Installation manual | Garmin C510 GPS Receiver User Manual

G3X
Installation Manual
190-01115-01
August, 2009
Revision A
© Copyright 2009
Garmin Ltd. or its subsidiaries
All Rights Reserved
Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted,
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and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and
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Garmin International, Inc.
1200 E. 151st Street
Olathe, KS 66062 USA
Telephone: 913-397-8200
Aviation Dealer Technical Support Line (Toll Free): (888) 606-5482
www.garmin.com
Garmin (Europe) Ltd
Liberty House
Bulls Copse Road
Hounsdown Business Park
Southampton, SO40 9RB, UK
Telephone: +44 (0) 8708501241
RECORD OF REVISIONS
Revision
A
Page A
Revision A
Revision
Date
08/26/09
Description
Initial Release
G3X Installation Manual
190-01115-01
WARNING
This product, its packaging, and its components contain chemicals known to the State of
California to cause cancer, birth defects, or reproductive harm. This Notice is being
provided in accordance with California's Proposition 65. If you have any questions or
would like additional information, please refer to our web site at
www.garmin.com/prop65.
NOTE
The Garmin G3X system includes products like the GDU 37X and the GSU 73 that are
not TSO-certified products and have received no FAA approval or endorsement.
Consequently the G3X system is not suitable for installation in type-certificated aircraft.
NOTE
Unless otherwise noted all installation guidance, requirements, and instructions apply to
one-display, two-display, and three-display G3X systems.
NOTE
References to the GDU 37X throughout this manual apply equally to the GDU 370 and
GDU 375 except where specifically noted.
INFORMATION SUBJECT TO EXPORT CONTROL LAWS
This document may contain information which is subject to the Export Administration
Regulations (“EAR”) issued by the United States Department of Commerce (15 CFR,
Chapter VII Subchapter C) and which may not be exported, released or disclosed to
foreign nationals inside or outside the United States without first obtaining an export
license. The preceding statement is required to be included on any and all reproductions
in whole or in part of this manual.
DOCUMENT PAGINATION
Section
Table of Contents
Section 1
Section 2
Section 3
Section 4
Section 5
Section 6
Section 7
Section 8
Section 9
Section 10
Appendix A
Appendix B
Appendix C
Appendix D
Appendix E
G3X Installation Manual
190-01115-01
Page Range
i – xii
1-1 – 1-8
2-1 – 2-6
3-1 – 3-6
4-1 – 4-8
5-1 – 5-4
6-1 – 6-28
7-1 – 7-14
8-1 – 8-26
9-1 – 9-12
10-1 – 10-2
A-1 – A-16
B-1 – B-28
C-1 – C-22
D-1 – D4
E-1 – E4
Page i
Revision A
TABLE OF CONTENTS
PARAGRAPH
PAGE
1
1.1
1.2
1.3
1.4
1.5
1.6
1.7
G3X Installation Overview ..............................................................................................................1-1
Unpacking Unit ................................................................................................................................1-1
Introduction ......................................................................................................................................1-1
System Overview .............................................................................................................................1-2
General G3X LRU Specifications....................................................................................................1-3
Installation Requirements.................................................................................................................1-5
Mounting ..........................................................................................................................................1-5
Wiring/Cabling Considerations........................................................................................................1-5
2
2.1
2.2
2.3
2.4
2.5
2.6
2.7
2.8
2.9
GDU 37X .........................................................................................................................................2-1
Equipment Description.....................................................................................................................2-1
Electrical Specifications...................................................................................................................2-2
Environmental Specifications ..........................................................................................................2-3
Installation Requirements.................................................................................................................2-4
Installation Considerations...............................................................................................................2-5
Mounting Requirements...................................................................................................................2-5
Unit Installation................................................................................................................................2-5
Maintenance .....................................................................................................................................2-5
Panel Cutout Template .....................................................................................................................2-6
3
3.1
3.2
3.3
3.4
3.5
3.6
3.7
3.8
3.9
GMU 44 ...........................................................................................................................................3-1
Equipment Description.....................................................................................................................3-1
Electrical Specifications...................................................................................................................3-1
Environmental Specifications ..........................................................................................................3-2
GMU 44 TSO/ETSO Compliance....................................................................................................3-2
Installation Requirements.................................................................................................................3-3
Installation Considerations...............................................................................................................3-3
GSU 73/GMU 44 Interconnect Harness Fabrication Instructions....................................................3-5
Mounting Instructions ......................................................................................................................3-6
Maintenance .....................................................................................................................................3-6
4
4.1
4.2
4.3
4.4
4.5
4.6
4.7
4.8
GSU 73.............................................................................................................................................4-1
Equipment Description.....................................................................................................................4-1
Electrical Specifications...................................................................................................................4-2
Environmental Specifications ..........................................................................................................4-3
Installation Requirements.................................................................................................................4-3
Installation Considerations...............................................................................................................4-4
Mounting Requirements...................................................................................................................4-6
Unit Installation................................................................................................................................4-7
Maintenance .....................................................................................................................................4-8
Page ii
Revision A
G3X Installation Manual
190-01115-01
PARAGRAPH
PAGE
5
5.1
5.2
5.3
5.4
5.5
5.6
GTP 59 .............................................................................................................................................5-1
Equipment Description.....................................................................................................................5-1
Installation Requirements.................................................................................................................5-1
TSO/ETSO Compliance...................................................................................................................5-2
Installation Considerations...............................................................................................................5-3
Unit Installation................................................................................................................................5-4
Maintenance .....................................................................................................................................5-4
6
6.1
6.2
6.3
6.4
6.5
6.6
Garmin GPS/XM Antennas..............................................................................................................6-1
GPS Antennas ..................................................................................................................................6-1
XM Antennas ...................................................................................................................................6-1
Antenna Mounting Considerations...................................................................................................6-2
Teardrop Footprint Antenna Installation (GA 55 and GA 56).........................................................6-7
ARINC 743 Footprint Antenna Installation (GA 55A, GA 57X) ..................................................6-14
Non-Structural Mount Installation .................................................................................................6-23
7
7.1
7.2
7.3
7.4
7.5
7.6
Software, Configuration, Databases, and XM Activation................................................................7-1
Configuration Mode .........................................................................................................................7-1
Software/Audio Data Identification .................................................................................................7-1
Software Loading Procedure............................................................................................................7-3
Configuration Pages .........................................................................................................................7-4
Garmin Database Updates..............................................................................................................7-12
XM Activation Instructions (GDU 375 only) ................................................................................7-14
8
8.1
8.2
8.3
Post-Installation Checkout and Calibration Procedures...................................................................8-1
Recommended Test Equipment .......................................................................................................8-2
GDU 37X Test Procedure ................................................................................................................8-2
GSU 73/GMU 44 Post-Installation Calibration Procedure ..............................................................8-4
9
9.1
9.2
9.3
9.4
9.5
9.6
Troubleshooting ...............................................................................................................................9-1
GDU 37X .........................................................................................................................................9-1
GMU 44 ...........................................................................................................................................9-2
GSU 73.............................................................................................................................................9-3
GSU 73 – Air Data Troubleshooting................................................................................................9-7
Troubleshooting On-board the Aircraft..........................................................................................9-10
GSU Page .......................................................................................................................................9-11
10
10.1
10.2
10.3
Return to Service Information........................................................................................................10-1
GDU 37X .......................................................................................................................................10-1
GSU 73...........................................................................................................................................10-1
GMU 44 .........................................................................................................................................10-2
G3X Installation Manual
190-01115-01
Page iii
Revision A
PARAGRAPH
PAGE
APPENDIX A: G3X Pinouts ................................................................................................................... A-1
A.1 GDU 37X ........................................................................................................................................ A-1
A.2 GMU 44 .......................................................................................................................................... A-5
A.3 GSU 73............................................................................................................................................ A-6
APPENDIX B: Connector Installation Instructions................................................................................. B-1
B.1 Thermocouple Installation into a Backshell.................................................................................... B-1
B.2 Jackscrew Configuration Module Installation into a Jackscrew Backshell..................................... B-3
B.3 Jackscrew Backshell Installation Instructions................................................................................. B-6
B.4 Circular Connector Installation Instructions ................................................................................. B-19
APPENDIX C: Outline and Installation Drawings.................................................................................. C-1
APPENDIX D: Interconnect Drawing ..................................................................................................... D-1
APPENDIX E: External Interface Drawing (Example Only).................................................................. E-1
Page iv
Revision A
G3X Installation Manual
190-01115-01
LIST OF ILLUSTRATIONS
FIGURE
PAGE
1-1
1-2
G3X Interconnect Example..............................................................................................................1-2
Coaxial Cable Installation ................................................................................................................1-7
2-1
2-2
GDU 37X Unit View .......................................................................................................................2-1
GDU 37X Mounting Accessories ....................................................................................................2-4
3-1
GMU 44 Unit View..........................................................................................................................3-1
4-1
4-2
4-3
GSU 73 Unit View ...........................................................................................................................4-1
GSU 73 Air Hose Fitting Locations.................................................................................................4-5
GSU 73 Orientation Calibration.......................................................................................................4-6
5-1
GTP 59 .............................................................................................................................................5-1
6-1
6-2
6-3
6-4
6-5
6-6
6-7
6-8
6-9
6-10
6-11
6-12
6-13
6-14
6-15
6-16
6-17
6-18
6-19
6-20
6-21
6-22
6-23
6-24
6-25
Recommended Antenna Placement..................................................................................................6-4
Carbon/Glass Buried Antenna Area.................................................................................................6-5
Glare Shield Buried Antenna Area...................................................................................................6-6
Doubler Design, Teardrop Footprint Antenna, Skin Thickness 0.032” to 0.049” ...........................6-9
Doubler Design, Teardrop Footprint Antenna, Skin Thickness 0.049” to 0.051” ...........................6-9
Doubler Design, Teardrop Footprint Antenna, Skin Thickness 0.051” to 0.063” .........................6-10
Sample Doubler Location, Teardrop Footprint Antenna, Metal Skin Aircraft ..............................6-10
Skin Cutout Detail, Teardrop Footprint Antenna, Skin Thickness 0.032” to 0.049”.....................6-11
Skin Cutout Detail, Teardrop Footprint Antenna, Skin Thickness 0.049” to 0.051”.....................6-11
Skin Cutout Detail, Teardrop Footprint Antenna, Skin Thickness 0.051” to 0.063”.....................6-12
Doubler Installation, Teardrop Footprint Antenna, Skin Thickness 0.032” to 0.049”...................6-12
Doubler Installation, Teardrop Footprint Antenna, Skin Thickness 0.049” to 0.051”...................6-13
Doubler Installation, Teardrop Footprint Antenna, Skin Thickness 0.051” to 0.063”...................6-13
Doubler Design, ARINC 743 Footprint Antenna, Skin Thickness 0.032” to 0.049”.....................6-16
Doubler Design, ARINC 743 Footprint Antenna, Skin Thickness 0.049” to 0.051”.....................6-17
Doubler Design, ARINC 743 Footprint Antenna, Skin Thickness 0.051” to 0.063”.....................6-18
Sample Doubler Location, ARINC 743 Antenna, Metal Skin Aircraft .........................................6-19
Skin Cutout Detail, GA 55A Antenna, Skin Thickness 0.032” to 0.049”......................................6-19
Skin Cutout Detail, GA 55A Antenna, Skin Thickness 0.049” to 0.051”......................................6-20
Skin Cutout Detail, GA 55A Antenna, Skin Thickness 0.051” to 0.063”......................................6-20
Doubler Installation, ARINC 743Footprint Antenna, Skin Thickness 0.032” to 0.049” ...............6-21
Doubler Installation, ARINC 743Footprint Antenna, Skin Thickness 0.049” to 0.051” ...............6-21
Doubler Installation, ARINC 743Footprint Antenna, Skin Thickness 0.051” to 0.063” ...............6-22
Installation of ARINC 743 Footprint Antenna...............................................................................6-22
Generic Non-structural ARINC 743 Footprint Antenna Installation .............................................6-23
G3X Installation Manual
190-01115-01
Page v
Revision A
FIGURE
PAGE
6-26
6-27
6-28
6-29
6-30
6-31
Example Bracket Antenna Mounting Under Glareshield...............................................................6-24
Example Non-structural Antenna Mounting Under Glareshield....................................................6-25
Example Teardrop Antenna Installation in Airframe Under Fabric Skin ......................................6-26
Example ARINC 743 Footprint in Airframe Under Fabric Skin ...................................................6-26
Example Non-structural Antenna Mounting on Airframe .............................................................6-27
Example Teardrop Footprint Antenna Mounting Under Fabric Skin ............................................6-28
8-1
8-2
Softkey Positions..............................................................................................................................8-1
Aircraft Alignment .........................................................................................................................8-10
9-1
9-2
9-3
9-4
9-5
9-6
9-7
9-8
Heading Failure Indication (Full-Screen PFD) ................................................................................9-2
Attitude, Air Data, and Engine/Airframe Failure Indication............................................................9-5
Attitude Failure Indication (PFD) ....................................................................................................9-5
AHRS Align Message (PFD) ...........................................................................................................9-6
No Info for TAS & OAT..................................................................................................................9-7
Airspeed and Altitude Failure Indications .......................................................................................9-7
Attitude, Heading, Air Data, and Engine/Airframe Failure .............................................................9-9
CONFIG GSU Page .......................................................................................................................9-11
A-1
A-2
A-3
A-4
A-5
View of J3701 Connector from Back of Unit ................................................................................. A-1
View of J441 Connector Looking at Rear of Unit .......................................................................... A-5
Rear View of Connector End Plate ................................................................................................. A-6
Rear Connector of J731 Viewed from Connector End of Unit ....................................................... A-6
Rear Connector of J732 Viewed from Connector End of Unit ....................................................... A-8
B-1
B-2
B-3
B-4
B-5
B-6
B-7
B-8
B-9
B-10
B-11
B-12
B-13
B-14
B-15
B-16
Insulation/Contact Clearance......................................................................................................... B-1
Jackscrew Backshell Thermocouple Installation........................................................................... B-2
Insulation/Contact Clearance......................................................................................................... B-4
Jackscrew Backshell Installation ................................................................................................... B-5
Shield Install onto a Jackscrew Backshell (78 pin example)......................................................... B-7
Method A.1 for Shield Termination .............................................................................................. B-8
Insulation/Contact Clearance....................................................................................................... B-10
Method A.2 (Daisy Chain) for Shield Termination..................................................................... B-12
Method B.1 (Quick Term) for Shield Termination ..................................................................... B-13
Method B.2 (Daisy Chain-Quick Term) for Shield Termination ................................................ B-14
Daisy Chain between Methods A and B...................................................................................... B-15
Method C.1 Double-Shield Termination ..................................................................................... B-16
Method C.2 Double-Shield Termination ..................................................................................... B-17
D-Sub Spliced Signal Wire illustration ....................................................................................... B-18
Circular Connector Install (19 contact example)......................................................................... B-20
Standard Shield Termination ....................................................................................................... B-20
Page vi
Revision A
G3X Installation Manual
190-01115-01
FIGURE
PAGE
B-17
B-18
B-19
B-20
B-21
Insulation/Contact Clearance....................................................................................................... B-23
Daisy Chain Shield Termination ................................................................................................. B-24
Quick Term Shield Termination.................................................................................................. B-25
Daisy Chain, Quick-Term Shield Termination............................................................................ B-27
Daisy Chain Shield Termination between Methods A and B...................................................... B-28
C-1.1
C-1.2
C-2.1
C-2.2
C-2.3
C-2.4
C-3.1
C-4.1
C-5.1
C-5.2
C-5.3
GDU 37X Outline Drawing........................................................................................................... C-1
GDU 37X Panel Cutout Drawing ................................................................................................. C-3
GMU 44 Mounting Rack............................................................................................................... C-5
GMU 44 Top Mounted Installation ............................................................................................... C-7
GMU 44 Bottom Mounted Installation ......................................................................................... C-9
GMU 44 Wiring Detail................................................................................................................ C-11
GSU 73 Outline Drawing ............................................................................................................ C-13
GTP 59 O.A.T. Probe Installation Drawing ................................................................................ C-15
GA 55/55A Installation Drawing ................................................................................................ C-17
GA 56 Installation Drawing ........................................................................................................ C-19
GA 57X Installation Drawing...................................................................................................... C-21
D-1.1 Notes, 14V Power, and Antenna ................................................................................................... D-1
D-1.2 GDU 37X and GSU 73.................................................................................................................. D-3
E-1.1 Notes, GDU 37X RS-232 and Audio Examples............................................................................ E-1
E-1.2 GSU 73 RS-232 and ARINC 429 Examples ................................................................................. E-3
E-1.3 TruTrak and Trio Auto Pilot Examples ......................................................................................... E-5
G3X Installation Manual
190-01115-01
Page vii
Revision A
LIST OF TABLES
TABLE
PAGE
1-1
1-2
1-3
1-4
1-5
1-6
1-7
G3X LRU Part Numbers ..................................................................................................................1-3
Contents of GDU 37X Assembly (010-00667-XX).........................................................................1-3
G3X LRU Power Requirements.......................................................................................................1-3
G3X LRU Physical Specifications...................................................................................................1-4
Contents of G3X Installation Kit (K10-00017-00) ..........................................................................1-5
Contents of G3X LRU Kit (K10-00016-00) ....................................................................................1-5
Pin Contact and Crimp Tools Part Numbers....................................................................................1-6
2-1
2-2
2-3
2-4
2-5
GDU 37X Supply Voltages..............................................................................................................2-2
GDU 37X Power Requirements.......................................................................................................2-2
GDU 37X GPS Specifications .........................................................................................................2-2
GDU 37X Supported Antennas........................................................................................................2-3
Contents of GDU 37X Connector Kit (011-01921-00)....................................................................2-4
3-1
3-2
3-3
3-4
3-5
3-6
3-7
3-8
3-9
GMU 44 Electrical Specifications....................................................................................................3-1
GMU 44 Environmental Specifications ...........................................................................................3-2
TSO/ETSO Compliance...................................................................................................................3-2
TSO/ETSO Deviations.....................................................................................................................3-2
GMU 44 Part Numbers ....................................................................................................................3-3
GMU 44 Accessories .......................................................................................................................3-3
Required Distance from Magnetic Disturbances..............................................................................3-4
Parts Needed for GMU 44 Installation.............................................................................................3-5
GMU 44 Connector Kit (011-00871-00) Contents, Reference Figure C-2.4...................................3-5
4-1
4-2
4-3
4-4
4-5
GSU 73 Supply Specifications.........................................................................................................4-2
GSU 73 Environmental Specifications ............................................................................................4-3
GSU 73 Available Equipment..........................................................................................................4-3
Contents of P731 Connector Kit (011-01818-00) ............................................................................4-3
Contents of P732 Connector Kit (011-01818-01) ............................................................................4-4
5-1
5-2
5-3
5-4
5-5
GTP 59 Part Number........................................................................................................................5-1
GTP 59 Outside Air Temperature Kit ..............................................................................................5-1
Applicable TSO/ETSOs for the GTP 59 ..........................................................................................5-2
TSO/ETSO Deviations for the GTP 59............................................................................................5-2
Parts Needed for GTP 59 Installation ..............................................................................................5-3
6-1
6-2
6-3
GPS Antennas ..................................................................................................................................6-1
GPS Antenna Minimum Requirements............................................................................................6-1
XM Antennas ...................................................................................................................................6-1
Page viii
Revision A
G3X Installation Manual
190-01115-01
TABLE
PAGE
6-4
6-5
6-6
6-7
XM Satellite Radio Antenna Minimum Requirements ....................................................................6-2
Teardrop Footprint Antenna Doubler Design and Installation.........................................................6-7
ARINC 743 Footprint Antenna Doubler Design and Installation ..................................................6-14
Minimum Distance Required Between Tube Structure and Antenna ............................................6-28
8-1
8-2
8-3
8-4
Post-Installation Calibration Procedure Summary ...........................................................................8-4
Data Validity Requirements for AHRS Calibration Procedures ......................................................8-5
Configuration Mode GSU Page Status Boxes..................................................................................8-5
Magnetometer Interference Test Sequence Example.....................................................................8-23
9-1
9-2
GSU 73 AHRS Operating Mode Table............................................................................................9-3
GSU 73 AHRS Pitch/Bank Limitations for Cold Start While Airborne ..........................................9-3
B-1
B-2
B-3
B-4
B-5
B-6
B-7
B-8
B-9
B-10
B-11
B-12
Thermocouple Kit GPN 011-00981-00........................................................................................... B-1
GPN: 011-00979-20 – Kit (w/EEPROM and pins)......................................................................... B-3
GPN: 011-00979-22 – Kit (w/EEPROM and sockets).................................................................... B-3
Parts supplied for a Shield Block Installation (Figure B-1) ............................................................ B-6
Parts NOT supplied for a Shield Block Installation (Figure B-1)................................................... B-6
Shielded Cable Preparations for Garmin Connectors...................................................................... B-8
Shielded Cable Preparations – (Quick Term) ............................................................................... B-14
Shielded Cable Preparations for Garmin Connectors.................................................................... B-16
Parts supplied for a Circular Connector Installation (Figure B-15) .............................................. B-19
Parts NOT supplied for a Circular Connector Installation (Figure B-15) ..................................... B-19
Shielded Cable Preparations for Garmin Connectors.................................................................... B-21
Shielded Cable Preparations – (Quick Term) ............................................................................... B-25
G3X Installation Manual
190-01115-01
Page ix
Revision A
Limited Warranty for Garmin GMU 44 and GTP 59 Products
The Garmin products GMU 44 and GTP 59 are warranted to be free from defects in materials or
workmanship for two years from the date of purchase. Within this period, Garmin will at its sole option,
repair or replace any components that fail in normal use. Such repairs or replacement will be made at no
charge to the customer for parts or labor, provided that the customer shall be responsible for any
transportation cost. This warranty does not cover failures due to abuse, misuse, accident or unauthorized
alteration or repairs.
THE WARRANTIES AND REMEDIES CONTAINED HEREIN ARE EXCLUSIVE AND IN LIEU OF
ALL OTHER WARRANTIES EXPRESS OR IMPLIED OR STATUTORY, INCLUDING ANY
LIABILITY ARISING UNDER ANY WARRANTY OF MERCHANTABILITY OR FITNESS FOR A
PARTICULAR PURPOSE, STATUTORY OR OTHERWISE. THIS WARRANTY GIVES YOU
SPECIFIC LEGAL RIGHTS, WHICH MAY VARY FROM STATE TO STATE.
IN NO EVENT SHALL GARMIN BE LIABLE FOR ANY INCIDENTAL, SPECIAL, INDIRECT OR
CONSEQUENTIAL DAMAGES, WHETHER RESULTING FROM THE USE, MISUSE, OR
INABILITY TO USE THIS PRODUCT OR FROM DEFECTS IN THE PRODUCT. Some states do not
allow the exclusion of incidental or consequential damages, so the above limitations may not apply to
you.
Garmin retains the exclusive right to repair or replace the unit or software or offer a full refund of the
purchase price at its sole discretion. SUCH REMEDY SHALL BE YOUR SOLE AND EXCLUSIVE
REMEDY FOR ANY BREACH OF WARRANTY.
To obtain warranty service, contact your local Garmin Authorized Service Center. For assistance in
locating a Service Center near you, call Garmin Customer Service at one of the numbers shown below.
Products sold through online auctions are not eligible for rebates or other special offers from Garmin.
Online auction confirmations are not accepted for warranty verification. To obtain warranty service, an
original or copy of the sales receipt from the original retailer is required. Garmin will not replace missing
components from any package purchased through an online auction.
Garmin International, Inc.
1200 East 151st Street
Olathe, Kansas 66062, U.S.A.
Phone: 913/397.8200
FAX: 913/397.0836
Page x
Revision A
Garmin (Europe) Ltd.
Liberty House, Bulls Copse Road
Hounsdown Business Park
Romsey, SO40 9RB, U.K.
Phone: +44/ (0) 870.8501241
Phone: +44/ (0) 870.8501251
G3X Installation Manual
190-01115-01
Limited Warranty for GSU 73 and GDU 37X Products
The Garmin products GSU 73 and GDU 37X are warranted to be free from defects in materials or
workmanship for one year from the date of purchase. Within this period, Garmin will at its sole option,
repair or replace any components that fail in normal use. Such repairs or replacement will be made at no
charge to the customer for parts or labor, provided that the customer shall be responsible for any
transportation cost. This warranty does not cover failures due to abuse, misuse, accident or unauthorized
alteration or repairs.
THE WARRANTIES AND REMEDIES CONTAINED HEREIN ARE EXCLUSIVE AND IN LIEU OF
ALL OTHER WARRANTIES EXPRESS OR IMPLIED OR STATUTORY, INCLUDING ANY
LIABILITY ARISING UNDER ANY WARRANTY OF MERCHANTABILITY OR FITNESS FOR A
PARTICULAR PURPOSE, STATUTORY OR OTHERWISE. THIS WARRANTY GIVES YOU
SPECIFIC LEGAL RIGHTS, WHICH MAY VARY FROM STATE TO STATE.
IN NO EVENT SHALL GARMIN BE LIABLE FOR ANY INCIDENTAL, SPECIAL, INDIRECT OR
CONSEQUENTIAL DAMAGES, WHETHER RESULTING FROM THE USE, MISUSE, OR
INABILITY TO USE THIS PRODUCT OR FROM DEFECTS IN THE PRODUCT. Some states do not
allow the exclusion of incidental or consequential damages, so the above limitations may not apply to
you.
Garmin retains the exclusive right to repair or replace the unit or software or offer a full refund of the
purchase price at its sole discretion. SUCH REMEDY SHALL BE YOUR SOLE AND EXCLUSIVE
REMEDY FOR ANY BREACH OF WARRANTY.
To obtain warranty service, contact your local Garmin Authorized Service Center. For assistance in
locating a Service Center near you, call Garmin Customer Service at one of the numbers shown below.
Products sold through online auctions are not eligible for rebates or other special offers from Garmin.
Online auction confirmations are not accepted for warranty verification. To obtain warranty service, an
original or copy of the sales receipt from the original retailer is required. Garmin will not replace missing
components from any package purchased through an online auction.
Garmin International, Inc.
1200 East 151st Street
Olathe, Kansas 66062, U.S.A.
Phone: 913/397.8200
FAX: 913/397.0836
G3X Installation Manual
190-01115-01
Garmin (Europe) Ltd.
Liberty House, Bulls Copse Road
Hounsdown Business Park
Romsey, SO40 9RB, U.K.
Phone: +44/ (0) 870.8501241
Phone: +44/ (0) 870.8501251
Page xi
Revision A
GSU 73 HARDWARE MOD LEVEL HISTORY
The following table identifies hardware modification (Mod) Levels for the GSU 73 LRU. Mod Levels
are listed with the associated service bulletin number, service bulletin date, and the purpose of the
modification. The table is current at the time of publication of this manual (see date on front cover) and is
subject to change without notice.
MOD
LEVEL
SERVICE
BULLETIN
NUMBER
SERVICE
BULLETIN
DATE
1
N/A
N/A
Page xii
Revision A
PURPOSE OF MODIFICATION
Improved HSCM accuracy when using +28V supply
G3X Installation Manual
190-01115-01
1
1.1
G3X Installation Overview
Unpacking Unit
Carefully unpack the equipment and make a visual inspection of the unit for evidence of damage incurred
during shipment. If any component of the G3X system is damaged, notify the carrier and file a claim. To
justify a claim, save the original shipping container and all packing materials. Do not return the unit to
Garmin until the carrier has authorized the claim.
Retain the original shipping containers for storage. If the original containers are not available, a separate
cardboard container should be prepared that is large enough to accommodate sufficient packing material
to prevent movement.
1.2
Introduction
This manual provides all of the mechanical and electrical information required for the installation of the
G3X system.
NOTE
The Garmin G3X system includes products like the GDU 37X and the GSU 73 that are
not TSO-certified products and have received no FAA approval or endorsement.
Consequently the G3X system is not suitable for installation in type-certificated aircraft.
The following outline describes the organization of this manual:
Section 1
This section contains a basic overview of the G3X system and interface. A Block
diagram is given to aid in the understanding of the system. This section also contains
generic information that pertains to all components of the G3X system, such as
mounting, wiring, and antenna location.
Section 2
This section describes the mechanical, electrical, and installation aspects of the
GDU 37X.
Section 3
This section describes the mechanical, electrical, and installation aspects of the
GMU 44.
Section 4
This section describes the mechanical, electrical, and installation aspects of the
GSU 73.
Section 5
This section describes the mechanical, electrical, and installation aspects of the
GTP 59.
Section 6
This section describes the mechanical, electrical, and installation aspects for the GPS
and XM antennas.
Section 7
This section describes the non-G3X LRU interfaces.
Section 8
This section contains software, configuration, database, and XM activation
information.
Section 9
This section contains post-installation checkout and calibration procedures for the
G3X.
Section 10
This section contains G3X troubleshooting information.
Section 11
This section contains information for ensuring the unit is suitable to be returned to
service.
Appendix A
This section contains pinout information for all G3X LRU’s.
Appendix B
This section contains connector installation instructions.
Appendix C
This section contains G3X Outline and Installation Drawings.
Appendix D
This section contains the G3X Interconnect Drawings.
Appendix E
This section contains the G3X External Interface Drawings.
G3X Installation Manual – Installation Overview
190-01115-01
Page 1-1
Revision A
1.3
System Overview
The G3X is an advanced technology avionics suite designed to integrate pilot/aircraft interaction into one
central system. The system combines primary flight instrumentation, aircraft systems instrumentation,
and navigational information, all displayed on one, two, or three color screens. The G3X system is
composed of several sub-units or Line Replaceable Units (LRUs). LRUs have a modular design and can
be installed directly behind the instrument panel or in a separate avionics bay if desired. This design
greatly eases troubleshooting and maintenance of the G3X system. A failure or problem can be isolated
to a particular LRU, which can be replaced quickly and easily. Each LRU has a particular function, or set
of functions, that contributes to the system’s operation. For additional information on LRU functions, see
the applicable section of this manual.
