching from both magnetos to one, the P-lead, ignition switch wiring, or
magneto timing is incorrect. Discontinue the test immediately and repair the ignition system.
7. Verify all EIS readings are consistent with normal operation performance in accordance with
aircraft type design, engine type design, and/or aircraft POH/AFM.
8. Verify all installed sensors and fittings are free of leaks.
8.12 ADAHRS and Magnetometer Ground Checks
This section contains the ground checks that may be performed on the magnetometer for ADAHRS
aspects of the G3X system.
8.12.1 Altimeter Check
The GDU 4X0 altitude displays must be verified per Title 14 CFR 91.411 and 14 CFR Part 43 Appendix
E, with the following exception to 14 CFR Part 43 Appendix E, paragraph (b)(1):

The tests of sub-paragraphs (iv) (Friction) and (vi) (Barometric Scale Error) are not applicable
because the digital outputs of the GSU 25D are not susceptible to these types of errors.
This procedure is recommended when the GSU 25D is removed and reinstalled/replaced or the pitot and
static system connections are disturbed.
8.12.2 Pitot-Static and Airspeed Tape Settings Checks
The following section verifies the correct operation of the GDU 4X0 altitude and airspeed display
functions. These tests require the use of a Calibrated Air data test set. When using a Calibrated Air data
test set, only simulate normal aircraft operating conditions, as defined in the aircraft Type Data
(POH/AFM) or other approved STC to avoid component damage.
Airspeeds above Vne should not be checked.
The aircraft or instrument manufacturer’s data should be referenced for tolerances for this test where
available.
1.
2.
3.
4.
Connect the calibrated air data test set to the aircraft.
Apply power to the aircraft.
Verify all self-tests pass on the main startup screen.
Using the air data test set, increase the airspeed until the PFD airspeed tape pointer is at the
bottom of the white band (Vs0).
5. Verify that the pitot and static pressure settings used on the test set match what is displayed on
the GDU.
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6. On the pitot static test set, change the airspeed until the PFD airspeed tape pointer is at the
bottom of the green band (Vs1).
7. Verify that the bottom of the green arc/band on the standby ASI and PFD airspeed tape are at the
same airspeed value.
8. Change the airspeed until the PFD airspeed tape pointer is at the top of the white band (Vfe).
9. Verify that the top of the white arc/band on the standby ASI and PFD airspeed tape are at the
same airspeed value.
10. Change the airspeed until the PFD airspeed tape pointer is at the top of the green band/bottom of
the yellow band (Vno).
11. Verify that the top of the green arc/band on the standby ASI and PFD airspeed tape are at the
same airspeed value.
12. Increase the airspeed to the upper red radial/top of yellow arc (Vne).
13. Verify that the red radial on the standby ASI and PFD airspeed tape are at the same airspeed
value.
14. Starting at the current airspeed, decrease the airspeed to zero, stopping at each of the airspeeds
listed in Table 8-2. verifying that the PFD and standby ASI airspeed values are within the
tolerances indicated in Table 8-2.
NOTE
The aircraft or instrument manufacturer’s data should be referenced for standby tolerances, if
available.
Table 8-2 – Airspeed Test Points
Test Set
(KTS)
Allowed Tolerance
(+/- KTS)
50
5.0
80
3.5
100
2.0
120
2.0
150
2.0
Recorded Result
GDU
Recorded Result G5 (or
installed Standby ASI)
8.12.3 Compass Swing
After the Magnetometer Calibration Procedure is completed, a compass swing must be performed to
verify the ADAHRS/GMU 11 heading accuracy.
1. Verify ‘Auto Mag. Variation’ is selected.
o With the PFD in Normal mode, navigate to the Position Setup Page (Menu → Main Menu
→ Setup →Position).
o Under Heading tab, ensure ‘Auto Mag. Variation’ is selected.
o Return to the main screen.
2. With the PFD in normal mode, all of the aircraft and avionics systems powered and operating
normally, position the aircraft on a known compass rose at a heading 360° (North), or select a
level and magnetically clean location and use a sight compass to position the aircraft to a heading
of 360° (North)
3. Record the HDG value displayed on the PFD as indicated in Table 8-3, below. Also record the
heading displayed on the standby compass. Verify or correct the standby compass deviation
card.
4. Repeat step 2 for each of the headings listed in Table 8-3.
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5. Calculate the heading errors by subtracting the displayed (B) value from the actual (A) value for
each of the headings in Table 8-3.
6. If all calculated heading errors displayed on the PFD are at or within +/-10° from the surveyed
heading, the installation is acceptable, and no further work is required to correct the GMU 11
installation.
7. If a Heading Error (A-B) is greater than +/- 10°, calculate the average error by adding all errors
and dividing by 12. This is the angle by which the GMU 11 must be physically rotated to correct
the installation.
8. Modify the installation to rotate the GMU 11 by the amount calculated in the previous step. When
looking down at the GMU 11, rotate clockwise for positive values, and counterclockwise for
negative values.
9. After physically correcting the GMU 11 installation, repeat the procedures in Sections 0 and
8.12.3.
Table 8-3 – Heading Verification – ADAHRS Check
Heading (A)
Displayed ADAHRS
Heading (B)
Heading Error (A-B)
Standby Compass
Heading
360° (North)
30°
60°
90°(East)
120°
150°
180°(South)
210°
240°
270°(West)
300°
330°
8.13 Garmin GFC 500 Autopilot
For aircraft equipped with Garmin GFC 500 autopilot system, perform interface checkout of the autopilot
in accordance with procedures outlined in GFC 500 Part 23 AML STC Installation Manual 190-02291-00.
8.14 Non-Garmin Autopilot Interface
Before proceeding with the autopilot interface tests, verify the PFD has been properly configured for the
autopilot (and flight director, if applicable) that is installed. For configuration instructions reference
Appendix B.5. and the G3X Touch EFIS Part 23 AML STC Installation Manual (190-02472-01). Only
those interfaces which are directly affected by the G3X Touch STC are covered by this manual; if any
other autopilot modifications were performed, they are outside the scope of this STC and must be
checked in accordance with the autopilot installation manual.
WARNING
It is important that the PFD be properly configured in order to prevent damage to the autopilot computer.
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NOTE
The following procedures are general in nature and it may be necessary to reference the autopilot
manufacturers testing instructions to allow the autopilot to be tested properly.
8.14.1 Autopilot Engagement Check
This section verifies that the autopilot can be engaged.
1. Verify the G3X Touch system is in normal mode. Allow the PFD to obtain a valid heading,
attitude, altitude, and GPS location.
2. Verify the GPS navigator is in normal mode.
3. Engage the autopilot. If the autopilot cannot be engaged, troubleshoot using the instructions in
the autopilot installation manual.
4. If step 3 was successful, disengage the autopilot.
8.14.2 Heading and Course Error Check
This section verifies that the heading and course error interface between the GDU 4X0 and autopilot
computer is functional. For dual GDU G3X Touch installations, the following instructions apply only to the
PFD.
