Garmin GMU 44, GTP 59, GDU 375, GDU 37X, GSU 73 User Manual

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Page 1

G3X

Installation Manual

190-01115-01 August, 2009 Revision A

Page 2

Garmin Ltd. or its subsidiaries

Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored in any storage medium, for any purpose without the express prior written consent of Garmin. Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revision hereto, provided that such electronic or printed copy of this manual or revision must contain the complete text of this copyright notice and provided further that any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited.

Garmin International, Inc.

1200 E. 151

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

Date

A 08/26/09 Initial Release

Description

Page A G3X Installation Manual Revision A 190-01115-01

Page 3

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 Page Range

Table of Contents i – xii

Section 1 1-1 – 1-8 Section 2 2-1 – 2-6 Section 3 3-1 – 3-6 Section 4 4-1 – 4-8 Section 5 5-1 – 5-4 Section 6 6-1 – 6-28 Section 7 7-1 – 7-14 Section 8 8-1 – 8-26 Section 9 9-1 – 9-12

Section 10 10-1 – 10-2 Appendix A A-1 – A-16 Appendix B B-1 – B-28 Appendix C C-1 – C-22 Appendix D D-1 – D4 Appendix E E-1 – E4

G3X Installation Manual Page i 190-01115-01 Revision A

Page 4

TABLE OF CONTENTS

PARAGRAPH PAGE

1 G3X Installation Overview ..............................................................................................................1-1

1.1 Unpacking Unit................................................................................................................................1-1

1.2 Introduction......................................................................................................................................1-1

1.3 System Overview.............................................................................................................................1-2

1.4 General G3X LRU Specifications....................................................................................................1-3

1.5 Installation Requirements.................................................................................................................1-5

1.6 Mounting..........................................................................................................................................1-5

1.7 Wiring/Cabling Considerations........................................................................................................1-5

2 GDU 37X.........................................................................................................................................2-1

2.1 Equipment Description.....................................................................................................................2-1

2.2 Electrical Specifications...................................................................................................................2-2

2.3 Environmental Specifications ..........................................................................................................2-3

2.4 Installation Requirements.................................................................................................................2-4

2.5 Installation Considerations...............................................................................................................2-5

2.6 Mounting Requirements...................................................................................................................2-5

2.7 Unit Installation................................................................................................................................2-5

2.8 Maintenance.....................................................................................................................................2-5

2.9 Panel Cutout Template.....................................................................................................................2-6

3 GMU 44 ...........................................................................................................................................3-1

3.1 Equipment Description.....................................................................................................................3-1

3.2 Electrical Specifications...................................................................................................................3-1

3.3 Environmental Specifications ..........................................................................................................3-2

3.4 GMU 44 TSO/ETSO Compliance....................................................................................................3-2

3.5 Installation Requirements.................................................................................................................3-3

3.6 Installation Considerations...............................................................................................................3-3

3.7 GSU 73/GMU 44 Interconnect Harness Fabrication Instructions....................................................3-5

3.8 Mounting Instructions......................................................................................................................3-6

3.9 Maintenance.....................................................................................................................................3-6

4 GSU 73.............................................................................................................................................4-1

4.1 Equipment Description.....................................................................................................................4-1

4.2 Electrical Specifications...................................................................................................................4-2

4.3 Environmental Specifications ..........................................................................................................4-3

4.4 Installation Requirements.................................................................................................................4-3

4.5 Installation Considerations...............................................................................................................4-4

4.6 Mounting Requirements...................................................................................................................4-6

4.7 Unit Installation................................................................................................................................4-7

4.8 Maintenance.....................................................................................................................................4-8

Page ii G3X Installation Manual Revision A 190-01115-01

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PARAGRAPH PAGE

5 GTP 59.............................................................................................................................................5-1

5.1 Equipment Description.....................................................................................................................5-1

5.2 Installation Requirements.................................................................................................................5-1

5.3 TSO/ETSO Compliance...................................................................................................................5-2

5.4 Installation Considerations...............................................................................................................5-3

5.5 Unit Installation................................................................................................................................5-4

5.6 Maintenance.....................................................................................................................................5-4

6 Garmin GPS/XM Antennas..............................................................................................................6-1

6.1 GPS Antennas ..................................................................................................................................6-1

6.2 XM Antennas...................................................................................................................................6-1

6.3 Antenna Mounting Considerations...................................................................................................6-2

6.4 Teardrop Footprint Antenna Installation (GA 55 and GA 56).........................................................6-7

6.5 ARINC 743 Footprint Antenna Installation (GA 55A, GA 57X)..................................................6-14

6.6 Non-Structural Mount Installation.................................................................................................6-23

7 Software, Configuration, Databases, and XM Activation................................................................7-1

7.1 Configuration Mode.........................................................................................................................7-1

7.2 Software/Audio Data Identification .................................................................................................7-1

7.3 Software Loading Procedure............................................................................................................7-3

7.4 Configuration Pages.........................................................................................................................7-4

7.5 Garmin Database Updates..............................................................................................................7-12