1.3.1 System Architecture
Figure 1-1 illustrates an example block diagram of a G3X installation. The flexibility of system allows
the installer to determine the architecture that best fits each installation.
SL 30/40
(1, 2)
RS-232
ELT
GMA 240
RS-232
STEREO/MONO AUDIO
Config Module
GDU 37X (PFD1)
Autopilot
GDU 37X (PFD2)
RS-232
A429
RS-485
RS-232
Static
Pitot
GMU 44
GTP 59
GDU 37X (MFD)
CAN
RS-232
GSU 73
RS-232
RS-232
GTX 330
Config Module
A429 (NAV)
A429 (AIR DATA)
RS-232
A429 (GPS)
A429 (NAV)
A429 (GPS)
GNS
430(W) (1)
GNS
430(W) (1)
Notes:
(1) Maximum of 2 COM/NAV units installed.
(2) GDU 37X to SL40 is TX only.
Figure 1-1. G3X Interconnect Example
Page 1-2
Revision A
G3X Installation Manual –Installation Overview
190-01115-01
1.4
General G3X LRU Specifications
1.4.1 Garmin LRU Part Numbers
Table 1-1. G3X LRU Part Numbers
LRU
Unit Only Part Number
Assembly Part Number
GDU 370 Americas DB
011-01747-15
010-00667-15
GDU 370 Atlantic DB
011-01747-20
010-00667-20
GDU 370 Pacific DB
011-01747-35
010-00667-35
GDU 375 Americas DB
011-01747-30
010-00667-25
GMU 44
011-00870-10
010-00296-10*
GSU 73
011-01817-00
010-00691-00*
GTP 59
011-00978-00*
NA
*Included in G3X LRU Kit (K10-00016-00)
Table 1-2. Contents of GDU 37X Assembly (010-00667-XX)
Item
Garmin P/N
Quantity
GDU 37X
011-01747-XX
1
GDU 37X Connector Kit
011-01921-00
1
GDU 37X Nutplate
115-01054-00
1
SD Card, Dummy
145-00561-00
1
Important Safety and Product Information
190-00720-50
1
GDU 37X Quick Reference Guide
190-01055-00
1
Jeppesen Free Single Update
190-10003-03
1
1.4.2 Power Specifications
All LRUs are capable of operating at either 14 or 28 VDC. Table 1-3 lists current draw specifications.
Table 1-3. G3X LRU Power Requirements
LRU
Supply Voltage
Current Draw
1.10 Amp @ 14Vdc
GDU 37X
10-29 Vdc
0.55 Amp @ 28Vdc
GMU 44
12Vdc (from GSU 73) Inc. in GSU Current Draw
1.75 Amp @ 14Vdc (Max)
GSU 73
10-29 Vdc
0.80 Amp @ 28Vdc (Max)
G3X Installation Manual – Installation Overview
190-01115-01
Page 1-3
Revision A
1.4.3 Physical Specifications
All width, height, and depth measurements are taken with unit rack (if applicable) and connectors.
Table 1-4. G3X LRU Physical Specifications
LRU
Width
Height
Depth
(GMU 44
Diameter,
including
flange*)
GDU 370
GDU 375
6.04 inches
(153.4 mm)
6.04 inches
(153.4 mm)
GMU 44
N/A
GSU 73
5.50 inches
(139.8 mm)
7.83 inches
(198.8 mm)
7.83 inches
(198.8 mm)
2.10 inches
(5.33 cm)
3.96 inches
(100.6 mm)
3.41 inches
(86.7 mm)
3.41 inches
(86.7 mm)
*3.35 inches
(85.1 mm)
7.33 inches
(186.2 mm)
Unit Weight
w/Nutplate
Unit Weight
& Connector
Weight
1.6 lbs
(0.713 kg)
1.7 lbs
(0.753 kg)
0.35 lbs.
(0.16 kg)
3.1 lbs
(1.41 kg)
1.8 lbs
(0.803 kg)
1.9 lbs
(0.843 kg)
0.50 lbs.
(0.23 kg)
3.5 lbs
(1.59 kg)
1.4.4 Cooling Requirements
While no forced cooling air is required for the G3X system, it is highly recommended that the air behind
the panel be kept moving (by ventilation or a fan).
•
•
•
No cooling air is required for the GDU 37X
No cooling air is required for the GMU 44
No cooling air is required for the GSU 73, however the GSU 73 should be mounted in a location
that provides adequate airflow to comply with the maximum outer case temperature listed in
Section 4.
NOTE
Avoid installing the G3X LRUs near heat sources. If this is not possible, ensure that
additional cooling is provided. Allow adequate space for installation of cables and
connectors. The installer will supply and fabricate all of the cables. All wiring should be
in accordance with FAA AC 43.13-1B and AC 43.13-2A.
Page 1-4
Revision A
G3X Installation Manual –Installation Overview
190-01115-01
1.5
Installation Requirements
One GDU 37X assembly (listed in Table 1-1) is required, dependent upon customer’s desired database
region. Each GDU 37X (010-00667-XX) comes with all equipment needed for installation.
1.5.1 Required Accessories
The following kits are required for the installation of the G3X.
Table 1-5. Contents of G3X Installation Kit (K10-00017-00)
Item
Garmin P/N
Quantity
GMU 44, Connector Kit
011-00871-00
1
Config Module w/EEPROM, Jackscrew
011-00979-20
1
Config Module w/Sockets, Jackscrew
011-00979-22
1
Thermocouple Kit
011-00981-00
1
GSU 73, Connector Kit, P9731
011-01818-00
1
GSU 73, Connector Kit, P9732
011-01818-01
1
G3X, Supplemental Parts
011-02347-00
1
GMU 44, Install Rack, Modified
115-00481-10
1
Table 1-6. Contents of G3X LRU Kit (K10-00016-00)
Item
Garmin P/N
Quantity
GMU 44, Unit Only
010-00296-10
1
GSU 73, Unit Only
010-00691-00
1
GTP 59, Unit Only
011-00978-00
1
1.6
Mounting
Refer to Section 2 through Section 6 for specific mounting instructions for each component of the G3X,
and to Appendix A for Outline & Installation Drawings.
1.7
Wiring/Cabling Considerations
Use MIL-W-22759/16 (or other approved wire) AWG #24 or larger wire for all connections unless
otherwise specified. The supplied standard pin contacts are compatible with up to AWG #22 wire. In
cases where some installations have more than one LRU sharing a common circuit breaker, sizing and
wire gauge is based on aircraft circuit breaker layout, length of wiring, current draw on units, and internal
unit protection characteristics. Do not attempt to combine more than one unit on the same circuit breaker.
RG400 or RG142 coaxial cable with 50 Ω nominal impedance and meeting applicable aviation
regulations should be used for the installation.
G3X Installation Manual – Installation Overview
190-01115-01
Page 1-5
Revision A
1.7.1
Wiring Harness Installation
Allow adequate space for installation of cables and connectors. Ensure that routing of the wiring does not
come in contact with sources of heat, RF or EMI interference. Analog Input wires routed too close to
spark plugs, plug wires, or magnetos may result in erratic readings.
The installer shall supply and fabricate all of the cables. Required connectors, etc. are provided with the
G3X Installation Kit (K10-00017-00). Electrical connections are made through D subminiature
connectors for the GDU 37X and GSU 73 units, and through a round 9-pin connector for the GMU 44.
Appendix A defines the electrical characteristics of all input and output signals. Required connectors and
associated hardware are supplied with the connector kit..
CAUTION
Check wiring connections for errors before connecting any wiring harnesses. Incorrect
wiring could cause internal component damage.
Table 1-7. Pin Contact and Crimp Tools Part Numbers
LRU
Contact Type
Garmin
Contact Part
Number
Recommended
Positioner
GDU 37X
Socket, Mil
Crimp, Size 20
336-00094-00
M22520/2-08,
Daniels K13-1
GSU 73
GTP 59
011-00979-20
(Config
module
w/EEPROM
kit)
011-00981-00
(thermocouple
kit)
Pin, Mil Crimp,
Size 22D
336-00021-00
Positronic P/N
9502-4,
ITT P/N
M22520/2-09,
Daniels P/N K42
GMU 44
Socket, Mil
Crimp, Size 20
336-00022-00
M22520/2-08,
Daniels K13-1
011-00979-22
(Config
module
w/Sockets &
Jackscrew kit)
Socket, Mil
Crimp, Size 20,
26-30 AWG
336-00022-01
Positronic P/N
9502-5
Recommended
Insertion/
Extraction Tool
M81969/1-04
for size 22D
pins and
M81969/1-02
for size 20 pins
Recommended
Hand Crimping
Tool
M22520/2-01
NOTES
1. Insertion/Extraction tools from ITT Cannon are all plastic; others are plastic with metal tip.
2. Non-Garmin part numbers shown are not maintained by Garmin and consequently are subject
to change without notice.
Page 1-6
Revision A
G3X Installation Manual –Installation Overview
190-01115-01
1.7.2 Cable Location Considerations
Use cable meeting the applicable aviation regulation for the interconnect wiring. Any cable meeting
specifications is acceptable for the installation. When routing cables, observe the following precautions:
• All cable routing should be kept as short and as direct as possible.
•
Check that there is ample space for the cabling and mating connectors.
•
Avoid sharp bends in cabling.
•
Avoid routing near aircraft control cables.
•
Avoid routing cables near power sources (e.g., 400 Hz generators, trim motors, etc.) or near
power for fluorescent lighting.
•
Route the GPS antenna cable as far as possible away from all COM transceivers and antenna
cables.
1.7.3
Cable Installation
1. Route the coaxial cable to the unit location. Secure the cable in accordance with good aviation
practices.
2. Trim the coaxial cable to the desired length and install the BNC connector (330-00087-00) per
the cabling instructions on Figure 1-2. If the connector is provided by the installer, follow the
connector manufacturer’s instructions for cable preparation.
Figure 1-2. Coaxial Cable Installation
3. Contacts for the 50, 62, and 78 pin connectors must be crimped onto the individual wires of
the aircraft wiring harness. Table 1-7 lists contact part numbers (for reference) and
recommended crimp tools.
G3X Installation Manual – Installation Overview
190-01115-01
Page 1-7
Revision A
1.7.4
Backshell Assemblies
Connector kits include backshell assemblies. The backshell assembly houses the configuration module
and a thermocouple reference junction (if applicable, see Appendix D). Garmin’s backshell connectors
give the installer the ability to quickly and easily terminate shield grounds at the backshell housing. The
instructions needed to install the Jackscrew Backshell, Configuration Module, and Thermocouple are
located in Appendix B.
NOTE
The GDU 37X rear connector (J3701) is electrically isolated. For installations using
shielded cables, a ground pin must be tied to the connector shell.
Page 1-8
Revision A
G3X Installation Manual –Installation Overview
190-01115-01
2
GDU 37X
Figure 2-1. GDU 37X Unit View
2.1
Equipment Description
NOTE
There is no TSO/ETSO applicable to the GDU G37X.
The GDU 37X provides a central display and user interface for the G3X system. The display is mounted
flush to the aircraft instrument panel using four #6 screws. The GDU 37X is available in two models,
GDU 370 and GDU 375. The GDU 370 is a Garmin Display Unit with a VFR WAAS-GPS receiver.
The GDU 375 provides these same features plus an XM receiver.
2.1.1 Navigation Functions
•
•
•
•
Display of position and ground speed
Display of stored navigation and map databases
Area navigation functions using the determined position/velocity and stored navigation data
Advisory approach navigation functions and associated databases
G3X Installation Manual – GDU 37X
190-01115-01
Page 2-1
Revision A
2.1.2 Interface Summary
The GDU 37X uses CAN and RS-232 communications interfaces. The GDU 37X communicates with the
following Garmin LRUs:
• Other GDU 37X
• GSU 73
• SL30 Nav/Comm Transceiver
• SL40 Comm Transceiver
• GNS 400/500 Series Units
• GTX 327/330 Transponder
2.2
Electrical Specifications
2.2.1 Electrical Characteristics
Characteristics
Power Requirements
Table 2-1. GDU 37X Supply Voltages
Specifications
14/28 VDC
2.2.2 Power Consumption
LRU
GDU 370
GDU 375
Table 2-2. GDU 37X Power Requirements
14V (Maximum)
14V (Typical)
28V (Maximum)
15W, 1.10 Amp
8.5W, .600 Amp 15W, 0.540 Amp
15W, 1.10 Amp
9.5W, .675 Amp 15W, 0.540 Amp
28V (Typical)
8.5W, .300 Amp
9.25W, .330 Amp
2.2.3 GPS Specifications
The GDU 37X uses a high-sensitivity GPS receiver that continuously tracks and uses up to 12 satellites to
compute and update its position.
Characteristics
Acquisition Time
Update Rate
Positional Accuracy
Antenna Power Supply
Page 2-2
Revision A
Table 2-3. GDU 37X GPS Specifications
Specifications
a) Warm Start (position known to 10 nm, time known to 10
minutes, with valid almanac and ephemeris): Less than 5
seconds
b) Cold Start (position known to 300 nm, time known to 10
minutes, with valid almanac): Less than 45 seconds
c) AutoLocate™ (with almanac, without initial position or
time): Less than 60 seconds
5/second, continuous
<10 meters
Voltage (4.5 to 5.0), current (50 mA max)
G3X Installation Manual – GDU 37X
190-01115-01
2.2.4 Antennas
Table 2-4 lists Garmin and non-Garmin antennas currently supported by the GDU 37X. Refer to Section
6 for Garmin antenna installation information. For non-Garmin antennas, follow the manufacturer’s
installation instructions.
NOTE
Only a single GPS antenna is required for installations using more than
one GDU 37X unit, as the GDU 37X will “share” the GPS information
with all GDU 37X units.
Table 2-4. GDU 37X Supported Antennas
Antenna Part
Number
Garmin Order
Number
Comant
CI 2480-201
N/A
XM
Comant
CI 420-10
N/A
BNC
GPS
Garmin
011-00149-04
010-10052-04
Ground
Plane Mt
TNC
XM
Garmin
013-00268-10
010-11373-00
GA 55
Stud Mount
TNC
XM
Garmin
011-01033-00
010-10600-01
GA 55A
ARINC 743
TNC
XM
Garmin
011-01153-00 010-10598-00
GA 56
Stud Mount
BNC
GPS
Garmin
011-00134-00 010-10040-01
GA 57X
[2]
Screw
Mount,
ARINC 743
Footprint
BNC
TNC
GPS
XM
Garmin
011-01032-10 010-11370-10
Mount Style
Conn
Type
Antenna
Type
Mfr
Comant
2480-201
VHF/GPS
[1]
Screw
Mount,
Teardrop
Footprint
BNC
TNC
VHF
COM,
GPS
Comant
420-10 XM
only
Antenna
Screw
Mount,
ARINC 743
Footprint
TNC
GA 26C
Suction Cup,
Magnetic or
Flange Mt
GA 26XM
Model
[1] The GPS antenna connector is TNC type. The VHF COM antenna connector is BNC type.
NOTE
The GPS antenna should provide a gain of 16 to 25dB, and requires a
4.5V to 5V supply voltage that can provide 50mA max.
2.3
Environmental Specifications
The GDU 37X has an Operating Temperature Range of -20°C to +60°C.
G3X Installation Manual – GDU 37X
190-01115-01
Page 2-3
Revision A
2.4
Installation Requirements
2.4.1 Accessories
The GDU 37X Connector Kit is provided with the GDU 37X unit and is required to install the unit
(Figure 2-2). The GDU 37X Nutplate (115-01054-00) is also supplied with the unit to reinforce the panel
cutout in thin panel installations.
The contents of the GDU 37X Connector Kit are listed in Table 2-5. One kit is required for each GDU
37X installed.
Table 2-5. Contents of GDU 37X Connector Kit (011-01921-00)**
Item
Garmin P/N
Quantity
Sub-Assy,bkshl w/Hdw,Jackscrew
011-01855-04
1
Conn, Rcpt,D-Sub, Crimp Socket, C
330-00625-50
1
Contact, Sckt, D-Sub, Crimp, Size 20
336-00094-00
20
2.4.2 Additional Equipment
A 3/32” hex drive tool is required to secure the GDU 37X to the panel as described in Section 2.7 Unit
Installation.
CONNECTOR KIT
011-01921-00
GDU 37x UNIT
011-01747-( )
Figure 2-2. GDU 37X Mounting Accessories
Page 2-4
Revision A
G3X Installation Manual – GDU 37X
190-01115-01
2.5
Installation Considerations
Fabrication of a wiring harness is required. Sound mechanical and electrical methods and practices are
recommended for installation of the GDU 37X. Refer to Section 1.6 for wiring considerations and to
Appendix A for pinouts.
Connector kits include backshell assemblies. Garmin’s backshell connectors give the installer the ability
to quickly and easily terminate shield grounds and install a configuration module (PFD1 only) at the
backshell housing. The instructions needed to assemble the backshell connector w/Shield Block
grounding system and configuration modules are located in Appendix B.
NOTE
The GDU 37X rear connector (J3701) is electrically isolated. For
installations using shielded cables, a ground pin must be tied to the
connector shell.
2.6
Mounting Requirements
Refer to Appendix C for outline and installation drawings.
2.7
Unit Installation
The GDU 37X is installed by holding the unit flush with the instrument panel and fastening the four
captured 3/32” hex socket head screws to the panel as shown in Figures C-1.1 and C-1.2.
2.8
Maintenance
Maintenance of the GDU 37X is “on condition” only. Periodic maintenance of the GDU 37X is not
required. Instructions for Continued Airworthiness (ICA) are not required for this product under 14 CFR
Part 21 since the GDU 37X has received no FAA approval or endorsement.
G3X Installation Manual – GDU 37X
190-01115-01
Page 2-5
Revision A
2.9
Panel Cutout Template
The below drawing can be used as a template when marking the panel for cutout. Dimensions below are
to verify accuracy of printout only, see Figure C-1.2 for complete dimensions.
GDU 37X PANEL CUTOUT TEMPLATE
IMPORTANT!
Ensure the Page Scaling setting
is set to NONE when printing
this page. Verify dimensions
of printed template are
accurate before cutting panel.
Cut out panel
to inside line
7.33 in
[186.2 mm]
5.57 in
[141.4 mm]
For corner holes, center punch and drill
(#36) / tap (6/32) to create threaded holes
OR
drill out with 25 drill bit and use Garmin
nut-plate P/N 115-01054-00
Page 2-6
Revision A
G3X Installation Manual – GDU 37X
190-01115-01
3. GMU 44
Figure 3-1. GMU 44 Unit View
3.1
Equipment Description
The Garmin GMU 44 Magnetometer is a remote mounted device that interfaces with a Garmin GSU 73 to
provide flight attitude and heading data for flight instrumentation.
An Attitude and Heading Reference System combines the functions of a Vertical Gyro and a Directional
Gyro to provide measurement of Roll, Pitch and Heading angles. The Garmin ADAHRS and
magnetometer replace traditional rotating mass instruments.
Using long-life solid-state sensing technology, the GMU 44 Magnetometer uses magnetic field
measurements to create an electronically stabilized AHRS.
The GMU 44 magnetometer provides magnetic information to support the function of the GSU 73. The
GSU 73 provides operating voltage to the GMU 44 Magnetometer.
3.1.1 Interface Summary
The following is an interface summary for the GMU 44.
•
3.2
GMU 44 to GSU 73 Interface: Power, RS-232, RS-485 (19,200 baud)
Electrical Specifications
Table 3-1. GMU 44 Electrical Specifications
Specification
Power Requirements
G3X Installation Manual – GMU 44
190-01115-01
Characteristic
Supply Voltage: 14/28 VDC. See Table 1-3 for current
specifications.
Page 3-1
Revision A
3.3
Environmental Specifications
Table 3-2 lists general environmental specifications.
Table 3-2. GMU 44 Environmental Specifications
Specification
Characteristic
Regulatory Compliance
RTCA/DO-160D Environmental Conditions and
EUROCAE/ED-14D
Unit Software
RTCA/DO-178B Level B
Operating Temperature
Range
-55° C to +70° C
Altitude
3.4
55,000 Feet
GMU 44 TSO/ETSO Compliance
Table 3-3. TSO/ETSO Compliance
Function
Direction Instrument,
Magnetic (Gyroscopically
Stabilized)
TSO/ETSO/SAE/
RTCA/EUROCAE
Category
TSO-C6d
ETSO-C6d
AS8013A
Applicable LRU
SW Part
Numbers
Applicable
Custom Logic
Device Part
Numbers
All
006-B0224-(__)
except
006-B0224-Z(_)
All
006-C0048-0(_)
3.4.1 TSO/ETSO Deviations
The following table provides a list of applicable TSO and SAE deviations for the GMU 44.
Table 3-4. TSO/ETSO Deviations
TSO
TSO-C6d
(GMU 44)
ETSO-C6d
(GMU 44)
Page 3-2
Revision A
Deviation
1. Garmin was granted a deviation from TSO-C6d to use RTCA DO-160D instead of RTCA
DO-160B as the standard for Environmental Conditions and Test Procedures for Airborne
Equipment.
2. Garmin was granted a deviation from TSO-C6d to use RTCA DO-178B instead of RTCA
DO-178A to demonstrate compliance for the verification and validation of the computer
software.
3. Garmin was granted a deviation from TSO-C6d to use SAE AS 8013A instead of SAE
AS 8013 as the Minimum Performance Standard.
4. Garmin was granted a deviation from TSO-C6d to list this secondary TSO in the
Installation Manual rather than on the article itself.
5. Garmin was granted a deviation from TSO-C6d to list the DO-178B software level in the
Installation Manual rather than on the article itself.
1. Garmin was granted a deviation from ETSO-C6d to use RTCA DO-160D instead of SAE
AS 8013 as the standard for Environmental Conditions and Test Procedures for Airborne
Equipment.
2. Garmin was granted a deviation from ETSO-C6d to use SAE AS 8013A instead of SAE
AS 8013 as the Minimum Performance Standard.
G3X Installation Manual – GMU 44
190-01115-01
3.5
Installation Requirements
3.5.1 Equipment Available
Table 3-5. GMU 44 Part Numbers
Model
Catalog Part
Number
GMU 44
010-00296-10*
*Included in G3X LRU Kit (K10-00016-00)
Unit Part Number
Installation Rack
011-00870-10
No
Table 3-6. GMU 44 Accessories
Item
Sub Assy, Connector Kit, GMU 44
GMU 44 Universal Mount***
Garmin P/N
Quantity
011-00871-00**
1
011-01779-01
1 (optional)
Installation Rack, GMU 44
115-00481-10**
1
**Included in G3X Installation Kit (K10-00017-00)
***Refer to AHRS Magnetometer Installation Considerations (190-01051-00) from www.garmin.com
3.6
Installation Considerations
If the requirements listed
interference test must be
G3X system.
Refer
Considerations document
website (www.garmin.com).
NOTE
in Table 3-7 cannot be met, a magnetometer
performed to ensure proper operation of the
to the AHRS/Magnetometer Installation
(190-01051-00) available from the Garmin
The following guidelines describe proper mechanical installation of the Garmin GMU 44 Magnetometer.
The guidelines include requirements for proper location selection in the aircraft, requirements for
supporting structure and mechanical alignment and restriction on nearby equipment.
Fabrication of a wiring harness is required. Sound mechanical and electrical methods and practices are
required for installation of the GMU 44. Refer to Section 1.6 for wiring considerations and to Appendix
A for pinouts.
The instructions needed to assemble the circular connector are located in Appendix B.
The GMU 44 is an extremely sensitive three-axis magnetic sensor. It is more sensitive to nearby
magnetic disturbances than a flux gate magnetometer. For this reason, when choosing a mounting
location for the GMU 44, observe the following distances from objects or devices that can disturb the
magnetic field. Table 3-7 specifies required distances from magnetic disturbances for GMU 44 location.
G3X Installation Manual – GMU 44
190-01115-01
Page 3-3
Revision A
Table 3-7. Required Distance from Magnetic Disturbances
Disturbance Source
Minimum Distance from GMU 44
Electric motors and relays, including servo motors
10 feet (3.0 meters)
Ferromagnetic structure greater than 1 kg total
(iron, steel, or cobalt materials, especially landing
gear structure)
8.2 feet (2.5 meters)
Ferromagnetic materials less than 1 kg total, such
as control cables
3 feet (1.0 meter)
Any electrical device drawing more than 100 mA
current
3 feet (1.0 meter)
Electrical conductors passing more than 100 mA
current [(must be twisted shielded pair if within 10
feet (3.0 meters)]
3 feet (1.0 meter)
Electrical devices drawing less than 100 mA current
2 feet (0.6 meter)
Magnetic measuring device (e.g. installed flux
gates, even if unpowered)
2 feet (0.6 meter)
Electrical conductors passing less than 100 mA
current [(must be twisted shielded pair if within 10
feet (3.0 meters)]
1.3 feet (0.4 meter)
Ensure that any electrical conductor that comes within 10 feet (3.0 meters) of the GMU 44 is installed as a
twisted shielded pair, not a single-wire conductor. (If possible, the shield should be grounded at both
ends.)
Use nonmagnetic materials to mount the GMU 44, and replace any magnetic fasteners within 0.5 meter
with nonmagnetic equivalents (e.g. replace zinc-plated steel screws used to mount wing covers or
wingtips with nonmagnetic stainless steel screws).
In general, wing mounting of the GMU 44 magnetometer is strongly preferred. Fuselage mounting is
strongly discouraged because of numerous potential disturbances that interfere with accurate operation.
Mechanical mounting fixtures for the GMU 44 must be rigidly connected to the aircraft structure. Use of
typical aircraft-grade materials and methods for rigid mounting of components is acceptable, so long as
adequate measures are taken to ensure a stiffened mounting structure.
Align the GMU 44 mounting rack to within 3.0° of the aircraft level reference in pitch and roll.
Align the GMU 44 mounting rack’s forward direction to within 0.5° in heading of the aircraft forward
direction (longitudinal axis). If it is not possible to guarantee this accuracy, installation alignment to
within 2.5° in heading is acceptable in combination with a post-installation heading alignment of the
aircraft to a precise heading to determine and set a heading offset. The heading offset procedure is
described in Section 8.3.4.
It is strongly preferred that the GMU 44 alignment is within 0.5° of the aircraft longitudinal axis, rather
than using the heading offset procedure.
Page 3-4
Revision A
G3X Installation Manual – GMU 44
190-01115-01
3.6.1 Consideration for Wing Grounded Lighting Fixtures
The following installation practices are recommended if the required GMU 44 mounting bracket is
located in the wing.
1. The wing tip lights should not have a power ground referenced to the chassis of the light
assembly that would then be referenced back to the airframe ground via the light assembly
mounting.
2. A dedicated power ground should be used and returned as a twisted pair with the power source
back into the fuselage for a wing mounted GMU 44.
These installation practices will prevent magnetically interfering currents from flowing in the wing skin
that encloses the GMU 44. Electrically isolating the light assembly should not be used as an alternative to
item 1 above, unless the isolated light assembly has been analyzed for adequate protection against direct
attachment of lightning.
Refer to Appendix C for outline and installation drawings.
3.7
GSU 73/GMU 44 Interconnect Harness Fabrication Instructions
Table 3-8 lists parts needed for the GMU 44 interconnect harness. Some of the parts for installation are
included in the GMU 44 Connector Installation Kit. Other parts are provided by the installer. Reference
numbers refer to item bubble numbers shown in Figure C-2.4.
Table 3-8. Parts Needed for GMU 44 Installation
Figure B-2.4 Ref
Description
Shield Termination
(method optional)
2
Shield Extension Wire
3, 4, 9
GMU 44 Connector Kit**
5
3-Conductor Cable
6
2-Conductor Cable
**Included in G3X Installation Kit (K10-00017-00)
1
Qty.
Included
0
0
1
0
0
GPN or MIL Spec
Parts used depend on method
chosen
M22759/16-22
011-00871-00
M27500-22TE3T14
M27500-22TE2T14
Table 3-9 lists material in the GMU 44 connector kit and the associated reference number, as shown in
Figure C-2.4. The GMU 44 magnetometer has an attached pigtail with male polarity. The harness
connector for the GMU 44 has female polarity.
Table 3-9. GMU 44 Connector Kit (011-00871-00)** Contents, Reference Figure C-2.4
Item
Garmin P/N
Quantity
Figure C-2.4 Ref
Screw,6-32x.250,PHP,BR,w/Nyl
211-60037-08
3
9
Conn,Circular,Female,9 Ckt
330-00360-00
1
4
Backshell,Circular,Kit,SS
330-90005-01
1
4
Cont,Sckt,Mil Crp,Size 20
336-00022-00
10
3
**Included in G3X Installation Kit (K10-00017-00)
G3X Installation Manual – GMU 44
190-01115-01
Page 3-5
Revision A
3.8
Mounting Instructions
After evaluation of the mounting location has been completed and ensuring that requirements are met,
assemble the GMU 44 mounting plate kits according to the dimensions given in Appendix C. Install the
unit assemblies.
Mount the GMU 44 to its mounting plate, taking care to tighten the mounting screws firmly. Use of nonmagnetic tools (e.g. beryllium copper or titanium) is recommended when installing or servicing the
GMU 44. Do not use a screwdriver that contains a magnet when installing or servicing the GMU 44.
The metal components in the GMU 44's connector may slightly affect the magnetic field sensed by the
GMU 44. Place the connector at least 2 inches from the body of the GMU 44 to minimize this effect.
After attaching the GMU 44's connector to its mate in the aircraft wiring, secure the connector in place
using good installation practices. This will ensure that any remaining magnetic effect can be
compensated for using Calibration Procedure C: Magnetometer Calibration (Section 9.3.3).
NOTE
If the GMU 44 is ever removed, the anti-rotation properties of the
mounting screws must be restored. This may be done by replacing the
screws with new Garmin PN 211-60037-08. If original screws must be
re-used, coat screw threads with Loctite 242 (blue) thread-locking
compound, Garmin PN 291-00023-02, or equivalent.
