Garmin | G500H TXi | Garmin G500H TXi G500H TXi Part 27 AML STC Maintenance Manual (ICA)

Garmin G500H TXi G500H TXi Part 27 AML STC Maintenance Manual (ICA)
G500H TXi Part 27 AML STC
Maintenance Manual
Contains Instructions for Continued Airworthiness
for STC SR02622SE
Aircraft make, model, registration number, serial number, and
applicable STC configuration information must be completed in
Appendix A and saved with aircraft permanent records.
© 2018
Garmin International, Inc., or its subsidiaries
All Rights Reserved
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For aviation product support, visit www.flyGarmin.com.
For information regarding the Aviation Limited Warranty, refer to Gamin's website.
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Page ii
INFORMATION SUBJECT TO EXPORT CONTROL LAWS
This document may contain information which is subject to the Export Administration Regulations (EAR) issued by the
United States Department of Commerce (15 CFR, chapter VII, subchapter C) and which may not be exported, released,
or disclosed to foreign nationals inside or outside of the United States without first obtaining an export license.
This information in this document is subject to change without notice. For updates and supplemental information
regarding the operation of Garmin products visit www.flyGarmin.com.
Software License Notification
AES Encryption
The product may include AES file encryption software, © 2002 DR. Brian Gladman, subject to the following license:
The free distribution and use of this software in both source and binary form is allowed (with or without changes)
provided:
• Distributions of this source code include the above copyright notice, this list of conditions, and the following
disclaimer.
• Distribution in binary form include the above copyright notice, this list of conditions, and the following
disclaimer in the documentation and/or other associated materials.
• The copyright holder’s name is not used to endorse products built using this software without specific written
permission.
Alternatively, provided this notice is retained in full, this product may be distributed under the terms of the GNU
General Public License (GPL) in which case the provisions of the GPL apply instead of those given above.
Disclaimer
The AES file encryption software is provided “as is” with no explicit or implied warranties in respect of its properties,
including, but not limited to, correctness and/or fitness for purpose.
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Page iii
SOFTWARE LICENSE AGREEMENT FOR GARMIN AVIATION PRODUCTS
The software embedded in your Garmin product (the “Licensed Software”) is owned by Garmin International, Inc.
(“Garmin” or “us”). The Licensed Software is protected under copyright laws and international copyright treaties. The
Licensed Software is provided under this Software License Agreement (hereinafter the “Agreement”) and is subject to
the following terms and conditions which are agreed to by End User (“Licensee”, “you” or “your”), on the one hand, and
Garmin and its licensors and affiliated companies of Garmin and its licensors, on the other hand. The Licensed Software
is licensed, not sold, to you. Garmin and Licensee may be referred to individually as a “Party” or jointly as the “Parties.”
IMPORTANT: CAREFULLY READ THIS ENTIRE AGREEMENT BEFORE USING THIS PRODUCT.
INSTALLING, COPYING, OR OTHERWISE USING THIS PRODUCT INDICATES YOUR
ACKNOWLEDGMENT THAT YOU HAVE READ THIS AGREEMENT AND AGREE TO ITS TERMS AND
CONDITIONS. IF YOU DO NOT AGREE TO THESE TERMS AND CONDITIONS, YOU MAY NOT USE THIS
PRODUCT.
1.
Definitions. The following capitalized terms shall have the meanings set forth below:
a. “Device” means any Garmin device that is delivered by or on behalf of Garmin to Licensee onto
which the Licensed Software is installed.
b. “Documentation” means Gamin's then-current instructional, technical or functional documentation
relating to the Devices or Licensed Software which is delivered or made available by Garmin in
connection with this Agreement.
c. “Licensed Software” means the software in binary executable form that is embedded in the
i. Devices and/or made available for use on the Devices via a software loader card.
d. “Permitted Purpose” means operating and using the Device on which the Licensed Software is
installed for the Device's intended use.
2.
License.
a. License Grant. Subject to the terms and conditions of this Agreement and Licensee's compliance with
the terms and conditions of this Agreement, Garmin hereby grants to Licensee a limited, royalty-free,
non-exclusive, non-sublicenseable, non-transferable and revocable right and license to use and
perform the Licensed Software as installed on the Devices and the Documentation solely for the
Permitted Purpose and only during the term of this Agreement, provided that the Licensed Software
may only be used by Licensee on Devices on which the Licensed Software has been installed or
otherwise made available by Garmin. Reservation of Rights. Garmin retains exclusive ownership of
all right, title and interest in and to the Licensed Software and Documentation. All of Gamin's rights in
and to the Licensed Software and Documentation not expressly licensed to Licensee under Section 2.1
are expressly reserved for Garmin. Nothing contained in this Agreement shall be construed as
conferring by implication, acquiescence, or estoppel any license or other right upon Licensee. Without
limiting the foregoing, the Parties acknowledge and agree that this Agreement grants Licensee a
license of the Licensed Software under the terms of Section 2.1, and shall not in any manner be
construed as a sale of the Licensed Software or any rights in the Licensed Software.
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3.
Restrictions; Protection and Third Party Devices.
a. Prohibited Uses. Licensee shall not, shall not attempt to and shall not permit any third party to:
(a) sublicense, lease, loan, sell, resell, market, transfer, rent, disclose, demonstrate, or distribute the
Licensed Software or Documentation to any third party; (b) uninstall the Licensed Software from the
Device on which it was originally installed; (c) make any use of or perform any acts with respect to the
Licensed Software or Documentation other than as expressly permitted in accordance with the terms
of this Agreement; (d) use the Licensed Software or Documentation in any manner that violates any
applicable law; (e) reproduce or copy the Licensed Software; (f) modify, adapt, alter, translate, port,
create derivative works of, reverse engineer, decompile or disassemble the Licensed Software or
Documentation or otherwise derive the source code or other proprietary information or trade secrets
from the Licensed Software; (g) remove, alter, or obscure any proprietary notices from the Licensed
Software or Documentation; (h) use the Licensed Software or Documentation to provide services to
third parties (such as business process outsourcing, service bureau applications or third party training);
(i) use the Licensed Software on any equipment, hardware or device other than a Device; or (j) export,
re-export or otherwise distribute, directly or indirectly, the Licensed Software or Documentation to a
jurisdiction or country to which the export, re- export or distribution of such Licensed Software or
Documentation is prohibited by applicable law.
b. Protection of Software and Documentation. Licensee shall use its best efforts to protect the Licensed
Software and Documentation from unauthorized access, distribution, modification, display,
reproduction, disclosure or use with at least the same degree of care as Licensee normally uses in
protecting its own software and documentation of a similar nature from unauthorized access,
distribution, modification, display, reproduction, disclosure or use. Licensee shall limit access to the
Licensed Software and Documentation to only those employees of Licensee who require access to the
Licensed Software or Documentation for the Permitted Purpose and who have been made aware of the
restrictions set forth in this Agreement. Licensee shall take prompt and appropriate action to prevent
unauthorized use or disclosure of the Licensed Software and Documentation.
4.
Term and Termination.
a. Term. The term of this Agreement shall commence on the Effective Date, and shall continue in
perpetuity thereafter, unless terminated earlier as provided in this Section 4.
b. Termination by Garmin. Garmin may immediately terminate this Agreement upon written notice to
Licensee if Licensee commits a material breach of this Agreement or breaches a material term of this
Agreement.
c. Effect of Termination. Upon any termination of this Agreement for any Party: (a) Licensee shall
immediately cease all use of the Licensed Software and Documentation; (b) all rights and licenses
granted to Licensee to the Licensed Software and Documentation and Gamin's related obligations
shall immediately terminate; and (c) Sections 4.3, 5 and 6 shall survive.
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Page v
5.