7.6 XM Activation Instructions (GDU 375 only)................................................................................7-14

8 Post-Installation Checkout and Calibration Procedures...................................................................8-1

8.1 Recommended Test Equipment .......................................................................................................8-2

8.2 GDU 37X Test Procedure................................................................................................................8-2

8.3 GSU 73/GMU 44 Post-Installation Calibration Procedure..............................................................8-4

9 Troubleshooting ...............................................................................................................................9-1

9.1 GDU 37X.........................................................................................................................................9-1

9.2 GMU 44 ...........................................................................................................................................9-2

9.3 GSU 73.............................................................................................................................................9-3

9.4 GSU 73 – Air Data Troubleshooting................................................................................................9-7

9.5 Troubleshooting On-board the Aircraft..........................................................................................9-10

9.6 GSU Page.......................................................................................................................................9-11

10 Return to Service Information........................................................................................................10-1

10.1 GDU 37X.......................................................................................................................................10-1

10.2 GSU 73...........................................................................................................................................10-1

10.3 GMU 44 .........................................................................................................................................10-2

G3X Installation Manual Page iii 190-01115-01 Revision A

Page 6

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 G3X Installation Manual Revision A 190-01115-01

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LIST OF ILLUSTRATIONS

FIGURE PAGE

1-1 G3X Interconnect Example..............................................................................................................1-2

1-2 Coaxial Cable Installation................................................................................................................1-7

2-1 GDU 37X Unit View .......................................................................................................................2-1

2-2 GDU 37X Mounting Accessories ....................................................................................................2-4

3-1 GMU 44 Unit View..........................................................................................................................3-1

4-1 GSU 73 Unit View...........................................................................................................................4-1

4-2 GSU 73 Air Hose Fitting Locations.................................................................................................4-5

4-3 GSU 73 Orientation Calibration.......................................................................................................4-6

5-1 GTP 59.............................................................................................................................................5-1

6-1 Recommended Antenna Placement..................................................................................................6-4

6-2 Carbon/Glass Buried Antenna Area.................................................................................................6-5

6-3 Glare Shield Buried Antenna Area...................................................................................................6-6

6-4 Doubler Design, Teardrop Footprint Antenna, Skin Thickness 0.032” to 0.049” ...........................6-9

6-5 Doubler Design, Teardrop Footprint Antenna, Skin Thickness 0.049” to 0.051” ...........................6-9

6-6 Doubler Design, Teardrop Footprint Antenna, Skin Thickness 0.051” to 0.063” .........................6-10

6-7 Sample Doubler Location, Teardrop Footprint Antenna, Metal Skin Aircraft ..............................6-10

6-8 Skin Cutout Detail, Teardrop Footprint Antenna, Skin Thickness 0.032” to 0.049”.....................6-11

6-9 Skin Cutout Detail, Teardrop Footprint Antenna, Skin Thickness 0.049” to 0.051”.....................6-11

6-10 Skin Cutout Detail, Teardrop Footprint Antenna, Skin Thickness 0.051” to 0.063”.....................6-12

6-11 Doubler Installation, Teardrop Footprint Antenna, Skin Thickness 0.032” to 0.049”...................6-12

6-12 Doubler Installation, Teardrop Footprint Antenna, Skin Thickness 0.049” to 0.051”...................6-13

6-13 Doubler Installation, Teardrop Footprint Antenna, Skin Thickness 0.051” to 0.063”...................6-13

6-14 Doubler Design, ARINC 743 Footprint Antenna, Skin Thickness 0.032” to 0.049”.....................6-16

6-15 Doubler Design, ARINC 743 Footprint Antenna, Skin Thickness 0.049” to 0.051”.....................6-17

6-16 Doubler Design, ARINC 743 Footprint Antenna, Skin Thickness 0.051” to 0.063”.....................6-18

6-17 Sample Doubler Location, ARINC 743 Antenna, Metal Skin Aircraft .........................................6-19

6-18 Skin Cutout Detail, GA 55A Antenna, Skin Thickness 0.032” to 0.049”......................................6-19

6-19 Skin Cutout Detail, GA 55A Antenna, Skin Thickness 0.049” to 0.051”......................................6-20

6-20 Skin Cutout Detail, GA 55A Antenna, Skin Thickness 0.051” to 0.063”......................................6-20

6-21 Doubler Installation, ARINC 743Footprint Antenna, Skin Thickness 0.032” to 0.049”...............6-21

6-22 Doubler Installation, ARINC 743Footprint Antenna, Skin Thickness 0.049” to 0.051”...............6-21

6-23 Doubler Installation, ARINC 743Footprint Antenna, Skin Thickness 0.051” to 0.063”...............6-22

6-24 Installation of ARINC 743 Footprint Antenna...............................................................................6-22

6-25 Generic Non-structural ARINC 743 Footprint Antenna Installation.............................................6-23

G3X Installation Manual Page v 190-01115-01 Revision A

Page 8

FIGURE PAGE

6-26 Example Bracket Antenna Mounting Under Glareshield...............................................................6-24