Important:
Mounting screws must be brass.
3.9
Maintenance
Maintenance of the GMU 44 is ‘on condition’ only. Periodic maintenance of the GMU 44 is not required.
Page 3-6
Revision A
G3X Installation Manual – GMU 44
190-01115-01
4
4.1
GSU 73
Equipment Description
NOTE
There is no TSO/ETSO applicable to the GSU 73.
The GSU 73 is intended for the LSA (light sport aircraft) and experimental aircraft markets. The Garmin
GSU 73 Sensor Unit is not a TSO-certified product and has received no FAA approval or endorsement.
The GSU 73 is intended to be used as a part of the G3X system and it is not suitable for installation in
type-certificated aircraft.
The GSU 73 is an LRU that provides AHRS and Air Data information as well as an interface to
Engine/Airframe sensors in a single mechanical package. The GSU 73 interfaces to a remote mounted
GMU 44 for heading information and also computes OAT and TAS from inputs provided by the GTP 59.
The GSU 73 is capable of maneuvers through a range of 360° in bank and pitch. The rotation rate
capability is ±200° per second.
Bank error and pitch error are within ±1.25° over the range of 30° bank, left and right, and 15° pitch nose
up and nose down. Heading is accurate to within 2° in straight and level flight.
Due to unsuitability of the magnetic fields near the Earth’s poles, operational accuracy is unknown north
of 70° North latitude and south of 70° South latitude. In addition, operational accuracy is unknown in the
following two regions:
1) North of 65° North latitude between longitude 75° W and 120° W. (Northern Canada)
2) South of 55° South latitude between longitude 120° E and 165° E. (Region south of Australia and
New Zealand)
Figure 4-1. GSU 73 Unit View
G3X Installation Manual – GSU 73
190-01115-01
Page 4-1
Revision A
4.1.1 Features Summary
Air Data
Interfaces
Pressure Altitude
Density Altitude
Vertical Speed
Mach Number
Indicated Airspeed
True Airspeed
CAN (1)
RS-232 (2 TX/2 RX)
ARINC 429 (4 RX/2 TX)
OAT Probe (GTP 59)
Magnetometer (GMU 44) (1 RS-232 TX/ 1 RS-485 RX)
AHRS
Engine/Airframe
Magnetic Heading
Pitch Angle
Roll Angle
Linear Accelerations
Pitch, Roll, Yaw Rotation Rates
28 Analog inputs, including those allocated as per below:
Dedicated Ammeters (2)
Constant Current Source Capability (6)
Divider Circuits to handle large input voltages (12)
Frequency Counter Inputs (4)
Discrete I/O (4 In/2 Out)
4.2
Electrical Specifications
Table 4-1. GSU 73 Supply Specifications
Characteristic
Input Voltage Range
Power Input
Specification
10-29 Vdc*
1.75 Amp @ 14 Vdc (Max)
0.80 Amp @ 28 Vdc (Max)
*Garmin recommends using a Mod 1level GSU 73 in aircraft that exclusively use a +28V supply.
Page 4-2
Revision A
G3X Installation Manual – GSU 73
190-01115-01
4.3
Environmental Specifications
The GSU 73 is a non-TSO’d product, Table 4-2 lists general environmental specifications.
NOTE
The GSU 73 may require a warm-up period of 15 minutes to reach full
accuracy (30 minutes if the environmental temperature is less than 0°C).
Table 4-2. GSU 73 Environmental Specifications
Characteristic
Specification
Aircraft Pressure Altitude Range
-1,400 feet to 50,000 Feet
Aircraft Vertical Speed Range
-20,000 feet per minute to +20,000 feet per minute
Aircraft Airspeed Range
450 Knots
Aircraft Mach Range
<1.00 Mach
Aircraft Total Air Temperature Range
-85°C to +85°C
Unit Operating Temperature Range
-40°C to +70°C
Max Outer Case Temperature
+73°C
4.4
Installation Requirements
4.4.1 Required Equipment
Table 4-3 lists the kits available for the GSU 73.
Table 4-3. GSU 73 Available Equipment
Item
Garmin P/N
Quantity
Configuration Module w/EEPROM and Jackscrew, Kit
011-00979-20**
1
Thermocouple Kit
011-00981-00**
1
Unit Assembly, GSU 73
011-01817-00*
1
P731 Connector Kit, GSU 73
011-01818-00**
1
P732 Connector Kit, GSU 73
011-01818-01**
1
*Included in G3X LRU Kit (K10-00016-00)
**Included in G3X Installation Kit (K10-00017-00)
Table 4-4. Contents of P731 Connector Kit (011-01818-00)**
Item
Garmin P/N
Quantity
Sub-Assy,Backshell w/Hdw,Jackscrew
011-01855-03
1
Connector ,Hi Dens, D-Sub, Mil Crimp 62ck
330-00185-62
1
Contact Pin, Mil Crimp, Size 22D
336-00021-00
20
**Included in G3X Installation Kit (K10-00017-00)
G3X Installation Manual – GSU 73
190-01115-01
Page 4-3
Revision A
Table 4-5. Contents of P732 Connector Kit (011-01818-01)**
Item
Garmin P/N
Quantity
Sub-Assy,Backshell w/Hdw,Jackscrew
011-01855-04
1
Connector ,Hi Dens, D-Sub, Mil Crimp 78ck
330-00185-78
1
Contact Pin, Mil Crimp, Size 22D
336-00021-00
30
**Included in G3X Installation Kit (K10-00017-00)
4.4.2 Additional Equipment Required
4.5
•
•
Cables: The installer will fabricate and supply all system cables.
Hardware: #10-32 pan or hex head screw (4 ea.) and #10-32 self-locking nut (4 ea)
•
Air hoses and fittings to connect pitot and static air to the GSU 73. The GSU 73 has a female
1/8-27 ANPT fitting for each pitot and static port. Use appropriate aircraft fittings to connect to
pitot and static system lines.
Installation Considerations
Fabrication of a wiring harness is required. Sound mechanical and electrical methods and practices
should be used for installation of the GSU 73. Refer to Section 1.6 for wiring considerations, and to
Appendix A for pinouts.
Connector kits include backshell assemblies. The backshell assembly houses the configuration module
(P732 only) and a thermocouple reference junction (if applicable). Garmin’s backshell connectors give
the installer the ability to quickly and easily terminate shield grounds at the backshell housing. The
instructions needed to install the Jackscrew Backshell, Configuration Module, and Thermocouple are
located in Appendix B.
Page 4-4
Revision A
G3X Installation Manual – GSU 73
190-01115-01
4.5.1 Pneumatic Plumbing
The GSU 73 has two ports that are connected to the aircraft’s pitot pressure source and static pressure
source. The two ports are labeled on the unit (see Figure 4-2). The pressure ports have 1/8-27 ANPT
female threads. The mating fitting must have 1/8-27 ANPT male threads.
J732
J731
Figure 4-2. GSU 73 Air Hose Fitting Locations
Use appropriate air hoses and fittings to connect the pitot and static lines to the unit. Avoid sharp bends
and routing near aircraft control cables. The GSU 73 should not be at the low point of the pitot or static
plumbing lines, to avoid moisture or debris collecting at or near the unit. Ensure that no deformations of
the airframe surface have been made that would affect the relationship between static air pressure and true
ambient static air pressure for any flight condition. Refer to part 43, Appendix E for approved practices
while installing hoses and connections.
4.5.2 Pneumatic Connections
The following steps should be used to aid in the fabrication of pneumatic hose connections and in
attaching the aircraft pitot pressure source and aircraft static pressure source to the GSU 73.
CAUTION
Check pneumatic connections for errors before operating the GSU 73.
Incorrect plumbing could cause internal component damage. Observe
the following cautions when connecting pneumatic lines.
1. Make sure the aircraft static pressure port is plumbed directly to the unit static pressure input port and
the aircraft pitot pressure port is plumbed directly to the unit pitot pressure input port.
2. Seal the threads of pneumatic fittings at the connector ports. Use caution to ensure there are no
pneumatic leaks.
3. Use care to avoid getting fluids or particles anywhere within the pitot and static lines connected to the
GSU 73.
The installer must fabricate any additional mounting equipment needed. Use outline and installation
drawings in Appendix C for reference.
G3X Installation Manual – GSU 73
190-01115-01
Page 4-5
Revision A
4.6
Mounting Requirements
Mount the GSU 73 with the connectors aligned within 1.0 deg of either the X or Y axis of the aircraft.
The direction of the unit will be accounted for during the calibration procedure as shown in Figure 4-3.
Figure 4-3. GSU 73 Orientation Calibration
The GSU 73 includes an extremely sensitive strap-down inertial measurement unit. It must be mounted
rigidly to the aircraft primary structure, preferably to a metallic structure to conduct heat away from the
unit. Do not mount the GSU 73 in an enclosed area, it should be mounted in a location that provides
adequate airflow to comply with the maximum outer case temperature listed in Section 4.3.
Page 4-6
Revision A
G3X Installation Manual – GSU 73
190-01115-01
Do not use shock mounting to mount the GSU 73. Shock mounts used for other types of inertial systems
are not acceptable for the GSU 73 AHRS. The mounting system must have no resonance with the unit
installed. Excessive vibration may result in degraded accuracy.
The supporting plate must be rigidly connected to the aircraft primary structure through strong structural
members capable of supporting substantial loads. Avoid areas that are prone to severe vibration.
The GSU 73 should be mounted within 13 feet (4.0 meters) longitudinally and 6.5 feet (2.0 meters)
laterally of the aircraft center of gravity. In cases where the longitudinal distance from the CG is planned
to be greater than 6.5 feet (2.0 meters), it is preferable to mount the GSU 73 forward of the aircraft center
of gravity if possible, to enable better acceleration outputs for autopilot use. The mounting location for
the GSU 73 should be protected from rapid thermal transients, in particular, large heat loads from nearby
high-power equipment.
The GSU 73 must be leveled to within 3.0° of the aircraft level reference, and an aircraft leveling and
offset calibration procedure carried out prior to flight. (This procedure is described in Section 9.)
Alternatively, if the GSU 73 can be guaranteed level to within 0.25° of the aircraft level reference, the
aircraft leveling and offset calibration procedure is not required.
Avoid placing the GSU 73 within 1 inch of magnetically mounted antennas, speaker magnets, or other
strongly magnetic items.
4.7
Unit Installation
For final installation and assembly, refer to the outline and installation drawings shown in Appendix C of
this manual.
1. Assemble the wiring harness and backshell connectors.
2. Assemble the pneumatic hoses and connectors.
3. Mount the unit to a suitable mounting location using #10-32 pan or hex head screws (4 ea) per
the requirements in Section 4.6.
4. Connect backshell connector and hoses.
NOTE
When mounting the GSU 73 to the airframe, it is important to ensure that
fastening hardware is tight for proper unit operation.
G3X Installation Manual – GSU 73
190-01115-01
Page 4-7
Revision A
4.8
Maintenance
Per Part 43 Appendix E, paragraph (b)(2), Garmin specifies a test procedure equivalent to part 43
Appendix E, paragraph (b)(1) with two exceptions. The tests of sub-paragraph (iv)(Friction) and (vi)
(Barometric Scale Error) are not applicable because the digital outputs of the GSU 73 are not susceptible
to these types of errors.
A GSU 73 Field Calibration Tool (not yet available) can be used to adjust the calibration of GSU 73 units
that have failed the 14 CFR Part 43 Appendix E tests due to altitude drift.
The GSU 73 utilizes an Earth magnetic field model which is updated once every five years. This IGRF
(International Geomagnetic Reference Field) update is expected to be available from Garmin by July 1 of
each of the following years: 2010, 2015, and every five years thereafter, so long as the GSU 73 remains a
Garmin –supported product. The IGRF model can be updated by the end user via the internet, it is not
necessary to return the GSU 73 to Garmin for this update. Otherwise maintenance of the GSU 73 is ‘on
condition’ only.
Page 4-8
Revision A
G3X Installation Manual – GSU 73
190-01115-01
5
GTP 59
Figure 5-1. GTP 59
5.1
Equipment Description
The Garmin GTP 59 is an outside mounted temperature probe that provides raw air temperature data. The
temperature input device is a three-wire temperature probe interface. OAT Power Out and OAT High are
connected internally at the OAT probe. The GTP 59 is a Resistive Temperature Device (RTD).
5.1.1 Available Equipment
The GTP 59 is available per the following part number.
Table 5-1. GTP 59 Part Number
Item
Garmin Part Number
GTP 59 OAT Probe Kit
011-00978-00*
*Included in G3X LRU (K10-00016-00)
5.2
Installation Requirements
Table 5-2 contains a list of items found in the GTP 59 Outside Air Temperature (OAT) Probe kit
(011-00978-00). The GTP 59 probe has an attached pigtail.
Table 5-2. GTP 59 Outside Air Temperature Kit*
Item
Garmin P/N
Quantity
Nut, 5/16”, Hex, Skirt
210-00055-00
1
Screw, 4-40 x .250, PHP, SS/P, w/NYL
211-60234-08
2
Washer, Lock, Self-Sealing, 5/16
212-00026-00
1
Contact, Pin, Mil Crimp, Size 22D
336-00021-00
5
GTP 59 OAT Probe
494-00022-xx
1
*Included in G3X LRU Kit (K10-00016-00)
G3X Installation Manual – GTP 59
190-01115-01
Page 5-1
Revision A
5.2.1 Additional Equipment Required
•
5.3
Cables - The installer will supply all system cables.
TSO/ETSO Compliance
The following table provides a list of applicable TSO/ETSOs for the GTP 59.
Table 5-3. Applicable TSO/ETSOs for the GTP 59
Function
TSO/ETSO
Applicable LRU
SW Part Numbers
Applicable CLD
Part Numbers
Air Data Computer
TSO-C106
ETSO-C106
Not Applicable
Not Applicable
5.3.1 TSO/ETSO Deviations
The following deviations have been requested and granted for the GTP 59.
Table 5-4. TSO/ETSO Deviations for the GTP 59
TSO/ETSO
TSO-C106
ETSO-C106
Page 5-2
Revision A
Deviation
1. Garmin was granted a deviation from TSO-C106 to use RTCA DO-160D,
including changes 1, 2, and 3, instead of RTCA DO-160B as the standard for
Environmental Conditions and Test Procedures for Airborne Equipment.
2. Garmin was granted a deviation from TSO-C106 to use Society of Automotive
Engineers (SAE) AS 8002 Rev A instead of SAE AS 8002 as the Minimum
Performance Standard.
1. Garmin was granted a deviation from ETSO-C106 to use Society of
Automotive Engineers (SAE) AS 8002 Rev A instead of SAE AS 8002 as the
Minimum Performance Standard.
G3X Installation Manual – GTP 59
190-01115-01
5.4
Installation Considerations
5.4.1 GTP 59 Icing
The GTP 59 OAT probe has no icing protection. If ice accumulates on the GTP 59 OAT probe, its
accuracy is unknown. Consequently, air temperature measurements may be incorrect if ice accumulates
on the probe. Furthermore, computations dependent upon air temperature measurements may be affected
(e.g. true airspeed and delta-ISA).
5.4.2 GTP 59 OAT Probe Installation
NOTE
The following instructions are general guidance.
NOTE
Do not mount the GTP 59 where aircraft exhaust gases will flow over it.
Table 5-5 contains a list of parts needed for the GTP 59 installation and interconnect harness. Reference
numbers in the table and instructions refer to item bubble numbers shown in Figure C-4.1.
Table 5-5. Parts Needed for GTP 59 Installation
Figure C-4.1
Description
1
2
3
4
5
Ring Terminal
3-Conductor Cable
OAT Sensor
Nut
Washer
Qty. Included
GPN
1
494-00022-xx
1
1
210-00055-00
212-00026-00
1. Prepare the surface. The metal body of the OAT probe should be grounded to the aircraft. The
installation requirements vary depending on the airframe material composition.
a. Aluminum airframe: When a mounting location has been found, prepare the inside surface of
the aircraft. Remove all paint from the contacting area and clean with a degreaser.
b. Composite airframe: If possible, mount the OAT probe through a grounded metal strap or
band. Otherwise, mount the OAT probe in an area of the airframe that has a significant
amount of underlying metal foil or mesh. To ensure adequate conductivity, it may be
necessary to mount the OAT probe through a metal doubler. Use fasteners that allow a
conductive path to the airframe.
2. Mount the OAT probe on the prepared surface. Place the ring terminal (2) over the end of the
OAT probe (4). Insert the probe and ring terminal into the hole in the skin of the aircraft. Place
the washer (6) over the end of the OAT probe on the outside skin of the aircraft. Thread the nut
(5) onto the OAT probe. Holding the OAT probe on the inside, tighten the nut (5) to 100 inchlbs. ±20 inch-lbs.
3. Route the OAT probe cable (3) to the GSU 73.
4. Cut the OAT Probe cable (3) to the required length. Strip back 2.0” to 3.5” of jacket while
retaining the shield on the OAT Probe cable (3). Trim away enough to leave 0.5” of shield
exposed.
G3X Installation Manual – GTP 59
190-01115-01
Page 5-3
Revision A
5. Strip back 1/8” (0.125”) of insulation and crimp pins (11) to each of the conductors in the
shielded cable.
6. Cut an AWG #16 (8) wire to 3” long. Strip back 0.5” of insulation from this cable. Connect the
shield of the OAT Probe cable (3) to the AWG #16 wire (8).
7. Attach the ring terminal (9) to the backshell, using the screw provided in the OAT Probe Kit (10)
and one of the tapped holes on the backshell termination area.
8. Insert newly crimped pins into the D-Sub connector and wires (3, 11) into the appropriate
connector housing location (12, 7) as specified by the installation wiring diagrams.
9. Verify that all necessary pins for the GSU 73 have been attached to the cables and snapped into
the proper slots of the 78 pin D-Sub connector.
10. Wrap the cable bundle with Silicone Fusion Tape (GPN: 249-00114-00 or a similar) at the point
where the backshell strain relief and cast housing contact the cable bundle. The smooth side of
the backshell strain relief should contact the tape.
5.5
Unit Installation
Refer to Figure C-4.1 GTP 59 O.A.T. Probe Wiring Detail for wiring and mounting instructions.
5.6
Maintenance
Maintenance of the GTP 59 is “on condition” only. Periodic maintenance of the GTP 59 is not
required.
Page 5-4
Revision A
G3X Installation Manual – GTP 59
190-01115-01
6
Garmin GPS/XM Antennas
For non-Garmin antennas, follow the manufacturer’s installation instructions. If using a Garmin GA 26C
or GA 26XM, refer to the accompanying installation instructions (190-00082-00 or 190-00522-03). For
GA 55/55A, or GA 56 or GA 57X antennas, refer to this section and the drawings in Appendix C.
Garmin recommends the antennas shown in Tables 6-1 and 6-3. However, any equivalent GPS or XM
antenna that meets the specifications listed in Tables 6-2 and 6-4 should work with the G3X.
6.1
GPS Antennas
Table 6-1. GPS Antennas
Model
Part
Number
Description
Weight
GA 26C
011-00149-04
GPS Antenna
NA
GA 56
011-00134-00
GPS Antenna
0.24 lbs (0.11 kg)
GA 57X
011-01032-10
GPS/XM Antenna
0.47 lbs (0.21 kg)
Mounting Configuration
Flange, Magnetic, or Suction
Cup Mount (for in-cabin
mounting)
Stud mount (Tear-drop form
factor)
Thru-mount (ARINC 743 style
mount)
Table 6-2. GPS Antenna Minimum Requirements
Characteristics
Specifications
Frequency Range
Gain
Noise Figure
Nominal Output Impedance
Supply Voltage
Supply Current
Output Connector
1565 to 1585 MHz
16 to 25 dB typical, 40dB max.
<4.00 dB
50 ohms
4.5 to 5.5 VDC
up to 50 mA
BNC
6.2 XM Antennas
Table 6-3. XM Antennas
Model
Part
Number
Description
Weight
XM Antenna
NA
GA 26XM 013-00268-10
GA 55
011-01033-00
XM Antenna
0.25 lbs (0.11 kg)
GA 55A
011-01153-00
XM Antenna
0.43 lbs (0.20 kg)
GA 57X
011-01032-10
GPS/XM Antenna
0.47 lbs (0.21 kg)
G3X Installation Manual – Antennas
190-01115-01
Mounting Configuration
Flange, Magnetic, or Suction
Cup Mount (for in-cabin
mounting)
Stud mount (Tear-drop form
factor)
Thru-mount (ARINC 743 style
mount)
Thru-mount (ARINC 743 style
mount)
Page 6-1
Revision A
Table 6-4. XM Satellite Radio Antenna Minimum Requirements
Characteristics
Frequency Range
Gain (Typical)
Noise Figure
Nominal Output Impedance
Supply Voltage
Supply Current (maximum)
Operating Temperature Gain
Specifications
2332.5 to 2345 MHz
24 dB*
<1.2 dB
50 ohms
3.6 to 5.5 VDC
55 mA
-50 to +85°C
*For each 1 dB gain over 24 dB, add 1 dB of attenuation into the antenna cable path
between the antenna and the GDU 375.
It is the installer’s responsibility to ensure that their choice of antenna meets FAA standards according to
the specific installation. This installation manual discusses only the antennas listed in Tables 6-1 and 6-3.
Other antennas may be acceptable but their installation is not covered by this manual.
There are several critical factors to take into consideration before installing an antenna for a satellite
communications system. These factors are addressed in the following sections.
6.3 Antenna Mounting Considerations
The information in this section does not pertain to in-cabin (internal) mounted antennas such as the
GA 26C, refer to the accompanying installation instructions (190-00082-00).
No special precautions need be taken to provide a bonding path between the GPS Antenna and the aircraft
structure.
6.3.1
VHF COM/GPS Interference
On some installation VHF COM transceivers, Emergency Locator Transmitter (ELT) antennas, and
Direction Finder (DF) receiver antennas can re-radiate through the GPS antenna. The GDU 37X does not
interfere with its own GPS receiver. However, placement of the GPS antenna relative to a COM
transceiver and COM antenna, ELT antenna, and DF receiver antenna is critical.
Use the following guidelines, in addition to others in this document, when locating the GDU 37X and its
antennas.
• GPS Antenna—Locate as far as possible from all COM antennas and all COM transceivers,
ELT antennas, and DF antennas. The GPS antenna is less susceptible to harmonic interference
if a 1.57542 GHz notch filter is installed on the COM transceiver antenna output.
• Locate the GDU 37X as far as possible from all COM antennas.
If a COM antenna is found to be the problem, a 1.57542 GHz notch filter (Garmin P/N 330-00067-00)
may be installed in the VHF COM coax, as close to the COM as possible.
If a COM is found to be radiating, the following can be done:
1. Replace or clean the VHF COM rack connector to ensure good coax ground.
2. Place grounding straps between the GDU 37X unit, VHF COM and a good ground.
3. Shield the VHF COM wiring harness.
Page 6-2
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G3X Installation Manual – Antennas
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6.3.2
GPS/XM Antenna Mounting Location
The GPS antenna is a key element in the overall system performance and integrity for a GPS navigation
system. The mounting location, geometry, and surroundings of the antenna can affect the system
performance and/or availability. The following guidance provides information to aid the installer in
ensuring that the optimum location is selected for the installation of the GPS antenna. The installation
guidelines presented here meet the intent of AC 20-138A section 16. The greater the variance from these
guidelines, the greater the chance of decreased availability. Because meeting all of these installations
guidelines may not be possible on all aircraft, these guidelines are listed in order of importance to achieve
optimum performance. Items 1-4 below are of equal importance and their significance may depend on
the aircraft installation. The installer should use their best judgment to balance the installation guidelines.
1.
2.
3.
4a.
Mount the antenna on top of the aircraft in a location with an unobstructed view of the
sky, as close to level as possible with respect to the normal cruise flight attitude of the
aircraft. If the normal flight attitude is not known, substitute the waterline, which is
typically referenced as level while performing a weight and balance check.
The GPS antenna should be mounted in a location to minimize the effects of airframe
shadowing during typical maneuvers. Typically mounting farther away from the tail
section reduces signal blockage seen by the GPS antenna.
The GPS antenna should ideally be located at the opposite end of the aircraft from the
COM unit in order to make the GPS less vulnerable to harmonics radiated from the COM
itself (see Section 1.7.3 for more GPS/COM interference information).
The GPS antenna should be mounted no closer than two feet (edge to edge) and ideally
three feet from any VHF COM antenna or any other antenna which may emit harmonic
(or other) interference at the L1 frequency of 1575.42 MHz. An aircraft EMC check
(reference VHF COM interference check in Post Installation Checkout procedures) can
verify the degradation of GPS in the presence of interference signals. If an EMC check
reveals unacceptable interference, insert a GPS notch filter in line with the offending
VHF COM or the (re-radiating) ELT transmitter.
NOTE
4b.
4c.
5.
6.
The separation requirement does not apply to GPS and COM combination antennas,
provided the antenna has been tested to meet Garmin’s minimum performance standards.
The separating requirement includes the combination with an XM antenna element as
well.
The GPS antenna should be mounted no closer than two feet (edge to edge) and ideally
three feet from any antennas emitting more than 25 watts of power. An aircraft EMC
check can verify the degradation of GPS in the presence of interference signals.
To minimize the effects of shadowing at 5° elevation angles, the GPS antenna should be
mounted no closer than 6 inches (edge to edge) from other antennas, including passive
antennas such as another GPS antenna or XM antenna.
To maintain a constant gain pattern and limit degradation by the windscreen, avoid
mounting the antenna closer than 3 inches from the windscreen.
For multiple GPS installations, the antennas should not be mounted in a straight line from
the front to the rear of the fuselage. Also varying the mounting location will help
minimize any aircraft shading by the wings or tail section (in a particular azimuth, when
one antenna is blocked the other antenna may have a clear view).
G3X Installation Manual – Antennas
190-01115-01
Page 6-3
Revision A
Figure 6-1 shows the recommended placement of antennas.
4
Figure 6-1. Recommended Antenna Placement
Page 6-4
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G3X Installation Manual – Antennas
190-01115-01
6.3.3
Buried Antenna (below the skin covering or glareshield) Mounting
There are potential performance issues related to buried antennas that the kit builder/installer should be
aware of prior to electing to install a buried antenna. See also Section 6.6.3, Non-structural Installation to
Glareshield.
•
•
•
Some gain of the antenna may be lost as the signal needs to penetrate through the skin of the
aircraft. The loss may not be apparent, but under the some of the worst case signal scenarios
signal availability may be affected.
The materials in some aircraft are not suitable for GPS signals to penetrate, care should be taken
to properly modify the aircraft structure to accommodate this. Modifications of this sort are not
recommended or inferred by Garmin or the installation of the G3X, and the installer should seek
the guidance of the kit manufacture for such modifications.
XM – FIS antennas may typically be buried without performance impact if the overlying material
is fairly transparent to the satellite signal.
Figure 6-2 shows example areas of some mounting locations which have been used. Low satellite
reception and tracking are compromised in these installations due to fuselage and tail blockage. It is not
possible to determine the full impact of these locations, however initial flight testing has not shown any
significant impact to GPS signal availability, your results may vary.
Figure 6-2. Carbon/Glass Buried Antenna Area
G3X Installation Manual – Antennas
190-01115-01
Page 6-5
Revision A
Mounting the antenna under the glare shield (Figure 6-3) is a good option for XM – FIS antennas,
although it is not typically the best option for a GPS antenna. This location results in the aft fuselage
shading the antenna.
Figure 6-3. Glare Shield Buried Antenna Area
NOTE
Due to the excessive temperature environment and large areas of signal blockage caused
by the fuselage, mounting the antenna under the engine cowling (forward of the firewall)
is not recommended and likely will not provide adequate GPS reception.
6.3.4 Antenna Doubler/Backing Plate
The antenna installation must provide adequate support for the antenna considering a maximum drag load
of 5 lbs. (at subsonic speed). When penetrating the skin with a large hole (i.e. for the coax connector) a
doubler plate is required to re-instate the integrity of the aircraft skin. Never weaken the aircraft structure
when choosing a mounting area. Make use of any available reinforcements where appropriate.
6.3.5 Antenna Grounding Plane
Although no ground plane is required, the antennas typically perform better when a ground plane is used.
The ground plane should be a conductive surface as large as practical, with a minimum diameter of 8
inches. To use an antenna in aircraft with fabric or composite skin, a ground plane is recommended. It is
usually installed under the skin of the aircraft, below the antenna, and is made of either aluminum sheet or
of wire mesh.
6.3.6 Antenna Grounding
The antenna is grounded through the mounting hardware and the coax connection. The mounting
hardware (washers and nuts) and doubler plate should make contact with an unpainted grounded surface
ensuring proper antenna grounding. It is important to have good conductivity between the coaxial shield
and the ground plane. The bottom of the antenna does not need to make contact with the ground plane
(i.e. the surface may be painted). The antenna will capacitively couple to the ground plane beneath the
paint or aircraft cover.
Page 6-6
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G3X Installation Manual – Antennas
190-01115-01
6.4 Teardrop Footprint Antenna Installation (GA 55 and GA 56)
This section describes the structural mounting of the teardrop footprint antenna installation.
An acceptable installation method is to use Garmin P/N: 115-00846-10 doubler plate with the GA 55 or
GA 56 stud mount antennas. Another acceptable method is to fabricate and install one of three doublers
(Figure 6-4, Figure 6-5, and Figure 6-6), depending on the thickness of the skin. The three doubler
designs vary only by number of rivets and hole preparation for installation with flush rivets. Table 6-5
provides a summary of design and installation details for selecting the appropriate antenna
doubler/backplate.
Figure 6-7 shows an example of the doubler installed between stringers on the top fuselage skin, just off
centerline. The location should be flat, with no gaps between the skin and doubler, to keep from
deforming the skin during installation.