8.14.2.1 Heading Error
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
Verify the G3X Touch system is in normal mode.
On the PFD set the heading bug to the current aircraft heading.
On the PFD, verify HDG/CRS Valid.
Engage the autopilot in HDG mode.
Adjust the heading bug to the right.
Verify that the control yoke or stick moves to the right.
Adjust the heading bug to the left.
Verify that the control yoke or stick moves to the left.
Adjust the heading bug to the aircraft heading.
Disengage the autopilot.
NOTE
If the control yoke or stick moves in the opposite direction of what is expected, reverse the
LEFT/RIGHT HDG Polarity on the Autopilot Calibration page and continue the checkout
process.
8.14.2.2 VOR Course Error
Some autopilot systems might not have course error capability; and this step is not necessary for those
systems.
1. Apply power to the aircraft and aircraft systems and allow the aircraft systems to initialize.
2. Tune the VHF NAV to the NAV/COM Test Set frequency for VOR operation.
3. Set the Course pointer on the PFD HSI 15 degrees to the left of aircraft heading and ensure that
the PFD CDI is displaying VOR navigation information.
4. Simulate a VOR signal with a “TO” course equal to the aircraft heading.
5. Slowly adjust the course pointer on the PFD CDI toward the aircraft heading until VOR captures.
6. Center PFD CDI course pointer on the aircraft heading.
7. Engage the autopilot in NAV mode.
8. Adjust the NAV ramp tester course and the PFD CDI course pointer 20 degrees to the left of
current aircraft heading.
9. Verify that the flight controls move toward the left.
10. Adjust NAV ramp tester course to aircraft heading.
11. Adjust the NAV ramp tester course and the PFD HSI CDI course pointer 20 degrees to the right
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of current aircraft heading.
12. Verify that the flight controls move toward the right.
13. Adjust the NAV ramp tester course to aircraft heading.
14. Disengage the autopilot.
8.14.2.3 Localizer
1. Tune the VHF NAV to the NAV/COM Test Set frequency for LOC operation.
2. On the NAV ramp tester simulate centered LOC needle presentation.
3. Set the Course pointer on the PFD HSI to the current aircraft heading.
4. Verify the PFD CDI displays centered deviation for LOC.
5. On the NAV ramp tester simulate 0.093 DDM Left LOC.
6. Verify PFD CDI deviation bar is one dot left.
7. Verify that the flight controls turn to the left.
8. On the NAV ramp tester simulate 0.093 DDM Right LOC.
9. Verify PFD CDI displays one dot right.
10. Verify that the flight controls turn to the right.
11. On the NAV ramp tester simulate centered LOC needle presentation.
12. Disengage the autopilot.
8.14.3 GPSS Course
This test is only performed for installations that are interfaced to a GPS navigation source and the
interfaced autopilot did not previously have a GPSS function. Conduct this test with the aircraft
positioned where it can receive GPS signal.
1. On the GPS navigator, enter a simple Direct-To flight plan with a waypoint that is on the current
aircraft heading and select the PFD CDI to display GPS. If the navigator has the capability to
enter user waypoints, a user waypoint can be entered to facilitate this test. It is suggested that
the waypoint be within 5 miles of the current aircraft position for best results.
2. On the PFD Attitude display, press the MENU button to display the 'PFD Options’ page, select
GPSS.
3. Verify the following:
On the PFD Attitude
 GPSS field is available when selected.
 The heading bug is a hollow cyan bug.
On the PFD CDI

4.
5.
6.
7.
8.
9.
10.
11.
12.
GPSS field in the menu has a green bar at the bottom indicating GPSS is selected.
 The heading bug is a hollow cyan bug on the CDI.
On the navigator select OBS to enter GPS OBS mode.
Set the OBS course for the current aircraft heading (it is assumed the waypoint is on the current
aircraft heading).
Engage the autopilot in HDG mode.
Adjust the OBS course 20 degrees to the left of current aircraft heading.
Verify that the flight controls move toward the left.
Adjust the OBS course 20 degrees to the right of current aircraft heading.
Verify that the flight controls move toward the right.
Adjust the OBS course to aircraft heading.
Disengage the autopilot.
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8.15 G5 Miscompare Check
This test is only performed on installations with G5 ADI as a standby instrument.
1. Apply power to the aircraft and G3X system and allow G5 to initialize.
2. Verify heading, altitude and IAS values on the G3X PFD match the values on the G5, and
heading, altitude and IAS miscompare messages are not displayed on the PFD.
3. Rotate G3X PFD knob that has been configured for controlling heading and verify “HDG xxxº” is
displayed on the G5 and matches the value on the G3X PFD, and the heading bugs move at the
same rate on both the G5 and G3X PFD.
4. Press the G5 knob then rotate to highlight “Heading” field, press the knob to make selection and
rotate to adjust:

Verify the values on the heading field on the G3X PFD incrementally change at the same
rate and values match the G5 ADI.
 Verify the heading bugs move at the same rate on both the G5 and G3X PFD
5. Rotate G3X PFD knob that has been configured for controlling the altitude bug and verify the
bugs move, values match and incrementally change at the same rate on both the G5 and G3X
PFD altitude tape.
6. Press the G5 knob then rotate to highlight “Altitude”, press the knob to make selection and rotate
to adjust:

Verify the altitude bugs move, values match and incrementally change at the same rate
on both the G5 ADI and G3X PFD altitude tape.
7. Rotate G3X PFD knob that has been configured for controlling “Baro” and verify the barometric
pressure and pressure altitude values incrementally change at the same rate and values match
on both the G5 ADI and G3X PFD.

Verify the “Baro” field on the G5 changes to a cyan color and the digits change to black
color but revert to black field with cyan digits, once the knob is no longer rotated.
8. Rotate G5 ADI knob and verify the barometric pressure and pressure altitude values
incrementally change at the same rate and values match on both the G5 ADI and G3X PFD.

Verify the “Baro” field on the G3X PFD changes to a cyan color and the digits change to
black color but revert to light background with cyan digits, once the knob is no longer
rotated.
8.16 EMI / RFI Check
An EMC check must be conducted once the G3X Touch system is installed and all interfaces to external
equipment are verified to be working correctly. The EMC check verifies that the G3X system is not
producing unacceptable interference in other avionics systems and other avionics systems are not
producing unacceptable interference in the G3X system. Table 8-4 below should be used to collect data
for this check.
1.
2.
3.
4.
5.
Enter equipment installed in the aircraft into the Source row and Victim column of the form.
Apply power to all avionics systems except for the components that are part of the G3X system.
Verify all existing avionics systems are functioning properly.
Apply power to the G3X system.
Remove power from all other avionics systems.
NOTE
Wait for the current system start up sequence to finish before applying power to the next system.
6. Apply power and/or operate the systems listed on the fillable form on Table 8-4, one system at a
time. Make sure to pull/push circuit breakers or turn on/off large loads, e.g. heaters, cycling flaps
(if electrical) etc.