6-27 Example Non-structural Antenna Mounting Under Glareshield....................................................6-25

6-28 Example Teardrop Antenna Installation in Airframe Under Fabric Skin......................................6-26

6-29 Example ARINC 743 Footprint in Airframe Under Fabric Skin...................................................6-26

6-30 Example Non-structural Antenna Mounting on Airframe .............................................................6-27

6-31 Example Teardrop Footprint Antenna Mounting Under Fabric Skin ............................................6-28

8-1 Softkey Positions..............................................................................................................................8-1

8-2 Aircraft Alignment.........................................................................................................................8-10

9-1 Heading Failure Indication (Full-Screen PFD)................................................................................9-2

9-2 Attitude, Air Data, and Engine/Airframe Failure Indication............................................................9-5

9-3 Attitude Failure Indication (PFD)....................................................................................................9-5

9-4 AHRS Align Message (PFD)...........................................................................................................9-6

9-5 No Info for TAS & OAT..................................................................................................................9-7

9-6 Airspeed and Altitude Failure Indications .......................................................................................9-7

9-7 Attitude, Heading, Air Data, and Engine/Airframe Failure.............................................................9-9

9-8 CONFIG GSU Page.......................................................................................................................9-11

A-1 View of J3701 Connector from Back of Unit.................................................................................A-1

A-2 View of J441 Connector Looking at Rear of Unit ..........................................................................A-5

A-3 Rear View of Connector End Plate.................................................................................................A-6

A-4 Rear Connector of J731 Viewed from Connector End of Unit.......................................................A-6

A-5 Rear Connector of J732 Viewed from Connector End of Unit.......................................................A-8

B-1 Insulation/Contact Clearance......................................................................................................... B-1

B-2 Jackscrew Backshell Thermocouple Installation........................................................................... B-2

B-3 Insulation/Contact Clearance......................................................................................................... B-4

B-4 Jackscrew Backshell Installation...................................................................................................B-5

B-5 Shield Install onto a Jackscrew Backshell (78 pin example)......................................................... B-7

B-6 Method A.1 for Shield Termination.............................................................................................. B-8

B-7 Insulation/Contact Clearance....................................................................................................... B-10

B-8 Method A.2 (Daisy Chain) for Shield Termination..................................................................... B-12

B-9 Method B.1 (Quick Term) for Shield Termination ..................................................................... B-13

B-10 Method B.2 (Daisy Chain-Quick Term) for Shield Termination ................................................B-14

B-11 Daisy Chain between Methods A and B......................................................................................B-15

B-12 Method C.1 Double-Shield Termination..................................................................................... B-16

B-13 Method C.2 Double-Shield Termination..................................................................................... B-17

B-14 D-Sub Spliced Signal Wire illustration.......................................................................................B-18

B-15 Circular Connector Install (19 contact example)......................................................................... B-20

B-16 Standard Shield Termination.......................................................................................................B-20

Page vi G3X Installation Manual Revision A 190-01115-01

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FIGURE PAGE

B-17 Insulation/Contact Clearance....................................................................................................... B-23

B-18 Daisy Chain Shield Termination................................................................................................. B-24

B-19 Quick Term Shield Termination..................................................................................................B-25

B-20 Daisy Chain, Quick-Term Shield Termination............................................................................B-27

B-21 Daisy Chain Shield Termination between Methods A and B...................................................... B-28

C-1.1 GDU 37X Outline Drawing........................................................................................................... C-1

C-1.2 GDU 37X Panel Cutout Drawing ................................................................................................. C-3

C-2.1 GMU 44 Mounting Rack............................................................................................................... C-5

C-2.2 GMU 44 Top Mounted Installation............................................................................................... C-7

C-2.3 GMU 44 Bottom Mounted Installation ......................................................................................... C-9

C-2.4 GMU 44 Wiring Detail................................................................................................................ C-11

C-3.1 GSU 73 Outline Drawing............................................................................................................ C-13

C-4.1 GTP 59 O.A.T. Probe Installation Drawing................................................................................ C-15

C-5.1 GA 55/55A Installation Drawing ................................................................................................ C-17

C-5.2 GA 56 Installation Drawing ........................................................................................................ C-19

C-5.3 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 Page vii 190-01115-01 Revision A

Page 10

LIST OF TABLES

TABLE PAGE

1-1 G3X LRU Part Numbers..................................................................................................................1-3

1-2 Contents of GDU 37X Assembly (010-00667-XX).........................................................................1-3

1-3 G3X LRU Power Requirements.......................................................................................................1-3

1-4 G3X LRU Physical Specifications...................................................................................................1-4

1-5 Contents of G3X Installation Kit (K10-00017-00)..........................................................................1-5

1-6 Contents of G3X LRU Kit (K10-00016-00)....................................................................................1-5

1-7 Pin Contact and Crimp Tools Part Numbers....................................................................................1-6

2-1 GDU 37X Supply Voltages..............................................................................................................2-2

2-2 GDU 37X Power Requirements.......................................................................................................2-2

2-3 GDU 37X GPS Specifications .........................................................................................................2-2