Table 6-5. Teardrop Footprint Antenna Doubler Design and Installation
Aircraft Skin Thickness
0.032” to 0.049”
0.049” to 0.051”
0.051” to 0.063”
Doubler Design (Figure)
Figure 6-4
Figure 6-5
Figure 6-6
12
16
16
MS20426AD4-x
MS20426AD4-x
MS20426AD4-x
Dimple
Dimple
Countersink
Countersink
Countersink
None
Skin Cutout Detail (Figure)
Figure 6-8
Figure 6-9
Figure 6-10
Doubler Installation (Figure)
Figure 6-11
Figure 6-12
Figure 6-13
Number of Rivets Required
Type of Rivets Required
1
Skin Preparation for Rivets
Doubler Preparation for Rivets
Notes:
1.
Rivet length determined at installation, dependent on thickness of material (rivet length = grip length +
1.5*rivet diameter)
Refer to Figure B-2.X for Garmin Antenna installation drawings.
6.4.1 Preparation of Doubler
1. Use Garmin P/N: 115-00846-10, or refer to Table 6-5 for guidance on selecting the appropriate
doubler drawing based on the thickness of skin at the antenna location. Make the doubler from
2024-T3 Aluminum (AMS-QQ-A-250/5), 0.063” sheet thickness.
2. For installation in aircraft skins of thickness less than 0.051”, countersink the rivet holes in the
doubler for use with flush head rivets (MS20426AD4-x).
3. When using Garmin P/N: 115-00846-10 doubler, sixteen rivet holes exist in the part. For
installation of Garmin P/N: 115-00846-10 in skins of thickness between 0.032” and 0.049”, only
the rivets identified for use through the skin cutout detail (Figure 6-8) and doubler installation
(Figure 6-11) are required.
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Page 6-7
Revision A
6.4.2 Antenna Installation Instructions
1. Refer to Table 6-5 and the drawings in Appendix C for guidance on selecting the appropriate
mounting cutout. Drill or punch the holes to match the mating part (doubler).
2. Install a doubler plate to reinforce the aircraft skin, as required. Refer to Section 6.4.1 for doubler
preparation and Table 6-5 for additional guidance on the doubler installation. Dimple aircraft
skin when the skin thickness is less than 0.051” for installation of flush head rivets. Countersink
aircraft skin when the skin thickness is between 0.051” and 0.063” for installation of flush head
rivets.
3. For the stud mount teardrop footprint antenna, place install gasket on top of aircraft skin using the
four screw holes to align the gasket.
4. Washers and locking nuts are required to secure the antenna. Torque the four #8-32 stainless
steel locking nuts 12-15 in-lbs. Torque should be applied evenly across all mounting studs or
screws to avoid deformation of the mounting area.
5. Ensure that the antenna base and aircraft skin are in continuous contact with the gasket or o-ring,
as appropriate to the antenna model.
6. Seal the antenna and gasket to the fuselage using Dow Corning 738 Electrical Sealant or
equivalent. Run a bead of the sealant along the edge of the antenna where it meets the exterior
aircraft skin. Use caution to ensure that the antenna connectors are not contaminated with
sealant.
CAUTION
Do not use construction grade RTV sealant or sealants containing acetic acid. These sealants may
damage the electrical connections to the antenna. Use of these type sealants may void the
antenna warranty.
Page 6-8
Revision A
G3X Installation Manual – Antennas
190-01115-01
6.4.3 Reference Figures
Figure 6-4. Doubler Design, Teardrop Footprint Antenna, Skin Thickness
0.032" to 0.049"
Figure 6-5. Doubler Design, Teardrop Footprint Antenna, Skin Thickness
0.049" to 0.051"
G3X Installation Manual – Antennas
190-01115-01
Page 6-9
Revision A
Figure 6-6. Doubler Design, Teardrop Footprint Antenna, Skin Thickness
0.051" to 0.063"
Figure 6-7. Sample Doubler Location, Teardrop Footprint Antenna, Metal Skin Aircraft
Page 6-10
Revision A
G3X Installation Manual – Antennas
190-01115-01
Figure 6-8. Skin Cutout Detail, Teardrop Footprint Antenna, Skin Thickness
0.032" to 0.049"
Figure 6-9. Skin Cutout Detail, Teardrop Footprint Antenna, Skin Thickness
0.049" to 0.051"
G3X Installation Manual – Antennas
190-01115-01
Page 6-11
Revision A
Figure 6-10. Skin Cutout Detail, Teardrop Footprint Antenna, Skin Thickness
0.051" to 0.063"
Figure 6-11. Doubler Installation, Teardrop Footprint Antenna, Skin Thickness
0.032" to 0.049"
Page 6-12
Revision A
G3X Installation Manual – Antennas
190-01115-01
Figure 6-12. Doubler Installation, Teardrop Footprint Antenna, Skin Thickness
0.049" to 0.051"
Figure 6-13. Doubler Installation, Teardrop Footprint Antenna, Skin Thickness
0.051" to 0.063"
G3X Installation Manual – Antennas
190-01115-01
Page 6-13
Revision A
6.5 ARINC 743 Footprint Antenna Installation (GA 55A, GA 57X)
This section describes the structural mounting of the ARINC 743 footprint antenna (GA 55A, GA 57X)
installation. One acceptable method is to use Garmin P/N: 115-00846-00 doubler plate. Another
acceptable method is to fabricate and install one of three doublers, Figure 6-14, Figure 6-15, or Figure 616, depending on the thickness of the skin. The three doubler designs vary only by number of rivets and
hole preparation for installation with flush rivets. Figure 6-24 shows installation of the ARINC 743
footprint antenna.
Table 6-6 provides a summary of design and installation details for the antenna doubler. Figure 6-17
shows an example of the doubler installed between stringers on the top fuselage skin, just off centerline.
The location should be flat, with no gaps between the skin and doubler, to keep from deforming the skin
during installation.
Table 6-6. ARINC 743 Footprint Antenna Doubler Design and Installation
Skin Thickness
0.032” to 0.049”
0.049” to 0.051”
0.051” to 0.063”
Figure 6-14
Figure 6-15
Figure 6-16
12
16
16
MS20426AD4-x
MS20426AD4-x
MS20426AD4-x
Dimple
Dimple
Countersink
Doubler Preparation for Rivets
Countersink
Countersink
None
Skin Cutout Detail (GA 55A)
Figure 6-18
Figure 6-19
Figure 6-20
Doubler Installation (Figure)
Figure 6-21
Figure 6-22
Figure 6-23
Doubler Design (Figure)
Number of Rivets Required
Type of Rivets Required
1
Skin Preparation for Rivets
Notes:
1.
Rivet length determined at installation, dependent on thickness of material (rivet length = grip length +
1.5*rivet diameter)
6.5.1 Preparation of Doubler
1. Use Garmin P/N: 115-00846-00, or refer to Table 6-6 for guidance on selecting the appropriate
doubler drawing based on the thickness of skin at the antenna location. Make the doubler from
2024-T3 Aluminum (AMS-QQ-A-250/5), 0.063” sheet thickness.
2. For installation in aircraft skins of thickness less than 0.051”, countersink the rivet holes in the
doubler for use with flush head rivets (MS20426AD4-x).
3. When using Garmin P/N: 115-00846-00 doubler, sixteen rivet holes exist in the part. For
installation of Garmin P/N: 115-00846-00 in skins of thickness between 0.032” and 0.049”, only
the rivets identified for use through the skin cutout detail (Figure 6-18) and doubler installation
(Figure 6-21) are required.
Page 6-14
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G3X Installation Manual – Antennas
190-01115-01
6.5.2 Antenna Installation Instructions
1. Refer to Table 6-6 (and to Figures in Appendix C) for guidance on selecting the appropriate
mounting cutout. Drill or punch the holes to match the mating part (doubler).
2. Install a doubler plate to reinforce the aircraft skin, as required. Refer to Section 6.5.1 for doubler
preparation and Table 6-6 for additional guidance on the doubler installation. Dimple aircraft
skin when the skin thickness is less than 0.051” for installation of flush head rivets. Countersink
aircraft skin when the skin thickness is between 0.051” and 0.063” for installation of flush head
rivets.
3. Place the install gasket on top of aircraft skin using the four screw holes to align the gasket.
4. Locking nuts are required to secure the antenna (locking nuts installed on doubler). Torque the
four supplied #10-32 stainless steel screws (Garmin P/N: 211-60212-20, MS51958-67, or
equivalent) 20-25 in-lbs. Torque should be applied evenly across all mounting studs to avoid
deformation of the mounting area.
5. Ensure that the antenna base and aircraft skin are in continuous contact with the gasket.
6. Seal the antenna and gasket to the fuselage using Dow Corning 738 Electrical Sealant or
equivalent. Run a bead of the sealant along the edge of the antenna where it meets the exterior
aircraft skin. Use caution to ensure that the antenna connectors are not contaminated with
sealant.
CAUTION
Do not use construction grade RTV sealant or sealants containing acetic acid. These
sealants may damage the electrical connections to the antenna. Use of these type sealants
may void the antenna warranty.
G3X Installation Manual – Antennas
190-01115-01
Page 6-15
Revision A
6.5.3 Reference Figures
Figure 6-14. Doubler Design, ARINC 743 Footprint Antenna,
Skin Thickness 0.032" to 0.049"
Page 6-16
Revision A
G3X Installation Manual – Antennas
190-01115-01
Figure 6-15. Doubler Design, ARINC 743 Footprint Antenna,
Skin Thickness 0.049" to 0.051"
G3X Installation Manual – Antennas
190-01115-01
Page 6-17
Revision A
Figure 6-16. Doubler Design, ARINC 743 Footprint Antenna,
Skin Thickness 0.051" to 0.063"
Page 6-18
Revision A
G3X Installation Manual – Antennas
190-01115-01
Figure 6-17. Sample Doubler Location, ARINC 743 Antenna, Metal Skin Aircraft
Figure 6-18. Skin Cutout Detail, ARINC 743 Footprint Antenna, Skin Thickness
0.032" to 0.049"
G3X Installation Manual – Antennas
190-01115-01
Page 6-19
Revision A
Figure 6-19. Skin Cutout Detail, ARINC 743 Footprint Antenna, Skin Thickness
0.049" to 0.051"
Figure 6-20. Skin Cutout Detail, ARINC 743 Footprint Antenna, Skin Thickness 0.051" to
0.063"
Page 6-20
Revision A
G3X Installation Manual – Antennas
190-01115-01
Figure 6-21. Doubler Installation, ARINC 743 Footprint Antenna, Skin
Thickness 0.032" to 0.049"
Figure 6-22. Doubler Installation, ARINC 743 Footprint Antenna, Skin
Thickness 0.049" to 0.051"
G3X Installation Manual – Antennas
190-01115-01
Page 6-21
Revision A
Figure 6-23. Doubler Installation, ARINC 743 Footprint, Skin Thickness 0.051" to 0.063"
Figure 6-24. Installation of ARINC 743 Footprint Antenna
Page 6-22
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G3X Installation Manual – Antennas
190-01115-01
6.6
Non-Structural Mount Installation
This section provides installation examples and considerations for non-structural mounting of teardrop
and ARINC 743 footprint antennas. Typical installations may be below a non-metallic glareshield, under
the composite or fabric skin, or on an external, non-structural surface. Other non-structural installations
may exist, but are not presented in this manual.
6.6.1 Generic Non-structural Antenna Installation
Figure 6-25 shows the generic non-structural installation for the ARINC 743 footprint (GA55A/GA 57X)
antenna. The teardrop footprint antennas (GA55, GA56 stud mount) can also be installed in this manner.
For mounting the teardrop style antenna (GA 55 or GA56), a doubler plate similar to Figure 6-4 or P/N
115-00846-10 can be used with the mounting surface to support the antenna. Rivets used to secure the
doubler plate to the mounting surface are optional in a non-structural installation. Screws, washers, and
locking nuts as shown in Appendix C are required to secure the Teardrop style antenna to the mounting
surface. Torque the locking nuts to 12-15 in-lbs, torque should be applied evenly across all mounting
studs.
A doubler plate similar to Figure 6-14, or P/N 115-00846-00 (ARINC 743 style) can be used with the
mounting surface to support the antenna. Rivets used to secure the doubler plate to the mounting surface
are optional in a non-structural installation. Locking nuts are required to secure the ARINC 743 antenna
(locking nuts installed on doubler). Torque the four supplied #10-32 stainless steel screws (Garmin P/N:
211-60212-20, MS51958-67, or equivalent) evenly across all mounting screws.
Figure 6-25. Generic Non-structural ARINC 743 Footprint Antenna Installation
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190-01115-01
Page 6-23
Revision A
6.6.2 Considerations for Non-Structural Mounting
External mounting of the antenna is preferred, although the antenna can be mounted inside the aircraft.
When mounted internally, the antenna does not have to be aligned with the aircraft forward direction, but
should be equal to the aircraft typical cruise attitude.
There should be a solid mechanical base in the mounting area for the antenna, and existing surfaces or
brackets may be used with the doubler plate. Alternately, non-structural brackets may be fabricated in the
field as necessary to mount the antenna. Brackets should be made of minimum 0.032” thickness
aluminum and should span as short a distance as possible.
Some fabric aircraft include aluminum paste in the fabric finishing process, often referred to as “silver
coats”. Presence of thick fabric and/or heavy “silver coats” may degrade the signal strength of the
antenna.
6.6.3 Non-structural Installation to Glareshield
Figure 6-26 shows an example of a bracket created to support an antenna mounted on the underside of the
glare shield. Figure 6-27 shows the non-structural mounting of the antenna under the glareshield, with the
bracket assembly shown in Figure 6-26.
Figure 6-26. Example Bracket Antenna Mounting Under Glareshield
Page 6-24
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G3X Installation Manual – Antennas
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Figure 6-27. Example Non-structural Antenna Mounting Under Glareshield
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190-01115-01
Page 6-25
Revision A
6.6.4 Non-structural Installation to Airframe
Internal Non-structural Installation
Figure 6-28 and Figure 6-29 show examples of under the fabric skin non-structural mounting of the
antenna to the airframe of a tube-and-fabric aircraft.
In Figure 6-28, a bracket is made to attach to the airframe, just under the fabric for a teardrop antenna
installation. The doubler plate and mounting hardware described in the generic installation (Section
6.6.1) are used with the bracket as the antenna mounting surface. In Figure 6-29, a similar case is shown
using the generic installation of the ARINC 743 footprint antenna. The doubler plate is optional for this
type of installation with either the Teardrop or the ARINC 743 antenna.
Figure 6-28. Example Teardrop Antenna Installation In Airframe Under Fabric Skin
Figure 6-29. Example ARINC 743 Footprint In Airframe Under Fabric Skin
Page 6-26
Revision A
G3X Installation Manual – Antennas
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External Non-structural Installation
Figure 6-30 is an example of an external, non-structural mounting of the antenna in a tube-and-fabric
aircraft. The antenna support bracket shown should be made of 2024-T3 Aluminum with a minimum
material thickness 0.032” and maximum distance between airframe tubes of 36”. The bracket is installed
to the airframe under the fabric, and the antenna is mounted externally to the bracket. The generic
installation of the (Section 6.6.1) antenna is used, with the antenna support bracket as the mounting
surface. Follow the applicable gasketing and sealant instructions in Section 6.4.2 (Teardrop style) or
Section 6.5.2 (ARINC 743 style).
Figure 6-30. Example Non-structural Antenna Mounting On Airframe
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Page 6-27
Revision A
Minimum Distance from Metal Tube Structure Requirements
Figure 6-31 shows minimum distance from metal tube structure requirements for internal, non-structural
mounting of the antenna. Table 6-7 presents minimum distance requirements between the tube structure
and the antenna for cases where the antenna sits underneath the fabric in a metal-tube structure aircraft.
Figure 6-31 illustrates the tube diameter (d) and minimum distance (l) references in the table.
Figure 6-31. Example Teardrop Footprint Antenna Mounting Under Fabric Skin
Table 6-7. Minimum Distance Required Between Tube Structure and Antenna
Illustrated Case
Top of antenna at or above the center of
the tube structure (Figure 6-31, top)
Top of antenna between the center and
bottom of the tube structure
(Figure 6-31, bottom)
Page 6-28
Revision A
Tube Diameter
d (in)
0.625
0.75
1.00
1.25
0.625
0.75
1.00
1.25
Minimum Distance
l (in)
3.6
4.3
5.7
7.2
7.2
8.6
11.5
14.3
G3X Installation Manual – Antennas
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7
7.1
Software, Configuration, Databases, and XM Activation
Configuration Mode
Some software loading and all configuration settings are performed in the configuration mode. To enter
configuration mode, hold down the left-hand softkey (softkey #1) while powering on the GDU 37X. If
more than one GDU 37X is installed, hold down softkey #1 on PFD1.
7.2
Software/Audio Data Identification
7.2.1 LRU Software Version Identification
Do the following steps to verify the unit’s current software version(s):
1. Turn on the unit in configuration mode.
2. Use the FMS Joystick to select the CONFIG MAIN page (if needed).
3. Note the displayed software version.
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7.2.2 Audio Data Identification
Do the following steps to view the unit’s current audio data information:
1. Turn on the unit in normal mode.
2. Press the MENU key twice to display the Main Menu
3. Use the FMS Joystick to select Database Information
4. Press the ENT key to display the Database Information page.
5. Use the FMS Joystick to scroll down as needed to display the audio database information.
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7.3
Software Loading Procedure
Software loading is performed in normal mode. Sections 7.3.1 and 7.3.2 describe the GDU and GSU
software load procedure.
7.3.1 GDU Software Loading Procedure
1. Power on the GDU in normal mode, then insert the properly formatted SD card into the SD
card slot.
NOTE
It is also acceptable to insert the SD card before powering on the unit.
2. A software update pop-up will appear on the screen, highlight YES and press the ENT key to
begin the update.
NOTE
If the below software update pop-up does not appear, select the Database Information
Menu to update the software.
3. The unit will reboot, then GDU software update will begin automatically.
4. Ensure power is not removed while the update is being performed
5. The unit will reboot after the update is complete.
7.3.2 GSU Software Loading Procedure
1. Power on the GDU in configuration mode.
2. Use the FMS Joystick to select the GSU Page.
3. Press the UPDATE SW softkey, then press the ENT Key to begin the update.
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7.4
Configuration Pages
7.4.1 Main Configuration Page
The Main Configuration Page is used to display LRU (device) specific information such as Unit and
System ID’s and Database information for the various databases used by the G3X. This page has no userselectable options.
1. In configuration mode, use the FMS Joystick to select and view the MAIN Page.
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7.4.2 ACFT Configuration Page
The Aircraft Configuration Page allows setting the parameters for Flight Planning, Aircraft Identifier, and
Map Symbol. The aircraft’s cruise speed, fuel flow, aircraft identifier, and map symbol can be entered on
this page.
The flight planning fields let you adjust the default values (cruise speed and fuel flow) used for flight
planning calculations.
Aircraft Identifier–The aircraft identifier can be entered using the FMS Joystick.
Map Symbol– The aircraft symbol that is displayed on the Map page can be selected.
1. In configuration mode, use the FMS Joystick to select the ACFT Page.
2. Use the FMS Joystick to select the desired configurable item and make the desired change.
Then press the ENT Key or use the FMS Joystick to select the next item. Press the FMS
Joystick to move the cursor to the page selection menu when finished.
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7.4.3 W/B (Weight/Balance) Configuration Page
The W/B Configuration Page allows setting the weight and balance parameters for the airplane, these
parameters are then used on the Main Menu W/B Page in normal mode. Weight/Balance may be used
during pre-flight preparations to verify the weight and balance conditions of the aircraft. By entering the
weight and arm values into the Aircraft window, the GDU 37X can calculate the total weight, moment,
and center of gravity (CG).
Before entering the various figures, the empty weight of the airplane and the arm (or “station”) for each
weight should be determined. These figures should be determined using the pilot’s operating handbook
for the airplane, which also notes the weight limitations and fore/aft CG limits. Compare those figures to
the values calculated by the GDU 37X.
Each station listed in the Station window has an editable name and arm location. This allows the setting
of the units of measure used for that station (weight, or units of avgas or jet fuel). An optional maximum
value can be set for a particular station (e.g. a fuel tank might have a max capacity of 50 gallons) or the
max can be set to zero so that no maximum will be imposed.
The LOADING LIMITS window contains fields for the entry of minimum and maximum aircraft weight,
and the minimum and maximum CG location.
1. In configuration mode, use the FMS Joystick to select the W/B Page.
2. Use the FMS Joystick to select the desired configurable item and make the desired change,
then press the ENT Key or use the FMS Joystick to select the next item.
3. To create a new station, press the NEW softkey, enter the name, units, max weight, and arm,
then highlight DONE and press the ENT key.
4. To edit or delete a station, highlight the desired station, then press the edit or delete softkey.
5. Press the FMS Joystick to move the cursor to the page selection menu when finished.
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7.4.4 UNITS Configuration Page
The Units Configuration Page allows selection of the desired displayed units for the listed items in the
Units Configuration window. The various settings for Location Format, Map Datum, and Heading can be
accessed in the Position Configuration window. See the G3X Pilot’s Guide for a description of Location
Format and Map Datum.
1. In configuration mode, use the FMS Joystick to select the UNITS Page.
2. Use the FMS Joystick to select the desired configurable item and make the desired change.
Then press the ENT Key or use the FMS Joystick to select the next item. Press the FMS
Joystick to move the cursor to the page selection menu when finished.
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7.4.5 DSPL (Display) Configuration Page
The DSPL Configuration Page allows setting the parameters for Display and Backlight Control
configuration.
1. In configuration mode, use the FMS Joystick to select the DSPL Page.
2. Use the FMS Joystick to select the desired configurable item and make the desired change.
Then press the ENT Key or use the FMS Joystick to select the next item. Press the FMS
Joystick to move the cursor to the page selection menu when finished.
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7.4.5.1 Display Configuration Window:
Backlight Intensity: Can be set to Auto or Manual (this setting is also available in normal mode on the
Display Setup page).
Auto–Sets the backlight intensity (display brightness) based on the aircraft’s instrument lighting bus
voltage.
Manual–Allows setting the display brightness by changing the Backlight Intensity (0-9) setting
found beside the ‘Manual’ setting.
Default Mode: Can be set to Auto or Manual (described above). This controls the backlight mode that
will be active each time the system is powered on.
7.4.5.2 Automatic Backlight Control Window (settings apply only to ‘Auto’
setting):
Input Voltage–Displays the current lighting bus voltage
Backlight Level–Displays the current backlight level (0-100%)
Graph–Brightness is displayed as the vertical (Y) axis, and aircraft lighting bus voltage is displayed as the
horizontal (X) axis. The graph changes according to the auto backlight control settings, and the lighting
bus voltage.
Off Threshold–Sets the lighting bus threshold voltage. At the threshold voltage, the backlighting is
turned on per the Min Brightness setting. Below the threshold voltage, the backlighting defaults to a
Backlight Level of 100% . The’ ±’ setting controls the range that the Off Threshold voltage is in effect.
Default values are 2.9V & ±0.15V.
Min Brightness (Voltage and Percentage)–Sets the lower bus voltage required to turn the backlighting on
to the percentage of brightness set by the Min % setting. Default values are 3.0V and 10%.
Max Brightness (Voltage and Percentage)–Sets the upper bus voltage required to turn the backlighting on
to the percentage of brightness set by the Max % setting. Default values are 12.0V and 100%.
Input Type–Sets the aircraft lighting bus voltage for either 12 or 24V input to match the aircraft lighting
bus voltage.
Time Constant–Adjusts the speed (in seconds), that the brightness level responds to changes in the input
voltage level.
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7.4.6 SOUND Configuration Page
The SOUND Configuration Page allows setting the parameters for various alert and message tones.
1. In configuration mode, use the FMS Joystick to select the SOUND Page.
2. Use the FMS Joystick to select the desired configurable item and make the desired change.
Then press the ENT Key or use the FMS Joystick to select the next item. Press the FMS
Joystick to move the cursor to the page selection menu when finished.
The configuration options for the SOUND Configuration Page are listed/described as follows:
Alert Volume – Controls the volume level of audio alerts (settings 1-10)
Message Tones – Controls the volume level of message tones (settings 1-10)
Terrain Audio – Enables/disables terrain awareness audio alerts
TIS Audio – Enables/disables TIS traffic audio alerts
Alert Output – If set to MONO + STEREO, alert tones and messages will be output on both the mono
and stereo outputs. If set to MONO ONLY, alert tones and messages will be output only on the mono
output.
Alert Source – If more than one GDU 37X is installed, an Alert Source field will appear on the SOUND
Configuration page. The Alert Source field allows the user to select which GDU will generate the alert
sounds. The Alert Source options are: PFD1, PFD2, MFD, or Auto (which will use whichever unit is
present, in the order PFD1, MFD, PFD2).
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7.4.7 COMM Configuration Page
The COMM Configuration Page allows setting the parameters for the communication ports.
1. In configuration mode, use the FMS Joystick to select the COMM Page.
2. Use the FMS Joystick to select the desired configurable item and make the desired change.
Then press the ENT Key or use the FMS Joystick to select the next item. Press the FMS
Joystick to move the cursor to the page selection menu when finished.
A small green dot will appear next to the name of each RS-232 port when it is receiving valid data.
The RS-232 comm port configuration options for the COMM Configuration Page are listed/described as
follows:
Garmin Data Transfer - The proprietary format used to exchange data with a PC.
NMEA Out - Supports the output of standard NMEA 0183 version 3.01 data at a baud rate of 4800.
Aviation In - The proprietary format used for input to the G3X (baud rate of 9600) from an FAA certified
Garmin panel mount unit. Allows the G3X to display a Go To or route selected on the panel mount unit,
which eliminates the need to enter the destination on both units.
Aviation In/NMEA & VHF Out - Receives aviation data and transmits out both NMEA data, at 9600
baud, and VHF frequency tuning information to a Garmin Nav/Comm radio.
TIS In - Receives TIS data from a Garmin Mode S transponder.
TIS In/NMEA & VHF Out - Receives TIS data and transmits out both NMEA data, at 9600 baud, and
VHF frequency tuning information to a Garmin Nav/Comm radio.
SL30 Nav/Comm - RS-232 format. Outputs frequency tuning and course selection data to an SL30, and
receives VOR/ILS signals to be displayed on the PFD.
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7.5
Garmin Database Updates
The GDU 37X MFD database updates can be obtained by visiting the ‘flyGarmin’ website
(www.fly.garmin.com). The ‘flyGarmin’ website requires the unit’s System ID to update databases, this
allows the databases to be encrypted with the unit’s unique System ID when copied to the SD Card. The
System ID is displayed on the System Setup Menu in normal mode, or on the Main Page in configuration
mode.
Since these databases are stored internally in each GDU, each GDU will need to be updated separately.
The SD card may be removed from the applicable GDU after installing the database(s). After the
databases have been updated, check that the appropriate databases are initialized and displayed on the
splash screen during power-up.
7.5.1 Updating Garmin Databases
Equipment required to perform the update is as follows:
• Windows-compatible PC computer (Windows 2000 or XP recommended)
• SanDisk SD Card Reader, P/Ns SDDR-93 or SDDR-99 or equivalent card reader
• Updated database obtained from the flyGarmin website
• SD Card, 2 GB recommended (Garmin recommends SanDisk® or Toshiba brand)
After the data has been copied to the SD card, perform the following steps:
1. Insert the SD card in the card slot of the GDU 37X to be updated.
2. Turn on the GDU 37X to be updated.
3. Upon turn-on, a screen appears which lists the databases on the SD card. A green checkbox
indicates that the database already installed on the G3X is up to date, an empty checkbox
indicates that the database on the SD card is more current and should be installed.
4.
The database(s) can be updated by either highlighting UPDATE ALL and pressing the ENT key;
or by using the FMS Joystick to highlight a single database and pressing the ENT Key.
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5. When the update process is complete, the screen updates the database status
6. Once the database(s) have been updated, the SD card can be removed from the unit.
7. The unit must be restarted by pressing the Restart softkey.
8. Repeat steps 1-7 for each installed GDU 37X.
7.5.2 Available Databases
Jeppesen® Aviation Data (NavData™)
The Jeppesen database contains the general aviation data (NavData) used by pilots (Airports, VORs,
NDBs, SUAs, etc.) and is updated on a 28-day cycle.
Terrain
The terrain database contains the elevation data which represents the topography of the earth. This
database is updated on an irregular basis.
Basemap
The basemap contains data for the topography and land features, such as rivers, lakes, and towns. It is
updated only periodically, with no set schedule. There is no expiration date.
Obstacle
The obstacle basemap contains data for obstacles, such as towers, that pose a potential hazard to aircraft.
Obstacles 200 feet and higher are included in the obstacle database. It is very important to note that not
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all obstacles are necessarily charted and therefore may not be contained in the obstacle database. This
database is updated on a 56-day cycle.
SafeTaxi
The SafeTaxi database contains detailed airport diagrams for selected airports. These diagrams aid in
following ground control instructions by accurately displaying the aircraft position on the map in relation
to taxiways, ramps, runways, terminals, and services. This database is updated on a 56-day cycle, and has
no expiration date.
FliteCharts
The FliteCharts database contains terminal procedure charts for the United States only. This database is
updated on a 28-day cycle. If not updated within 180 days of the expiration date, FliteCharts will no
longer be user-accessible.
AOPA Airport Directory
The AOPA Airport Directory provides data on airports and heliports throughout the U.S. and offers
detailed information for over 5,300 U. S. airports, along with the names and phone numbers of thousands
of FBOs. Look up taxi services, plan an overnight, and choose fuel stops; plus find ground transportation,
lodging, restaurants, local attractions, and more. This database is updated on a quarterly cycle, and has no
expiration date.
7.6
XM Activation Instructions (GDU 375 only)
Follow the below instructions to activate the XM receiver in the GDU 375.
Before XM Satellite Weather can be used, the service must be activated by calling XM at 1.800.985.9200.
Service is activated by providing XM Satellite Radio with a Radio ID. XM Satellite Radio uses the Radio
ID to send an activation signal that allows the G3X MFD to display weather data an/or entertainment
programming. XM service should activate in 45 to 60 minutes.