7. Verify the G3X system functions properly and no related messages are displayed.
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8. Verify each radio is functioning properly by completing the following:
a. For each VHF COM radio, monitor one local frequency, one remote frequency, and one
unused frequency.
b. Verify no unintended squelch breaks or audio tones interfere with communications.
c. For each VHF NAV radio, monitor one local frequency, one remote frequency, and one
unused frequency.
d. Verify there are no guidance errors.
e. Verify no audio tones interfere with the station ID.
f. For each GPS Navigator, enter a simple flight plan and display as appropriate. i.e.
Navigator Display, PFD, CDI etc., if installed.
g. Verify there are no guidance errors.
9. If an EI FT-60 or an EI FT-90 fuel flow sensor is installed, verify the fuel flow indication is accurate
and the indication does not fluctuate or invalidate the display.
a. Transmit various modulating tones on each COM radio (e.g. Whistling).
b. See section the G3X Touch EFIS Part 23 AML STC Installation Manual (190-02472-01)
for details if the fuel flow indication fluctuates.
NOTE
EMI check of the fuel flow must be performed with the engine running.
10. Verify all other avionic systems are functioning properly.
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SOURCE
<add equipment here>
<add equipment here>
Autopilot / SAS
Transponder
Audio Panel
TAS/TCAS
Radar Altimeter
Hydraulic System
Gov RPM Incr / Decr
Anti-Collision Lt
Landing Lights
Generator
Pos Lt
Pulse Light
Pitot Heat
Fuel Valve
Communication Radio(s)
Navigation Radio(s)
Magnetic compass
GTP 59 (OAT indication)
GEA24 (if installed)
GDL 5XR (if installed)
GSU 25D (PIT/ROLL)
GAD 29B (If installed)
GMU 11 (Mag. Heading)
GDU #1
GDU #2 (If installed)
Table 8-4 – EMI Victim/Source Matrix
GDU #1
GDU #2
(If installed)
GMU 11
(Mag. heading)
GAD 29B
(If installed)
GSU 25D
(PIT/ROLL)
GDL 5XR (if
installed)
GEA 24 (if
installed)
GTP 59 (OAT
Indication)
Magnetic
Compass
Navigation
Radio(s)
Communication
Radio(s)
Fuel Valve
Pitot Heat
Pulse Light
Generator
Pos Lt
Anti-Collision Lt
Landing Lights
Gov RPM Incr /
Decr
Hyd System
Radar Altimeter
TAS/TCAS
Transponder
Audio Panel
Autopilot / SAS
<add equipment
here>
<add equipment
here>
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APPENDIX A
INSTALLATION SPECIFIC INFORMATION
A copy of this appendix must be used to record information for a specific installation of the G3X Touch
EFIS Part 23 AML STC system. The completed copy must be kept with the aircraft permanent records.
This appendix includes the following information:
A.1 Maintenance Records
This Post-Installation Configuration Log should be completed during the initial installation, with any
software modifications post initial installation, and maintained with the aircraft permanent records.
 G3X software version used to perform software updates.

Record part and serial numbers of all LRU’s at installation.

Record Mod Status of all LRU’s at installation.

Record part and serial numbers of any LRU which was replaced.

Record any database updates which were performed during maintenance.

Any other applicable information related to the maintenance work performed on the aircraft.
Table A-1 – G3X Post-Installation Log
Post-Installation Configuration Log
Date:
Aircraft Model:
Aircraft Make:
Aircraft
Registration #:
Aircraft Serial #:
Engine:
New Software Version (if
applicable):
Original Software Version:
Unit/Option
Installed/Enabled?
(check if installed or
configured)
LRU Part Number
LRU Serial
Number
Mod Status
GDU 460
GDU 470
GMU 11
GSU 25D
GTP 59
GAD 29B
GAD 27
GEA 24
GDL 5XR
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A.2 Equipment Locations
Appendix B contains a documentation sheet for recording G3X Touch EFIS LRU’s included in the
installation and its location on the aircraft. The document will be completed during the initial installation
and maintained with the aircraft records.
Table A-2 – G3X Equipment Locations
Date:
Aircraft Make/Model:
LRU
Aircraft Reg #/Serial #:
Station C.G
Description of Location
GDU 460
in.
GDU 470
in.
GMU 11
in.
GSU 25D
in.
GTP 59
in.
GAD 29B
in.
GAD 27
in.
GEA 24
in.
GDL 5XR
in.
A.3 Wire Routing
Figure A-1 is a generic aircraft drawing to be used for documenting the wire routing for the installation of
the G3X Touch EFIS LRUs. The drawing will be completed during the initial installation and maintained
with the aircraft records.
Record equipment locations and sketch the approximate location of wire routing on the figure below as
applicable.
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Figure A-1– Generic Aircraft Figure
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Page A-3
APPENDIX B
EXTERNAL INTERFACE CONFIGURATION
B.1 GPS/VHF Nav Interfaces
The GPS position sources listed in Table B-1 are compatible with the G3X Touch. Reference Section
3.2.2 for entering configuration and changing data on G3X units.
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 existing configuration settings (before making any changes) for
reference.
Table B-1 – Compatible Equipment – GPS/VHF Nav Interfaces
MFR
Garmin
Model
GNS 4XX(W)/
5XX(W) Series
Data
Format
G3X Configuration Setting
Interfacing Equipment
Configuration Setting
ARINC
492
ARINC 429 Configuration
Page:
429 Output 1: “EFIS /Airdata
Format 1” and “Nav 1”
429 Input 1: “Garmin GPS”
and “Nav 1”
429 Input 2: “Garmin
VOR/ILS” and “Nav 1” (GNS
430(W)/530(W))
For dual GNS configure #1
GNS as above and #2 GNS
as below:
429 Output 2: “EFIS /Airdata
Format 1” and “Nav 2”
429 Input 3: “Garmin GPS”
and “Nav 2” for GNS #2 (If
Applicable)
429 Input 4: “Garmin
VOR/ILS” and “Nav 2” for
GNS #2 (GNS
430(W)/530(W))
GNS 4XX(W)/5XX(W)
Main ARINC Config Page:
IN 1 Speed: “LOW”
IN 1 Data: “EFIS/Air Data”
OUT Speed: “LOW”
OUT Data: “GAMA 429”
SDI: “LNAV 1”
VNAV: “Enable Labels” (WAAS
Units Only)
For dual GNS configure as
above and below:
SDI: “LNAV 2” on #2 GNS (dual
GNS ONLY)
VNAV: “Enable Labels” on #2
GNS (WAAS Units Only)
RS-232
RS-232 Configuration Page
Serial Port ‘x’: “MapMX”
(WAAS Unit) or “Aviation In”
(Non-WAAS unit)
Serial Port ‘x’ (Connext):
“Garmin Instrument Data”
(GTN 4XXW/5XXW Only)
RS-232 Configuration Page
CHNL 1 Input: “OFF”
CHNL 1 Output: “MapMX”
(WAAS units only) or “Aviation”
(Non-WAAS unit)
CHNL 2 Input/Output:
“Connext” (When Connext is
used)
Main Software v3.30
or later is required.