Disclaimer; Limitations of Liability; Indemnity.
a. Disclaimer. To the maximum extent permitted by applicable law, the licensed software and
documentation (including any results to be obtained from any use of the licensed software and
documentation) are provided “as is” and “as available” with no warranties, guarantees or
representations and neither Garmin nor its affiliates make any representation, warranty or guarantee,
statutory or otherwise, under law or from the course of dealing or usage of trade, express or implied,
including any warranties of merchantability, fitness for a particular purpose, non-interference, noninfringement, title, or similar, under the laws of any jurisdiction. Garmin does not warrant that the
licensed software or documentation will meet licensee's requirements or that operation of the
software will be uninterrupted or error free. Licensee assumes the entire risk as to the quality and
performance of the licensed software and documentation. The licensed software is not intended for
use in any nuclear, medical, or other inherently dangerous applications, and Garmin disclaims all
liability for any damage or loss caused by such use of the licensed software.
b. Exclusion of damages; limitation of liability. Notwithstanding anything to the contrary herein, to the
maximum extent permitted by applicable law, under no circumstances and regardless of the nature of
any claim shall Garmin be liable to licensee for an amount in excess of USD $100, or be liable in any
amount for any special, incidental, consequential, punitive or indirect damages, loss of goodwill or
profits, liquidated damages, data loss, computer failure or malfunction, attorneys' fees, court costs,
interest or exemplary or punitive damages, arising out of or in connection with the use or
performance or non-performance of the licensed software or documentation, even if Garmin has been
advised of the possibility of such loss or damages.
c. Indemnity. Licensee shall indemnify, defend and hold Garmin and its affiliates harmless against any
and all losses, claims, actions, causes of action, liabilities, demands, fines, judgments, damages and
expenses suffered or incurred by Garmin or its affiliated companies in connection with: (a) any use or
misuse of the Licensed Software or Documentation by Licensee or any third party in Licensee's
reasonable control; or (b) Licensee's breach of this Agreement.
6.
General.
a. No Devices or Services. Licensee acknowledges and agrees that nothing in this Agreement shall be
construed as requiring Garmin to: (a) provide or supply the Devices or any other devices or hardware
to Licensee; (b) grant any licenses to any software other than the Licensed Software; or (c) provide any
services, such as support, maintenance, installation or professional services for the Licensed Software.
b. Non-Exclusive. Each Party's rights and obligations under this Agreement are non-exclusive. Garmin is
not precluded from marketing, licensing, providing, selling or distributing the Licensed Software or
Documentation, or any other products, software, documentation or services, either directly or through
any third party.
c. Assignment. Licensee may not assign this Agreement or any of its rights, interests or obligations
hereunder without the prior written consent of Garmin. Any purported assignment in violation of this
Section 6.3 shall be null and void. Subject to the foregoing, this Agreement shall be binding upon and
shall inure to the benefit of the Parties and their respective successors and permitted assigns and
transferees.
d. Feedback and Data. Licensee may from time to time provide feedback, comments, suggestions,
questions, ideas, or other information to Garmin concerning the Licensed Software or Documentation
or Gamin's products, services, technology, techniques, processes or materials (“Feedback”). Garmin
may in connection with any of its products or services freely use, copy, disclose, license, distribute and
otherwise exploit such Feedback in any manner without any obligation, payment, royalty or restriction
whether based on intellectual property rights or otherwise.
e. Governing Law. The validity, interpretation and enforcement of this Agreement will be governed by
the substantive laws, but not the choice of law rules, of the state of Kansas. This Agreement shall not be
governed by the 1980 UN Convention on Contracts for the International Sale of Goods.
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G500H TXi Part 27 AML STC Maintenance Manual
Page vi
f.
g.
h.
i.
j.
k.
l.
190-02401-01
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Legal Compliance. You represent and warrant that (i) you are not located in a country that is subject to
a U.S. Government embargo, or has been designated by the U.S. Government as a “terrorist
supporting” country, and (ii) you are not listed on any U.S. Government list of prohibited or restricted
parties.
Injunctive Relief. The Parties acknowledge and agree that irreparable damage would occur if any
provision of this Agreement was not performed in accordance with its specific terms or was otherwise
breached and as such, the Parties will be entitled to an injunction or injunctions to prevent breaches of
this Agreement and to enforce specifically the performance of the terms and provisions of this
Agreement without proof of actual damages, this being in addition to any other remedy to which any
Party is entitled at law or in equity.
Amendments and Waivers. This Agreement may be amended and any provision of this Agreement
may be waived, provided that any such amendment or waiver will become and remain binding upon a
Party only if such amendment or waiver is set forth in a writing by such Party. No course of dealing
between or among any persons having any interest in this Agreement will be deemed effective to
modify, amend or discharge any part of this Agreement or any rights or obligations of any Party under
or by reason of this Agreement. No delay or failure in exercising any right, power or remedy hereunder
will affect or operate as a waiver thereof; nor will any single or partial exercise thereof or any
abandonment or discontinuance of steps to enforce such a right, power or remedy preclude any further
exercise thereof or of any other right, power or remedy. The rights and remedies hereunder are
cumulative and not exclusive of any rights or remedies that any Party would otherwise have.
Severability. The provisions of this Agreement will be severable in the event that for any reason
whatsoever any of the provisions hereof are invalid, void or otherwise unenforceable, any such invalid,
void or otherwise unenforceable provisions will be replaced by other provisions which are as similar
as possible in terms to such invalid, void or otherwise unenforceable provisions but are valid and
enforceable and the remaining provisions will remain valid and enforceable to the fullest extent
permitted by applicable law, in each case so as to best preserve the intention of the Parties with respect
to the benefits and obligations of this Agreement.
No Third-Party Beneficiaries. This Agreement is solely for the benefit of the Parties and does not
confer on third parties any remedy, claim, reimbursement, claim of action or other right in addition to
those existing without reference to this Agreement.
Entire Agreement. This Agreement shall constitute the entire agreement between Garmin and you with
respect to the subject matter hereof and will supersede all prior negotiations, agreements and
understandings of Garmin and you of any nature, whether oral or written, with respect to such subject
matter.
Interpretation. In this Agreement: (a) headings are for convenience only and do not affect the
interpretation of this Agreement; (b) the singular includes the plural and vice versa; (c) the words 'such
as', 'including', 'particularly' and similar expressions are not used as, nor are intended to be, interpreted
as words of limitation; (d) a reference to a person includes a natural person, partnership, joint venture,
government agency, association, corporation or other body corporate; a thing includes a part of that
thing; and a party includes its successors and permitted assigns; and (e) no rule of construction applies
to the disadvantage of a Party because that Party was responsible for the preparation of this
Agreement. Any translation of this Agreement from English is provided as a convenience only. If this
Agreement is translated into a language other than English and there is a conflict of terms between the
English version and the other language version, the English version will control.
G500H TXi Part 27 AML STC Maintenance Manual
Page vii
RECORD OF REVISIONS
Revision
1
190-02401-01
Rev. 1
Revision Date
11/12/2018
Description
Initial Release
G500H TXi Part 27 AML STC Maintenance Manual
Page viii
DEFINITIONS OF WARNINGS, CAUTIONS, AND NOTES
WARNING
Warnings indicate that injury or death is possible if the instructions are disregarded.
CAUTION
Cautions indicate that damage to the equipment is possible.
NOTE
Notes provide additional information.
WARNING
This product, its packaging, and its components contain chemicals known to the State of California to cause
cancer, birth defects, or reproductive harm. This notice is being provided in accordance with California's
Proposition 65. For questions or additional information, refer to WWW.GARMIN.COM/PROP65.
WARNING
Perchlorate Material – special handling may apply. Refer to WWW.DTSC.CA.GOV/
HAZARDOUSWASTE/PERCHLORATE.
CAUTION
To avoid damage to the GDU 700( )/1060, take precautions to prevent Electrostatic Discharge (ESD) when
handling the unit, connectors, and associated wiring. ESD damage can be prevented by touching an object of
the same electrical potential as the unit before handling the unit itself.
CAUTION
The GDU 700( )/1060 has a special anti-reflective coated display that is sensitive to skin oils, waxes, and
abrasive cleaners. Cleaners containing ammonia will harm the anti-reflective coating. Clean the display with a
clean, lint-free cloth and a cleaner that is safe for anti-reflective coatings.