1. The Radio ID can be displayed by accessing the XM Audio Page, and then pressing the INFO
Softkey. Record the Radio ID for reference during XM Activation.
2. Make sure that the aircraft's XM antenna has an unobstructed view of the southern sky. It is
highly recommended that the aircraft be outside of and away from the hangar.
3. Hook up the aircraft to external power if available. The complete activation process may take 4560 minutes or more, depending on the demand on the XM activation system.
4. Power on the avionics and allow the G3X to power up. Do not power cycle the units during the
activation process.
5. Go to the XM Info Page. During the activation process the unit may display several different
activation levels, this is normal and should be ignored. When the service class (Aviator Lite,
Aviator, or Aviator Pro) and all of the weather products for the class that you subscribed to are
displayed, the activation is complete. Wait 30 seconds to allow the GDU 375 to store the
activation before removing power.
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8. Post-Installation Checkout and Calibration Procedures
The checkout procedures in this section are recommended to be performed after installing the G3X. The
calibration procedures are required to be performed after installing the G3X. It is assumed that the person
performing these checks is familiar with the aircraft, has a working knowledge of typical avionics
systems, and has experience using the test equipment defined in this section.
The calibration procedures in this section are performed in the configuration mode. To enter
configuration mode, hold down the left-hand softkey while powering on the GDU 37X. In a two-display
or three-display system hold down the left-hand softkey on the PFD while powering on the unit.
All three status boxes on the GSU Page (config mode) must indicate a positive state (green check marks)
before performing any calibration procedures. The GMU 44 and GSU 73 units must be communicating
with the GDU 37X, and the GPS antenna must have clear view of the sky or a GPS repeater to produce
positive status indications.
The CONFIG GSU Page must be “unlocked” by pressing the softkeys 2, 3, 4 in order (Figure 8-1) to
select a calibration procedure.
Figure 8-1 – Softkey Positions
NOTE
All procedures in this section require that the GPS receiver is receiving sufficient satellite
signal to compute a present position. This requires outdoor line-of-site to GPS satellite
signals or a GPS indoor repeater
NOTE
As these procedures involve engine run-up and moving the aircraft, it is recommended
that the installer read this entire section before beginning the checkout procedure.
NOTE
Unless otherwise noted, all procedures apply to both one-display and two-display
systems.
CAUTION
Be sure to check all aircraft control movements before flight is attempted to ensure that
the wiring harness does not touch any moving part.
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8.1
Recommended Test Equipment
The following test equipment is recommended to conduct and complete all post installation
checkout procedures in this section: (All test equipment should have current calibration
records)
•
•
•
•
•
8.2
Pitot/static ramp tester
Digital Multi-Meter (DMM)
Ground power unit capable of supplying 14/28 Vdc power to the aircraft systems and avionics
Outdoor line-of-site to GPS satellite signals or GPS indoor repeater
Digital Level or equivalent
GDU 37X Test Procedure
Test the GPS Receiver:
1. Power on unit and use the FMS Joystick to select the Info Page.
2. Verify that the GPS receiver is functional and able to calculate its present position.
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Test the XM Receiver (if applicable):
1. Power on unit and use the FMS Joystick to select the XM Page.
2. Verify that the XM receiver is functioning correctly as indicated by the green signal strength
bars. See Section 8.6 for XM Activation Instructions if needed.
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8.3
GSU 73/GMU 44 Post-Installation Calibration Procedures
After mechanical and electrical installation of the GSU 73 AHRS and GMU 44 magnetometer have been
completed, prior to operation, a set of post-installation calibration procedures must be carried out.
Table 8-1 describes the necessary calibration procedures:
Table 8-1. Post-Installation Calibration Procedure Summary
Calibration
Procedure
A
B
C
D
Procedure Name
AHRS Orientation
Pitch/Roll Offset
Compensation
Magnetometer
Calibration
Heading Offset
Compensation
E
Engine Run-Up
Vibration Test
F
Magnetometer
Interference Test
Procedure
Description
Validate GSU 73
Orientation
Level Aircraft
Compass Rose
Taxi Maneuver
Compass Rose
Alignment with
Magnetic North
Validate vibration
characteristics of
installation
Validate no
magnetic
interference with
GMU 44
Installations Requiring
Procedure
Procedure A is required for all
installations
Procedure B is required for all
installations
Procedure C is required for all
installations
Installations in which GMU 44
alignment is not within 0.5° of
aircraft longitudinal axis
Procedure E is required for all
installations
Procedure F is required for initial
installation verification.
This test should also be repeated to
verify all subsequent electrical
changes associated with devices
within 10.0 feet of the GMU 44
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 same
wing as a GMU 44 unit. Likewise,
this test should also be repeated to
verify all subsequent changes to
materials within 10.0 feet of the
GMU 44. 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
44 unit.
Garmin recommends this test be
performed at least once every 12
months by all aircraft
manufacturers on a minimum of
one production aircraft for every
airframe type or model equipped
with the G3X system.
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For each Calibration Procedure, Table 8-2 lists the LRU’s that require valid calibration data.
Table 8-2. Data Validity Requirements for AHRS Calibration Procedures
AHRS Calibration Procedure
Pitch/Roll Offset
Magnetic Calibration
Heading Offset
Engine Run-Up
Magnetometer Interference Test
Mounting Orientation Identification
Valid Status Required
GPS or Air Data
GPS or Magnetometer
GPS or Air Data.
Magnetometer always required.
GPS or Air Data
GPS or Air Data.
Magnetometer always required.
None
Table 8-3 lists the type of valid calibration data required to be output by each LRU for the Calibration
Procedures listed in Table 8-2.
Table 8-3. Configuration Mode GSU Page Status Boxes
Status Box
GPS
Air Data
Magnetometer
Valid Status
3D or 3D Differential GPS solution available
True Airspeed (TAS) available. NOTE: A valid outside air temperature
(OAT) measurement is required for TAS to be valid.
Measurement of local 3D magnetic field available
The GSU Page status boxes referred to in Table 8-3 are shown in the following figure.
If removal and replacement of a GMU 44 unit is required after post-installation calibration has been
completed, the GMU 44 mounting rack must not be moved. If the mounting screws that secure the
GSU 73 unit or the GMU 44 mounting rack are loosened for any reason, a new post-installation
calibration procedure, A, B, C and E (plus D if required initially) must be carried out before the aircraft
can be returned to service.
Any GMU 44 removal and replacement requires repeating the magnetometer calibration, and if
applicable, the heading offset compensation.
The addition, removal or modification of components that are ferrous, or otherwise magnetic, within 10.0
feet of the GMU 44 magnetometer location after the magnetometer interference test or magnetometer
calibration procedure were completed requires a repeat of both procedures.
Furthermore, electrical changes to the installation that affect components within 10.0 feet of the GMU 44
magnetometer after the magnetometer calibration and magnetometer interference procedures were
completed will require a repeat of the magnetometer interference test. If new magnetic interference is
detected, it must be resolved and then the magnetometer calibration procedure must be repeated. Wiring
or grounding changes associated with a device located in the same wing as the GMU 44 is a good
example of such a change.
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8.3.1 Calibration Procedure A: AHRS ORIENTATION
1. Enter configuration mode by holding down the left-hand softkey while powering on the GDU
37X.
2. Use the FMS Joystick to select the GSU Page.
3. Unlock the GSU Page by pressing softkeys 2, 3, 4 in order.
4. Ensure that all the required status boxes are checked (Tables 8-2 and 8-3). The GMU 44 and
GSU 73 units must be communicating with the GDU 37X, and the GPS antenna must have
clear view of the sky or a GPS repeater to produce positive status indications.
5. Use the FMS Joystick to select AHRS ORIENTATION (if not already selected).
6. Use the FMS Joystick to highlight the Calibrate button, press the ENT Key.
7. Determine the direction the connectors of the GSU 73 are facing per the on-screen
instructions.
8. Use the FMS Joystick to highlight the Calibrate button at the bottom of the display, press the
ENT Key to begin the calibration.
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9. Use the FMS Joystick to select the direction of the GSU 73 connectors per the on-screen
instructions, select OK and press the ENT Key to continue.
10. After a few minutes the calibration will finish and a Done button will appear at the bottom of
the display, ensure that a CALIBRATION SUCCESSFUL message appears at the bottom of
the display, press the ENT Key to return to the GSU Status Page.
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8.3.2 Calibration Procedure B: Pitch/Roll Offset Compensation by Aircraft
Leveling
1. Enter configuration mode by holding down the left-hand softkey while powering on the
GDU 37X (if needed).
2. Use the FMS Joystick to select the GSU Page (if needed).
3. Unlock the GSU Page by pressing softkeys 2, 3, 4 in order (if needed).
4. Ensure that all the required status boxes are checked (Tables 8-2 and 8-3). The GMU 44 and
GSU 73 units must be communicating with the GDU 37X, and the GPS antenna must have
clear view of the sky or a GPS repeater to produce positive status indications.
5. Use the FMS Joystick to select PITCH/ROLL OFFSET.
6. Use the FMS Joystick to highlight the Calibrate button, press the ENT Key.
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7. Ensure that the aircraft has been properly leveled per the on-screen instructions.
8. Use the FMS Joystick to highlight the Calibrate button at the bottom of the display, press the
ENT Key to begin the calibration.
9. After a few minutes the calibration will finish and a Done button will appear at the bottom of
the display, ensure that a CALIBRATION SUCCESSFUL message appears at the bottom of
the display, press the ENT Key to return to the GSU Status Page.
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8.3.3 Calibration Procedure C: Magnetometer Calibration
NOTE
Calibration Procedure B must be successfully completed prior to Calibration
Procedure C.
NOTE
Calibration Procedure C must be carried out at a location that is determined to be free of
magnetic disturbances, such as a compass rose. Attempting to carry out this maneuver on
a typical ramp area will not yield a successful calibration. The accuracy of the AHRS
cannot be guaranteed if this calibration is not performed at a magnetically clean location.
A method for evaluating the magnetic disturbances at a candidate site is described in
Section 8.3.7.
Taxi the aircraft to a site that has been determined to be free of magnetic disturbances. Ensure that there
are no nearby magnetic materials on or near the perimeter of the site. If unavoidable, maneuver the
aircraft to keep the magnetometer from passing within twenty feet (6.1 meters) of such objects.
Additionally ensure that vehicles or other aircraft are an adequate distance [forty feet (12.2 meters)] away
from the aircraft under test.
At the site, align the aircraft to a heading of magnetic north (±5°). It is best to offset the aircraft position
to the left (west) of the North/South axis to allow turning clockwise around the site as indicated in Figure
8-2.
Figure 8-2 – Aircraft Alignment
With the aircraft stationary, initiate the GSU 73 AHRS magnetometer calibration procedure as follows:
1. Enter configuration mode by holding down the left-hand softkey while powering on the GDU
37X (if needed).
2. Use the FMS Joystick to select the GSU Page (if needed).
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3. Unlock the GSU Page by pressing softkeys 2, 3, 4 in order (if needed).
4. Ensure that all the required status boxes are checked (Tables 8-2 and 8-3). The GMU 44 and
GSU 73 units must be communicating with the GDU 37X, and the GPS antenna must have
clear view of the sky or a GPS repeater to produce positive status indications.
5. On the GSU Status Page, use the FMS Joystick to select MAGNETOMER.
6. Use the FMS Joystick to highlight the Calibrate button, press the ENT Key.
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7. Ensure that the aircraft has been properly positioned per the on-screen instructions.
8. Use the FMS Joystick to highlight the Calibrate button at the bottom of the display, press the
ENT Key to begin the calibration.
9. The PFD advises the operator when to turn the aircraft, when to stop, and when to turn again.
10. Upon instruction to turn, taxi the aircraft in a right turn. After approximately 30° of turn
from the last heading the PFD instructs the operator to stop the aircraft.
NOTE
Due to the difficulties in executing smooth, accurate turns the PFD may incorrectly
interpret a station and instruct to “HOLD POSITION” prior to full completion of a 30°
turn. If this scenario is encountered, it is best for the operator to ignore the “HOLD
POSITION” command and instead use outside references to complete the approximate
30° of turn. Instead of using the PFD instruction to turn as a real-time indication of when
to turn, simply judge the 30° (±5°) turn increments of the aircraft by using the compass
rose radials. Dwelling at these 30° increments for the time recommended by the PFD
should result in successful calibration.
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11. The PFD guides the operator to dwell at multiple headings around a complete circle.
NOTE
Due to high winds or excessive airframe vibration, the operator may encounter a
condition where the PFD restarts the 18-second countdown without full completion of the
previous countdown. If this is encountered more than once for a given station, the
operator should begin turning to the next station (approximately 30°). A minimum of 2
successful stations per quadrant is required, where a successful station is a full 18-second
countdown followed by instruction to move. Ensure that if stations are skipped, a
minimum of 2 stations per quadrant are completed. Thus, it may sometimes be required
to dwell at a station after a countdown restart. A maximum of 30 stations is allowed for
the entire calibration procedure. If too many countdown restarts are encountered, the
calibration will fail with the message, “TOO MANY STATIONS.”
12. When the calibration is finished, a Done button will appear at the bottom of the display,
ensure that a CALIBRATION SUCCESSFUL message appears at the bottom of the display,
press the ENT Key to return to the GSU Status Page.
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8.3.4 Calibration Procedure D: Heading Offset Compensation
NOTE
Calibration Procedures B and C must have been successfully completed before
Calibration Procedure D can be performed.
This procedure is optional, and generally not recommended as it is difficult to orient the entire aircraft
with an absolute accuracy of less than a few degrees. This procedure is required only when the GMU 44
Magnetometer has not been installed facing forward and parallel to within 0.5º of the aircraft longitudinal
axis. For calibration accuracy, maneuver the aircraft with assistance from outside the cockpit to precisely
align the aircraft to cardinal compass heading reference lines on the compass rose.
In order to accomplish the necessary degree of accuracy in heading alignment, it is generally required that
the aircraft be physically towed by hand. Towing tugs should not be used as they distort the magnetic
field in their vicinity.
1. Enter configuration mode by holding down the left-hand softkey while powering on the GDU
37X (if needed).
2. Use the FMS Joystick to select the GSU Page (if needed).
3. Unlock the GSU Page by pressing softkeys 2, 3, 4 in order (if needed).
4. On the GSU Status Page, use the FMS Joystick to select HEADING OFFSET.
5. Ensure that all the required status boxes are checked (Tables 8-2 and 8-3). The GMU 44 and
GSU 73 units must be communicating with the GDU 37X, and the GPS antenna must have a
clear view of the sky or a GPS repeater to produce positive status indications.
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6. Use the FMS Joystick to highlight the Calibrate button, press the ENT Key.
7. Ensure that the aircraft has been properly positioned per the on-screen instructions.
8. Use the FMS Joystick to highlight the Calibrate button at the bottom of the display, press the
ENT Key to begin the calibration.
9. The PFD display advises the operator when to turn the aircraft to a cardinal heading, when to
stop, and when to turn to another heading. During the procedure, the operator turns to
magnetic headings of 360, 090, 180, and 270 degrees, within a tolerance of ±0.25°.
Maneuver the aircraft with the longitudinal axis aligned with the desired heading line of the
compass rose.
10. Repeat the preceding steps 3, 4, and 5 until a Calibration OK message is displayed.
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11. After the complete calibration is finished, a Done button will appear at the bottom of the
display, ensure that a CALIBRATION SUCCESSFUL message appears at the bottom of the
display, press the ENT Key to return to the GSU Status Page.
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8.3.5 Calibration Procedure E: Engine Run-Up Vibration Test
NOTE
Calibration Procedure E is required for all installations to validate the vibration
characteristics of the installation. Calibration Procedures B through D are not required
prior to this procedure.
1. Enter configuration mode by holding down the left-hand softkey while powering on the
GDU 37X (if needed).
2. Use the FMS Joystick to select the GSU Page (if needed).
3. Unlock the GSU Page by pressing softkeys 2, 3, 4 in order (if needed).
4. Ensure that all the required status boxes are checked (Tables 8-2 and 8-3). The GMU 44 and
GSU 73 units must be communicating with the GDU 37X, and the GPS antenna must have
clear view of the sky or a GPS repeater to produce positive status indications.
5. Use the FMS Joystick to select ENGINE RUN-UP TEST.
6. Use the FMS Joystick to highlight the Calibrate button, press the ENT Key.
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7. Ensure that the aircraft has been properly positioned per the on-screen instructions.
8. Use the FMS Joystick to highlight the Calibrate button at the bottom of the display, press the
ENT Key to begin the calibration.
9. The PFD display instructs the operator to gradually increase power from idle to full throttle
and back to idle over the course of a couple of minutes.
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.
The following are potential causes for failure of the engine run-up test:
a) Excessive flexibility of GSU 73 and/or GMU 44 mechanical mounting with respect
to airframe (See Section 2.6 entitled “Aircraft Mounting Requirements for
GSU 73/GMU 44”).
b) Vibrational motion of GSU 73 and/or GMU 44 caused by neighboring equipment
and/or supports.
c) Mounting of GSU 73 at a location that is subject to severe vibrations (example; close
to an engine mount.)
d) Mounting screws and other hardware for GSU 73 and/or GMU 44 not firmly
attached.
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e) Absence of mounting supports recommended by the aircraft manufacturer.
f) GSU 73 connector not firmly attached to unit.
g) Cabling leading to GSU 73 or GMU 44 not firmly secured to supporting structure.
h) An engine/propeller combination that is significantly out of balance.
NOTE
In some aircraft, attempting the engine run-up test on a day with very strong and/or gusty
winds may cause the test to occasionally fail. However, windy conditions should not be
taken as evidence that the test would pass in calm conditions; an actual pass is required
before the installation can be considered adequate.
10. After a few minutes the calibration will finish and a Done button will appear at the bottom of
the display, ensure that a ENGINE RUN-UP TEST PASSED message appears at the bottom
of the display, press the ENT Key to return to the GSU Status Page.
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8.3.6 Calibration Procedure F: Magnetometer Interference Test
NOTE
Calibration Procedure F is required for initial installation verification. This test should
also be repeated to verify all subsequent electrical changes associated with devices within
10.0 feet of the GMU 44 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 same wing as a GMU 44 unit. Likewise, this test should also be
repeated to verify all subsequent changes to materials within 10.0 feet of the GMU 44.
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 44 unit. This
procedure validates that no electronic device is interfering with the operation of the
GMU 44 magnetometer which directly impacts the determination of attitude and heading
by the GSU 73 AHRS. Calibration Procedures A through E are not required prior to this
execution of this procedure.
NOTE
Garmin recommends this test be performed at least once every 12 months by all aircraft
manufacturers on a minimum of one production aircraft for every airframe type or model
equipped with the G3X system.
1. Enter configuration mode by holding down the left-hand softkey while powering on the
GDU 37X (if needed).
2. Use the FMS Joystick to select the GSU Page (if needed).
3. Unlock GSU Page by pressing softkeys 2, 3, 4 in order (if needed).
4. Ensure that all the required status boxes are checked (Tables 8-2 and 8-3). The GMU 44 and
GSU 73 units must be communicating with the GDU 37X, and the GPS antenna must have
clear view of the sky or a GPS repeater to produce positive status indications.
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5. Use the FMS Joystick to select MAGNETOMETER INTERFERENCE TEST.
6. Use the FMS Joystick to highlight the Calibrate button, press the ENT Key.
7. Ensure that the aircraft has been properly prepared per the on-screen instructions. See Table
8-2 for a sample test sequence.
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8. Use the FMS Joystick to highlight the Calibrate button at the bottom of the display, press the
ENT Key to begin the calibration.
9. The operator should carry out the actions called for in the prepared test sequence.
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.
10. After the calibration is finished, a Done button will appear at the bottom of the display,
ensure that a MAG INTERFERENCE TEST PASSED message appears at the bottom of the
display, press the ENT Key to return to the GSU Status Page.
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Table 8-4. Magnetometer Interference Test Sequence Example
Elapsed Time Since Start
of Test (min:secs)
0:00
0:10
0:20
0:30
0:40
0:50
1:00
1:20
1:40
1:50
2:00
2:10
2:20
2:30
2:40
2:50
3:00
3:10
3:20
3:30
3:40
3:50
4:00
4:10
4:20
4:30
4:40
4:50
5:00
Action
Test begins
Aileron full right
Aileron full left
Aileron level
Flaps down
Flaps up
Landing gear up
Landing gear down
Speed brake up
Speed brake down
Navigation lights on
Navigation lights off
Landing lights on
Landing lights off
Taxi lights on
Taxi lights off
Landing + Taxi lights on
Landing + Taxi lights off
Strobes on
Strobes off
Recognition lights on
Recognition lights off
Turn on all wing-tip lights simultaneously (typically will include
navigation lights, recognition lights and strobe)
Turn off all wing-tip lights simultaneously
Beacon on
Beacon off
Pitot heat on
Pitot heat off
End of test
If the test fails, the installation should be considered unreliable until the source of magnetic interference is
identified and remedied. The magnetometer interference test must be repeated until passed. When the
magnetometer interference test fails, record the three magnetometer maximum deviation values and their
corresponding timestamps. A maximum deviation value greater than 5.0 milliGauss in either the X or Y
axes, or greater than 8.0 milligauss in the Z axis indicates a problem that must be resolved. Compare the
corresponding timestamps with the prepared test sequence to identify which action produced the problem.
Contact Garmin for assistance in resolving the problem.
NOTE
Two common reasons for a failed magnetometer interference test are:
1) New equipment is installed in close proximity to the GMU 44 magnetometer.
2) An existing or new electronic device has become grounded through the aircraft
structure instead of via the proper ground wire in a twisted shielded pair.
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8.3.7 Site Evaluation of Magnetic Disturbances for Magnetometer Calibration
Procedure
As mentioned in Section 8.3.3, the Magnetometer Calibration Procedure (Calibration Procedure C) must
be carried out at a site that is determined to be free of magnetic disturbances.
NOTE
Typically, a compass rose is an acceptable location to perform the magnetometer
calibration procedure. However, because not all compass roses are well maintained, even
an existing compass rose should be regularly evaluated using the method described here
to determine if it is free of magnetic disturbances. If evaluation of an existing compass
rose indicates that magnetic disturbances are present, then an alternative location must be
found to perform the Magnetometer Calibration Procedure.
A G3X-equipped airplane can be used to evaluate a candidate site for magnetic disturbances and
determine whether it is a suitable location to perform the magnetometer calibration procedure. The
magnetometer calibration procedure itself contains the logic to simultaneously survey the location for
magnetic cleanliness while it is computing the magnetometer calibration parameters.
The G3X-equipped airplane installation used to evaluate the site must have already completed the
pitch/roll offset compensation procedure (Procedure B). However, prior completion of the Magnetometer
Calibration Procedure (Procedure C) is not required.
In order to evaluate a candidate site, the Magnetometer Calibration Procedure must be performed twice:
once turning clockwise around the site, and once turning counter-clockwise. Both times, the procedure
should be conducted as described in Section 8.3.3 of this document, with the exception of the direction of
turns around the site.
NOTE
Although Section 8.3.3 indicates that the Magnetometer Calibration Procedure should be
performed by making a series of clockwise turns around the site, the procedure can also
be performed by making counter-clockwise turns for the purpose of evaluating the site
for magnetic disturbances.
If, upon completion of the Magnetometer Calibration Procedure in both the clockwise and counterclockwise directions, the PFD displays the “CALIBRATION SUCCESSFUL / SITE IS CLEAN”
message, then the candidate site is sufficiently free of magnetic disturbances and is acceptable for
performing the Magnetometer Calibration Procedure. It is important to perform the procedure in both the
clockwise and counter-clockwise directions to ensure that the magnetometer sweeps over a large enough
area at the candidate site.
If, upon completion of the Magnetometer Calibration Procedure in either of the two directions, the PFD
displays either the “MAG FIELD AT SITE NOT UNIFORM”, or “MAG FIELD AT SITE DIFFERS
FROM IGRF MODEL” message, then the site contains magnetic disturbances that are too large.
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NOTE
The Magnetometer Calibration Procedure must consistently report “CALIBRATION
SUCCESSFUL / SITE IS CLEAN” in both the clockwise and counter-clockwise
directions for the site to be considered acceptable. More than one failure out of ten
attempts in a given direction would be sufficient reason to conclude the site is not
acceptable.
A site that is used repeatedly to perform the Magnetometer Calibration Procedure should be re-evaluated
every 12 months, and after any significant construction or placement of magnetic objects (above or below
ground) within 50 meters of the location.
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9
Troubleshooting
In this section the term ‘Red-X’ refers to a red “X” that appears on different areas of the display to
indicate the failure of that particular function.
Refer to the G3X Pilot’s Guide (190-01054-00) for a complete listing of System Status Messages.
For additional assistance, contact your G3X Dealer, then for further help (if needed), contact Garmin
Aviation Product Support at US Toll Free Number 1-888-606-5482, or US 1-913-397-8200.
NOTE
The information in this section is for troubleshooting use only and does not supersede any
approved Maintenance or Installation Manual instructions.
9.1
GDU 37X
9.1.1 SD Card Slot
A stuck or sticking SD card issue can sometimes be caused by the card thickness variability (especially if
there is more than one label on the card). This is usually caused by the card sticking in the overlay
opening, not by the card sticking to the socket inside the unit. Try another card (without a label if
possible) to confirm the problem before returning. If the second card sticks, the SD socket board inside
the unit may be misaligned with the overlay and the GDU 37X will require repair. If the thickness of the
card was the cause, see if more than one label was on the card. If the labels weren’t the cause, determine
what brand of SD card was being used (Garmin recommends using SanDisk® or Toshiba brand cards).
9.1.2 Crosstalk Error (Dual or Three Screen Systems)
Crosstalk Error messages occur if there is a mismatch in GDU 37X software versions. If this occurs, the
GDU’s will not communicate with each other, and a software mismatch message will be reported on the
INFO page (press the MSG softkey). Ensure both displays are running the same software version to clear
the issue.
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9.2
GMU 44
Figure 9-1 – Heading Failure Indication (Full-Screen PFD)
9.2.1 Red-X Failures
If a Red-X (steady or intermittent) is displayed on the heading (Figure 9-1), 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 44 or its calibration.
2. When the aircraft is taxiing on the ground with a yaw rate of less than 1.5 degrees/second
(i.e., taxiing essentially in a straight line) GPS track information is used to update heading
information. This logic is applied regardless of magnetic anomaly detection.
3. The GDU may display Red-X on the heading if the GSU 73 does not have GPS information,
or if it senses a magnetic anomaly.
4. While a magnetic anomaly is detected and the aircraft is determined to be stationary, the
value of the heading output is frozen. When either the aircraft is determined to be no longer
stationary or the magnetic anomaly ceases, heading will be unfrozen and determined as
useable. In this context, the aircraft is considered to be stationary when its yaw rate is less
than 1.0 degrees/second and all other angular rate and acceleration values are sufficiently
small. (moving or shaking the wings or tail for example can cause a Red-X to be displayed).
5. Check to see if any new equipment has been installed on the aircraft, and reference Table 3-5
for minimum distances for installed equipment from the GMU 44 to prevent interference.
If the GMU 44 heading is not present on the GDU 37X, there may be a problem with the RS-232 line
between the GSU 73 and GMU 44. Troubleshoot any possible wiring/connector issues before replacing
either unit.
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9.3
GSU 73
GSU 73 ground operation is heavily dependent on GPS data inputs. Be sure to correct any GPS
performance problems (i.e. interference caused by some types of cell phones or anything that transmits in
the area) before troubleshooting the GSU 73/GMU 44. For GPS data to be considered usable, the
receiver must be tracking at least 4 satellites and have a 3D GPS Solution.
GSU 73 AHRS operation needs at least two of the three inputs from; the GPS receiver, the GMU 44, and
the Air data (also part of the GSU 73) for proper operation. See Table 9-1 below for the attitude and
heading outputs the GSU 73 can provide based on the available data inputs.
Table 9-1 – GSU 73 AHRS Operating Mode Table
GSU 73 Mode
GPS data
Primary
Reversion No GPS
Reversion No Mag
Reversion No Mag,
No Air
Coast On Gyros
Output Unreliable
Good
Bad
Good
Good
Bad
Bad
GSU 73 Input
GMU44 data Air data data
Doesn’t
Good
matter
Good
Good
Bad or
Good
anomaly
Bad or
Bad
anomaly
Either or Both Bad
Either or Both Bad
GSU 73 Output
Heading
Pitch
Roll
Valid
Valid
Valid
Valid
Valid
Valid
Invalid
Valid
Valid
Invalid
Valid
Valid
Invalid
Invalid
Invalid
Invalid
Invalid
Invalid
For complaints concerning GSU 73 realignments performed while in the air (i.e. the pilot feels that the
realignment is taking too long or does not seem to be reinitializing), Table 9-2 shows the pitch and roll
limits that the pilot must maintain for the GSU 73 to realign itself. If the pilot was performing maneuvers
outside these limits, the GSU 73 may not properly reinitialize.
Table 9-2 – GSU 73 AHRS Pitch/Bank Limitations for Cold Start While Airborne
Mode of Operation Entered
Following Initialization
Sensor Inputs Available and Valid
All
Air Data
GPS
Mag
Inertials
(internal)
Bank Limit
in Degrees
Pitch Limit
in Degrees
Primary
YES
YES
YES
NA
± 20.0
± 5.0
Reversion No GPS
Reversion No Mag
YES
NO
YES
YES
± 10.0
± 5.0
YES
YES
NO
YES
± 10.0
± 5.0
YES
YES
NO
NO
± 10.0
± 5.0
Reversion No Mag, No Air
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9.3.1 Attitude/Heading Failure Troubleshooting
Prior to troubleshooting an Attitude Failure on-board the aircraft, gather information from the pilot by
asking the following questions.
1. What specifically was the nature of the failure? Was it a Red-X of only heading, only
pitch/roll, or both?