For dual GNS, configure #1
GNS as above and #2 GNS
as below:
RS-232 Configuration Page
Serial Port ‘x’: “MapMX”
(WAAS Unit) or “Aviation In”
(Non-WAAS unit) (PFD or
MFD)
NOTE: “x” = Connected Port
#
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G3X Touch EFIS Part 23 AML STC
Main CDI/OBS Config Page
(GNS 430(W)/530(W)
Press Menu and select “Ignore
SEL CRS for VLOC” Option
Note: Menu will display “Allow
SEL Course for VLOC” when
set correctly.
VOR/ILS ARINC 429 Config
Mode Page (GNS
430(W)/530(W)
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MFR
Model
Data
Format
G3X Configuration Setting
(GNS #1 must be connected
to a lower number port than
GNS #2. In dual GDU
installations GNS, #2 may be
connected to any port on the
MFD))
GNS 480
ARINC
492
ARINC 429 Configuration
Page:
429 Output 1: “EFIS /Airdata
Format 1” and “Nav 1”
429 Input 1: “Garmin GPS”
and “Nav 1”
429 Input 2: “Garmin
VOR/ILS” and “Nav 1”
GNS 480 Main ARINC Setup
Page:
IN 2SEL: “EFIS”
IN 2 Speed: “LOW”
IN 2 SDI: “SYS1”
OUT 1SEL: “GAMA 429”
OUT 1 Speed: “LOW”
OUT 1 SDI: “SYS1”
OUT 2 SEL: “VOR/ILS”
OUT 2 Speed: “LOW”
OUT 2 SDI: “SYS1”
RS-232
RS-232 Configuration Page
Serial Port ‘x’: “MapMX”
NOTE: “x” = Connected Port
#
GNS 480 Serial Setup Page
CHNL 1 Output: “MapMX
ARINC 429 Configuration
Page:
429 Output 1: “EFIS /Airdata
Format 1” and “Nav 1”
429 Input 1: “Garmin GPS”
and “Nav 1”
429 Input 2: “Garmin
VOR/ILS” and “Nav 1”
GTN Main ARINC 429 Config
Page:
IN 1 Speed: “LOW”
IN 1 Data: “EFIS Format 2”
OUT 1 Speed: “LOW”
OUT 1 Data: “Garmin 429”
SDI: “LNAV 1”
When interfaced with NonGarmin autopilot:
IN 2 Speed: “LOW” (2)
IN 2 Data: “GAD Format 1” (2)
Software v2.3 or later
is required.
GTN 6XX/ 7XX
Software v6.51 is
required
Interfacing Equipment
Configuration Setting
RX and TX Speed: “LOW”
SDI: “VOR/ILS 1” (“VOR/ILS 2”
for GNS 2)
ARINC
429
For dual GTN configure as
above (GTN 1) and below
(GTN 2):
429 Output 1: “EFIS /Airdata
Format 1” and “Nav 2”
429 Input 3: “Garmin GPS”
and “Nav 2” for GTN #2 (If
Applicable)
429 Input 4: “Garmin
VOR/ILS” and “Nav 2” for
GTN #2
RS-232
RS-232 Configuration Page
Serial Port ‘x’: “MapMX”
(PFD)
Serial Port ‘x’:
“GTN Connext 2” (PFD)
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Resolver Interface Page
Resolver: “Not Installed”
Miscellaneous Setup Page
CDI Select: “USE”
For dual GTN configure as
above and below (GTN 2) :
IN 1 Speed: “LOW”
IN 1 Data: “EFIS Format 2”
OUT 1 Speed: “LOW”
OUT 1 Data: “Garmin 429”
SDI: “LNAV 2” on #2 GTN (dual
GTN ONLY)
When interfaced with NonGarmin autopilot:
IN 2 Speed: “LOW” (2)
IN 2 Data: “GAD Format 1” (2)
GTN RS-232 Configuration
Page: On Both GTNs
CHNL x Input: “MapMX Format
2”
CHNL x Output: “MapMX
Format 2”
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MFR
Model
Data
Format
G3X Configuration Setting
For dual GTN configure as
above (GTN 1) and below
(GTN 2): (1)
Serial Port ‘x’: “MapMX”
(PFD or MFD) for GTN 2
NOTE: “x” = Connected Port
# (GTN 1 must be connected
to a lower number port than
GTN 2. In dual GDU
installations GTN, #2 may be
connected to any port on the
MFD)
Interfacing Equipment
Configuration Setting
CHNL x Input/Output:
“Connext Format 2” (When
Connext is used, #1 GTN Only)
NOTE: “x” = Connected Port
Main Indicator (Analog)
Config Page:
Selected Course for VLOC:
“Ignored”
VOR/LOC/GS Config Page:
Nav Radio: “Enabled”
ARINC 429 Config:
TX Speed: “LOW”
SDI: “VOR/ILS 1” (“VOR/ILS 2”
for GTN 2)
Notes:
(1) In installations with dual GTNs, GTN 1 must be connected to a lower number RS-232 port than
GTN 2. In dual GDU installations GTN, #2 may be connected to any port on the MFD)
(2) Only used when a Non-Garmin autopilot is interfaced, reference applicable interconnect diagrams
in the G3X Touch EFIS AML STC Installation Manual (190-02472-01).
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B.2 GPS NAV Interface
The GPS Nav position source listed in Table B-2 is compatible with the G3X Touch. Reference Section
3.2.2 for entering configuration and changing data on G3X units
Table B-2 – Compatible Equipment – GPS NAV
MFR
Model
Garmin
GNC
300XL/GPS
155XL
GPS 175
Data
Format
G3X Configuration Setting
Interfacing Equipment
Configuration Setting
ARINC
429
ARINC 429 Configuration Page:
429 Output 1: “EFIS /Airdata
Format 1” and “Nav 1”
429 Input 1: “Garmin GPS” and
“Nav 1”
GNC 300XL/GPS 155XL ARINC
429 Config Page:
IN: “Course Heading”
OUT: “King EFS 40/50”
RS-232
RS-232 Configuration Page:
Serial Port ‘x’: “Aviation In”
NOTE: “x” = Connected Port #
GNC 300XL/GPS 155XL I/O
CHANNEL 1 Config Page:
IN: “OFF”
OUT: “Aviation”
ARINC 429 Configuration Page:
GPS 175 ARINC 429 Config Page:
429 Output 1: “EFIS /Airdata Format
1” and “Nav 1”
IN 1: “EFIS/AIR DATA”, Low Speed
ARINC
429
429 Input 1: “Garmin GPS” and “Nav
1”
RS-232
RS-232 Configuration Page:
Serial Port ‘x’: “MAPMX”
GNX 375
ARINC
429
SDI: “LNAV 1”
GPS 175 RS-232 CHNL 1 Config
Page:
Serial Port ‘x’ (Connext): “CONNEXT
57600 BAUD”
IN & OUT: “MAPMX FORMAT 1”
NOTE: “x” = Connected Port #
IN & OUT: “CONNEXT 57600”
ARINC 429 Configuration Page:
GNX 375 ARINC 429 Config Page:
429 Output 1: “EFIS /Airdata Format
1” and “Nav 1”
IN 1: “EFIS/AIR DATA”, Low Speed
429 Input 1: “Garmin GPS” and “Nav
1”
RS-232
OUT 1: “GAMA FORMAT 1”, Low
Speed
RS-232 Configuration Page:
Serial Port ‘x’: “MAPMX”
Serial Port ‘x’ (Connext): “CONNEXT
57600 BAUD” (2)
NOTE: “x” = Connected Port #
NOTE: No GSU configuration is
required
GPS 175 RS-232 CHNL 2 Config
Page:
OUT 1: “GAMA FORMAT 1”, Low
Speed
SDI: “LNAV 1”
GNX 375 RS-232 CHNL 1 Config
Page (Connected to GDU):
IN & OUT: “MAPMX FORMAT 1”
GNX 375 RS-232 CHNL ‘x’ Config
Page (Connected to GDU for
Connext & ADS-B):
IN & OUT: “CONNEXT 57600”
GNX 375 RS-232 CHNL ‘x’ Config
Page (Connected to GSU 25D):
IN & OUT: “TRANSPONDER FRMT
1”
Transponder Configuration Page:
Transponder Type: “GNX 375” (1)
On-screen Controls: “Show” (if
desired) or “Hide”
Notes:
(1) Set type on transponder configuration page of the GDU in configuration mode if remote control of
Transponder on G3X GDU is desired.