CAUTION
Do not store any G500H TXi component in or near water.
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Table of Contents
1.
INTRODUCTION ............................................................................................................................................... 1-1
1.1
PURPOSE ............................................................................................................................................................ 1-1
1.2
SCOPE................................................................................................................................................................ 1-1
1.3
APPLICABILITY ..................................................................................................................................................... 1-1
1.4
PUBLICATIONS ..................................................................................................................................................... 1-1
1.5
REVISION AND DISTRIBUTION .................................................................................................................................. 1-1
1.6
TERMINOLOGY AND ACRONYMS ............................................................................................................................... 1-1
1.6.1
Terminology ............................................................................................................................................. 1-1
1.6.2
Acronyms ................................................................................................................................................. 1-2
2.
SYSTEM DESCRIPTION...................................................................................................................................... 2-1
2.1
SYSTEM OVERVIEW............................................................................................................................................... 2-1
2.1.1
PFD Functionality..................................................................................................................................... 2-1
2.1.2
MFD Functionality ................................................................................................................................... 2-1
2.1.3
Entering Configuration Mode .................................................................................................................. 2-1
2.1.4
SD Card Location Options ........................................................................................................................ 2-1
2.1.5
Electrical Load Information...................................................................................................................... 2-2
2.2
LRU DESCRIPTION, CONTROL, AND OPERATION ......................................................................................................... 2-2
2.2.1
GDU 700P Display .................................................................................................................................... 2-2
2.2.2
GDU 700L Display .................................................................................................................................... 2-3
2.2.3
GDU 1060 Display .................................................................................................................................... 2-4
2.2.4
GCU 485 Control Unit .............................................................................................................................. 2-5
2.2.5
Backup GPS Antenna ............................................................................................................................... 2-5
2.2.6
GSU 75H ADAHRS .................................................................................................................................... 2-6
2.2.7
GMU 44( ) Magnetometer ....................................................................................................................... 2-6
2.2.8
GTP 59 OAT Probe .................................................................................................................................... 2-7
2.2.9
FS 510 ...................................................................................................................................................... 2-7
3.
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ....................................................................................... 3-1
3.1
AIRWORTHINESS LIMITATIONS ................................................................................................................................ 3-1
3.2
SERVICING INFORMATION ...................................................................................................................................... 3-2
3.2.1
Periodic Maintenance Instructions .......................................................................................................... 3-2
3.2.2
Special Tools ............................................................................................................................................ 3-2
3.3
MAINTENANCE INTERVALS ..................................................................................................................................... 3-2
3.4
VISUAL INSPECTION .............................................................................................................................................. 3-3
3.5
ELECTRICAL BONDING CHECK .................................................................................................................................. 3-4
3.6
OVERHAUL PERIOD ............................................................................................................................................... 3-4
3.7
SPECIAL INSPECTION REQUIREMENTS ........................................................................................................................ 3-5
3.7.1
GTP 59 OAT .............................................................................................................................................. 3-5
3.7.2
GMU 44( ) ................................................................................................................................................ 3-5
3.8
APPLICATION OF PROTECTIVE TREATMENTS ............................................................................................................... 3-5
3.9
DATA RELATIVE TO STRUCTURAL FASTENERS ............................................................................................................. 3-5
3.10 ADDITIONAL INSTRUCTIONS .................................................................................................................................... 3-5
4.
TROUBLESHOOTING ........................................................................................................................................ 4-1
4.1
GENERAL SYSTEM TROUBLESHOOTING ...................................................................................................................... 4-1
4.1.1
Configuration & Maintenance Logs ......................................................................................................... 4-1
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4.1.2
Configuration Summary .......................................................................................................................... 4-2
4.1.3
Flight Data Logs....................................................................................................................................... 4-2
4.1.4
ADAHRS Log Download ........................................................................................................................... 4-3
4.1.5
Screen Shot .............................................................................................................................................. 4-3
4.2
CONNECTOR INFORMATION ................................................................................................................................... 4-4
4.2.1
GCU 485................................................................................................................................................... 4-4
4.2.2
GSU 75H .................................................................................................................................................. 4-5
4.2.3
GMU 44 ................................................................................................................................................... 4-6
4.2.4
GMU 44B ................................................................................................................................................. 4-7
4.2.5
GTP 59 ..................................................................................................................................................... 4-7
4.3
TROUBLESHOOTING FLOW CHARTS........................................................................................................................... 4-8
5.
EQUIPMENT, MAINTENANCE, AND CHECKOUT PROCEDURES ........................................................................... 5-1
5.1
GDU 1060/700 ................................................................................................................................................. 5-1
5.1.1
Removal................................................................................................................................................... 5-2
5.1.2
Cooling Fan Replacement ........................................................................................................................ 5-3
5.1.3
Configuration Module Replacement ........................................................................................................ 5-4
5.1.4
Master Configuration Module Replacement............................................................................................ 5-5
5.1.5
Re-installation ......................................................................................................................................... 5-5
5.2
GCU 485 ........................................................................................................................................................... 5-6
5.2.1
Removal................................................................................................................................................... 5-6
5.2.2
Re-Installation ......................................................................................................................................... 5-6
5.3
GSU 75H .......................................................................................................................................................... 5-7
5.3.1
Removal................................................................................................................................................... 5-8
5.3.2
Installation .............................................................................................................................................. 5-8
5.3.3
Checkout.................................................................................................................................................. 5-8
5.4
GMU 44( ) ........................................................................................................................................................ 5-9
5.4.1
Removal................................................................................................................................................. 5-11
5.4.2
Re-Installation ....................................................................................................................................... 5-11
5.4.3
Checkout................................................................................................................................................ 5-11
5.5
GTP 59 ........................................................................................................................................................... 5-12
5.5.1
Removal................................................................................................................................................. 5-12
5.5.2
Re-Installation ....................................................................................................................................... 5-12
5.5.3
Checkout................................................................................................................................................ 5-12
5.6
BACKUP GPS ANTENNA....................................................................................................................................... 5-13
5.6.1
Removal................................................................................................................................................. 5-14
5.6.2
Installation ............................................................................................................................................ 5-14
5.6.3
Checkout................................................................................................................................................ 5-14
5.7
CALIBRATION..................................................................................................................................................... 5-15
5.7.1
Attitude/Heading .................................................................................................................................. 5-15
5.7.2
Analog NAV Calibration ......................................................................................................................... 5-15
5.8
UPLOADING SOFTWARE ....................................................................................................................................... 5-15
5.9
SYSTEM CHECKS ................................................................................................................................................. 5-16
5.9.1
Configuration Ground Check .................................................................................................................. 5-16
5.9.2
LRU Status check ................................................................................................................................... 5-16
5.9.3
Pitot-Static, Airspeed Setting, and Altimeter Checks ............................................................................. 5-16
APPENDIX A
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INSTALLATION SPECIFIC INFORMATION .................................................................................................................. A-1
G500H TXi Part 27 AML STC Maintenance Manual
Page xi
1. INTRODUCTION
1.1 Purpose
This document is designed for use by the installing agency of the Garmin G500H TXi system as a Maintenance Manual
and ICA in response to FAR Part 27.1529, and Part 27 Appendix A. This manual includes a description of the G500H TXi
system and maintenance information required by the operator to adequately maintain the Garmin G500H TXi system
installed under AML STC SR02622SE.
1.2 Scope
This document provides maintenance instructions and identifies the Instruction for Continued Airworthiness for the
modification of the aircraft for installation of the Garmin G500H TXi system installed under AML STC SR02622SE.
1.3 Applicability
This document applies to all aircraft with the G500H TXi system installed in accordance with AML STC SR02622SE.
Modification of an aircraft by this STC obligates the aircraft operator to include the maintenance information provided
by this document in the operator’s Aircraft Maintenance Manual and the operator’s Aircraft Scheduled Maintenance
Program, if applicable.