2-4 GDU 37X Supported Antennas........................................................................................................2-3

2-5 Contents of GDU 37X Connector Kit (011-01921-00) ....................................................................2-4

3-1 GMU 44 Electrical Specifications....................................................................................................3-1

3-2 GMU 44 Environmental Specifications...........................................................................................3-2

3-3 TSO/ETSO Compliance...................................................................................................................3-2

3-4 TSO/ETSO Deviations.....................................................................................................................3-2

3-5 GMU 44 Part Numbers ....................................................................................................................3-3

3-6 GMU 44 Accessories .......................................................................................................................3-3

3-7 Required Distance from Magnetic Disturbances..............................................................................3-4

3-8 Parts Needed for GMU 44 Installation.............................................................................................3-5

3-9 GMU 44 Connector Kit (011-00871-00) Contents, Reference Figure C-2.4...................................3-5

4-1 GSU 73 Supply Specifications.........................................................................................................4-2

4-2 GSU 73 Environmental Specifications ............................................................................................4-3

4-3 GSU 73 Available Equipment..........................................................................................................4-3

4-4 Contents of P731 Connector Kit (011-01818-00)............................................................................4-3

4-5 Contents of P732 Connector Kit (011-01818-01)............................................................................4-4

5-1 GTP 59 Part Number........................................................................................................................5-1

5-2 GTP 59 Outside Air Temperature Kit..............................................................................................5-1

5-3 Applicable TSO/ETSOs for the GTP 59..........................................................................................5-2

5-4 TSO/ETSO Deviations for the GTP 59 ............................................................................................5-2

5-5 Parts Needed for GTP 59 Installation ..............................................................................................5-3

6-1 GPS Antennas ..................................................................................................................................6-1

6-2 GPS Antenna Minimum Requirements............................................................................................6-1

6-3 XM Antennas...................................................................................................................................6-1

Page viii G3X Installation Manual Revision A 190-01115-01

Page 11

TABLE PAGE

6-4 XM Satellite Radio Antenna Minimum Requirements....................................................................6-2

6-5 Teardrop Footprint Antenna Doubler Design and Installation.........................................................6-7

6-6 ARINC 743 Footprint Antenna Doubler Design and Installation..................................................6-14

6-7 Minimum Distance Required Between Tube Structure and Antenna............................................6-28

8-1 Post-Installation Calibration Procedure Summary...........................................................................8-4

8-2 Data Validity Requirements for AHRS Calibration Procedures......................................................8-5

8-3 Configuration Mode GSU Page Status Boxes..................................................................................8-5

8-4 Magnetometer Interference Test Sequence Example.....................................................................8-23

9-1 GSU 73 AHRS Operating Mode Table............................................................................................9-3

9-2 GSU 73 AHRS Pitch/Bank Limitations for Cold Start While Airborne..........................................9-3

B-1 Thermocouple Kit GPN 011-00981-00...........................................................................................B-1

B-2 GPN: 011-00979-20 – Kit (w/EEPROM and pins)......................................................................... B-3

B-3 GPN: 011-00979-22 – Kit (w/EEPROM and sockets).................................................................... B-3

B-4 Parts supplied for a Shield Block Installation (Figure B-1) ............................................................B-6

B-5 Parts NOT su pplied for a Shield Block Installation (Figure B-1)................................................... B-6

B-6 Shielded Cable Preparations for Garmin Connectors...................................................................... B-8

B-7 Shielded Cable Preparations – (Quick Term) ...............................................................................B-14

B-8 Shielded Cable Preparations for Garmin Connectors.................................................................... B-16

B-9 Parts supplied for a Circular Connector Installation (Figure B-15) .............................................. B-19

B-10 Parts NOT supplied for a Circular Connector Installation (Figure B-15).....................................B-19

B-11 Shielded Cable Preparations for Garmin Connectors....................................................................B-21

B-12 Shielded Cable Preparations – (Quick Term) ...............................................................................B-25

G3X Installation Manual Page ix 190-01115-01 Revision A

Page 12

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. Garmin (Europe) Ltd. 1200 East 151

Street Liberty House, Bulls Copse Road Olathe, Kansas 66062, U.S.A. Hounsdown Business Park Phone: 913/397.8200 Romsey, SO40 9RB, U.K.

FAX: 913/397.0836 Phone: +44/ (0) 870.8501241 Phone: +44/ (0) 870.8501251

Page x G3X Installation Manual Revision A 190-01115-01

Page 13

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.

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.

Garmin International, Inc. Garmin (Europe) Ltd. 1200 East 151

Street Liberty House, Bulls Copse Road Olathe, Kansas 66062, U.S.A. Hounsdown Business Park Phone: 913/397.8200 Romsey, SO40 9RB, U.K.

FAX: 913/397.0836 Phone: +44/ (0) 870.8501241 Phone: +44/ (0) 870.8501251

G3X Installation Manual Page xi 190-01115-01 Revision A

Page 14

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

PURPOSE OF MODIFICATION

1 N/A N/A Improved HSCM accuracy when using +28V supply

Page xii G3X Installation Manual Revision A 190-01115-01

Page 15

1 G3X Installation Overview

1.1 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 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 Section 8

This section describes the non-G3X LRU interfaces. 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 Section 11

This section contains G3X troubleshooting information. This section contains information for ensuring the unit is suitable to be returned to

service.