(2) Only one ADS-B Source maybe configured at a time.
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B.3 VHF NAV/COM Interface
The navigation receivers listed in Table B-3 are compatible with the G3X Touch system. These receivers
transmit data to the G3X Touch system digitally.
Table B-3 – Compatible Equipment – VHF NAV/COM
MFR
Garmin
Model
Data
Format
G3X Configuration Setting
Interfacing Equipment
Configuration Setting
GNC 255
One or two
navigation
receivers can
be connected
RS-232
RS-232 Configuration Page:
Serial Port ‘x’: “Garmin VHF
Nav/Comm”
NOTE: “x” = Connected Port #
Nav Configuration Page:
CDI Indicator Type: “Serial”
SYS Configuration Page:
Serial Port IO Mode: “NMEA”
SL 30
RS-232
RS-232 Configuration Page:
Serial Port ‘x’: “Garmin VHF
Nav/Comm”
NOTE: “x” = Connected Port #
Nav Setup Pages:
Attitude Config Page:
Indicator Head Type: “Serial”
SL 40
RS-232
RS-232 Configuration Page:
Serial Port ‘x’: “Garmin VHF
Comm”
NOTE: “x” = Connected Port #
N/A
GTR 225
RS-232
RS-232 Configuration Page:
Serial Port ‘x’: “Garmin VHF
Comm”
NOTE: “x” = Connected Port #
SYS Configuration Page:
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Serial Port IO Mode: “NMEA”
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B.4 Traffic and Weather Source
Table B-4 – Compatible Traffic and Weather Sources
MFR
Garmin
Model
GTX 33(ES)
Data
Format
RS-232
GTX 330(ES)
GTX 32
GTX 327
G3X Configuration Setting
Transponder Configuration Page:
GTX RS-232 Config Mode Page:
Transponder Type: “GTX 32” or “GTX
33” or “GTX 33ES” or “GTX 327” (1) or
“GTX 328” (1) or “GTX 330” (1) or “GTX
330ES” as appropriate.
RS-232 Input: “Remote”
GTX 328
Note: No GSU configuration is required
RS-232
GTX 335
GTX 335R
Input/Output Format: “XPDR FMT 1”
GTX 328/330 Squat Switch Config
Mode Page:
(3)
GTX 325
Interfacing Equipment
Configuration Setting
Squat Switch: “NO”
Transponder Configuration Page:
GTX 325/335 RS-232 Set Up Page:
Transponder Type: “GTX 325” (1) or
“GTX 335” (1) or “GTX 335R as
appropriate.
RS-232 CH 1 (Connected to GSU 25D:
“XPDR FMT 1”
For ADS-B
GTX 335R Connected to Garmin
Navigator for Position Source for
ADS-B Out
Transponder Configuration Page:
RS-232 Port ‘x’: ‘ADS-B+ GPS”
(3)
NOTE: No GSU configuration is
required
GTX 335 RS-232 CH (Connected to
Garmin Navigator) Input: “ADS-B+”
GTN/GNS RS-232 Configuration
Page:
RS-232 CH (Connected to GTX)
Output: “ADS-B+ Format 1”
NOTE: “x” = Connected Port #
GTX 345
RS-232
Transponder Configuration Page:
GTX RS-232 Set Up Page:
Transponder Type: “GTX 345” (1)
RS-232 CH 1 (Connected to GSU 25D)
Input/Output Format: “XPDR FMT 1”
On-screen Controls: “Show” (if
desired) or “Hide”
RS-232 Configuration Page:
RS-232 CH ‘x’ (Connected to GDU):
Input/output: “Connext FMT 1”
RS-232 Port ‘x’: ‘Connext 57600 Baud”
(GDU port connected to GTX) (2)
For ADS-B
- For Traffic/Weather (if no other
source is connected)
GTX RS-232 CH (Connected to
Garmin Navigator) Input: “ADS-B+”
The GTX 345 also provides FIS-B
weather data with this interface.
GTN/GNS RS-232 Configuration
Page:
NOTE: No GSU configuration is
required
RS-232 CH (Connected to GTX)
Output: “ADS-B+ Format 1”
NOTE: “x” = Connected Port #
NOTE: “x” = Connected Port #
GTX 345R
RS-232
Transponder Configuration Page:
GTX Installed with GTN
HSDB (w/
GTN or GTS)
Transponder Type: “GTX 345R”
GTN Interfaced Equipment Page:
ADS-B IN Source Type: “GTX #1”
RS-232 Port ‘x’: ‘Connext FMT 1”
(GTX port connected to GDU)
RS-232 Configuration Page:
RS-232 Port ‘x’: ‘Connext 57600 Baud”
(GDU port connected to GTX) (2)
GTN/GNS RS-232 Configuration
Page:
RS-232 CH (Connected to GTX)
Output: “ADS-B+ Format 1”
For Traffic/Weather (if no other source
is connected)
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Page B-6
MFR
Model
Data
Format
G3X Configuration Setting
Interfacing Equipment
Configuration Setting
ADS-B/TIS-B
GTX 345R Connected to Garmin
Navigator for Position Source for
ADS-B Out (2)
Transponder Configuration Page:
HSDB Devices: Enable “GTN” or
“GTS”
NOTE: No GSU configuration is
required
NOTE: “x” = Connected Port #
GDL 5XR
RS-232
RS-232 Configuration Page:
N/A
RS-232 Port ‘x’: ‘Connext 57600 Baud”
(GDU port connected to GDL) (2)
NOTE: “x” = Connected Port #
GTS 8XX
Software
V4.10 and
later
RS-232
RS-232 Configuration Page:
ARINC 429 (if
connected to
GTX)
RS-232 Port ‘x’: GTS Instrument Data
GTS 8XX Traffic Display Destination
Page:
Enhanced COM Port: “RS-232 Port x”
If a remote GTX that supports TIS-A is
installed disable as shown below:
Transponder Configuration Page:
TIS-A Traffic Data: “Disable”
If direct audio connection from GTS to
Audio Panel is wired, perform the
following:
If GTX is installed:
GTS 8XX Transponder 1
Communication Page:
A429 Primary TX/RX: set to “TX/RX
Channel x and Check HIGH SPEED”
GTS 8XX GPS Position Velocity Page:
Sound Configuration Page:
A429 Primary RX: set to “RX Channel x
and Check HIGH Speed”
Traffic Audio: “Disable”
NOTE: “x” = Connected Port #
Traffic N/A Alert: “Disable”
Notes:
(3) Set type on transponder configuration page of the GDU in configuration mode if remote control of
Transponder on G3X GDU is desired.