1.4 Publications
In addition to this manual, the following documents are recommended for performing maintenance on the G500H TXi
system. It is the responsibility of the owner/operator to ensure the latest applicable versions of these documents are used
during operation, servicing, or maintenance of the G500H TXi system.
Table 1-1: Reference Documentation
Document
Garmin P/N
G500H TXi Part 27 AML STC Installation Manual
190-02401-00
RFMS for the Garmin G500H TXi Display System
190-02401-02
1.5 Revision and Distribution
This document is required for maintaining the continued airworthiness of the aircraft. Garmin Dealers may obtain the
latest revision of this document at the Garmin Dealer Resource Center, https://dealers.garmin.com. Dealers are notified of
manual revision changes via a Garmin Service Bulletin posted to the Dealer Resource Center. Owner and operators may
obtain the latest revision of this document at www.flyGarmin.com or by contacting a Garmin dealer. Garmin contact
information is available at www.flyGarmin.com.
1.6 Terminology and Acronyms
1.6.1
Terminology
Except where specifically noted, references made to the “GDU 1060/700” will apply to the GDU 1060, GDU 700P, and
GDU 700L equally. Except where specifically noted, references made to the “G500H TXi” will apply to an installed
system with one or more GDU 1060 or GDU 700 and all LRUs interfaced to the GDU. Except where specifically noted,
references made to Garmin products with a “( )” designation after the model number refer to all sub-models in that
series. (i.e., a reference to GDU 700() refers to both the GDU 700P and the GDU 700L variants).
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Throughout this document references will be made to metallic aircraft. For the purposes of this manual, metallic aircraft
will be those with an aluminum skin. Nonmetallic aircraft refers to all other aircraft (e.g., composite skin). Unless
otherwise stated, all units of measure are US standard units.
1.6.2
Acronyms
The following terminology is used within this document.
ADAHRS:
ADC:
AES:
AFM:
AFMS:
AHRS:
AML:
BIT:
CAR:
CE:
CFR:
CG:
COM:
ESD:
FAA:
FAR:
GCU:
GDC:
GDL:
GDU:
GMU:
GND:
GNS:
GPL:
GPS:
GRS:
GSU:
GTN:
GTP:
HSI:
Air Data & Attitude Heading Reference
System
Air Data Computer
Advanced Encryption Standard
Airplane Flight Manual
Airplane Flight Manual Supplement
Attitude Heading Reference System
Approved Model List
Built In Test
Civil Air Regulation
European Committee
Code of Federal Regulations
Center of Gravity
Communication Radio
Electro Static Discharge
Federal Aviation Administration
Federal Aviation Regulation
Garmin Control Unit
Garmin Data Computer
Garmin Datalink LRU
Garmin Display Unit
Garmin Magnetometer Unit
Ground
Garmin Navigation System
General Public License
Global Positioning System
Garmin Reference System
Garmin Sensor Unit
Garmin Touch Navigator
Garmin Temperature Probe
Horizontal Situation Indicator
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IAS:
Indicated Airspeed
ICA:
Instructions for Continued Airworthiness
ID:
Identifier
ISA:
International Standard Atmosphere
LCD:
Liquid Crystal Display
LRU:
Line Replaceable Unit
MAG:
Magnetic
MFD:
Multi-function Display
MIN:
Minimum
NAV:
Navigation
OAT:
Outside Air Temperature
ODA:
Organization Designation Authorization
PFD:
Primary Flight Display
PN:
Part Number
POH:
Pilot’s Operating Handbook
PPS:
Pulse Per Second
PWR:
Power
RFM:
Rotorcraft Flight Manual
RFMS:
Rotorcraft Flight Manual Supplement
SAT:
Standard Air Temperature
SBAS:
Satellite Based Augmentation System
SD:
SanDisk Memory
STC:
Supplemental Type Certificate
SVT:
Synthetic Vision Technology
SYS:
System
TAT:
Total Air Temperature
TCAD:
Traffic Collision and Avoidance
TSO:
Technical Standard Order
VDC:
Volts of Direct Current
WAAS:
Wide Area Augmentation System
XM:
XM Satellite Radio
G500H TXi Part 27 AML STC Maintenance Manual
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2. SYSTEM DESCRIPTION
2.1 System Overview
The G500H TXi installation can provide PFD and MFD functions. Three display models, the GDU 700P, GDU 700L,
and GDU 1060 are used to convey the information.
2.1.1
PFD Functionality
The PFD provides at a minimum attitude, heading, airspeed, altitude and vertical speed. Optional features such as
Synthetic Vision, HSI map overlays, and more can also be provided by the PFD. The minimum PFD installation consists
of:
• GDU 1060/700 display
• ADAHRS (GSU 75H or GRS 79H/GDC 72H or GRS 77H/GDC 74H)
• GMU 44 magnetometer
• GTP 59 temperature probe
• WAAS GPS navigation source
2.1.2
MFD Functionality
The MFD provides at a minimum a moving map display. The display can optionally provide traffic, terrain, audio, and
weather functions depending on installed equipment. In addition, the MFD can be used as a PFD Display Backup when
installed in accordance with the G500H TXi Part 27 AML STC Installation Manual. The MFD minimum system
installation consists of:
• GDU 1060/700 display
• WAAS GPS navigation source
2.1.3
Entering Configuration Mode
The configuration mode of the GDU 1060/700 can be accessed by holding down the inner knob located at the bottom
right of the unit upon initial power up. The knob must be pressed until the Garmin startup screen has disappeared and the
configuration menu is presented.
2.1.4
SD Card Location Options
The GDU 1060/700 has two SD card slots that can be used for various tasks. The following list describes what tasks can
be performed from which SD card slot:
• Either Slot
• Installer Unlock
• Feature Enablement
• Screenshots (If a card is present in both slots the screenshot will print to the top slot only)
• Update databases (bottom or right slot provides a faster load time)
• Top/Left Slot Only
• Software updates
• GSU/GRS Log Downloads
• Flight Log Download
• Save configuration to SD card
• Save error log to SD card
• Load configuration from SD card
• Bottom/Right Slot
• Update Databases (faster)
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2.1.5
Electrical Load Information
Electrical load information for the G500H TXi system LRU’s is provided below. Appendix A of this document contains
details specific to the load changes for the specific aircraft installation.
LRU
Table 2-1: G500/600 TXi LRU Electrical Load
14 Volt Current Draw
28 Volt Current Draw
Typical
Maximum
Typical
Maximum
GDU 700( )
GDU 1060
3.0 A
5.0 A
6.0 A
8.0 A
1.5 A
2.5 A
3.0 A
4.0 A
GSU 75H/GMU 44/GTP 59
760 mA
958 mA
380 mA
479 mA
GCU 485
120 mA
357 mA
64 mA
179 mA
2.2 LRU Description, Control, and Operation
2.2.1
GDU 700P Display
The GDU 700P is a 7-inch LCD portrait-oriented panel mount control and display unit. The GDU 700P can be configured
as a PFD or MFD. The GDU 700P requires a compatible GPS/SBAS navigator for MFD and PFD functionality.
Figure 2-1: GDU 700P PFD and MFD
The GDU 700P has numerous features and controls as shown above. These features and controls are:
•
•
•
Power Button - Pressing and releasing the power button with the unit powered on will cause a dialog box to
appear that allows the display to be powered off or under certain circumstances switched to a backup display
layout. Pressing and holding the button for 5 seconds will power off the display with no further prompt.
Photocell - The photocell may be configured to be used by the display to automatically adjust the display backlighting in reference to ambient light conditions.
Top Card Slot - A Card slot in the display that accepts standard SD cards. See Section 2.1.5 for more
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•
•
2.2.2
information on SD card options.
Bottom Card Slot - A Card slot in the display that accepts standard SD cards. See Section 2.1.5 for more
information on SD card options.
Dual Concentric Knobs - Control knobs that can be used to scroll and select through various options on the
display. The outer knob is used to scroll through available screens on the PFD or MFD. Pressing the knob acts
as an enter or selection of the currently highlighted information.