2. If there was a Red-X of pitch or roll information, did the PFD display the "AHRS Align:
Keep Wings Level" message (which is indicative of an AHRS reset), or the "Attitude Fail"
message (which is indicative of either AHRS invalidating its output, or a communication path
failure)?
3. What exactly was the aircraft doing in the two minutes that preceded the failure (taxing on
the ground, flying straight-and-level flight, turning, climbing, etc)? If the problem occurred
on the ground, was it within 100 feet of a hanger using GPS repeaters?
4. How long did the failure last? Was it brief or sustained? Was it repetitive in nature? If it
was repetitive, about how many times did it happen? Did it happen on more than one day?
5. Was the problem correlated with a specific maneuver or a specific geographic area?
6. Can the problem be repeated reliably?
7. Were any of the following message advisory alerts observed (must navigate to the INFO page
and press the MSG softkey to see them) within an hour of the occurrence of the problem?
•
AHRS not receiving airspeed
•
AHRS not receiving any GPS information
•
AHRS magnetic-field model out of date
•
AHRS extended operation in no-GPS mode
8. Did the onset of the problem occur shortly after a software upload to one or more of the G3X
LRU’s, or shortly after a repeat of the magnetometer calibration procedure?
9. Was a cell phone on in the aircraft at the time?
10. Were there any GPS Alert messages or loss of position lock?
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Figure 9-2 – Attitude, Air Data, and Engine/Airframe Failure Indication
(Reversionary or Split-Screen PFD)
Figure 9-3 – Attitude Fail Indication (PFD)
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Figure 9-4 – AHRS Align Message (PFD)
9.3.2 Heading/Pitch/Roll Troubleshooting
The GSU 73 may not be able to provide valid heading/pitch/roll data for the following reasons:
1. The GSU 73 external memory module in the harness (that stores the installation configuration
parameters) is either not present or not wired properly. If this is the case, then the external
installation configuration parameters will not be considered calibrated. If an “AHRS not
Calibrated” message is displayed, the AHRS and/or Magnetometer calibration needs to be
performed, or the GSU 73 configuration module is inoperative.
2. The external installation configuration parameters are not considered calibrated. These
parameters are categorized into 2 sets: AHRS installation, and Magnetic installation. If either
of these is not calibrated, the GSU 73 heading, pitch, and roll may all be flagged as invalid
and an “AHRS not Calibrated” message is displayed. Calibrate the unit to the installation.
3. There is not sufficient or valid sensor information being provided to the GSU 73 for it to
compute valid attitude information. Table 9-1 summarizes the inputs the GSU needs to
provide Attitude and Heading information.
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9.4
GSU 73 –Air Data Troubleshooting
Under normal operating conditions, the GSU 73 provides the following air data information:
•
•
•
•
•
•
•
•
•
Total Air Temperature is measured
Outside Air Temperature (OAT)
Indicated Airspeed (IAS)
True Airspeed (TAS)
Barometric Altitude
Density Altitude
Pressure Altitude
Static Pressure
Differential Pressure
If the TAS and/or OAT indications are dashed out as shown in Figure 9-5:
1. Check the GTP 59 OAT probe wiring and connection for faults.
2. Check GSU 73 configuration module wiring for damage. Replace if any is found.
3. Replace the GTP 59 OAT probe.
4. If the problem persists, replace the GSU 73 with a known good unit
Figure 9-5 – No info for TAS & OAT
NOTE
TAS information can only be displayed at speeds greater than 20 Knots (i.e. TAS is
invalid when the aircraft is sitting still).
If the Airspeed and/or Altitude is failed and shows a Red-X condition as shown in Figure 9-6:
Figure 9-6 – Airspeed and Altitude Failure Indications
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1. Inspect GSU73 pitot/static plumbing integrity
2. Inspect pitot/static ports and associated equipment
3. If the problem persists replace the GSU 73 with a known good unit
9.4.1 Troubleshooting GSU 73 Engine Indication Failures
See Figure 9-7 for example. The following may help to determine to cause of an Engine Indication
failure.
1. Does cycling power restore operation?
2. Did the operator give it sufficient time to start and initialize?
3. Did the problem begin after a software or configuration load?
4. Did the problem happen on the ground or while airborne?
5. Is only the EGT Red-X’d? If so, the GSU 73 configuration module, configuration module
wiring, thermocouple reference, or applicable thermocouple is defective. Check the wiring
and replace the configuration module or applicable thermocouple.
6. Are there one or more temperatures that drop as the electrical load increases? If a
temperature probe shorts (usually where the bayonet is crimped) a ground loop is created
forcing the reference (low side) to increase which causes the temperature reading to decrease.
7. Does the EGT temperature slowly drift up and eventually flag? This is an indication of an
(electrical) open in the temperature probe or wiring.
8. Is the air data information on the PFD intermittently Red-X’ing? If the GSU 73 +5VDC
transducer power supply is shorted to ground, it will cause an intermittent air data Red-X
issue to occur.
9. If the AMP indication Red-X’d, check the Alternator Shunt for correct resistance. Refer to
the applicable aircraft manual.
10. If the Trim Indication is Red-X’d, check the Elevator Trim Pot Sensor and wiring.
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Figure 9-7 – Attitude, Heading, Air Data, and Engine/Airframe Failure
(Reversionary or Split-Screen PFD)
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Page 9-9
Revision A
9.5
Troubleshooting On-board the Aircraft
1. Review the airframe logbook to verify if any G3X or other avionics or electrical maintenance
had been performed recently that may have contributed to the failure.
2. Check for loose wire terminals on the circuit breaker connections on the power wire(s)
causing intermittent power connections. Also, check for intermittent circuit breakers.
3. Have ground power put on the aircraft.
4. Turn on the G3X and record the system software level on the GDU start up page.
5. After the system is initialized, note any Red-X’s on the displays, ALERT messages and RedX’s on the GDU.
If the failure cannot be verified, proceed to the following physical inspection.
1. Turn off the G3X and remove the interior panels to gain access to the GSU 73.
Inspect the physical installation of the GSU 73.
2. Check that the connectors are fully seated, and that the jack screw connectors are fully
tightened on both sides of the GSU 73 connector.
3. Check for a loose wire harness that is able to move around during flight. This condition may
cause the wire to pull on or vibrate the connector making intermittent connections.
4. Ensure that the GSU 73 is mounted securely. If any doubt exists, use a screwdriver to check
the tightness of the four mounting screws.
5. Look in the vicinity of the GSU 73 for any heavy objects that may not be fastened tight to the
structure that could induce GSU 73 vibration.
6. Look for evidence of water or fluid contamination in the area around the GSU 73.
7. Unplug the GSU 73 connector and check for bent pins.
8. Inspect the wire harness clamp on the rear of the connector to verify that it is not too tight and
smashing/shorting the wires. If the wire clamp is installed upside down, it has sharp edges
that can cut into the wires. Also verify the presence of protective wire wrap between the
wires and the clamp.
If the condition is not resolved by following the preceding instructions, contact Garmin Product Support
for additional assistance. A Garmin Field Service Engineer may ask the technician to download the fault
logs to a PC (via the USB port on the GSU 73) and email the logs back to Garmin to help determine if the
problem is in the GSU 73 or in the aircraft.
Page 9-10
Revision A
G3X Installation Manual –Troubleshooting
190-01115-01
9.6
GSU Page
All three status boxes on the GSU Page (config mode) must indicate a positive state (green check marks)
before performing any calibration procedures (Section 8). The GMU 44 and GSU 73 units must be
communicating with the GDU 37X, and the GPS antenna must have clear view of the sky to produce
positive status indications.
Figure 9-8 – CONFIG GSU Page
G3X Installation Manual - Troubleshooting
190-01115-01
Page 9-11
Revision A
This page intentionally left blank
Page 9-12
Revision A
G3X Installation Manual –Troubleshooting
190-01115-01
10 Return to Service Information
These return to service procedures are intended to verify the serviceability of the appliance only. These
tests alone do not verify or otherwise validate the airworthiness of the installation.
10.1 GDU 37X
10.1.1 Original GDU 37X is Reinstalled
No software or configuration loading is required if the original GDU 37X is reinstalled. Continue to
Section 10.2.
10.1.2 Original GDU 37X(s) Installed in a Different Position
No software or configuration loading is required if the GDU 37X is installed in a different location.
Continue to Section 10.2.
10.1.3 New GDU 37X(s) Installed
If a new GDU 37X is installed (new serial number), verify the correct software version on the MAIN
page in configuration mode. Additionally verify that all installed displays have the same software
version, as well as NavData, terrain, and obstacle databases. If the correct software version is not
installed, update the displays to the current G3X system software available on the web. No configuration
is required if the configuration module is still operational. Continue to Section 10.2.
10.1.4 New GDU 37X (PFD) Configuration Module Installed
Ensure that a new configuration module is obtained for the replacement installation. If a new
configuration module is installed and no change is made to the PFD, the PFD will write the required
configuration information to the configuration module. If the PFD and the configuration module are both
replaced, the system will need to be configured (Section 7).
NOTE
Do not use a used GDU configuration module as a replacement. Data that may reside on
the used configuration module may cause system configuration errors.
10.2 GSU 73
NOTE
A pitot/static check as outlined in 91.411 and Part 43 Appendix E must be completed if
the pitot/static lines are broken.
10.2.1 Original GSU 73 is Reinstalled
No software or configuration loading is required if the original GSU 73 is reinstalled. Continue to
Section 10.3.
G3X Installation Manual – Return to Service
190-01115-01
Page 10-1
Revision A
10.2.2 New GSU 73 Installed
If a new GSU 73 is installed (new serial number), verify the correct software version on the MAIN page
in configuration mode. If the correct software version is not installed, load the GSU 73 software
contained in the G3X system software loaded to the displays. If the configuration module is operational,
no software configuration is required. Continue to Section 10.3.
10.3 GMU 44
NOTE
If the GMU 44 is removed, the anti-rotation properties of the mounting screws must be restored. This
may be done by replacing the screws with new Garmin P/N 211-60037-08. If original screws must be reused, coat screw threads with Loctite 242 (blue) thread-locking compound, Garmin P/N 291-00023-02, or
equivalent. Important: Mounting screws must be brass.
10.3.1 GMU 44 is Reinstalled
Any time a GMU 44 is reinstalled, a new magnetometer calibration is required (Section 8.3.3). Continue
to Section 10.3.2
10.3.2 New GMU 44 Installed
If a new GMU 44 is installed (new serial number), a new magnetometer calibration (Section 8.3.3) and
verification of the correct software version (Section 7.2) is required. If the correct software version is not
installed, load the GMU 44 software contained in the G3X system software which is loaded to the
displays (Section 7). Following a successful magnetometer calibration, and software verification the
Return to Service Procedure is complete.
Page 10-2
Revision A
G3X Installation Manual – Return to Service
190-01115-01
APPENDIX A G3X Pinouts
A.1 GDU 37X
A.1.1
P3701 Connector
PIN 17
PIN 1
PIN 18
PIN 34
PIN 33
PIN 50
Figure A-1. View of J3701 Connector from Back of Unit
Pin
Pin Name
1
MONO AUDIO OUT HI
2
STEREO AUDIO OUT LO
3
STEREO AUDIO OUT LEFT
4
SPARE
5
SPARE
6
SPARE
7
SPARE
8
SPARE
9
CDU SYSTEM ID PROGRAM* 2
10
CDU SYSTEM ID PROGRAM* 1
11
RESERVED FOR FUTURE DEVELOPMENT, DO NOT USE
12
RESERVED FOR FUTURE DEVELOPMENT, DO NOT USE
13
RS-232 OUT 3
14
RS-232 IN 2
15
POWER GROUND
16
POWER GROUND
17
CONFIG MODULE POWER OUT
18
MONO AUDIO OUT LO
19
STEREO AUDIO OUT RIGHT
20
STEREO AUDIO OUT LO
21
SPARE
22
SPARE
23
SPARE
24
SPARE
25
CDU SYSTEM ID PROGRAM* 3
26
28V LIGHTING BUS HI
27
SIGNAL GROUND
28
CAN BUS TERMINATION
29
RS-232 IN 3
30
RS-232 OUT 2
31
AIRCRAFT POWER 2
32
AIRCRAFT POWER 1
* Indicates Active Low
G3X Installation Manual – Pinouts
190-01115-01
I/O
Out
-Out
-----In
In
--Out
In
--Out
-Out
-----In
In
--In
Out
In
In
Page A-1
Revision A
Connector P3701, continued
Pin
Pin Name
33
CONFIG MODULE CLOCK
34
SIGNAL GROUND
35
SIGNAL GROUND
36
SIGNAL GROUND
37
SIGNAL GROUND
38
SPARE
39
SPARE
40
SPARE
41
SPARE
42
CDU SYSTEM ID PROGRAM* 4
43
14V LIGHTING BUS HI
44
SIGNAL GROUND
45
CAN BUS LO
46
CAN BUS HI
47
RS-232 IN 1
48
RS-232 OUT 1
49
CONFIG MODULE GROUND
50
CONFIG MODULE DATA
* Indicates Active Low
A.1.2
I/O
I/O
--------In
In
-I/O
I/O
In
Out
-I/O
Aircraft Power
AIRCRAFT POWER 1 and AIRCRAFT POWER 2 are “diode ORed” to provide aircraft power
redundancy.
Pin Name
Connector
Pin
AIRCRAFT POWER 1
P3701
32
AIRCRAFT POWER 2
P3701
31
POWER GROUND
P3701
15
POWER GROUND
P3701
16
A.1.3
I/O
In
In
---
Mode Selections
Configure the GDU 37X units per the following tables. A GDU 37X can be manually placed in
reversionary mode by grounding Pin 25. Grounding pin 42 will place the GDU 37X in Demo mode,
which is for in-store demonstration use only, never ground pin 42 in an aircraft installation.
PFD MODE 1, P3701 Pin 10
Open
Ground
Open
Ground
PFD MODE 3
P3701 Pin 25
Open
Ground
Page A-2
Revision A
GDU Mode
Auto Reversionary
Forced Reversionary
PFD MODE 2, P3701 Pin 9
Open
Open
Ground
Ground
GDU Mode
MFD
PFD1
PFD2
Do Not Use
PFD MODE 4
P3701 Pin 42
Open
Ground
GDU Mode
Normal Operation
Demo Mode
G3X Installation Manual – Pinouts
190-01115-01
A.1.4
Serial Data
A.1.4.1 RS-232
The RS-232 outputs conform to EIA Standard RS-232C with an output voltage swing of 0-5V when
driving a standard RS-232 load.
Pin Name
Connector
Pin
I/O
RS-232 IN 1
P3701
47
In
RS-232 OUT 1
P3701
48
Out
RS-232 IN 2
P3701
14
In
RS-232 OUT 2
P3701
30
Out
RS-232 IN 3
P3701
29
In
RS-232 OUT 3
P3701
13
Out
A.1.4.2 CAN Bus
This data bus conforms to the BOSCH standard for Controller Area Network 2.0-B. This bus complies
with ISO 11898. CAN BUS TERMINATION should be connected to CAN BUS LO for the GDU that is
located at the end of the bus (farthest from the GSU 73).
Pin Name
Connector
Pin
I/O
CAN BUS HI
P3701
46
I/O
CAN BUS LO
P3701
45
I/O
CAN BUS TERMINATION
P3701
28
--
A.1.4.3 Configuration Module
In multiple GDU 37X installations, it is only necessary to connect a configuration module to PFD1.
Pin Name
Connector
Pin
I/O
CONFIG MODULE CLOCK
P3701
33
I/O
CONFIG MODULE DATA
P3701
50
I/O
CONFIG MODULE POWER OUT
P3701
17
Out
CONFIG MODULE GROUND
P3701
49
--
A.1.5
Lighting
The GDU 37X display and keys can be configured to track 28 VDC or 14 VDC lighting busses using
these inputs.
Pin Name
Connector
Pin
I/O
14V LIGHTING BUS HI
P3701
43
In
28V LIGHTING BUS HI
P3701
26
In
G3X Installation Manual – Pinouts
190-01115-01
Page A-3
Revision A
A.1.6
Audio
A.1.6.1 Mono Audio
Pin Name
MONO AUDIO OUT HI
MONO AUDIO OUT LO
Connector
P3701
P3701
Pin
1
18
I/O
Out
--
A.1.6.2 Stereo Audio
Pin Name
Connector
Pin
I/O
STEREO AUDIO OUT LEFT
P3701
3
Out
STEREO AUDIO OUT LO
P3701
20
-STEREO AUDIO OUT RIGHT
P3701
19
Out
STEREO AUDIO OUT LO
P3701
2
-The left and right common pins (pins 2 and 20) may be tied together or only one may be used. It is not
necessary to use both common pins.
Page A-4
Revision A
G3X Installation Manual – Pinouts
190-01115-01
A.2 GMU 44
A.2.1
P441 Connector
Figure A-2. View of J441 Connector Looking at Rear of Unit
Pin
1
2
3
4
5
6
7
8
9
A.2.2
Pin Name
SIGNAL GROUND
RS-485 OUT B
SIGNAL GROUND
RS-485 OUT A
SPARE
POWER GROUND
SPARE
RS-232 IN
+12 VDC POWER
I/O
-Out
-Out
---In
In
Power Function
Power-input pins accept 14/28 VDC. AIRCRAFT POWER 2 is for connecting to an alternate power
source, such as on aircraft with two electrical buses.
Pin Name
Connector
Pin
I/O
+12 VDC POWER, GMU 44
P441
9
In
POWER GROUND, GMU 44
P441
6
--
A.2.3
Serial Data
A.2.3.1 RS-232
Pin Name
RS-232 IN
Connector
P441
Pin
8
I/O
In
Connector
P441
P441
Pin
4
2
I/O
Out
Out
A.2.3.2 RS-485
Pin Name
RS-485 OUT A
RS-485 OUT B
G3X Installation Manual – Pinouts
190-01115-01
Page A-5
Revision A
A.3 GSU 73
A.3.1 Connector Description
The GSU 73 has one 62-pin connector (J731) and one 78-pin connector (J732) located on the connector
end of the unit, as shown below. J731 and J732 are clearly marked on the connector end plate.
J732
J731
Figure A-3 Rear View of Connector End Plate
A.3.2
Pin List
A.3.2.1 P731 Connector
Figure A-4 Rear Connector J731 Viewed from Connector End of Unit
J731 pins are configured as shown in preceding figure. J731 pin assignments are given in the following
table, additional tables group pin connections by function.
Pin
Pin Name
1
MAGNETOMETER RS-485 IN B
2
MAGNETOMETER RS-485 IN A
3
SIGNAL GROUND
4
GSU SYSTEM ID PROGRAM* 1
5
GSU SYSTEM ID PROGRAM* 2
6
RESERVED
7
CAN BUS HI
8
CAN BUS LO
9
DISCRETE IN* 1
10
DISCRETE IN* 2
11
DISCRETE IN* 3
12
DISCRETE IN* 4
13
DISCRETE OUT* 1
14
DISCRETE OUT* 2
15
MAGNETOMETER RS-232 OUT
* Indicates Active Low
Page A-6
Revision A
I/O
In
In
-In
In
-I/O
I/O
In
In
In
In
Out
Out
Out
G3X Installation Manual – Pinouts
190-01115-01
Connector P731, continued
Pin
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
51
52
53
54
55
56
57
58
59
60
61
62
Pin Name
RS-232 IN 2
RS-232 OUT 2
RS-232 IN 3
RS-232 OUT 3
ARINC 429 OUT 1 A
ARINC 429 OUT 1 B
ARINC 429 OUT 2 A
ARINC 429 OUT 2 B
SIGNAL GROUND
ARINC 429 IN 1 A
ARINC 429 IN 1 B
ARINC 429 IN 2 A
ARINC 429 IN 2 B
CAN BUS TERMINATION
ARINC 429 IN 3 A
ARINC 429 IN 3 B
ARINC 429 IN 4 A
ARINC 429 IN 4 B
SIGNAL GROUND
SIGNAL GROUND
SIGNAL GROUND
SIGNAL GROUND
MAGNETOMETER POWER OUT
MAGNETOMETER GROUND
SIGNAL GROUND
SPARE
SPARE
SIGNAL GROUND
SPARE
SPARE
SPARE
AIRCRAFT POWER 1
SPARE
AIRCRAFT POWER 2
SPARE
SPARE
SPARE
SIGNAL GROUND
SIGNAL GROUND
SPARE
SPARE
SPARE
SIGNAL GROUND
POWER GROUND
SIGNAL GROUND
POWER GROUND
SPARE
G3X Installation Manual – Pinouts
190-01115-01
I/O
In
Out
In
Out
Out
Out
Out
Out
-In
In
In
In
-In
In
In
In
----Out
--------In
-In
-------------Page A-7
Revision A
A.3.2.2 P732 Connector
Figure A-5 Rear Connector J732 Viewed from Connector End of Unit
Pin
Pin Name
1
ANALOG IN 2 LO
2
ANALOG IN 3 HI
3
ANALOG IN 8 LO
4
ANALOG IN 9 LO
5
ANALOG IN 14 LO
6
ANALOG IN 17 LO
7
ANALOG IN 24 LO
8
ANALOG IN 23 LO
9
THERMOCOUPLE REF IN LO
10
THERMOCOUPLE REF IN HI
11
ANALOG IN 20 LO
12
ANALOG IN 19 LO
13
ANALOG IN 6 LO
14
ANALOG IN 12 LO
15
OAT PROBE IN HI
16
OAT PROBE POWER OUT
17
FREQUENCY COUNTER IN* 1
18
SIGNAL GROUND
19
FREQUENCY COUNTER IN* 2
20
CONFIG MODULE CLOCK
21
ANALOG IN 2 HI
22
ANALOG IN 3 LO
23
ANALOG IN 8 HI
24
ANALOG IN 9 HI
25
ANALOG IN 14 HI
26
ANALOG IN 16 HI
27
ANALOG IN 24 HI
28
ANALOG IN 23 HI
29
ANALOG IN 11 LO
30
ANALOG IN 11 HI
31
ANALOG IN 20 HI
32
ANALOG IN 19 HI
33
ANALOG IN 6 HI
34
ANALOG IN 12 HI
35
OAT PROBE IN LO
36
FREQUENCY COUNTER IN* 3
37
SIGNAL GROUND
38
FREQUENCY COUNTER IN* 4
39
CONFIG MODULE DATA
* Indicates Active Low
Page A-8
Revision A
I/O
In
In
In
In
In
In
In
In
In
In
In
In
In
In
In
Out
In
-In
Out
In
In
In
In
In
In
In
In
In
In
In
In
In
In
In
In
-In
I/O
G3X Installation Manual – Pinouts
190-01115-01
Connector P732, continued
Pin
Pin Name
40
ANALOG IN 4 LO
41
ANALOG IN 1 LO
42
ANALOG IN 10 LO
43
ANALOG IN 7 LO
44
ANALOG IN 15 LO
45
ANALOG IN 16 LO
46
ANALOG IN 25 LO
47
ANALOG IN 22 HI
48
ANALOG/CURRENT MONITOR IN 2 HI
49
ANALOG IN 21 LO
50
ANALOG/CURRENT MONITOR IN 1 LO
51
ANALOG IN 18 LO
52
ANALOG IN 13 LO
53
ANALOG IN 5 LO
54
SPARE
55
+12 VDC TRANSDUCER POWER OUT
56
TRANSDUCER POWER OUT LO (GROUND)
57
TRANSDUCER POWER OUT LO (GROUND)
58
+10 VDC TRANSDUCER POWER OUT
59
CONFIG MODULE POWER OUT
60
ANALOG IN 4 HI
61
ANALOG IN 1 HI
62
ANALOG IN 10 HI
63
ANALOG IN 7 HI
64
ANALOG IN 15 HI
65
ANALOG IN 17 HI
66
ANALOG IN 25 HI
67
ANALOG IN 22 LO
68
ANALOG/CURRENT MONITOR IN 2 LO
69
ANALOG IN 21 HI
70
ANALOG/CURRENT MONITOR IN 1 HI
71
ANALOG IN 18 HI
72
ANALOG IN 13 HI
73
ANALOG IN 5 HI
74
TRANSDUCER POWER OUT LO (GROUND)
75
+5 VDC TRANSDUCER POWER OUT
76
RESERVED (FUEL SENSOR PULL-UP 2 (ANALOG IN 15))
77
RESERVED (FUEL SENSOR PULL-UP 1 (ANALOG IN 14))
78
CONFIG MODULE GROUND
* Indicates Active Low
G3X Installation Manual – Pinouts
190-01115-01
I/O
In
In
In
In
In
In
In
In
In
In
In
In
In
In
-Out
--Out
Out
In
In
In
In
In
In
In
In
In
In
In
In
In
In
-Out
----
Page A-9
Revision A
A.3.3
Power I/O
A.3.3.1 Aircraft Power
The GSU 73 has four inputs for aircraft power bus inputs of 14/28Vdc.
Pin
47
49
59
61
Connector
P731
P731
P731
P731
Pin Name
AIRCRAFT POWER 1
AIRCRAFT POWER 2
POWER GROUND
POWER GROUND
I/O
IN
IN
---
A.3.3.2 Transducer Output Power
The GSU 73 supplies output power for engine/airframe sensors that may require supply voltage
excitation. The GSU 73 outputs voltage levels of +5, +10, and +12 Vdc.
Pin
55
56
58
57
75
74
Connector
P732
P732
P732
P732
P732
P732
Pin Name
+12VDC TRANSDUCER POWER OUT
TRANSDUCER POWER OUT LO (GROUND)
+10VDC TRANSDUCER POWER OUT
TRANSDUCER POWER OUT LO (GROUND)
+5VDC TRANSDUCER POWER OUT
TRANSDUCER POWER OUT LO (GROUND)
I/O
OUT
-OUT
-OUT
--
A.3.3.3 Magnetometer Power
The GSU 73 outputs supply voltage to the GMU 44 via pins 38 & 39.
Pin
38
39
A.3.4
Connector
P731
P731
Pin Name
MAGNETOMETER POWER OUT
MAGNETOMETER GROUND
I/O
OUT
--
GSU System ID Program
Pins 4 & 5 must be left open (floating) for proper G3X configuration.
Pin
Connector
4
P731
5
P731
* Indicates Active Low
Page A-10
Revision A
Pin Name
GSU SYSTEM ID PROGRAM* 1
GSU SYSTEM ID PROGRAM* 2
I/O
IN
IN
G3X Installation Manual – Pinouts
190-01115-01
A.3.5
Serial Data Electrical Characteristics
A.3.5.1 ARINC 429 Input/Output
The ARINC 429 outputs conform to ARINC 429 electrical specifications when loaded with up to 5
standard ARINC 429 receivers.
Pin
20
21
22
23
25
26
27
28
30
31
32
33
Connector
P731
P731
P731
P731
P731
P731
P731
P731
P731
P731
P731
P731
Pin Name
ARINC 429 OUT 1A
ARINC 429 OUT 1B
ARINC 429 OUT 2A
ARINC 429 OUT 2B
ARINC 429 IN 1A
ARINC 429 IN 1B
ARINC 429 IN 2A
ARINC 429 IN 2B
ARINC 429 IN 3A
ARINC 429 IN 3B
ARINC 429 IN 4A
ARINC 429 IN 4B
I/O
OUT
OUT
OUT
OUT
IN
IN
IN
IN
IN
IN
IN
IN
A.3.5.2 RS-232 Input/Output
The RS-232 outputs conform to EIA Standard RS-232C with an output voltage swing of at least ±5V
when driving a standard RS-232 load.
Pin
15
16
17
18
19
Connector
P731
P731
P731
P731
P731
G3X Installation Manual – Pinouts
190-01115-01
Pin Name
MAGNETOMETER RS-232 OUT
RS-232 IN 2
RS-232 OUT 2
RS-232 IN 3
RS-232 OUT 3
I/O
OUT
IN
OUT
IN
OUT
Page A-11
Revision A
A.3.5.3 RS-485 Input
The GSU 73 contains one channel of RS-485 serial data communications.
Pin
1
2
Connector
P731
P731
Pin Name
MAGNETOMETER RS-485 IN B
MAGNETOMETER RS-485 IN A
I/O
IN
IN
A.3.5.4 CAN Bus
This data bus conforms to the BOSCH standard for Controller Area Network 2.0-B. This bus complies
with ISO 11898. CAN BUS TERMINATION should be connected to CAN BUS LO if GSU is located at
the end of the bus.
Pin
7
8
29
Connector
P731
P731
P731
Pin Name
CAN BUS HI
CAN BUS LO
CAN BUS TERMINATION
I/O
I/O
I/O
--
A.3.5.5 Configuration Module Interface
Pin
20
39
59
78
A.3.6
Connector
P732
P732
P732
P732
Pin Name
CONFIG MODULE CLOCK
CONFIG MODULE DATA
CONFIG MODULE POWER OUT
CONFIG MODULE GROUND
I/O
OUT
I/O
OUT
--
Discrete I/O
A.3.6.1 Active Low Discrete Inputs
The GSU 73 has 4 configurable discrete inputs conforming to:
a) Low: 0 VDC < Vin < 3.5 VDC, OR Rin < 375 ohms (active)
b) High: 8 VDC < Vin < 36 VDC, OR Rin> 100k ohms (inactive)
Pin
Connector
9
P731
10
P731
11
P731
12
P731
* Indicates Active Low
Page A-12
Revision A
Pin Name
DISCRETE IN* 1
DISCRETE IN* 2
DISCRETE IN* 3
DISCRETE IN* 4
I/O
IN
IN
IN
IN
G3X Installation Manual – Pinouts
190-01115-01
A.3.6.2 Discrete Outputs
INACTIVE: Floating (can be pulled up to externally sourced Vout in the range 0 ≤ Vout ≤ 33VDC)
Leakage current in the INACTIVE state is typically ≤ 10 uA to ground
ACTIVE: Vout ≤ 0.5VDC with ≤ 20 mA sink current
Sink current must be externally limited to 20 mA max
Pin
Connector
13
P731
14
P731
* Indicates Active Low
A.3.7
Pin Name
DISCRETE OUT* 1
DISCRETE OUT* 2
I/O
OUT
OUT
Analog Input Configuration
Some analog inputs are multi-purpose capable and have several configuration options. These inputs are
configured automatically at power on by a configuration file stored in the GDU. The following table
summarizes the configuration options.