(4) Only one ADS-B Source maybe configured at a time.
(5) If a GDL 50R/52R is installed with a GTX 33ES or GTX 335R, ensure UAT and 1090ES are
enabled (green indicator). Reference the G3X Touch EFIS Part 23 AML STC Installation Manual
(190-02472-01) for detailed configuration information.
(6) See Table B.2 for GNX 375 configuration information.
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
190-02472-02
Revision 2
Page B-7
B.5 Non-Garmin Autopilot Systems
Non-Garmin autopilots listed in Table B-5 are compatible with the G3X Touch system.
Table B-5 – Compatible Equipment – Non-Garmin Autopilots
MFR
Century
Model
Data
Format
G3X Configuration Setting
1C388*
analog
Analog Autopilot Configuration
Page:
Autopilot Type: “Century 1C388”
GPS Steering: “Enabled”
GPSS Scale Factor: “1.000”
1C388M*
analog
Analog Autopilot Configuration
Page:
Autopilot Type: “Century 1C388M”
GPS Steering: “Enabled”
GPSS Scale Factor: “1.000”
1C388C*
analog
Analog Autopilot Configuration
Page:
Autopilot Type: “Century 1C388C”
GPS Steering: “Enabled”
GPSS Scale Factor: “1.000”
1C388MC*
analog
Analog Autopilot Configuration
Page:
Autopilot Type: “Century
1C388MC”
GPS Steering: “Enabled”
GPSS Scale Factor: “1.000”
1C388-2*
analog
Analog Autopilot Configuration
Page:
Autopilot Type: “Century 1C388-2”
GPS Steering: “Enabled”
GPSS Scale Factor: “1.000”
1C388-3*
analog
Analog Autopilot Configuration
Page:
Autopilot Type: “Century 1C388-3”
GPS Steering: “Enabled”
GPSS Scale Factor: “1.000”
2000
analog
Analog Autopilot Configuration
Page:
Autopilot Type: “Century 2000”
GPS Steering: “Enabled”
GPSS Scale Factor: “1.000”
21
analog
Analog Autopilot Configuration
Page:
Autopilot Type: “Century 21”
GPS Steering: “Enabled”
GPSS Scale Factor: “1.000”
31
analog
Analog Autopilot Configuration
Page:
Autopilot Type: “Century 31”
GPS Steering: “Enabled”
GPSS Scale Factor: “1.000”
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
Interfacing Equipment
Configuration Information
190-02472-02
Revision 2
Page B-8
MFR
Cessna
Honeywell /
Bendix
King
Model
Data
Format
G3X Configuration Setting
41
analog
Analog Autopilot Configuration
Page:
Autopilot Type: “Century 41”
GPS Steering: “Enabled”
GPSS Scale Factor: “1.000”
IV
analog
Analog Autopilot Configuration
Page:
Autopilot Type: “Century IV”
GPS Steering: “Enabled”
GPSS Scale Factor: “1.000”
300 IFCS
400 IFCS
800 IFCS
analog
Analog Autopilot Configuration
Page:
Autopilot Type: “Cessna 300 (AC)”,
“Cessna 400 (AC)” or “Cessna 800
(AC)” – as applicable.
GPS Steering: “Enabled”
GPSS Scale Factor: “1.000”
300B IFCS
400B IFCS
800B IFCS
analog
Analog Autopilot Configuration
Page:
Autopilot Type: “Cessna 300 (DC)”,
“Cessna 400 (DC)” or “Cessna 800
(DC)” – as applicable.
GPS Steering: “Enabled”
GPSS Scale Factor: “1.000”
KAP 100
analog
Analog Autopilot Configuration
Page:
Autopilot Type: “Bendix King KAP
100”
GPS Steering:
“Enabled”
GPSS Scale
Factor: “1.000”
KAP 140
analog
Analog Autopilot Configuration
Page:
Autopilot Type: “Bendix King KAP
140”
GPS Steering:
“Enabled”
GPSS Scale
Factor: “1.000”
KAP 150
analog
Analog Autopilot Configuration
Page:
Autopilot Type: “Bendix King KAP
150”
GPS Steering:
“Enabled”
GPSS Scale
Factor: “1.000”
KAP 200
analog
Analog Autopilot Configuration
Page:
Autopilot Type: “Bendix King KAP
200”
GPS Steering:
“Enabled”
GPSS Scale
Factor: “1.000”
KFC 150
analog
Analog Autopilot Configuration
Page:
Autopilot Type: “Bendix King KFC
150”
GPS Steering:
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
Interfacing Equipment
Configuration Information
190-02472-02
Revision 2
Page B-9
MFR
Model
Data
Format
G3X Configuration Setting
“Enabled”
Factor: “1.000”
S-TEC
Interfacing Equipment
Configuration Information
GPSS Scale
KFC 200
analog
Analog Autopilot Configuration
Page:
Autopilot Type: “Bendix King KFC
200”
GPS Steering:
“Enabled”
GPSS Scale
Factor: “1.000”
KFC 225
analog,
ARINC 429
GPSS
Analog Autopilot Configuration
Page:
Autopilot Type: “Bendix King KFC
225”
System 20
analog,
discrete
Analog Autopilot Configuration
Page:
Autopilot Type: “S-Tec System 20”
GPS Steering: “Enabled”
GPSS Scale Factor: “1.000”
Must be configured to operate
with KI-525 (KCS-55) heading
system.
System 30
analog,
discrete
Analog Autopilot Configuration
Page:
Autopilot Type: “S-Tec System 30”
GPS Steering: “Enabled”
GPSS Scale Factor: “1.000”
Must be configured to operate
with KI-525 (KCS-55) heading
system.
System 40
analog,
discrete
Analog Autopilot Configuration
Page:
Autopilot Type: “S-Tec System 40”
GPS Steering: “Enabled”
GPSS Scale Factor: “1.000”
Must be configured to operate
with KI-525 (KCS-55) heading
system.