GDU 700L Display
The GDU 700L is a 7-inch LCD landscape-oriented panel mount control and display unit. The GDU 700L has numerous
features and controls as shown in Figure 2-2. These features and controls are:
•
•
•
•
•
Power Button - Pressing and releasing the power button with the unit powered on will cause a dialog box to
appear that allows the display to be powered off or under certain circumstances switched to a backup display
layout. Pressing and holding the button for 5 seconds will power off the display with no further prompt.
Photocell - The photocell may be configured to be used by the display to automatically adjust the display backlighting in reference to ambient light conditions.
Left Card Slot - A Card slot in the display that accepts standard SD cards. See Section 2.1.5 for more
information on SD card options.
Right Card Slot - A Card slot in the display that accepts standard SD cards. See Section 2.1.5 for more
information on SD card options.
Dual Concentric Knobs - Control knobs that can be used to scroll and select through various options on the
display. Pressing the knob acts as an enter or selection of the currently highlighted information.
Figure 2-2: GDU 700L Features and Controls
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2.2.3
GDU 1060 Display
The GDU 1060 is a 10.6” LCD panel mount control and display unit capable of displaying PFD and MFD data. The
GDU 1060 be interfaced to an external ADAHRS. Shown below is a combined PFD/MFD display. The GDU 1060
requires interface with a compatible GPS/SBAS navigator.
Figure 2-3: The GDU 1060 functioning as an MFD/PFD
The GDU 1060 has numerous features and controls:
Power Button - Pressing and releasing the power button with the unit powered on will cause a dialog box to appear that
allows the display to be powered off or under certain circumstances switched to a backup display layout. Pressing and
holding the button for 5 seconds will power off the display with no further prompt.
Photocell - The photocell may be configured to be used by the display to automatically adjust the display back-lighting
in reference to ambient light conditions.
• Top Card Slot - A Card slot in the display that accepts standard SD cards. See Section 2.1.5 for more
information on SD card options.
• Bottom Card Slot - A Card slot in the display that accepts standard SD cards. See Section 2.1.5 for more
information on SD card options.
• Dual Concentric Knobs - Control knobs that can be used to scroll and select through various options on the
display.
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2.2.4
GCU 485 Control Unit
The GCU 485 is an optional panel mount remote control unit that provides an alternate method of controlling the G500H
TXi PFD display parameters. The GCU 485 Control Unit is available in variations containing different numbers of
buttons. All variations contain three knobs in the same configuration as shown below.
Figure 2-4: GCU 485
2.2.5
Backup GPS Antenna
GDU 1060/700 PFD and MFD displays have an optional backup GPS. If a backup GPS antenna is installed, the backup
GPS is automatically used when the primary GPS source is lost. The backup GPS antenna is located on the instrument
panel glare shield.
Figure 2-5: Garmin Backup GPS Antenna
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2.2.6
GSU 75H ADAHRS
The GSU 75H ADAHRS is a remote LRU that provides flight altitude, vertical speed, airspeed, attitude, OAT, and
heading data for flight instrumentation. The GSU 75H receives data from the GMU 44( ) magnetometer and GTP 59
OAT probe. The GSU 75H utilizes GPS signals sent from the GPS/SBAS navigator. Attitude, heading, and air data is
sent using ARINC 429 digital signals to the GDU 1060/700P. An RS-232 digital connection can be used for
maintenance information.
Figure 2-6: GSU 75H ADAHRS
2.2.7
GMU 44( ) Magnetometer
The GMU 44 and GMU 44B magnetometer sense magnetic field information. The GMU 44( ) data is sent to the system
AHRS. This unit receives power directly from the AHRS source and communicates with the AHRS using an RS-485
digital interface.
Figure 2-7: GMU 44 Magnetometer
Figure 2-8: GMU 44B Magnetometer
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2.2.8
GTP 59 OAT Probe
The GTP 59 is an outside air temperature probe that interfaces to the ADC. The OAT data is to display and true airspeed
computations. The GTP 59 is mounted externally on the aircraft, usually near or inside air inlet ducts, the underside of
wing access panels, or on the empennage below the horizontal stabilizer.
Figure 2-9: GTP 59 OAT Probe
2.2.9
FS 510
The Flight Stream 510 is optionally installed in the G500H TXi display if the aircraft is equipped with only GNS
navigators. The card provides wireless connection to a portable electronic device to support database uploading and
some control of the GDL 69( ). If a GTN 6XX/7XX is installed, the Flight Stream 510 must be installed in the GTN.
This STC does not approve the installation of the Flight Stream 510 in a GTN series navigator, alternate means of
airworthiness approval is required.
It is necessary to have the Garmin Pilot application on a portable electronic device to update databases using a Flight
Stream 510 wireless card. Download Garmin Pilot for Android or Garmin Pilot for iOS from www.garmin.com for
additional information.
Flight Stream installation priority and functions when installed in particular units:
• TXi MFD – Full functionality (except flight plan transfers) including DB concierge
•
TXi PFD – Full functionality (except flight plan transfers) but database concierge times out shortly
after power-up
Figure 2-10: Flight Stream 510
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3.2 Servicing Information
There are no servicing requirements for the G500H TXi system. In the event of a system or LRU failure, troubleshoot
the G500H TXi system in accordance with Section 4.
3.2.1
Periodic Maintenance Instructions
G500H TXi system LRUs are designed to detect internal failures. A thorough self-test is executed automatically upon
application of power to the units, and built-in tests are continuously executed while the LRUs are operating. Detected
errors are indicated on the GDU 1060/700 display via failure annunciations, system messages, or a combination of the
two. A list of reported errors for the system can be printed in the form of a maintenance log using the instructions
provided in Section 4.1.
3.2.2
Special Tools
A milliohm meter with an accuracy of ±0.1 milliohms (or better) is required to measure the electrical bonding between
the G500H TXi system components and aircraft ground.
A pitot-static ground tester is required for ADC and standby instrument checkout procedures and maintenance.
3.3 Maintenance Intervals
Table 3-1 Periodic Maintenance
Item
G500H TXi System
Visual Inspection
Description/ Procedure
Interval
All installed system LRUs, switches, knobs, and wiring harnesses
12 Calendar
must be inspected to ensure continued integrity of the installation.
Months
The inspection must be performed in accordance with Section 3.4.
AHRS Magnetic Field
Model Update
The AHRS utilize an Earth magnetic field model which is updated
once every five years as part of the Aviation Database maintained
by the owner/operator. If the magnetic model is not up to date, the
unit will issue an alert upon startup indicating the model has
Every 5 years
expired. A service bulletin containing the updated magnetic field
model and instructions for installation can be obtained from the
dealer resource center or by contacting Garmin.
Electrical Bonding
Check
Perform an electrical bonding check of the G500H TXi system
LRUs in accordance with Section 3.5.
GDU 1060/700
Cooling Fan
Replacement
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Determine fan hours using the following procedure:
1. Power on the GDU 1060/700 in configuration mode
2. Navigate to Diagnostics → Temp & Power Stats
3. See Power Statistics as “Fan OPER Hours”
Refer to Section 5.1.2 for fan replacement procedure.
Every 2000
Flight hours or
10 years, whichever
comes first
Recommended
every 3000 fan
operating hours
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Altimeter Checks
Interval must be in
Test according to 14 CFR §43 Appendix E.
accordance with
See the pitot-static checkout procedure in Section 5.9.3 for system
Title 14 CFR 91.411
specific checkout procedure.
and 91.413
Lightning Damage
Check
Conduct an inspection of the G500H TXi system in accordance
with 3.7.
After a suspected or
actual lightning
strike
Removal and replacement of the G500H TXi system LRUs can be
Equipment Removal and
accomplished by referring to section 5 of this manual for
On Condition
Replacement
instructions.
Cleaning GDU 1060/
700 front panel
The front bezel, keypad, and display can be cleaned with a soft
cotton cloth dampened with clean water. DO NOT use any
chemical cleaning agents. Care should be taken to avoid
scratching the surface of the display.