Appendix A Appendix B Appendix C Appendix D Appendix E

G3X Installation Manual – Installation Overview Page 1-1 190-01115-01 Revision A

This section contains pinout information for all G3X LRU’s. This section contains connector installation instructions. This section contains G3X Outline and Installation Drawings.

This section contains the G3X Interconnect Drawings.

This section contains the G3X External Interface Drawings.

Page 16

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.

Config Module

Autopilot

GMU 44

GTP 59

Config Module

RS-232

A429

RS-485 RS-232

GNS

430(W)

SL 30/40

(1, 2)

RS-232

ELT

RS-232

GDU 37X (PFD1)

Pitot

CAN

Static

GSU 73

A429 (GPS)

A429 (NAV)

A429 (AIR DATA)

(1)

RS-232

A429 (GPS)

A429 (NAV)

GNS

430(W)

RS-232

GMA 240

STEREO/MONO AUDIO

GDU 37X (MFD)

RS-232

GTX 330

(1)

Figure 1-1. G3X Interconnect Example

GDU 37X (PFD2)

RS-232

Notes: (1) Maximum of 2 COM/NAV units installed. (2) GDU 37X to SL40 is TX only.

Page 1-2 G3X Installation Manual –Installation Overview Revision A 190-01115-01

Page 17

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 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

115-01054-00 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

GDU 37X 10-29 Vdc

GMU 44 12Vdc (from GSU 73) Inc. in GSU Current Draw

GSU 73 10-29 Vdc

1.10 Amp @ 14Vdc

0.55 Amp @ 28Vdc

1.75 Amp @ 14Vdc (Max)

0.80 Amp @ 28Vdc (Max)

G3X Installation Manual – Installation Overview Page 1-3 190-01115-01 Revision A

Page 18

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

GDU 370

GDU 375

GMU 44

GSU 73

6.04 inches (153.4 mm)

N/A

5.50 inches (139.8 mm)

7.83 inches (198.8 mm)

2.10 inches (5.33 cm)

3.96 inches

(100.6 mm)

Depth

(GMU 44 Diameter, including

flange*)

3.41 inches (86.7 mm)

*3.35 inches

(85.1 mm)

7.33 inches

(186.2 mm)

Unit 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)

Unit Weight

w/Nutplate

& Connector

Weight

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 G3X Installation Manual –Installation Overview Revision A 190-01115-01

Page 19

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 Page 1-5 190-01115-01 Revision A

Page 20

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

GDU 37X

GSU 73 GTP 59

011-00979-20

(Config module

w/EEPROM

kit)

011-00981-00

(thermocouple

kit)

GMU 44

011-00979-22

(Config module

w/Sockets &

Jackscrew kit)

Socket, Mil

Crimp, Size 20

Pin, Mil Crimp,

Size 22D

Socket, Mil

Crimp, Size 20

Socket, Mil

Crimp, Size 20,

26-30 AWG

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.

Garmin

Contact Part

Number

336-00094-00

336-00021-00

336-00022-00

336-00022-01

Recommended

Positioner

M22520/2-08,

Daniels K13-1

Positronic P/N

9502-4, ITT P/N

M22520/2-09,

Daniels P/N K42

M22520/2-08,

Daniels K13-1

Positronic P/N

9502-5

NOTES

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

Page 1-6 G3X Installation Manual –Installation Overview Revision A 190-01115-01

Page 21

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 Page 1-7 190-01115-01 Revision A

Page 22

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 G3X Installation Manual –Installation Overview Revision A 190-01115-01

Page 23

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 Page 2-1 190-01115-01 Revision A

Page 24

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

Table 2-1. GDU 37X Supply Voltages

Characteristics Specifications

Power Requirements 14/28 VDC

2.2.2 Power Consumption

Table 2-2. GDU 37X Power Requirements

LRU 14V (Maximum) 14V (Typical) 28V (Maximum) 28V (Typical) GDU 370 GDU 375

15W, 1.10 Amp 8.5W, .600 Amp 15W, 0.540 Amp 8.5W, .300 Amp 15W, 1.10 Amp 9.5W, .675 Amp 15W, 0.540 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.