System 50
analog,
discrete
Analog Autopilot Configuration
Page:
Autopilot Type: “S-Tec System 50”
GPS Steering: “Enabled”
GPSS Scale Factor: “1.000”
Must be configured to operate
with KI-525 (KCS-55) heading
system.
System 55
analog,
discrete
Analog Autopilot Configuration
Page:
Autopilot Type: “S-Tec System 55”
GPS Steering: “Enabled”
GPSS Scale Factor: “1.000”
Must be configured to operate
with KI-525 (KCS-55) heading
system.
System
55X
analog,
discrete,
ARINC 429
Analog Autopilot Configuration
Page:
Autopilot Type: “S-Tec System
55X”
Must be configured to operate
with KI-525 (KCS-55) heading
system.
System 60
analog,
discrete
Analog Autopilot Configuration
Page:
Must be configured to operate
with KI-525 (KCS-55) heading
system.
Autopilot Type: “S-Tec System 60”
GPS Steering: “Enabled”
GPSS Scale Factor: “1.000”
System 65
Analog
discrete
Analog Autopilot Configuration
Page:
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
Must be configured to operate
with KI-525 (KCS-55) heading
system.
190-02472-02
Revision 2
Page B-10
MFR
Model
Data
Format
G3X Configuration Setting
Interfacing Equipment
Configuration Information
Autopilot Type: “S-Tec System 65”
GPS Steering: “Enabled”
GPSS Scale Factor: “1.000”
Piper
Autocontrol
III/IIIB
analog
Altimatic
III/IIIB-1/IIIC
analog
Analog Autopilot Configuration Page:
Autopilot Type: “Piper AutoControl”
GPS Steering: “Enabled”
GPSS Scale Factor: “1.000”
Analog Autopilot Configuration Page:
Autopilot Type: “Piper Altimatic”
GPS Steering: “Enabled”
GPSS Scale Factor: “1.000”
B.6 Audio Panel
This STC does not specify any configuration requirements for the audio panel to which the G3X system is
interfaced. Refer to installation guidance for the selected audio panel for configuration information.
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
190-02472-02
Revision 2
Page B-11
B.7 EIS Sensors
G3X EIS gauge displays require data captured by approved sensors that are configured in accordance
with Table B-6. EIS Sensors that are authorized as Interface Only require a separate installation
approval.
Table B-6 – Compatible EIS Sensors
Function
Cylinder
Head
Temperature
Exhaust Gas
Temperature
Turbo Inlet
Temperature
Oil Pressure
Oil Temp
Manifold
Pressure
Carb Air
Temp
Mfg
Garmin P/N
Description
Alcor
494-70008-00
Varies
Varies
Alcor
N/A
N/A
494-70001-00
Varies
N/A
Alcor 86252 (K type
probe)
K Type Thermocouple
J Type Thermocouple
Alcor 86255 (K type
probe)
K Type Thermocouple
Alcor
494-70002-00
Alcor 86245 (Type K
probe)
Varies
N/A
K Type Thermocouple
Garmin
011-04202-30
150 PSIG Brass
Textron
Aviation
Textron
Aviation
UMA
N/A
Beech 102-389017-1
N/A
Beech 102-389017-3
N/A
T1EU150G
UMA
N/A
T1EU150G-CS
UMA
494-70009-00
UMA
UMA
UMA
Mil-Spec
Varies
Garmin
N/A
N/A
N/A
N/A
N/A
011-04202-00
UMA
N/A
T3B3-2.5G (K Type
probe)
T3B3
T3B3A
T3B3-2.5
MS28034
K Type Thermocouple
Garmin (30 PSIA
Brass)
T1EU50A
UMA
N/A
T1EU50A-CS
UMA
494-70010-00
T3B10-SG (K Type
probe)
Mil-Spec
N/A
MS28034
Varies
N/A
Garmin
011-04202-20
K Type Thermocouple
(various
manufacturers)
75 PSIG Brass
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
G3X Sensor Input
Configuration
CHT → Type K
Interface Only
CHT → Type K
CHT → Type J
EGT → Type K
Interface Only
Interface Only
Interface Only
EGT → Type K
Interface Only
Misc Temp 1 or 2
→Turbine Inlet Temp 1
or 2 (Type K
Thermocouple)
Misc Temp 1 or 2
→Turbine Inlet Temp 1
or 2 (Type K
Thermocouple)
Oil Pressure → Kavlico
P4055-5020-4
Oil Pressure → Beech
102-389017
Oil Pressure → Beech
102-389017
Oil Pressure → UMA
T1EU150G
Oil Pressure → UMA
T1EU150G
Oil Temp → Type K
Interface Only
Oil Temp → Type K
Oil Temp → Type K
Oil Temp → Type K
Oil Temp → MS28034
Oil Temp → Type K
Manifold Pressure →
Kavlico P4055-5020-1
Manifold Pressure →
UMA T1EU50A
Manifold Pressure →
UMA T1EU50A
Misc Temp 1 or 2
→Carb Temp (Type K
Thermocouple)
Misc Temp 1 or 2 →
Carb Temp (MS28034)
Misc Temp 1 or 2
→Carb Temp (Type K
Thermocouple)
Fuel Pressure →
Kavlico P4055-5020-3
(0-75 PSI)
STC Approval
Interface Only
Interface &
Installation
Interface Only
Interface Only
Interface Only
Interface Only
Interface &
Installation
Interface Only
Interface Only
Interface Only
Interface Only
Interface Only
Interface &
Installation
Interface Only
Interface Only
Interface &
Installation
Interface Only
Interface Only
Interface &
Installation
190-02472-02
Revision 2
Page B-12
Function
Mfg
Garmin P/N
Description
Garmin
011-04202-10
15 PSIG Brass
UMA
N/A
T1EU70G
UMA
N/A
T1EU70G-CS
UMA
N/A
T1EU35G
UMA
N/A
T1EU35G-CS
Shunt
Varies
N/A
Voltage
Varies
N/A
N/A
Fuel
Quantity
Resistive
float
CIES
CORP
AA55524 (various
mfgr)
N/A (sense Bus
Voltage)
Resistive float
CIES
CORP
Electroni
cs
Internatio
nal
Electroni
cs
Internatio
nal
Textron
Aviation
N/A
Fuel Press
Fuel Flow &
Return FF
N/A
494-10001-00
CiES CC284022XXXX-105 (0-5V
Analog)
CiES CC284022XXXX-101 (Digital)
EI FT-60 (Red Cube)
494-10001-01
G3X Sensor Input
Configuration
Fuel Pressure →
Kavlico P4055-5020-2
(0-15 PSI)
Fuel Pressure → UMA
T1EU70G (0-70 PSI)
Fuel Pressure → UMA
T1EU70G (0-70 PSI)
Fuel Pressure → UMA
T1EU35G (0-35 PSI)
Fuel Pressure → UMA
T1EU35G (0-35 PSI)
Shunt 1 or 2 (manual
configuration)
Volts 1 or 2 (manual
configuration)
Fuel 1 or 2 → Resistive
STC Approval
Interface &
Installation
Interface Only
Interface Only
Interface Only
Interface Only
Interface Only
Interface Only
Interface Only
Fuel 1 or 2 → Voltage
Interface Only
Fuel 1 or 2 → Digital
Interface Only