Display Backlight
The display backlight LEDs are rated by the manufacturer as
having a usable life of at least 36,000 hours. This life may be
more or less than the rated time depending on the operating
conditions of the GDU 1060/700. Over time the backlight lamp
may dim and the display may not perform as well in direct
On Condition
sunlight conditions. The user must determine by observation when
the display brightness is not suitable for its intended use. Contact a
Garmin factory repair station when the backlight lamp requires
service.
On Condition
3.4 Visual Inspection
Operation of the G500H TXi system is not permitted unless an inspection, as described in this section, has been
completed within the preceding 12 calendar months. Conduct the following visual inspection of the G500H TXi system
LRUs and associated wiring harnesses to ensure installation integrity:
1.
2.
3.
4.
Inspect all units for security of attachment, including visual inspection of brackets and other supporting
structure attaching all units to the airframe.
Inspect all switches, annunciators, knobs and buttons for legibility.
Visually inspect each unit’s wiring (including electrical bonding straps), overbraid, and connectors for chafing,
deterioration, damage or wear.
Visually check for any signs of corrosion.
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3.5 Electrical Bonding Check
G500H TXi LRU electrical bonding must be checked every 2000 flight hours or ten (10) years, whichever occurs first.
During the check, any cables normally attached to the LRU must be disconnected from the LRU. Resistance must be
measured from a bare metal portion of the LRU to an airframe grounding location. The airframe grounding location
should be as close to the LRU as possible unless otherwise noted in the following table.
Table 3-2 Existing Electrical Bonding Requirements
LRU
Maintenance Requirement
GDU 1060/700
GCU 485
20 Milliohms
GSU 75H
GTP 59
GMU 44( )
GDC 74H
GDC 72H
GRS 77H
GRS 79H
5 Milliohms
If measured resistance is greater than applicable values in the table above, bonding must repaired and meet applicable
requirements in accordance with the following table.
Table 3-3 Repaired Electrical Bonding Requirements
LRU
Repair Requirement
GDU 1060/700
GCU 485
10 Milliohms
GSU 75H
GTP 59
GMU 44( )
GDC 74H
GDC 72H
GRS 77H
GRS 79H
2.5 Milliohms
3.6 Overhaul Period
The system does not require overhaul at a specific time period. Power on self-test and continuous BIT will monitor the
health of the G500H TXi system. If any LRU indicates an internal failure, the unit may be removed and replaced.
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3.7 Special Inspection Requirements
After a suspected lightning strike, the following actions must be performed.
3.7.1
GTP 59 OAT
Inspect the GTP 59 OAT for signs of lightning damage. Check the self-sealing washer (P/N 212-00026-00) used on the
probe tip outside of the aircraft for any evidence of melting or lack of seal. Replace washer if damaged. If there is
evidence of lightning strike to the OAT or any lightning damage, replace the GTP 59.
3.7.2
GMU 44( )
Perform the magnetic interference check in accordance with Section 6.5.5 of the G500H TXi Part 27 Installation
Manual. The purpose of this check is to ensure the structure around the GMU 44 did not get magnetized by the lightning
event to the point of affecting GMU 44 performance.
3.8 Application of Protective Treatments
None.
3.9 Data Relative to Structural Fasteners
Data relative to structural fasteners, such as type, torque, and installation requirements can be found in
Section 5 of this manual.
3.10 Additional Instructions
Store G500H TXi equipment in a dry cool area. Protect electrical connectors from damage.
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4. TROUBLESHOOTING
This section provides information to assist troubleshooting if fault codes are displayed on the GDU or problems occur
after completing system maintenance. See Appendix A of this document retained in the aircraft permanent records for a
list of the interfaced equipment and system configuration data. When troubleshooting the G500H TXi system, refer to
wire routing diagrams, plug and pin descriptions, communication port settings saved in the configuration data and
equipment locations retained in Appendix A of this document. General interconnect data for the G500H TXi system is
available in the G500H TXi Part 27 AML STC Installation Manual.
4.1 General System Troubleshooting
Before troubleshooting the G500H TXi system, use the Configuration log tool to print the current configuration log to
ensure that system configuration settings match those recorded in the aircraft’s permanent records.
If the current aircraft configuration does not match the configuration log retained with the aircraft permanent records,
load the saved configuration from the SD card retained with the permanent aircraft records. If this cannot be
accomplished, or does not correct the configuration, the configuration must be corrected by a Garmin dealer using an
installer unlock card and the configuration instructions provided in Section 5 of the G500H TXi Part 27 AML STC
Installation Manual. Basic troubleshooting of the G500H TXi system can be accomplished using the instructions
provided in Table 4-1.
Table 4-1 G500H TXi Failures
Symptom
Recommended Action
GDU 1060/700 Blank
1) Check power/ground wiring for GDU.
2) Press the power button until the Garmin logo is visible.
Configuration Mode pages
grayed out with an installer
unlock card
1) Ensure a GDU master configuration module is selected.
2) Ensure a functional configuration module is present.
3) Ensure the GDU ID’s are set for all GDU’s
An Alert message is displayed on Troubleshoot the alert message using the flowcharts provided in Section 4.3.
the GDU or present in the
Maintenance log
4.1.1
Configuration & Maintenance Logs
Print a new configuration log and add it to the aircraft maintenance records if the software or system configuration was
changed during maintenance. The maintenance log will display reported system faults, alert messages, frequency, most
recent occurrence time of the fault (if any). If any faults are reported on the maintenance log, refer to the troubleshooting
flowcharts contained in Section 4.1.
To see the maintenance and error log on the GDU:
1. Power all GDU 1060/700 units into configuration mode.
2. On GDU1 navigate to Diagnostics → Maintenance / Error Log → Maintenance Log.
To save or copy the aircraft configuration or print the maintenance and error log:
1. Power all GDU 1060/700 units into configuration mode.
2. Insert an SD card into the top/left SD card slot.
3. Press the SD Save button.
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4.
5.
6.
7.
Enter a name for the configuration file (e.g., GDU_CNFG_N12345_v2_30), select Enter when done.
The GDU 1060/700 will automatically create three new folders:
a. The ‘aircraft_cfg’ folder has .gca files that store encrypted GDU 1060/700 configuration settings.
This file can only be read by a GDU 1060/700. Instructions to load the configuration settings are
shown below.
b. The ‘configuration_summary’ folder has .htm files that can be opened and printed with common
internet browsers (e.g., Chrome). It can be printed from most browsers using cntrl+p. This is required
for the aircraft maintenance records/ICA.
c. The ‘maintenance_logs’ folder has .htm files that can be opened and printed with common internet
browsers (e.g., Chrome).
Once the save process is completed, eject the SD card.
Label the SD card with the aircraft registration number and the GDU 1060/700 system software version.
The files in the ‘aircraft_cfg’ folder can be loaded onto the same or a different GDU 1060/700. Do not load a
configuration file from a GDU 1060/700 with newer, more recent, system software version. Loading the system
configuration from an SD card will overwrite the current system configuration and is not reversible, save your current
configuration to the SD card first. Information not contained in the selected configuration file will be grayed out and
cannot be selected.
To load your aircraft configuration settings from an SD card:
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
4.1.2
Insert an SD card into the Top/Left slot of any GDU 1060/700 in the system
Power on all GDUs in the G500H TXi system in configuration mode
Ensure you have set the GDU IDs, SYS ID Source, and feature enablements before continuing
From the Home screen, select SD load
Select the Aircraft Configuration File you want to load
Select the To GDU to which you want to load configuration settings
Select the check box next to the configuration to be loaded
Select SD Load
Verify the loaded configuration(s) are identical to those recorded in the aircraft’s permanent records.
Perform Configuration Ground Check in Section 5.9.1. If any interfaces have a yellow triangle present on the
system summary after loading a configuration from the SD card, verify the interface settings match the
configuration settings stored with the permanent aircraft records. If the settings do not match, the configuration
must be corrected by a Garmin dealer.
Configuration Summary
The configuration summary cay be used to verify the system settings and LRU configurations.
1.
2.
3.
4.