Table 2-3. GDU 37X GPS Specifications

Characteristics Specifications

Acquisition Time 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 Update Rate 5/second, continuous Positional Accuracy <10 meters Antenna Power Supply Voltage (4.5 to 5.0), current (50 mA max)

Page 2-2 G3X Installation Manual – GDU 37X Revision A 190-01115-01

Page 25

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

Model Mount Style

Comant 2480-201 VHF/GPS [1]

Comant 420-10 XM only Antenna

Screw Mount, Teardrop Footprint

Screw Mount, ARINC 743 Footprint

Conn

Type

BNC TNC

Antenna

Type

VHF COM, GPS

Mfr

Comant CI 2480-201 N/A

Antenna Part

Number

TNC XM Comant CI 420-10 N/A

Garmin Order

Number

Suction Cup,

GA 26C

Magnetic or

BNC GPS Garmin 011-00149-04 010-10052-04

Flange Mt

GA 26XM

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

Screw GA 57X [2]

Mount,

ARINC 743

BNC TNC

GPS XM

Garmin 011-01032-10 010-11370-10

Footprint

[1] The GPS antenna connec tor 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 Page 2-3 190-01115-01 Revision A

Page 26

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 G3X Installation Manual – GDU 37X Revision A 190-01115-01

Page 27

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 Page 2-5 190-01115-01 Revision A

Page 28

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.

7.33 in

[186.2 mm]

Cut out panel

to inside line

5.57 in

[141.4 mm]

For corner holes, center punch and drill

(#36) / tap (6/32) to create threaded holes

drill out with 25 drill bit and use Garmin

nut-plate P/N 115-01054-00

Page 2-6 G3X Installation Manual – GDU 37X Revision A 190-01115-01

Page 29

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.

• GMU 44 to GSU 73 Interface: Power, RS-232, RS-485 (19,200 baud)

3.2 Electrical Specifications

Table 3-1. GMU 44 Electrical Specifications

Specification Characteristic

Power Requirements

G3X Installation Manual – GMU 44 Page 3-1 190-01115-01 Revision A

Supply Voltage: 14/28 VDC. See Table 1-3 for current

specifications.

Page 30

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 55,000 Feet

3.4 GMU 44 TSO/ETSO Compliance

Table 3-3. TSO/ETSO Compliance

Applicable

Custom Logic

Device Part

Numbers

All

006-C0048-0(_)

Function

Direction Instrument, Magnetic (Gyroscopically Stabilized)

TSO/ETSO/SAE/

RTCA/EUROCAE

TSO-C6d

ETSO-C6d

AS8013A

Category

Applicable LRU

SW Part

Numbers

All

006-B0224-(__)

except

006-B0224-Z(_)

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 Deviation

TSO-C6d (GMU 44)

ETSO-C6d (GMU 44)

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.

Page 3-2 G3X Installation Manual – GMU 44 Revision A 190-01115-01

Page 31

3.5 Installation Requirements

3.5.1 Equipment Available

Table 3-5. GMU 44 Part Numbers

Model

GMU 44 010-00296-10* 011-00870-10 No

*Included in G3X LRU Kit (K10-00016-00)

Catalog Part

Number

Table 3-6. GMU 44 Accessories

Unit Part Number Installation Rack

Item Garmin P/N Quantity

Sub Assy, Connector Kit, GMU 44 011-00871-00** 1

GMU 44 Universal Mount*** 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

NOTE

If the requirements listed in Table 3-7 cannot be met, a magnetometer interference test must be performed to ensure proper operation of the G3X system. Refer to the AHRS/Magnetometer Installation Considerations document (190-01051-00) available from the Garmin website (

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.

www.garmin.com).

G3X Installation Manual – GMU 44 Page 3-3 190-01115-01 Revision A

Page 32

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

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

3 feet (1.0 meter)

feet (3.0 meters)]

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

1.3 feet (0.4 meter)

feet (3.0 meters)]

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 G3X Installation Manual – GMU 44 Revision A 190-01115-01

Page 33

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

2 Shield Extension Wire 0 M22759/16-22

3, 4, 9 GMU 44 Connector Kit** 1 011-00871-00

5 3-Conductor Cable 0 M27500-22TE3T14 6 2-Conductor Cable 0 M27500-22TE2T14

**Included in G3X Installation Kit (K10-00017-00)

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

Shield Termination

(method optional)

Qty.

Included

GPN or MIL Spec

Parts used depend on method

chosen

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 Page 3-5 190-01115-01 Revision A

Page 34

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

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).

use a screwdriver that contains a magnet when installing or servicing the GMU 44.

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 G3X Installation Manual – GMU 44 Revision A 190-01115-01

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4 GSU 73

4.1 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 Page 4-1 190-01115-01 Revision A

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4.1.1 Features Summary

Air Data Interfaces

Pressure Altitude CAN (1) Density Altitude RS-232 (2 TX/2 RX) Vertical Speed ARINC 429 (4 RX/2 TX) Mach Number OAT Probe (GTP 59) Indicated Airspeed Magnetometer (GMU 44) (1 RS-232 TX/ 1 RS-485 RX) True Airspeed

AHRS

Magnetic Heading 28 Analog inputs, including those allocated as per below: Pitch Angle Dedicated Ammeters (2) Roll Angle Constant Current Source Capability (6) Linear Accelerations Divider Circuits to handle large input voltages (12) Pitch, Roll, Yaw Rotation Rates Frequency Counter Inputs (4) Discrete I/O (4 In/2 Out)

Engine/Airframe

4.2 Electrical Specifications

Table 4-1. GSU 73 Supply Specifications

Characteristic Specification

Input Voltage Range 10-29 Vdc*

Power Input

*Garmin recommends using a Mod 1level GSU 73 in aircraft that exclusively use a +28V supply.