Configurable Parameter
Resistive Divider
Description/Characteristic
Resistive Divider can be enabled or disabled for Analog Input
channels 14-25. Enabling & Disabling is achieved via software
configuration.
When Disabled: Hardware scaling is 1:1 and input impedance is
greater than 10 MΩ.
When Enabled: Hardware scaling is approximately 45:1 and input
impedance is approximately 100 kΩ.
Voltage Measurement Ranges
There are six voltage measurement ranges for analog inputs:
•
25 mV, 55 mV, 100 mV, 1.0 Vdc, 2.5 Vdc, and 5.0 Vdc
(Applies to both 1:1 and 45:1 scaling).
Effective voltage range in 45:1 mode:
•
1.125 Vdc, 2.475 Vdc, 4.5 Vdc, and 45 Vdc.
Bipolar/Unipolar
Each analog input can be configured to measure Bi-Polar (positive
and negative) or Uni-Polar (positive only) voltages. All analog inputs
are differential.
Constant Current Source
Analog Input channels 12, 13, 22, 23, 24, & 25 can be configured to
supply a 250 µA constant current source (CCS) from the positive
differential input used to measure resistive sensors. The negative
(LO) side of a CCS configured input must be tied to unit ground to
provide a current path to ground.
Miscellaneous Sensor
Configuration Parameters
G3X Installation Manual – Pinouts
190-01115-01
•
Update Rate
•
Voltage Translation Equations
•
Minimum/Maximum Values for Sensors
•
Hysteresis Value
•
Digital Filtering Value
Page A-13
Revision A
NOTE
If installing an ungrounded thermocouple to an Analog In input, a DC reference must be added to the LO
input. This can be accomplished by adding a resistance of 1 MΩ or less between ground and the Analog
In LO input that the ungrounded thermocouple is installed on.
Pin
61
41
21
1
2
22
60
40
73
53
33
13
63
43
23
3
24
4
62
42
30
29
34
14
72
52
25
5
64
44
26
45
65
6
71
51
32
12
31
11
69
49
Connector
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
Pin Name
ANALOG IN 1 HI
ANALOG IN 1 LO
ANALOG IN 2 LO
ANALOG IN 2 LO
ANALOG IN 3 HI
ANALOG IN 3 LO
ANALOG IN 4 HI
ANALOG IN 4 LO
ANALOG IN 5 HI
ANALOG IN 5 LO
ANALOG IN 6 HI
ANALOG IN 6 LO
ANALOG IN 7 HI
ANALOG IN 7 LO
ANALOG IN 8 HI
ANALOG IN 8 LO
ANALOG IN 9 HI
ANALOG IN 9 LO
ANALOG IN 10 HI
ANALOG IN 10 LO
ANALOG IN 11 HI
ANALOG IN 11 LO
ANALOG IN 12 HI
ANALOG IN 12 LO
ANALOG IN 13 HI
ANALOG IN 13 LO
ANALOG IN 14 HI
ANALOG IN 14 LO
ANALOG IN 15 HI
ANALOG IN 15 LO
ANALOG IN 16 HI
ANALOG IN 16 LO
ANALOG IN 17 HI
ANALOG IN 17 LO
ANALOG IN 18 HI
ANALOG IN 18 LO
ANALOG IN 19 HI
ANALOG IN 19 LO
ANALOG IN 20 HI
ANALOG IN 20 LO
ANALOG IN 21 HI
ANALOG IN 21 LO
I/O
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
continued
Page A-14
Revision A
G3X Installation Manual – Pinouts
190-01115-01
Pin
47
67
28
8
27
7
66
46
70
50
48
68
10
9
A.3.8
Connector
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
P732
Pin Name
ANALOG IN 22 HI
ANALOG IN 22 LO
ANALOG IN 23 HI
ANALOG IN 23 LO
ANALOG IN 24 HI
ANALOG IN 24 LO
ANALOG IN 25 HI
ANALOG IN 25 LO
ANALOG/CURRENT MONITOR IN 1 HI
ANALOG/CURRENT MONITOR IN 1 LO
ANALOG/CURRENT MONITOR IN 2 HI
ANALOG/CURRENT MONITOR IN 2 LO
THERMOCOUPLE REF IN HI
THERMOCOUPLE REF IN LO
I/O
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
IN
Temperature Inputs
Temperature input is used for Outside Air Temperature (OAT) computations. The temperature input is a
three-wire temperature probe interface. OAT Power Out and OAT High are connected internally at the
OAT probe. A GTP 59 or other supported temperature probe is required for the GSU 73 installation. The
GTP 59 is a Resistive Temperature Device (RTD). Refer to Figure C-1?????? for the temperature probe
interconnect.
Pin
15
16
35
A.3.9
Connector
P732
P732
P732
Pin Name
OAT PROBE IN HI
OAT PROBE POWER OUT
OAT PROBE IN LO
I/O
IN
OUT
IN
Frequency Counter Inputs
Digital signals are updated to the display at a rate of 10 times per second (10 Hz). Digital inputs are low
when the signal is ≤ 2 Vdc or the resistance to ground is ≤ 375 Ω, and high when the signal is > 3.5 Vdc
or the resistance to ground is > 100 k Ω. Digital inputs can also be configured as discrete inputs.
Pin
Connector
17
P732
19
P732
36
P732
38
P732
* Indicates Active Low
G3X Installation Manual – Pinouts
190-01115-01
Pin Name
FREQUENCY COUNTER IN* 1
FREQUENCY COUNTER IN* 2
FREQUENCY COUNTER IN* 3
FREQUENCY COUNTER IN* 4
I/O
IN
IN
IN
IN
Page A-15
Revision A
The following table lists the minimum frequency, maximum frequency, and duty cycles for each of these
inputs.
Pin Name
Minimum Frequency
Maximum Frequency
Duty
Cycle
FREQUENCY COUNTER IN* 1
1 Hz
500 Hz/100 KHz*
50%
FREQUENCY COUNTER IN* 2
1 Hz
500 Hz/100 KHz*
50%
FREQUENCY COUNTER IN* 3
1 Hz
500 Hz/100 KHz*
50%
FREQUENCY COUNTER IN* 4
1 Hz
500 Hz/100 KHz*
50%
*Each frequency counter channel will be configured for a high or low speed input based on the signal
being measured.
A.3.10 Fuel Select Outputs
Pin
76
77
Page A-16
Revision A
Connector
P732
P732
Pin Name
RESERVED (FUEL SENSOR PULL-UP 2 (ANALOG IN 15))
RESERVED (FUEL SENSOR PULL-UP 1 (ANALOG IN 14))
I/O
OUT
OUT
G3X Installation Manual – Pinouts
190-01115-01
APPENDIX B Connector Installation Instructions
B.1
Thermocouple Installation into a Backshell
Table B-1 lists parts needed to install a Thermocouple. Parts for this installation are included in the
Thermocouple Kit (011-00981-00), which is included in the G3X Installation Kit (K10-00017-00).
Figure Ref
1
2
3
Table B-1. Thermocouple Kit GPN 011-00981-00
Description
Qty. Needed
PN or MIL spec
3” Thermocouple, K type
1
925-L0000-00
Pins #22 AWG
2
336-00021-00
Screw
1
211-60234-08
NOTE
For the following steps please refer to indicated item numbers in Figures B-1, and B-2.
1. Strip back approximately 0.17 inches of insulation from both the positive and negative
thermocouple leads (item 1) and crimp a pin (item 2) to each lead. It is the responsibility of the
installer to determine the proper length of insulation to be removed. Wire must be visible in the
inspection hole after crimping and the insulation must be 1/64 – 1/32 inches from the end of the
contact as shown in Figure B-1.
Figure B-1. Insulation/Contact Clearance
2. Insert newly crimped pins and wires (items 1 & 2) into the appropriate connector housing (item 4)
location as specified by the installation specific wiring diagram.
3. Place thermocouple (item 1) body onto backshell (item 5) boss. Upon placing the thermocouple
(item 1) body, orient it such that the wires exit downward.
4. Attach thermocouple (item 1) tightly to backshell (item 5) using screw (item 3).
5. Attach cover (item 6) to backshell (item 5) using screws (item 7).
G3X Installation Manual – Appendix B
190-01115-01
Page B-1
Revision A
Figure B-2. Jackscrew Backshell Thermocouple Installation
Page B-2
Revision A
G3X Installation Manual – Appendix B
190-01115-01
B.2
Jackscrew Configuration Module Installation into a Jackscrew Backshell
Tables B-2 & B-3 list parts needed to install a Jackscrew Configuration Module with pins or with sockets.
Parts for these installations are included in the 011-00979-20 and 011-00979-22 kits, which are included
in the G3X Installation Kit (K10-00017-00).
Configuration modules are to be installed in the backshells of the P732 connector for the GSU
73, and the P3701 connector for the GDU 37X designated as PFD1.
Table B-2. GPN: 011-00979-20 – Kit (w/EEPROM and pins)
Figure
Ref
1
3
4
10
Description
Potted Module (w/EEPROM
and Temp.sensor)
4 cond. Cable harness
Pins Size 22D
Pan head screw
Qty. Needed
GPN or MIL spec
1
011-02179-00
1
4
1
325-00122-00
336-00021-00
211-60232-07
Table B-3. GPN: 011-00979-22 – Kit (w/EEPROM and sockets)
Figure
Ref
1
3
9
10
Description
Potted Module (w/EEPROM
and Temp.sensor)
4 cond. Cable harness
Socket, Size 20, 26-30 AWG
Pan head screw
G3X Installation Manual – Appendix B
190-01115-01
Qty. Needed
GPN or MIL spec
1
011-02179-00
1
4
1
325-00122-00
336-00022-01
211-60232-07
Page B-3
Revision A
NOTES
For the following steps please refer to Figures B-3 & B-4.
1. Strip back approximately 0.17 inches of insulation from each wire of the four conductor wire
harness (item 3) and crimp either a pin (item 4) or a socket (item 9) to each conductor. It is the
responsibility of the installer to determine the proper length of insulation to be removed. Wire
must be visible in the inspection hole after crimping and the insulation must be 1/64 – 1/32 inches
from the end of the contact as shown in Figure B-3.
Figure B-3. Insulation/Contact Clearance
2. Insert newly crimped pins (or sockets) and wires (items 3 and 4) into the appropriate connector
housing (item 5) location as specified by the installation specific wiring diagram.
3. Attach the module (item 1) to backshell (item 6) using screw (item 10).
4. Plug the four conductor wire harness (item 3) into the connector on the module (item 1).
5. Orient the connector housing (item 5) so that the inserted four conductor wire harness (item 3) is
on the same side of the backshell (item 6) as the module (item 1)—as shown in drawing.
6. Attach cover (item 7) to backshell (item 6) using screws (item 8).
Page B-4
Revision A
G3X Installation Manual – Appendix B
190-01115-01
Figure B-4. Jackscrew Backshell Installation
G3X Installation Manual – Appendix B
190-01115-01
Page B-5
Revision A
B.3
Jackscrew Backshell Installation Instructions
B.3.1 Shield Block Installation Parts
Tables B-4 and B-5 list the parts needed to install a Shield Block. Parts listed in Table B-4 are supplied
in the jackscrew backshell kits (011-01855-03 and 011-01855-04). Parts listed in Table B-5 are to be
provided by the installer.
Table B-4. Parts supplied for a Shield Block Installation (Figure B-1)
Figure
Ref
Description
GPN or MIL spec
for 011-01855-03
GPN or MIL spec
For 011-01855-04
1
Cast Backshell Housing
125-00174-00
125-00175-00
6
Contacts
336-00094-00
336-00094-00
12
Clamp
115-01078-03
115-01078-04
13
Screw,4-40x.375,PHP,SS/P,w/Nylon
211-60234-10
211-60234-10
14
Cover
115-01079-03
115-01079-04
15
Screw,4-40x.187,FLHP100,SS/P,w/Nylon
211-63234-06
211-63234-06
Table B-5. Parts NOT supplied for a Shield Block Installation (Figure B-1)
Figure
Ref
Description
GPN or MIL spec
2
Multiple Conductor Shielded Cable (2-conductor shown in Figure B-1)
Parts used depend
on method chosen
3
Drain Wire Shield Termination (method optional)
Parts used depend
on method chosen
4
Braid, Flat (19-20 AWG equivalent, tinned plated copper strands 36
AWG, Circular Mil Area 1000 -1300)
Parts used depend
on method chosen
5
Floating Shield Termination (method optional)
Parts used depend
on method chosen
7
8
9
10
11
Ring terminal, #8, insulated, 18-22 AWG
MS25036-149
Ring terminal, #8, insulated, 14-16 AWG
MS25036-153
Ring terminal, #8, insulated, 10-12 AWG
MS25036-156
Screw, PHP, 8-32x.312", Stainless
MS51957-42
Screw, PHP, 8-32x.312", Cad Plated Steel
MS35206-242
Split Washer, #8, (.045" compressed thickness) Stainless
MS35338-137
Split Washer, #8, (.045" compressed thickness) Cad-plated steel
MS35338-42
Flat Washer, Stainless, #8, .032" thick, .174"ID, .375" OD
NAS1149CN832R
Flat washer, Cad-plated Steel, #8, .032" thick, .174"ID, .375" OD
NAS1149FN832P
Silicon Fusion Tape
Page B-6
Revision A
-
G3X Installation Manual – Appendix B
190-01115-01
NOTE
In Figure B-5, “AR” denotes quantity “As Required” for the particular installation.
Figure B-5. Shield Install onto a Jackscrew Backshell (78 pin example)
G3X Installation Manual – Appendix B
190-01115-01
Page B-7
Revision A
B.3.2 Shield Termination Technique – Method A.1 (Standard)
NOTE
For the following steps please refer to the drawings showing the installation of a
Jackscrew Backshell.
1. The appropriate number of Jackscrew Backshells will be included in the particular LRU
connector kit.
Figure B-6. Method A.1 for Shield Termination
Table B-6. Shielded Cable Preparations for Garmin Connectors
Backshell
Size
1
2
3
4
5
Number
of Pins
Std/HD
9/15
15/26
25/44
37/62
50/78
Float
Min
(inches)
1.25
1.5
1.5
1.5
1.5
Float
Max
(inches)
2.25
2.5
2.5
2.5
2.5
Ideal Float
(inches)
1.75
2.0
2.0
2.0
2.0
Window
Min
(inches)
2.75
3.0
3.0
3.0
3.0
Window
Max
(inches)
5.25
5.5
5.5
5.5
5.5
Ideal
Window
(inches)
4.25
4.5
4.5
4.5
4.5
2. At one end of a shielded cable (item 2) measure a distance between “Window Min” to “Window
Max” (Table B-6) and cut a window (max size 0.35”) in the jacket to expose the shield
(Figure B-6). Use caution when cutting the jacket to avoid damaging the individual braids of the
shield. When dealing with a densely populated connector with many cables, it may prove
beneficial to stagger the windows throughout the “Window Min” to “Window Max” range. If
staggering is not needed the “Ideal Window” length is recommended.
Suggested tools to accomplish the window cut:
•
•
•
Page B-8
Revision A
Coaxial Cable Stripper
Thermal Stripper
Sharp Razor Blade
G3X Installation Manual – Appendix B
190-01115-01
3. Connect a Flat Braid (item 4) to the shield exposed through the window of the prepared cable
assembly (item 2) from step 2. The Flat Braid should go out the front of the termination towards
the connector. It is not permitted to exit the rear of the termination and loop back towards the
connector (Figure B-6). Make this connection using an approved shield termination technique.
NOTE
FAA AC 43.13-1B Chapter 11, Section 8 (Wiring Installation Inspection Requirements)
may be a helpful reference for termination techniques.
Preferred Method:
Slide a solder sleeve (item 3) onto the prepared cable assembly (item 2) and connect the Flat Braid
(item 4) to the shield using a heat gun approved for use with solder sleeves. It may prove beneficial
to use a solder sleeve with a pre-installed Flat Braid versus having to cut a length of Flat Braid to be
used. The chosen size of solder sleeve must accommodate both the number of conductors present in
the cable and the Flat Braid (item 4) to be attached.
Solder Sleeves with pre-installed Flat Braid
A preferred solder sleeve would be the Raychem S03 Series with the thermochromic temperature
indicator (S03-02-R-9035-100, S03-03-R-9035-100, S03-04-R-9035-100). These solder sleeves come
with a pre-installed braid and effectively take the place of items 3 and 4. For detailed instructions on
product use, reference Raychem installation procedure RCPS 100-70.
Raychem recommended heating tools:
•
•
•
•
•
HL1802E
AA-400 Super Heater
CV-1981
MiniRay
IR-1759
Individual solder sleeves and Flat Braid
Solder Sleeves:
Reference the following MIL-Specs for solder sleeves.
(M83519/1-1, M83519/1-2, M83519/1-3, M83519/1-4, M83519/1-5)
Flat Braid:
If the preferred Raychem sleeves are not being used, the individual flat braid selected should
conform to ASTMB33 for tinned copper and be made up of 36 AWG strands to form an
approximately 19-20 AWG equivalent flat braid. A circular mil area range of 1000 to 1300 is
required. The number of individual strands in each braid bundle is not specified. (e.g.
QQB575F36T062)
NOTE
Flat Braid as opposed to insulated wire is specified in order to allow continuing air
worthiness by allowing for visual inspection of the conductor.
G3X Installation Manual – Appendix B
190-01115-01
Page B-9
Revision A
Secondary Method:
Solder a Flat Braid (item 4) to the shield exposed through the window of the prepared cable assembly
(item 2). Ensure a solid electrical connection through the use of acceptable soldering practices. Use
care to avoid applying excessive heat that burns through the insulation of the center conductors and
shorts the shield to the signal wire. Slide a minimum 0.75 inches of Teflon heat shrinkable tubing
(item 3) onto the prepared wire assembly and shrink using a heat gun. The chosen size of heat
shrinkage tubing must accommodate both the number of conductors present in the cable and the Flat
Braid (item 4) to be attached.
Teflon Heat Shrinkable Tubing:
Reference the following MIL-Spec for Teflon heat shrinkable tubing (M23053/5-X-Y).
4. At the same end of the shielded cable (item 2) and ahead of the previous shield termination, strip
back “Float Min” to “Float Max” (Table B-6) length of jacket and shield to expose the insulated
center conductors (Figure B-6). The “Ideal Float” length may be best to build optimally.
Preferred Method:
The jacket and shield should be cut off at the same point so no shield is exposed. Slide 0.75 inches
minimum of Teflon heat shrinkable tubing (item 5) onto the cable and use a heat gun to shrink the
tubing. The chosen size of heat shrinkage tubing must accommodate the number of conductors
present in the cable.
Secondary Method:
Leave a max 0.35 inches of shield extending past the jacket. Fold this 0.35 inches of shield back over
the jacket. Slide a solder sleeve (item 5) over the end of the cable and use a heat gun approved for
solder sleeves to secure the connection. The chosen size of solder sleeve must accommodate the
number of conductors present in the cable.
5. Strip back approximately 0.17 inches of insulation from each wire of the shielded cable (item 2)
and crimp a contact (item 6) to each conductor. It is the responsibility of the installer to
determine the proper length of insulation to be removed. Wire must be visible in the inspection
hole after crimping and the insulation must be 1/64 – 1/32 inches from the end of the contact as
shown in Figure B-7.
Figure B-7. Insulation/Contact Clearance
Page B-10
Revision A
G3X Installation Manual – Appendix B
190-01115-01
6. Insert newly crimped pins and wires into the appropriate connector housing location as specified
by the installation wiring diagrams.
7. Cut the Flat Braid (item 4) to a length that, with the addition of a ring terminal, will reach one of
the tapped holes of the Jackscrew backshell (item 1) (Figure B-5). An appropriate amount of
excess length without looping should be given to the Flat Braid (item 4) to allow it to freely move
with the wire bundle.
NOTE
Position the window splice to accommodate a Flat Braid (item 4) length of no more than
4 inches.
8. Guidelines for terminating the newly cutoff Flat Braid(s) (item 4) with insulated ring terminals
(item 7):
• Each tapped hole on the Jackscrew Backshell (item 1) may accommodate only two ring
terminals (item 7).
• It is preferred that only two Flat Braid(s) (item 4) be terminated per ring terminal. Two Flat
Braids per ring terminal will necessitate the use of a Ring terminal, #8, insulated, 14-16
AWG (MS25036-153).
• If only a single Flat Braid is left or if only a single Flat Braid is needed for this connector a
Ring terminal, #8, insulated, 18-22 AWG (MS25036-149) can accommodate this single Flat
Braid.
• If more braids exist for this connector than two per ring terminal, it is permissible to
terminate three braids per ring terminal. This will necessitate the use of a Ring terminal, #8,
insulated, 10-12 AWG (MS25036-156).
9. Repeat steps 2 through 8 as needed for the remaining shielded cables.
10. Terminate the ring terminals to the Jackscrew Backshell (item 1) by placing items on the Pan
Head Screw (item 8) in the following order: Split Washer (item 9), Flat Washer (item 10) first
Ring Terminal, second Ring Terminal (if needed) before finally inserting the screw into the
tapped holes on the Jackscrew Backshell. Do not violate the guidelines presented in Step 8
regarding ring terminals.
11. It is recommended to wrap the cable bundle with Silicone Fusion Tape (item 11)
(GPN: 249-00114-00 or a similar version) at the point where the backshell clamp and cast
housing will contact the cable bundle.
NOTE
Choosing to use this tape is the discretion of the installer.
12. Place the smooth side of the backshell clamp (item 12) across the cable bundle and secure using
the three screws (item 13). Warning: Placing the grooved side of the clamp across the cable
bundle may risk damage to wires.
13. Attach the cover (item 14) to the backshell (item 1) using the two screws (item 15).
G3X Installation Manual – Appendix B
190-01115-01
Page B-11
Revision A
B.3.3 Shield Termination Technique - Method A.2 (Daisy Chain)
In rare situations where more braids need to be terminated for a connector than three per ring terminal it is
allowable to daisy chain a maximum of two shields together before coming to the ring terminal
(Figure B-8). All other restrictions and instructions for the shield termination technique set forth for
Method A.1 are still applicable.
NOTE
The maximum length of the combined braids should be approximately 4 inches.
Figure B-8. Method A.2 (Daisy Chain) for Shield Termination
B.3.4 Shield Termination – Method B.1 (Quick Term)
If desired, the drain wire termination (item 3) and the floating shield termination (item 5) can be
effectively combined into a “Quick Term”. This method eliminates the float in the cable insulation and
moves the placement of the window which was described by the dimensions “Window Min” and
“Window Max” from Method A. This technique is depicted in Figure B-9.
NOTE
The original purpose for separating the shield drain termination (item 3) from the float
termination (item 5) in Method A was to allow for a variety of lengths for the drain wires
so that the shield drain terminations (item 3) would not all “bunch up” in the harness and
to eliminate loops in the drain wires. If Method B is chosen, as described in this section,
care must be taken to insure that all drain shield terminations can still be inspected. With
connectors which require a large number of shield terminations it may be best to use
Method A. This will allow the drain shield terminations (item 3) a larger area to be
dispersed across.
Using this method, the instructions from Section B.3.2 (Method A) are followed except that:
1. Step 2 is eliminated
2. Steps 3 and 4 are replaced by the following:
At the end of the shielded cable (item 2), strip “Quick Term Min” to “Quick Term Max” (Table
B-7) length of the jacket to expose the shield. Next trim the shield so that at most 0.35 inches
remains extending beyond the insulating jacket. Fold this remaining shield back over the jacket.
Page B-12
Revision A
G3X Installation Manual – Appendix B
190-01115-01
Connect a Flat Braid (item 4) to the folded back shield of the prepared cable assembly. The flat
braid should go out the front of the termination towards the connector. It is not permitted to exit
the rear of the termination and loop back towards the connector. (Figure B-9). Make this
connection using an approved shield termination technique.
NOTE
FAA AC 43.13-1B Chapter 11, Section 8 (Wiring Installation Inspection Requirements)
may be a helpful reference for termination techniques.
Preferred Method:
Slide a solder sleeve (item 3) onto the prepared cable assembly (item 2) and connect the
Flat Braid (item 4) to the shield using a heat gun approved for use with solder sleeves. It
may prove beneficial to use a solder sleeve with a pre-installed Flat Braid versus having
to cut a length of Flat Braid to be used. The chosen size of solder sleeve must
accommodate both the number of conductors present in the cable and the Flat Braid
(item 4) to be attached.
NOTE
Reference Section B.3.2 for recommended solder sleeves and flat braid. The same
recommendations are applicable to this technique.
Secondary Method:
Solder a Flat Braid (item 4) to the folded back shield on the prepared cable assembly (item 2). Ensure
a solid electrical connection through the use of acceptable soldering practices. Use care to avoid
applying excessive heat that burns through the insulation of the center conductors and shorts the
shield to the signal wire. Slide a minimum of 0.75 inches of Teflon heat shrinkable tubing (item 3)
onto the prepared wire assembly and shrink using a heat gun. The chosen size of heat shrinkage
tubing must accommodate both the number of conductors present in the cable as well as the Flat
Braid (item 4) to be attached.
Teflon Heat Shrinkable Tubing:
Reference the following MIL-Spec for general Teflon heat shrinkable tubing
(M23053/5-X-Y)
Figure B-9. Method B.1 (Quick Term) for Shield Termination
G3X Installation Manual – Appendix B
190-01115-01
Page B-13
Revision A
Table B-7. Shielded Cable Preparations – (Quick Term)
Backshell
Size
Number of
Pins
Std/HD
1
2
3
4
5
9/15
15/26
25/44
37/62
50/78
Quick
Term
Min
(inches)
1.25
1.5
1.5
1.5
1.5
Quick
Term
Max
(inches)
2.25
2.5
2.5
2.5
2.5
Quick
Term
Float
(inches)
1.75
2.0
2.0
2.0
2.0
B.3.5. Shield Termination-Method B.2 (Daisy Chain-Quick Term)
In rare situations where more braids need to be terminated for a connector than three per ring terminal it is
allowable to daisy chain a maximum of two shields together before coming to the ring terminal
(Figure B-10). All other restrictions and instructions for the shield termination technique set forth for
Method B.1 are still applicable.
NOTE
The maximum
4 inches.
length
of
the
combined
braids
should
be
approximately
Figure B-10. Method B.2 (Daisy Chain-Quick Term) for Shield Termination
Page B-14
Revision A
G3X Installation Manual – Appendix B
190-01115-01
B.3.6. Daisy Chain between Methods A and B
In rare situations where more braids need to be terminated for a connector than three per ring terminal and
a mixture of Methods A and B have been used, it is allowable to daisy chain a maximum of two shields
together from a Method A termination to a Method B (Figure B-11). All other restrictions and
instructions for the shield termination technique set forth for Method A and B are still applicable.
NOTE
The maximum length of the combined braids should be approximately
4 inches.
Figure B-11. Daisy Chain between Methods A and B
G3X Installation Manual – Appendix B
190-01115-01
Page B-15
Revision A
B.3.7 Double-Shield Termination Technique - Method C.1
In rare situations where double shielding may be necessary, the outer shield should be grounded at both
ends, while the inner shield should be grounded only at one end.
All other restrictions set forth for in Table B-8 are applicable.
NOTE
The maximum length of the braids should be approximately 4 inches.
Figure B-12. Method C.1 Double-Shield Termination
Table B-8. Shielded Cable Preparations for Garmin Connectors
Backshell
Size
1
2
3
4
5
Page B-16
Revision A
Number of
Pins
Std/HD
9/15
15/26
25/44
37/62
50/78
Float Min
(inches)
Float Max
(inches)
Ideal Float
(inches)
1.25
1.5
1.5
1.5
1.5
2.25
2.5
2.5
2.5
2.5
1.75
2.0
2.0
2.0
2.0
Window
Min
(inches)
2.75
3.0
3.0
3.0
3.0
Window
Max
(inches)
5.25
5.5
5.5
5.5
5.5
G3X Installation Manual – Appendix B
190-01115-01
B.3.8 Double-Shield Termination Technique (Quick Term) - Method C.2
In addition to method C.1, described previously, another suitable method for double-shielding wires is
presented in Figure B-13. All restrictions set forth for Method C.1 (Table B-8) are still applicable.
NOTE
The maximum length of the braids should be approximately 4 inches.
Figure B-13. Method C.2 Double-Shield Termination
B.3.9 ID Program Pins (Strapping)
ID Program Pins provide a ground reference used by the hardware as a means of configuration for system
identification. The following instructions will illustrate how this ground strapping should be
accomplished with the Jackscrew Backshell:
1. Cut a 4 inch length of 22 AWG insulated wire.
WARNING
Flat Braid is not permitted for this purpose. Use only insulated wire to avoid inadvertent
ground issues that could occur from exposed conductors.
2. Strip back approximately 0.17 inches of insulation and crimp a contact (item 6) to the 4” length of
22 AWG insulated wire. It is the responsibility of the installer to determine the proper length of
insulation to be removed. Wire must be visible in the inspection hole after crimping and the
insulation must be 1/64 – 1/32 inches from the end of the contact as shown in Figure B-7.
3. Insert newly crimped pins and wires into the appropriate connector housing location as specified
by the installation wiring diagrams.
4. At the end opposite the pin on the 22 AWG insulated wire strip back 0.2 inches of insulation.
5. Terminate this end via the ring terminals with the other Flat Braid per Steps 8 and 11 pertaining
to shield termination. If this ground strap is only wire to terminate, attach a Ring terminal, #8,
insulated, 18-22 AWG (MS25036-149).
G3X Installation Manual – Appendix B
190-01115-01
Page B-17
Revision A
B.3.10 Splicing Signal Wires
NOTES
Figure B-14 illustrates that a splice must be made within a 3 inch window from outside
the edge of clamp to the end of the 3 inch max mark.