4.1.3
Power all GDU 1060/700 units into configuration mode.
Open the system summary (Home → Summary).
Verify that all configuration settings listed are consistent with the printed configuration log.
Verify if any LRU sections have a yellow warning triangle present that the configuration is valid.
Flight Data Logs
The flight data log can be used to check for system issues. The TXi system continuously records flight data to an SD
card installed in the top/left slot. If a FS510 is installed, the data will be streamed via Bluetooth to the paired Personal
Electronic Device.
1.
2.
3.
Power all GDU 1060/700 units into normal mode.
Insert an SD card into the top/left SD card slot.
a. The GDU will automatically create a ‘data_log’ folder containing .csv files.
Eject the SD card from the GDU and insert it into a computer. This file can be viewed and printed with a
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spreadsheet program (e.g., MS Excel) or graphically processed by a compatible program.
4.1.4
ADAHRS Log Download
If a GDU 700/1060 is interfaced to a GSU 75H or GRS 79, the AHRS Log data will be available for download to an SD
card in the Top slot of the GDU. To download log data, perform the following steps:
1.
2.
3.
4.
5.
Insert an SD card into the Top or Left slot of the GDU 700/1060.
Start the GDU in Configuration mode.
Access the GSU/GRS Flight Log Downloads Page (Diagnostics → AHRS & ADC → GSU/GRS Flight
Log Downloads).
Press Select Unit and choose which AHRS unit data should be retrieved from.
Select the flight log parameters that should be downloaded by using one of the following buttons:
a. The Log Entry button selects entry by power on count, date, and time.
b.
6.
7.
4.1.5
The Log Entry Start button selects log entry start in minutes.
c. The Duration button selects log entry by duration in minutes.
Press Download to SD Card.
A dialog box will annunciate that the download is complete, the SD card can be removed.
Screen Shot
The screen shot can be used to record and share images of the display.
1. Power on the GDU 1060/700 unit into normal or configuration mode.
2. Insert an SD card into the top/left SD card slot.
3. Press the right inner knob located at the bottom right and the power button simultaneously.
a. The GDU 1060/700 will automatically create a ‘print’ folder containing .bmp files that can be viewed
with common operating systems.
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4.2
Connector Information
This section contains connector information and description of pin functions for all LRUs that can be installed as part of
G500H TXi STC. Refer to the LRU TSO installation manuals for more detailed signal information on each LRU. All Dsub connectors follow a similar pin numbering scheme as shown below.
4.2.1
GCU 485
The GCU 485 has a single connector:
Ref. Des.
P4851
Description
Conn. Male. HD D-Sub. 15 Ckt
CONN P/N
330-00366-15
Kit P/N
011-01824-00
Figure 4-1 GCU 485 Connector
J4851/P4851 Connector
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Pin
Function
I/O
1
2
RS-232 OUT 1
RS-232 IN 1
OUT
IN
3
RS-232 OUT 2
OUT
4
RS-232 IN 2
IN
5
POWER GROUND
--
6
SIGNAL GROUND
--
7
AIRCRAFT_POWER_1
IN
8
SIGNAL GROUND
--
9
AIRCRAFT_POWER_2
IN
10
RESERVED
--
11
LIGHTING BUS HI
IN
12
LIGHTING BUS LO
IN
13
RESERVED*
--
14
RESERVED
--
15
POWER GROUND
--
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4.2.2
GSU 75H
The GSU 75 has one connector.
Ref. Des.
P751
Description
Conn. HD D-Sub. Male Str. Mil Crp. Sealed, w/GND indents,
78 Pin
CONN P/N
Kit P/N
330-00776-78
011-03109-00
Figure 4-2 GSU 75H Connector
J751/P751 Connector
Pin
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
Function
ARINC 429 OUT (ADC) 1A
ARINC 429 OUT (ADC) 1B
ARINC 429 OUT (ADC) 2A
OAT LO
OAT HI
OAT PWR
ARINC 429 OUT (ADAHRS) 1B
ARINC 429 OUT (ADAHRS) 3A
ARINC 429 OUT (ADAHRS) 3B
RS-422 IN A
RS-422 IN B
RS-232 OUT (AHRS) 3
MAGNETOMETER PWR OUT
AIRCRAFT PWR 1
SIGNAL GND
AIRCRAFT PWR 2
RS-232 OUT (ADC) 2
RS-232 IN (ADC) 2
RESERVED
RESERVED
ARINC 429 OUT (ADC) 3A
ARINC 429 OUT (ADC) 3B
190-02401-01
Rev. 1
I/O
OUT
OUT
OUT
IN
IN
OUT
OUT
OUT
OUT
IN
IN
OUT
OUT
IN
-IN
OUT
IN
I/O
I/O
OUT
OUT
Pin
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
44
Function
ARINC 429 OUT (ADC) 2B
GND
PPS SELECT
SIGNAL GND
ARINC 429 OUT (ADAHRS) 1A
ARINC 429 OUT (ADAHRS) 3A
ARINC 429 OUT (ADAHRS) 3B
SIGNAL GND
RS-232 GND (AHRS) 3
RS-232 GND (AHRS) 1
MAGNETOMETER GND
AIRCARFT GND 1
RESERVED
AIRCARFT GND 2
RS-232 GND (ADC) 2
RESERVED
RESERVED
PPS IN 1 B
PPS IN 2 A
ARINC 429 IN (ADC) 1A
ARINC 429 IN (ADC) 1B
ARINC 429 IN (ADC) 2A
I/O
OUT
-IN
-OUT
OUT
OUT
---------I/O
IN
IN
IN
IN
IN
G500H TXi Part 27 AML STC Maintenance Manual
Page 4-5
45
46
47
48
49
50
51
52
53
54
55
56
57
58
59
60
61
ARINC 429 IN (AHRS) 1A
ARINC 429 IN (AHRS) 1B
ARINC 429 IN (AHRS) 3A
SIGNAL GND
ARINC 429 OUT (ADAHRS) 2A
ARINC 429 OUT (ADAHRS) 2B
RS-232 OUT (AHRS) 1
RS-232 IN (AHRS) 1
CONFIG MODULE PWR
CONFIG MODULE DATA
CONFIG MODULE CLOCK
DISCRETE IN 1*
SYS ID 2*
RESERVED
RESERVED
PPS IN 1 A
PPS IN 2 B
4.2.3
GMU 44
IN
IN
IN
-OUT
OUT
OUT
IN
OUT
I/O
OUT
IN
IN
IN
I/O
IN
IN
62
63
64
65
66
67
68
69
70
71
72
73
74
75
76
77
78
ARINC 429 IN (ADC) 3A
ARINC 429 IN (ADC) 3B
ARINC 429 IN (ADC) 2B
ARINC 429 IN (AHRS) 2A
ARINC 429 IN (AHRS) 2B
ARINC 429 IN (AHRS) 3B
RS-232 GND (ADC) 1
RS-232 OUT (ADC) 1
RS-232 IN (ADC) 1
RS-232 OUT (AHRS) 2
RS-232 IN (AHRS) 2
RS-232 GND (AHRS) 2
CONFIG MODULE GND
SYS ID 1*
DISCRETE IN 3*
DISCRETE IN 4
DISCRETE IN 2*
IN
IN
IN
IN
IN
IN
-OUT
IN
OUT
IN
--IN
IN
IN
IN
The GMU 44 has one connector.
Ref. Des.
P441
Description
Conn, Circular, Female, 9 Ckt
CONN P/N
330-00360-00
Kit P/N
011-00871-00
J441/P441 Connector
Figure 4-3 GMU 44 Connector
190-02401-01
Rev. 1
Pin #
Function
I/O
1
2
SIGNAL GROUND
RS-485 OUT B
-Out
3
SIGNAL GROUND
--
4
RS-485 OUT A
Out
5
SPARE
--
6
POWER GROUND
--
7
SPARE
--
8
RS-232 IN
In
9
+12 VDC POWER
In
G500H TXi Part 27 AML STC Maintenance Manual
Page 4-6
4.2.4
GMU 44B
The GMU 44B has one connector.