1.75 Amp @ 14 Vdc (Max)

0.80 Amp @ 28 Vdc (Max)

Page 4-2 G3X Installation Manual – GSU 73 Revision A 190-01115-01

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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

Unit Operating Temperature Range

Max Outer Case Temperature

-85°C to +85°C

-40°C to +70°C

+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 Page 4-3 190-01115-01 Revision A

Page 38

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

• 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.

4.5 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 G3X Installation Manual – GSU 73 Revision A 190-01115-01

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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 Page 4-5 190-01115-01 Revision A

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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.

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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 Page 4-7 190-01115-01 Revision A

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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.

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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 Page 5-1 190-01115-01 Revision A

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5.2.1 Additional Equipment Required

• Cables - The installer will supply all system cables.

5.3 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

Air Data Computer

TSO-C106

ETSO-C106

Applicable LRU

SW Part Numbers

Not Applicable Not Applicable

Applicable CLD

Part Numbers

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 Deviation

TSO-C106

ETSO-C106 1. Garmin was granted a deviation from ETSO-C106 to use Society of

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.

Automotive Engineers (SAE) AS 8002 Rev A instead of SAE AS 8002 as the Minimum Performance Standard.

Page 5-2 G3X Installation Manual – GTP 59 Revision A 190-01115-01

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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 Qty. Included GPN

1 Ring Terminal 2 3-Conductor Cable 3 OAT Sensor 4 Nut 1 210-00055-00 5 Washer 1 212-00026-00

1. Prepare the surface. The metal body of the OAT probe should be grounded to the aircraft. The

installation requirements vary depending on the airframe material composition. a. Aluminum airframe: When a mounting location has been found, prepare the inside surface of

the aircraft. Remove all paint from the contacting area and clean with a degreaser.

b. Composite airframe: If possible, mount the OAT probe through a grounded metal strap or

band. Otherwise, mount the OAT probe in an area of the airframe that has a significant amount of underlying metal foil or mesh. To ensure adequate conductivity, it may be necessary to mount the OAT probe through a metal doubler. Use fasteners that allow a conductive path to the airframe.

2. Mount the OAT probe on the prepared surface. Place the ring terminal (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 Page 5-3 190-01115-01 Revision A

1 494-00022-xx

Page 46

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 G3X Installation Manual – GTP 59 Revision A 190-01115-01

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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

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)

Part

Number

Description Weight 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 1565 to 1585 MHz Gain 16 to 25 dB typical, 40dB max. Noise Figure <4.00 dB Nominal Output Impedance 50 ohms Supply Voltage 4.5 to 5.5 VDC Supply Current up to 50 mA Output Connector BNC

6.2 XM Antennas

Table 6-3. XM Antennas

Model

GA 26XM 013-00268-10 XM Antenna NA

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 Page 6-1 190-01115-01 Revision A

Part

Number

Description Weight Mounting Configuration

Flange, Magnetic, or Suction Cup Mount (for in-cabin mounting)

Stud mount (Tear-drop form factor)

Thru-mount (ARINC 743 style mount)

Page 48

Table 6-4. XM Satellite Radio Antenna Minimum Requirements

Characteristics Specifications

Frequency Range 2332.5 to 2345 MHz Gain (Typical) 24 dB* Noise Figure <1.2 dB Nominal Output Impedance 50 ohms Supply Voltage 3.6 to 5.5 VDC Supply Current (maximum) 55 mA Operating Temperature Gain -50 to +85°C

*For each 1 dB gain over 24 dB, add 1 dB of attenuation into the antenna cable path between the antenna and the GDU 375.

It is the installer’s responsibility to ensure that their choice of antenna meets FAA standards according to the specific installation. This installation manual discusses only the antennas listed in 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 G3X Installation Manual – Antennas Revision A 190-01115-01

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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. Mount the antenna on top of the aircraft in a location with an unobstructed view of the sky, as close to level as possible with respect to the normal cruise flight attitude of the aircraft. If the normal flight attitude is not known, substitute the waterline, which is typically referenced as level while performing a weight and balance check.

2. The GPS antenna should be mounted in a location to minimize the effects of airframe shadowing during typical maneuvers. Typically mounting farther away from the tail section reduces signal blockage seen by the GPS antenna.

3. The GPS antenna should ideally be located at the opposite end of the aircraft from the COM unit in order to make the GPS less vulnerable to harmonics radiated from the COM itself (see Section 1.7.3 for more GPS/COM interference information).

4a. The GPS antenna should be mounted no closer than two feet (edge to edge) and ideally

three feet from any VHF COM antenna or any other antenna which may emit harmonic (or other) interference at the L1 frequency of 1575.42 MHz. An aircraft EMC 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

The separation requirement does not apply to GPS and COM combination antennas, provided the antenna has been tested to meet Garmin’s minimum performance standards. The separating requirement includes the combination with an XM antenna element as well.