Fuel Flow → EI FT-60
Interface &
Installation
EI FT-90 (Gold Cube)
Fuel Flow → EI FT-90
Interface &
Installation
N/A
102-389012-11
Fuel Flow → Beech
102-389012
Interface Only
JPI
N/A
JPI 700900-1 (201)
Fuel Flow → Floscan
206 B6
Interface Only
JPI
N/A
JPI 700900-2 (231)
Fuel Flow → Floscan
231
Interface Only
Floscan
N/A
Floscan 201 B-6
Interface Only
Floscan
N/A
Floscan 231
UMA
N/A
UMA T1A9-1 (Slick
Mag)
UMA
N/A
UMA T1A9-2 (Bendix
Mag)
N/A
Magneto P-lead, 4Cylinder
Magneto P-lead, 6Cylinder
Magneto P-lead, 6Cylinder, 0.64000:1
Prop Gear Ratio
Fuel Flow → Floscan
206 B6
Fuel Flow → Floscan
231
RPM 1 or 2 → UMA
T1A9 Mag Port (4 or 6Cylinder)
RPM 1 or 2 → UMA
T1A9 Mag Port (4 or 6Cylinder)
RPM → Magneto PLead (1.000 pulse/rev)
RPM → Magneto PLead (1.500 pulse/rev)
RPM → Magneto PLead (2.344 pulse/rev)
RPM
N/A
N/A
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
Interface Only
Interface Only
Interface Only
N/A (No sensor
req’d)
N/A (No sensor
req’d)
N/A (No sensor
req’d)
190-02472-02
Revision 2
Page B-13
Function
Mfg
Garmin P/N
N/A
N/A
N/A
N/A
N/A
N/A
Description
Magneto P-lead, 6Cylinder, 0.64167:1
Prop Gear Ratio
Magneto P-lead, 6Cylinder, 0.64200:1
Prop Gear Ratio
Magneto P-lead, 6Cylinder, 0.66700:1
Prop Gear Ratio
Magneto P-lead, 6Cylinder, 0.75000:1
Prop Gear Ratio
Dual Magneto P-lead,
4-Cylinder
Dual Magneto P-lead,
6-Cylinder
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
G3X Sensor Input
Configuration
RPM → Magneto PLead (2.337 pulse/rev)
STC Approval
N/A (No sensor
req’d)
RPM → Magneto PLead (2.337 pulse/rev)
N/A (No sensor
req’d)
RPM → Magneto PLead (2.249 pulse/rev)
N/A (No sensor
req’d)
RPM → Magneto PLead (2.000 pulse/rev)
N/A (No sensor
req’d)
RPM → Magneto PLead (2.000 pulse/rev)
RPM → Magneto PLead (1.500 pulse/rev)
N/A (No sensor
req’d)
N/A (No sensor
req’d)
190-02472-02
Revision 2
Page B-14
B.8 Antennas
This section contains general information for interfaced GPS, GPS/WAAS, SXM, and ADS-B antennas.
This STC provides installation approval only for the Garmin glareshield-mounted GPS Antenna (01104036-00), refer to the G3X Touch EFIS Part 23 AML STC Installation Manual (190-02472-01) for
installation guidance. All other antennas are approved as interface only and require separate installation
approval.
A minimum of one GPS antenna is required for G3X installations as the connected GDU (PFD) will share
GPS data with the second GDU (if installed). Additional GPS antennas may be used for redundancy but
are not required.
Table B-7 – Supported GPS & SXM Antennas
Make & Model
P/N
Approved G3X
Function
LRU
Connection
Mounting
Comant 2480-201
(GPS/VHF Com)
CI 2480-201
GPS
GDU 4X0
Blade antenna, external
Garmin Glareshield GPS
Antenna
011-0403600
GPS
GDU 4X0
Glareshield mounted via hook &
loop or screws
Garmin GA 56
011-0013400
GPS
GDU 4X0
Stud mount, teardrop, external
Garmin GA 37
(GPS/SXM)
013-0024500
SXM
GDL 51R/52R ARINC 743, external
Garmin GA 55
011-0103300
SXM
GDL 51R/52R Stud-mount, teardrop, external
Garmin GA 55A
011-0115300
SXM
GDL 51R/52R Through-mount, ARINC 743,
external
The GPS antenna interface on the GDL 5XR is not used in this STC.
Only the SXM connection to the GA 37 antenna is approved in this STC. The GPS connection to the GA
37 is not compatible with any G3X LRUs but might be used for other installed equipment under their
respective interface approvals.
Also note that if a previously installed G5 is connected to a GPS antenna mounted externally on the
airframe, that antenna must be disconnected when the G5 is used as a standby instrument for G3X. It
may be possible to repurpose the external antenna for other avionics if it is compatible under their
respective interface approvals.
The GPS antenna should provide a gain of 16 to 25 dB. The GDU 4X0 supplies power to the antenna at
4.5-5.5 VDC with a maximum current of 50 mA.
The following information describes antenna performance requirements for proper system functionality.
Table B-8 – GPS or GPS/WAAS Antenna Minimum Requirements
Characteristics
Specifications
Frequency Range
1565 to 1585 MHz
Gain
16 to 25 dB typical, 40 dB max.
Noise Figure
<4.00 dB
Nominal Output Impedance
50Ω
Supply Voltage
4.5 to 5.5 VDC
Supply Current
up to 50 mA
Output Connector
BNC or TNC
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
190-02472-02
Revision 2
Page B-15
Table B-9 – SXM Satellite Radio Antenna Minimum Requirements
Characteristics
Frequency Range
Specifications
2332.5 to 2345 MHz
Gain
24 dB*
Noise Figure
<1.2 dB
Nominal Output Impedance
50Ω
Supply Voltage
3.5 to 5.5 VDC
Supply Current
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.
B.9 ADS-B Antenna Interface
The GDL 50R or GDL 52R requires an external monopole or blade-type ADS-B antenna for reception.
The antenna should be mounted on the bottom of the aircraft and located at least 3.3 feet from high
power transmitting antennas such as VHF Comm, HF transmitter, DME, Transponder, and Radar. The
connection is made by attaching the coax cable from the external antenna to the BNC connector on the
GDL 50R/52R. The GDL 50R/52R requires a UHF antenna that meets the following specifications:

Standard 50 Ω vertically polarized antenna with a VSWR < 1.7:1 at 978 MHz and < 1.5:1 at 1090
MHz.

TSO-C66, TSO-C74, or TSO-C112 antennas that also meet the VSWR specification.
Maintenance Manual
G3X Touch EFIS Part 23 AML STC
190-02472-02
Revision 2
Page B-16
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