WARNING
Keep the splice out of the backshell for pin extraction, and outside of the strain relief to
avoid preloading.
Figure B-14 shows a two wire splice, but a maximum of three wires can be spliced. If a third wire is
spliced, it is located out front of splice along with signal wire going to pin.
Splice part numbers:
Raychem D-436-36/37/38
MIL Spec MIL-S-81824/1
This technique may be used with shield termination methods: A.1, A.2, B.1, B.2, C.1 and C.2.
Figure B-14. D-Sub Spliced Signal Wire illustration
Page B-18
Revision A
G3X Installation Manual – Appendix B
190-01115-01
B.4
Circular Connector Installation Instructions
B.4.1 Pigtail Installation Parts
Table B-9 provides a list of parts needed to install a circular connector with backshell. Parts for this
installation are included in the pigtail connector kits and some are to be provided by the OEM/installer.
Table B-9. Parts supplied for a Circular Connector Installation (Figure B-15)
Figure Ref
Description
GPN or MIL spec
2
Contacts
336-00022-00
3
Circular Backshell Non-Magnetic (includes 2 self-tapping
screws and circular connector)
330-90005-01
Table B-10. Parts NOT supplied for a Circular Connector Installation (Figure B-15)
Figure Ref
Description
1
Circular Connector, 19 CKT
Multiple Conductor Shielded Cable (2 conductor
4
shown in Figure B-15)
5
Drain Wire Shield Termination (method optional)
6
Braid, Flat (19-20 AWG equivalent, tinned
plated copper strands 36 AWG, Circular Mil
Area 1000 -1300)
7
Floating Shield Termination (method optional)
8
Ring terminal, #6, insulated, 18-22 AWG
Ring terminal, #6, insulated, 14-16 AWG
Ring terminal, #6, insulated, 10-12 AWG
G3X Installation Manual – Appendix B
190-01115-01
GPN or MIL spec
MS3474L14-19SW
Reference Installation Wiring
Diagrams
Parts used depend on method
chosen
Parts used depend on method
chosen
Parts used depend on method
chosen
MS25036-102
MS25036-107
MS25036-111
Page B-19
Revision A
NOTE
In Figure B-15, “AR” denotes quantity “As Required” for the particular installation.
Figure B-15. Circular Connector Install (19 contact example)
B.4.2 Standard Shield Termination Technique – Method A
Figure B-16. Standard Shield Termination
Page B-20
Revision A
G3X Installation Manual – Appendix B
190-01115-01
Table B-11. Shielded Cable Preparations for Garmin Connectors
Float (in)
Window (in)
Backshell Size Insert Arrangement
Min
Max
Ideal
Min
Max
Ideal
14
19
1.35
1.60
1.50
2.10
4.60
3.60
1. At one end of a shielded cable (item 4) measure a distance between “Window Min” to “Window
Max” (Table B-11) and cut a window (max size 0.35”) in the jacket to expose the shield (Figure
B-16). Use caution when cutting the jacket to avoid damaging the individual braids of the shield.
When dealing with a densely populated connector with many cables, it may prove beneficial to
stagger the windows throughout the “Window Min” to “Window Max” range. If staggering is not
needed the “Ideal Window” length is recommended.
Suggested tools to accomplish the window cut:
•
•
•
Coaxial Cable Stripper
Thermal Stripper
Sharp Razor Blade
2. Connect a Flat Braid (item 6) to the shield exposed through the window of the prepared cable
assembly (item 4) from step 1. The Flat Braid should go out the front of the termination towards
the connector. It is not permitted to exit the rear of the termination and loop back towards the
connector (Figure B-16). Make this connection using an approved shield termination technique.
NOTE
FAA AC 43.13-1B Chapter 11, Section 8 (Wiring Installation Inspection Requirements)
may be a helpful reference for termination techniques.
Preferred Method
Slide a solder sleeve (item 5) onto the prepared cable assembly (item 4) and connect the Flat Braid
(item 6) to the shield using a heat gun approved for use with solder sleeves. It may prove beneficial
to use a solder sleeve with a pre-installed Flat Braid versus having to cut a length of Flat Braid to be
used. The chosen size of solder sleeve must accommodate both the number of conductors present in
the cable and the Flat Braid (item 6) to be attached.
Recommended Solder Sleeve
A preferred solder sleeve would be the Raychem S03 Series with the thermochromic temperature
indicator (S03-02-R-9035-100, S03-03-R-9035-100, S03-04-R-9035-100). These solder sleeves come
with a pre-installed braid and effectively take the place of items 5 and 6. For detailed instructions on
product use, reference Raychem installation procedure RCPS 100-70.
Raychem recommended heating tools:
•
•
•
•
•
HL1802E
AA-400 Super Heater
CV-1981
MiniRay
IR-1759
G3X Installation Manual – Appendix B
190-01115-01
Page B-21
Revision A
Secondary Method
Solder a flat braid (item 6) to the shield exposed through the window of the prepared cable assembly
(item 4). Ensure a solid electrical connection through the use of acceptable soldering practices. Use
care to avoid applying excessive heat that burns through the insulation of the center conductors and
shorts the shield to the signal wire. Slide a minimum 0.75 inches of Teflon heat shrinkable tubing
(item 5) onto the prepared wire assembly and shrink using a heat gun. The chosen size of heat
shrinkage tubing must accommodate both the number of conductors present in the cable and the flat
braid (item 6) to be attached.
Solder Sleeves:
Reference the following MIL-Specs for solder sleeves.
(M83519/1-1, M83519/1-2, M83519/1-3, M83519/1-4, M83519/1-5)
Flat Braid:
If the preferred Raychem sleeves are not being used, the individual flat braid selected should
conform to ASTMB33 for tinned copper and be made up of 36 AWG strands to form an
approximately 19-20 AWG equivalent flat braid. A circular mil area range of 1000 to 1300 is
required. The number of individual strands in each braid bundle is not specified. (e.g.
QQB575F36T062)
Teflon Heat Shrinkable Tubing:
Reference the following MIL-Spec for Teflon heat shrinkable tubing (M23053/5-X-Y).
NOTE
Flat Braid as opposed to insulated wire is specified in order to allow continuing air
worthiness by allowing for visual inspection of the conductor.
3. At the same end of the shielded cable (item 4) and ahead of the previous shield termination, strip
back “Float Min” to “Float Max” (Table B-11) length of jacket and shield to expose the insulated
center conductors (Figure B-16). The “Ideal Float” length may be best to build optimally.
Preferred Method
The jacket and shield should be cut off at the same point so no shield is exposed. Slide 0.75 inches
minimum of Teflon heat shrinkable tubing (item 7) onto the cable and use a heat gun to shrink the
tubing. The chosen size of heat shrinkage tubing must accommodate the number of conductors
present in the cable.
Secondary Method
Leave a max 0.35 inches of shield extending past the jacket. Fold the exposed .35 inches of shield
back over the jacket. Slide a solder sleeve (item 7) over the end of the cable and use a heat gun
approved for solder sleeves to secure the connection. The chosen size of solder sleeve must
accommodate the number of conductors present in the cable.
4. Strip back approximately 0.17 inches of insulation from each wire of the shielded cable (item 4)
and crimp a contact (item 2) to each conductor. It is the responsibility of the installer to
determine the proper length of insulation to be removed. Wire must be visible in the inspection
hole after crimping and the insulation must be 1/64 – 1/32 inches from the end of the contact as
shown in Figure B-17.
Page B-22
Revision A
G3X Installation Manual – Appendix B
190-01115-01
Figure B-17. Insulation/Contact Clearance
5. Insert newly crimped contacts and wires into the appropriate connector housing location as
specified by the installation wiring diagrams.
6. Cut the flat braid (item 6) to a length that, with the addition of a ring terminal, will reach the
grounding hole of the circular backshell (item 3) (Figure B-15). An appropriate amount of excess
length without looping should be given to the flat braid (item 6) to allow it to freely move with
the wire bundle.
NOTE
Position the window splice to accommodate a flat braid (item 6) length of no more than 4
inches.
7. Guidelines for terminating the newly cutoff flat braid(s) (item 6) with insulated ring terminals
(item 9):
• The grounding hole on the circular backshell (item 3) may accommodate a max of 4 ring
terminals (item 9).
• It is preferred that only two Flat Braid(s) (item 6) be terminated per ring terminal. Two flat
braids per ring terminal will necessitate the use of a #6 ring terminal, 14-16 AWG
(MS25036-107).
• If only a single flat braid is left or if only a single flat braid is needed, a #6 ring terminal, 1822 AWG (MS25036-102), can accommodate a single flat braid.
• If more braids exist for this connector than two per ring terminal, it is permissible to
terminate three braids per ring terminal. This will necessitate the use of a #6 ring terminal,
10-12 AWG (MS25036-111).
8. Repeat steps 1 through 7 as needed for the remaining shielded cables.
9. Terminate the ring terminals to the circular backshell (item 3) by placing items on the provided
pan head screw in the following order: flat washer (provided with circular backshell), first ring
terminal, second ring terminal, third ring terminal (if needed) before finally inserting the screw
into the grounding hole on the circular backshell and securing with the provided locking nut. Do
not violate the guidelines presented in step 7 regarding ring terminals.
G3X Installation Manual – Appendix B
190-01115-01
Page B-23
Revision A
B.4.3 Daisy Chain Shield Termination Technique – Method A
In rare situations where more braids need to be terminated for a connector than three per ring terminal it is
allowable to daisy chain a maximum of two shields together before coming to the ring terminal (Figure
B-18). All other restrictions and instructions for the shield termination technique set forth for Method
A.1 are still applicable.
NOTE
The maximum length of the combined braids should be approximately 4 inches.
Figure B-18. Daisy Chain Shield Termination
Page B-24
Revision A
G3X Installation Manual – Appendix B
190-01115-01
B.4.4 Quick Term Shield Termination – Method B
If desired, the drain wire termination (item 5) and the floating shield termination (item 7) can be
effectively combined into a “Quick Term”. This method eliminates the float in the cable insulation and
moves the placement of the window which was described by the dimensions “Window Min” and
“Window Max” from Method A. This technique is depicted in Figure B-19.
NOTE
The original purpose for separating the shield drain termination (item 5) from the float
termination (item 7) in Method A was to allow for a variety of lengths for the drain wires
so that the shield drain terminations (item 5) would not all “bunch up” in the harness and
to eliminate loops in the drain wires. If Method B is chosen, as described in this section,
care must be taken to insure that all drain shield terminations can still be inspected. With
connectors which require a large number of shield terminations it may be best to use
Method A. This will allow the drain shield terminations (item 5) a larger area to be
dispersed across.
Figure B-19. Quick Term Shield Termination
Table B-12. Shielded Cable Preparations – (Quick Term)
Quick Term
Quick Term Float
Backshell
Insert
Quick Term Min
Max
(inches)
Size
Arrangement
(inches)
(inches)
14
19
1.35
1.60
1.50
1. At the end of the shielded cable (item 4), strip “Quick Term Min” to “Quick Term Max” (Table
B-12) length of the jacket to expose the shield. Next trim the shield so that at most 0.35 inches
remains extending beyond the insulating jacket. Fold this remaining shield back over the jacket.
2. Connect a flat braid (item 6) to the folded back shield of the prepared cable assembly. The flat
braid should go out the front of the termination towards the connector. It is not permitted to exit
the rear of the termination and loop back towards the connector (Figure B-19). Make this
connection using an approved shield termination technique.
NOTE
FAA AC 43.13-1B Chapter 11, Section 8 (Wiring Installation Inspection Requirements)
may be a helpful reference for termination techniques.
G3X Installation Manual – Appendix B
190-01115-01
Page B-25
Revision A
Preferred Method
Slide a solder sleeve (item 5) onto the prepared cable assembly (item 4) and connect the flat braid
(item 6) to the shield using a heat gun approved for use with solder sleeves. It may prove beneficial
to use a solder sleeve with a pre-installed flat braid versus having to cut a length of flat braid to be
used. The chosen size of solder sleeve must accommodate both the number of conductors present in
the cable and the flat braid (item 6) to be attached.
NOTE
Reference Section B.3.2 for recommended solder sleeves and heating tools. The same
recommendations are applicable to this technique.
Secondary Method
Solder a flat braid (item 6) to the folded back shield on the prepared cable assembly (item 4). Ensure
a solid electrical connection through the use of acceptable soldering practices. Use care to avoid
applying excessive heat that burns through the insulation of the center conductors and shorts the
shield to the signal wire. Slide a minimum of 0.75 inches of Teflon heat shrinkable tubing (item 5)
onto the prepared wire assembly and shrink using a heat gun. The chosen size of heat shrinkage
tubing must accommodate both the number of conductors present in the cable as well as the flat braid
(item 6) to be attached.
NOTE
Reference Section B.3.2 for recommended solder sleeves, flat braids, and heat shrinkable
tubing. The same recommendations are applicable to this technique.
3. Strip back approximately 0.17 inches of insulation from each wire of the shielded cable (item 4)
and crimp a contact (item 2) to each conductor. It is the responsibility of the installer to
determine the proper length of insulation to be removed. Wire must be visible in the inspection
hole after crimping and the insulation must be 1/64 – 1/32 inches from the end of the contact as
shown in Figure B-17.
4. Insert newly crimped contacts and wires into the appropriate connector housing location as
specified by the installation wiring diagrams.
5. Cut the flat braid (item 6) to a length that, with the addition of a ring terminal, will reach the
grounding hole of the circular backshell (item 3) (Figure B-15). An appropriate amount of excess
length without looping should be given to the flat braid (item 6) to allow it to freely move with
the wire bundle.
6. Guidelines for terminating the newly cutoff flat braid(s) (item 6) with insulated ring terminals
(item 9):
• The grounding hole on the circular backshell (item 3) may accommodate a max of 4 ring
terminals (item 9).
• It is preferred that only two Flat Braid(s) (item 6) be terminated per ring terminal. Two flat
braids per ring terminal will necessitate the use of a #6 ring terminal, 14-16 AWG
(MS25036-107).
• If only a single flat braid is left or if only a single flat braid is needed, a #6 ring terminal, 1822 AWG (MS25036-102), can accommodate a single flat braid.
• If more braids exist for this connector than two per ring terminal, it is permissible to
terminate three braids per ring terminal. This will necessitate the use of a #6 ring terminal,
10-12 AWG (MS25036-111).
7. Repeat steps 1 through 7 as needed for the remaining shielded cables.
Page B-26
Revision A
G3X Installation Manual – Appendix B
190-01115-01
8. Terminate the ring terminals to the circular backshell (item 3) by placing items on the provided
pan head screw in the following order: flat washer (provided with circular backshell), first ring
terminal, second ring terminal, third ring terminal (if needed) before finally inserting the screw
into the grounding hole on the circular backshell and securing with the provided locking nut. Do
not violate the guidelines presented in step 7 regarding ring terminals.
B.4.5 Daisy Chain, Quick-Term Shield Termination – Method B
In situations where more braids need to be terminated for a connector than three per ring terminal it is
allowable to daisy chain a maximum of two shields together before coming to the ring terminal (Figure
B-20). All other restrictions and instructions for the shield termination technique set forth for Method B.1
are still applicable.
The maximum
4 inches.
length
of
the
NOTE
combined
braids
should
be
approximately
Figure B-20. Daisy Chain, Quick-Term Shield Termination
G3X Installation Manual – Appendix B
190-01115-01
Page B-27
Revision A
B.4.6 Daisy Chain Shield Termination Between Methods A and B
In rare situations where more braids need to be terminated for a connector than three per ring terminal and
a mixture of Methods A and B have been used, it is allowable to daisy chain a maximum of two shields
together from a Method A termination to a Method B (Figure B-21). All other restrictions and
instructions for the shield termination technique set forth for Method A and B are still applicable.
NOTE
The maximum
4 inches.
length
of
the
combined
braids
should
be
approximately
Figure B-21. Daisy Chain Shield Termination between Methods A and B
Page B-28
Revision A
G3X Installation Manual – Appendix B
190-01115-01
APPENDIX C OUTLINE AND INSTALLATION DRAWINGS
2X 1.72
43.7
.004
0.1
3.89
98.7
FRONT SURFACE OF PANEL
#6-32 CAPTIVE
SCREW (4 PLCS)
3.41
[86.7]
5.47
139.1
.28
7.2
.93
23.7
.29
7.3
2X 2.34
59.4
4.50
114.4
7.83
198.8
XM
CONN.
7.25
184.2
GPS
CONN.
2.98
75.8
1.09
27.7
.59
15.0
6.04
153.4
1.08
27.5
1.92
48.7
3.41
86.7
NOTES:
1.
DIMENSIONS: INCHES[MM]
2.
DIMENSIONS ARE SHOWN FOR REFERENCE ONLY.
Figure C-1.1 GDU 37X Outline Drawing
G3X Installation Manual – Outline & Installation Drawings
190-01115-01
Page C-1 (Page C-2 blank)
Revision A
APPENDIX C OUTLINE & INSTALLATION DRAWINGS
Drawing is not to scale! Use for dimensions only.
PANEL CUTOUT
.19
4.9
TYP.
4X
R.39
10.0
TYP.
.160
4.1
011-01747-( )
GDU 37x OUTLINE
(REF.)
3.67
93.1
2X 3.58
91.1
CL
1.50
38.0
NOTES:
1. DIMENSIONS: INCHES[mm].
2. DIMENSIONS SHOWN FOR
REFERENCE ONLY.
1.24
31.5
0
0.0
CL
CONNECTOR KIT
011-01921-00
2X 3.58
91.1
4X 45°
2.78
70.7
2.21
56.2
0
0.0
2X 2.69
68.4
GDU 37x UNIT
011-01747-( )
2X 2.69
68.4
2.78
70.7
3.67
93.1
Figure C-1.2 GDU 37X Panel Cutout Drawing
G3X Installation Manual – Outline & Installation Drawings
190-01115-01
Page C-3 (Page C-4 blank)
Revision A
APPENDIX C OUTLINE AND INSTALLATION DRAWINGS
GMU 44 MOUNTING RACK
AIRCRAFT HOLES
3X
.213
OPTIONAL CLEARANCE
HOLES FOR HOLD-DOWN SCREWS
3.370 85.60
2.520 64.01
120
2.175 55.25
3X
.164 4.17
THRU (IN THIN MATERIAL, USING LOCKING NUTS)
OR
DRILL AND TAP
6-32 UNC IN MATERIAL THICKER
THAN 3/16 [4.8]
3 PLCS
120
2X 1.485 37.72
.725 18.42
0
2.51 63.75
2.49 63.25
2.572 65.33
2.511 63.79
1.256 31.90
.061 1.54
0
.795 20.19
NOTE:
1. DIMENSIONS IN INCHES [mm]
2. SEE SECTIONS 3 AND 4 FOR MOUNTING INSTRUCTIONS OF THE
GSU 73 AHRS AND GMU 44 MAGNETOMETER UNIT.
3. FOLLOW "FORWARD" AND "TOP" INDICATIONS ON UNIT AND RACK.
Figure C-2.1 GMU 44 Mounting Rack
G3X Installation Manual – Outline & Installation Drawings
190-01115-01
Page C-5 (Page C-6 blank)
Revision A
APPENDIX C OUTLINE AND INSTALLATION DRAWINGS
GMU 44 INSTALLATION
FROM ABOVE
(PREFERRED)
6-32 PAN
HEAD BRASS SCREWS
0.24 [6.1] MAX THREAD LENGTH
WITHOUT CLEARANCE HOLES
GMU 44
8.4 214
3.37 85.60
AIRCRAFT
MOUNTING
RACK
6-32 100 FLAT
HEAD BRASS SCREWS
REQUIRED
.3 8
NOTES:
1. DIMENSIONS IN INCHES [mm]
AIRCRAFT MOUNTING
SURFACE
2.10 53.34
1.84 46.61
2.38 60.33
Figure C-2.2. GMU 44 Top Mounted Installation
G3X Installation Manual – Outline & Installation Drawings
190-01115-01
Page C-7 (Page C-8 blank)
Revision A
APPENDIX C OUTLINE AND INSTALLATION DRAWINGS
GMU 44 INSTALLATION
FROM BELOW
(NOT PREFERRED)
AIRCRAFT
MOUNTING
RACK
NOTES:
1. DIMENSIONS IN INCHES [mm]
6-32 100 FLAT
HEAD BRASS SCREWS
REQUIRED
AIRCRAFT MOUNTING
SURFACE
GMU 44
8.4 214
3.370 85.60
6-32 PAN
HEAD BRASS SCREWS
0.24 [6.1] MAX THREAD LENGTH
WITHOUT CLEARANCE HOLES
.3 8
2.23 56.52
2.38 60.33
Figure C-2.3 GMU 44 Bottom Mounted Installation
G3X Installation Manual – Outline & Installation Drawings
190-01115-01
Page C-9 (Page C-10 blank)
Revision A
APPENDIX C OUTLINE AND INSTALLATION DRAWINGS
NOTE:
1. BUBBLE NUMBERS IN THIS DRAWING REFER TO
REFERENCE NUMBERS LISTED IN TABLES 3-6 AND 3-7.
Figure C-2.4 GMU 44 Wiring Detail
G3X Installation Manual – Outline & Installation Drawings
190-01115-01
Page C-11 (Page C-12 blank)
Revision A
APPENDIX C OUTLINE AND INSTALLATION DRAWINGS
2X .25 6.4
2X 5.00 127.0
.40 10.2
2.8 71
.65 16.6
P732 CONNECTOR KIT
011-01818-01
CONFIGURATION MODULE KIT
(NOT SHOWN)
011-00979-20
4.50 114.3
4.25 108.0
THERMOCOUPLE KIT
(NOT SHOWN)
011-00981-00
4X .210 5.33
SEE NOTE 3
P731 CONNECTOR KIT
011-01818-00
GSU 73 UNIT
011-01817-00
4.46 113.2
PITOT AIR FITTING
1/8-27 ANPT FEMALE THREAD
P732
P731
1.96 49.8
STATIC AIR FITTING
1/8-27 ANPT FEMALE THREAD
TYP 3.96 100.6
1.8 46
1.45 36.7
.87 22.1
3.2 81
2X 1.17 29.7
5.50 139.7
2X 5.50 139.8
2X 7.33 186.2
NOTES:
1.
DIMENSIONS: INCHES[mm].
2.
DIMENSIONS ARE SHOWN FOR REFERENCE ONLY.
3.
MOUNTING HOLES FOR #10 PAN HEAD OR HEX HEAD FASTENERS.
4.
CENTER OF GRAVITY LOCATION INCLUDES UNIT WITH CONNECTOR KITS.
Figure C-3.1 GSU 73 Outline Drawing
G3X Installation Manual – Outline & Installation Drawings
190-01115-01
Page C-13 (Page C-14 blank)
Revision A
APPENDIX C OUTLINE AND INSTALLATION DRAWINGS
.03 x 45
CHAMFER
.02 x 45
CHAMFER
5/16 - 32 UNEF-2A
.563
+.000
-.012
.50
0
.050
SEE NOTE 2
1.57
.57
.255
SEE NOTE 3
SEE NOTE 4
NOTES:
1. DIMENSIONS: INCHES
2. MAX HEIGHT OF INCOMPLETE THREAD: 0.050
3. CABLE: M27500-22TE3V14. CABLE LENGTH TO BE 10 FEET 6 INCHES
4. 16 AWG WIRE: M22759/16-16. LENGTH OF WIRE OUTSIDE OF CASE TO BE 3.5 INCHES +0.25, -0.
5. SOLDER TERMINAL: MS25036-109
6. SHIELD OF CABLE ELECTRICALLY CONNECTED TO 16 AWG WIRE.
7. BUBBLE NUMBERS IN THIS DRAWING REFER TO REFERENCE NUMBERS LISTED IN TABLE 5-3.
Figure C-4.1 GTP 59 O.A.T. Probe Installation Drawing
G3X Installation Manual – Outline & Installation Drawings
190-01115-01
Page C-15 (Page C-16 blank)
Revision A
APPENDIX C OUTLINE AND INSTALLATION DRAWINGS
GA 55A FLANGE MOUNT
GA 55 STUD MOUNT
ARD
FORW
D
AR
RW
FO
011-00134-00
ANTENNA, AVIATION,
GA 55
4X 211-60212-20
#10-32 PHP x 1.00[25.4]
TORQUE 20 TO 25 in-lbs
253-00002-00
GASKET, NEOPRENE
011-01153-00
GA 55A XM ANTENNA
253-00138-00
MOLDED GASKET
AIRCRAFT SKIN
ON TOP OF FUSELAGE
AIRCRAFT SKIN
115-00031-00
BACKING PLATE
4X 210-10004-09
#8-32 SELF LOCKING NUT
1.91 48.5
FORWARD
.83 [21.1]
.60 15.2
FORWARD
4.23 107.4
FABRICATE AND INSTALL DOUBLER PLATE
AS REQUIRED TO COMPLY WITH APPLICABLE
AIRWORTHINESS REGULATIONS
2.59 65.8
4.70 119.4
2.90 73.7
2.37 60.2
.80 20.2
.49 12.3
.60 15.2
.25 6.4
XM
TNC CONNECTOR
.22 5.6
.50 12.7
4X #8-32 STUD
.800 20.3
2X 0
.65 16.5
2X 0
2X 1.625 41.28
.813 20.64
.188 4.78
FORWARD
4X
011-01153-00
ANTENNA OUTLINE
4.23 107.4
2X .89 22.6
.70 17.8
FORWARD
1.000 25.40
2X 1.750 44.45
FRONT VIEW
3.00 76.2
5.00 127.0
2X 1.25 31.8
SIDE VIEW
2X 1.600 40.64
BNC CONNECTOR
.750 19.05
.625 15.88
2.350 59.69
2X 3.300 83.82
4X .220 5.59
.625 15.88
MOUNTING CUTOUT
2.59 [65.8]
BACKING PLATE
OUTLINE
MOUNTING CUTOUT
(ANTENNA OUTLINE)
NOTES:
1. DIMENSIONS: INCHES[mm]
Figure C-5.1 GA 55/55A Installation Drawing
G3X Installation Manual – Outline & Installation Drawings
190-01115-01
Page C-17 (Page C-18 blank)
Revision A
APPENDIX C OUTLINE AND INSTALLATION DRAWINGS
GA 56 STUD MOUNT
D
AR
RW
FO
011-00134-00
ANTENNA, AVIATION,
GA 56
253-00002-00
GASKET, NEOPRENE
AIRCRAFT SKIN
ON TOP OF FUSELAGE
115-00031-00
BACKING PLATE
.83 [21.1]
4X 210-10004-09
#8-32 SELF LOCKING NUT
.60 15.2
FORWARD
4.23 107.4
1.91 48.5
2.59 65.8
.22 5.6
.50 12.7
4X #8-32 STUD
BNC CONNECTOR
.813 20.64
4X
.188 4.78
4.23 107.4
2X .89 22.6
2X 1.625 41.28
FORWARD
1.000 25.40
2X 1.750 44.45
FRONT VIEW
3.00 76.2
5.00 127.0
2X 1.25 31.8
SIDE VIEW
.625 15.88
2.59 [65.8]
BACKING PLATE
OUTLINE
MOUNTING CUTOUT
(ANTENNA OUTLINE)
Figure C-5.2 GA 56 Installation Drawing
G3X Installation Manual – Outline & Installation Drawings
190-01115-01
Page C-19 (Page C-20 blank)
Revision A
APPENDIX C OUTLINE & INSTALLATION DRAWINGS
FORWARD
4.70 119.4
2.90 73.7
2.35 59.7
.80 20.2
.49 12.3
ARD
FORW
.60 15.2
.25 6.4
XM
TNC CONNECTOR
GPS BNC CONNECTOR
2X 1.600 40.64
2X .800 20.3
2X 0
.65 16.5
4X 211-60212-20
#10-32 PHP x 1.00[25.4]
TORQUE 20 TO 25 in-lbs
011-01032-10
GA 57X GPS/XM ANTENNA
.70 17.8
253-00138-00
MOLDED GASKET
2X 0
011-01032-00
ANTENNA OUTLINE
FORWARD
1.000 25.40
2X
.750 19.05
.625 15.88
AIRCRAFT SKIN
2.350 59.69
2X 3.300 83.82
4X .220 5.59
MOUNTING CUTOUT
FABRICATE AND INSTALL DOUBLER PLATE
AS REQUIRED TO COMPLY WITH APPLICABLE
AIRWORTHINESS REGULATIONS
NOTES:
1. DIMENSIONS: INCHES[mm]
Figure C-5.3. GA 57X Installation Drawing
G3X Installation Manual – Outline & Installation Drawings
190-01115-01
Page C-21 (Page C-22 blank)
Revision A
APPENDIX D INTERCONNECT DRAWING
Figure D-1.1 Notes, 14V Power, and Antennas
G3X Installation Manual – Interconnect Drawings
190-01115-01
Page D-1 (Page D-2 blank)
Revision A
APPENDIX D INTERCONNECT DRAWING
Figure D-1.2 GDU 37X and GSU 73
G3X Installation Manual – Interconnect Drawings
190-01115-01
Page D-3 (Page D-4 blank)
Revision A
APPENDIX E EXTERNAL INTERFACE DRAWING (EXAMPLE ONLY)
Figure E-1.1 Notes, GDU 37X RS-232 and Audio Examples
G3X Installation Manual – External Interface Drawings
190-01115-01
Page E-1 (Page E-2 blank)
Revision A
APPENDIX E EXTERNAL INTERFACE DRAWING (EXAMPLE ONLY)
Figure E-1.2 GSU 73 RS-232 and ARINC 429 Examples
G3X Installation Manual – External Interface Drawings
190-01115-01
Page E-3 (Page E-4 blank)
Revision A
APPENDIX E EXTERNAL INTERFACE DRAWING (EXAMPLE ONLY)
Figure E-1.3 Tru Trak and Trio Auto Pilot Examples
G3X Installation Manual – External Interface Drawings
190-01115-01
Page E-5 (Page E-6 blank)
Revision A
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