4b. The GPS antenna should be mounted no closer than two feet (edge to edge) and ideally

three feet from any antennas emitting more than 25 watts of power. An aircraft EMC check can verify the degradation of GPS in the presence of interference signals.

4c. To minimize the effects of shadowing at 5° elevation angles, the GPS antenna should be

mounted no closer than 6 inches (edge to edge) from other antennas, including passive antennas such as another GPS antenna or XM antenna.

5. To maintain a constant gain pattern and limit degradation by the windscreen, avoid mounting the antenna closer than 3 inches from the windscreen.

6. For multiple GPS installations, the antennas should not be mounted in a straight line from the front to the rear of the fuselage. Also varying the mounting location will help minimize any aircraft shading by the wings or tail section (in a particular azimuth, when one antenna is blocked the other antenna may have a clear view).

G3X Installation Manual – Antennas Page 6-3 190-01115-01 Revision A

Page 50

Figure 6-1 shows the recommended placement of antennas.

Figure 6-1. Recommended Antenna Placement

Page 6-4 G3X Installation Manual – Antennas Revision A 190-01115-01

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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 Page 6-5 190-01115-01 Revision A

Page 52

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 G3X Installation Manual – Antennas Revision A 190-01115-01

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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)

Number of Rivets Required

Type of Rivets Required1

Skin Preparation for Rivets

Doubler Preparation for Rivet

Skin Cutout Detail (Figure)

Doubler Installation (Figure)

Notes:

1. Rivet length determined at installation, dependent on thickness of material (rivet length = grip length +

1.5*rivet diameter)

Figure 6-4 Figure 6-5 Figure 6-6

12 16 16

MS20426AD4-x MS20426AD4-x MS20426AD4-x

Dimple Dimple Countersink

Countersink Countersink None

Figure 6-8 Figure 6-9 Figure 6-10

Figure 6-11 Figure 6-12 Figure 6-13

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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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.

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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"

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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

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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"

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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"

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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"

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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”

Doubler Design (Figure)

Number of Rivets Required

Type of Rivets Required1

Skin Preparation for Rivets

Doubler Preparation for Rivets

Skin Cutout Detail (GA 55A)

Doubler Installation (Figure)

Figure 6-14 Figure 6-15 Figure 6-16

12 16 16

MS20426AD4-x MS20426AD4-x MS20426AD4-x

Dimple Dimple Countersink

Countersink Countersink None

Figure 6-18 Figure 6-19 Figure 6-20

Figure 6-21 Figure 6-22 Figure 6-23

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.

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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

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6.5.3 Reference Figures

Figure 6-14. Doubler Design, ARINC 743 Footprint Antenna,

Skin Thickness 0.032" to 0.049"

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Figure 6-15. Doubler Design, ARINC 743 Footprint Antenna,

Skin Thickness 0.049" to 0.051"

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Figure 6-16. Doubler Design, ARINC 743 Footprint Antenna,

Skin Thickness 0.051" to 0.063"

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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"

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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"

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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"

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Figure 6-23. Doubler Installation, ARINC 743 Footprint, Skin Thickness 0.051" to 0.063"

Figure 6-24. Installation of ARINC 743 Footprint Antenna

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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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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

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Figure 6-27. Example Non-structural Antenna Mounting Under Glareshield

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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

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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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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)

Tube Diameter

d (in)

0.625 3.6

0.75 4.3

1.00 5.7

1.25 7.2

0.625 7.2

0.75 8.6

1.00 11.5

1.25 14.3

Minimum Distance

l (in)

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7 Software, Configuration, Databases, and XM Activation

7.1 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)

• 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

8.2 GDU 37X Test Procedure

Test the GPS Receiver:

1. Power on unit and use the FMS Joystick to select the Info Page.

2. Verify that the GPS receiver is functional and able to calculate its present position.

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Test the 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 AHRS Orientation Validate GSU 73

B Pitch/Roll Offset

C Magnetometer

D Heading Offset

E Engine Run-Up

F Magnetometer

Procedure Name Procedure

Description

Orientation Level Aircraft Procedure B is required for all

Compensation

Compass Rose

Calibration

Taxi Maneuver Compass Rose

Compensation

Alignment with Magnetic North Validate vibration

Vibration Test

characteristics of installation Validate no

Interference Test

magnetic interference with GMU 44

Installations Requiring

Procedure

Procedure A is required for all installations

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 Valid Status Required

Pitch/Roll Offset GPS or Air Data Magnetic Calibration GPS or Magnetometer

Heading Offset

Engine Run-Up GPS or Air Data

Magnetometer Interference Test

Mounting Orientation Identification 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.

GPS or Air Data. Magnetometer always required.

Table 8-3. Configuration Mode GSU Page Status Boxes

Status Box Valid Status

GPS 3D or 3D Differential GPS solution available

Air Data

Magnetometer Measurement of local 3D magnetic field available

The GSU Page status boxes referred to in Table 8-3 are shown in the following figure.

True Airspeed (TAS) available. NOTE: A valid outside air temperature (OAT) measurement is required for TAS to be valid.

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).

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).

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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