Ref. Des.
P442
Description
6 Pin Rectangular Connector
CONN P/N
330-01430-01
Kit P/N
011-04205-00
Figure 4-4 GMU 44B Connector
J442/P442 Connector
Pin
1
2
3
4
5
6
4.2.5
Function
I/O
SHIELD GROUND
RS-422 OUT B
RS-422 OUT A
POWER GROUND
RS-232 IN
MAG POWER INPUT
-OUT
OUT
-IN
IN
GTP 59
The GTP 59 has a 3-conductor shielded cable that extend from the probe.
190-02401-01
Rev. 1
Conductor Color
WHITE
BLUE
Name
PROBE POWER LEAD
RESISTIVE ELEMENT HI
I/O
IN
OUT
ORANGE
RESISTIVE ELEMENT LO
OUT
G500H TXi Part 27 AML STC Maintenance Manual
Page 4-7
4.3 Troubleshooting Flow Charts
This section provides troubleshooting flow charts for most system failures and alert messages. It is recommended that
system troubleshooting and repair only be completed by a Garmin dealer. If a specific alert or fault condition is not
listed, or the fault still exists after completing the given corrective action, contact Garmin Aviation Technical Support at
the number listed for your specific region on the “Support” tab of the FlyGarmin.com website.
AHRS/ADC Fault
Messages
AHRS 1/2 reports
an in-tarmac
magnetic
anomaly
AHRS 1/2 reports
a local earth
magnetic
anomaly
AHRS 1/2
magnetic model
database needs
update
AHRS 1/2 not
receiving valid
magnetometer
data
ADC 1/2 error
correction
inoperative
Service
required
Maintenance
Log Message
Maintenance
Log Message
ADC 1/2 airspeed
error correction is
unavailable
AHRS 1/2 is not
receiving true
airspeed
Cause
Cause
The alert flag has
been set by the
ADC
ADC loss of
communication
OR
No GTP 59 signal
Cause
Cause
Cause
Cause
The AHRS has
detected an in
tarmac anomaly at
the given location
The AHRS has
detected a local earth
anomaly at the given
location
The designated
AHRS Magnetic
Model is out of
date
Communication lost
with GMU 44
OR
GMU 44 installation
incorrect
Corrective
Action
Corrective
Action
Corrective
Action
Corrective
Action
Corrective
Action
Corrective
Action
If this error shows
up repeatedly
conduct the
magnetic
interference check
in Section 6.5.6 of
the G500H Txi
AML STC
Installation Manual
Update the
magnetic model
database.
Inspect GMU 44
wiring and
connections
If other ADC or
AHRS faults are
present correct
those faults first.
Verify ADC power
If this error shows
up repeatedly
conduct the
magnetic
interference check
in Section 6.5.6 of
the G500H Txi
AML STC
Installation Manual
Ensure GMU 44
installation is
within ±3° of level
and less than 6°
difference from the
AHRS unit in
accordance with
G500H Txi AML
STC installation
manual
Verify ADC 1/2
configuration and
wiring.
Inspect ADC/
AHRS wiring and
connections
Inspect GTP 59,
connections, and
wiring.
If fault still exists,
contact Garmin.
Figure 4-5 ADAHRS Troubleshooting
190-02401-01
Rev. 1
G500H TXi Part 27 AML STC Maintenance Manual
Page 4-8
Audio Fault
Audio
Inoperative
Cause
Audio device failed
OR
Audio clip failed to
play
Corrective
Action
Verify audio device
is online
Inspect audio
device
connections and
wiring
Troubleshoot in
accordance with
audio device
maintenance
manual
If fault still exists,
contact Garmin.
Figure 4-6 Audio Troubleshooting
190-02401-01
Rev. 1
G500H TXi Part 27 AML STC Maintenance Manual
Page 4-9
External LRU Alert
Messages
Satellite
weather
inoperative
Satellite
weather not
registered
Sirius XM
receiver
inoperative
Maintenance
Log Message
Maintenance
Log Message
Maintenance
Log Message
Comunication lost
with GSR 56
GSR 56 weather
not registered
GCU 485
communication lost
Cause
Cause
Comunication lost
with GSR 56
The GSR 56
weather function
has not been
registered
Corrective
Action
Inspect GSR 56
wiring and
connectors.
Controller
Unavailable
Cause
Cause
GDL 69/69a has either
lost communication with
GDU or is reporting a
failed condition
The GDU has lost
communication with
the GCU 485
Corrective
Action
Corrective
Action
Corrective
Action
Register the GSR
56 weather
function as
described in the
G500H TXi AML
STC Installation
Manual
Inspect GDL 69/
69a wiring and
connectors.
Ensure all LRUs in
the system are
online.
Verify power to
GCU 485 is on
Inspect GCU 485
wiring and
connections
If fault still exists,
contact Garmin.
Figure 4-7 External LRU Failure Troubleshooting
190-02401-01
Rev. 1
G500H TXi Part 27 AML STC Maintenance Manual
Page 4-10
External LRU Service
Alerts
Service
Soon
Service
Required
Maintenance
Log Message
Maintenance
Log Message
External LRU Reports
config module needs
service
External LRU
reports service
required
Receiving data
from the wrong
side LRU.
ADC 1/2 or AHRS 1/2
config does not match
the GDU config
Cause
Cause
Cause
Cause
The external LRU
config module is
missing or has
failed
The external LRU
is reporting that
service is required
Incorrect SDI on
external LRU
OR
Incorrect GDU
configuration settings
GDU and external
AHRS/ADC LRU report
different configuration
versions
Corrective
Action
Corrective
Action
Corrective
Action
Corrective
Action
Inspect connector
pins and wiring to
external LRU
config module
Return External
LRU to Garmin for
service.
Inspect external
LRU SDI strapping
pins to ensure
correct SDI
Verify ADC/AHRS
interface settings
on GDU and copy
the configuration
to the ADC/AHRS
Replace External
LRU config
module
Verify GDU
configuration
matches
installation wiring/
port configuration
If fault still exists,
contact Garmin.
Figure 4-8 External LRU Service Troubleshooting
190-02401-01
Rev. 1
G500H TXi Part 27 AML STC Maintenance Manual
Page 4-11
GDU Alert Messages
Display Hot,
display
dimmed
Cooling fan
failed
Backlight
calibration
lost
Demo mode,
do not use in
flight
Maintenance
Log Message
Maintenance
Log Message
The GDU has
exceeded its internal
temp threshold
GDU Software
Mismatch
Cause
Cause
GDU cooling fan
failure
OR
GDU cooling fan
obstruction
Corrective
Action
Verify cooling fan
ports are clear
Service
Required
J2 Pin 39 on the
GDU is grounded
Corrective
Action
Replace cooling
fan in accordance
with Section 5.1.2
Cause
One or more
GDUs in the
system have a
different software
version
Corrective
Action
Corrective
Action
Corrective
Action
Return the GDU to
Garmin for service
Inspect GDU
connectors and
wiring to remove
the signal from the
Demo Mode
Select Pin
Ensure all GDUs
have the same
system software
installed
If fault still exists,
contact Garmin.
Figure 4-9 GDU Troubleshooting
190-02401-01
Rev. 1
G500H TXi Part 27 AML STC Maintenance Manual
Page 4-12
PFD Fault Messages
GPS 1/2
inoperative
Service
Soon
AHRS 1/2
not receiving
GPS Aiding
NAV 1/2
inoperative
GDU( ) GPU
monitor
restarted the
unit
Maintenance
Log Message
Maintenance
Log Message
Maintenance
Log Message
Maintenance
Log Message
Maintenance
Log Message
GPS 1/2 interface
failed.
GPS TIME MARK
1/2 FAIL
AHRS 1/2 not
receiving GPS
aiding
NAV 1/2
interface/unit
failed
GDU( ) <ALT, IAS, EIS, or
Attitude> GPU monitor
restarted the unit.
Cause
Cause
Cause
Cause
Cause
Cause
Improper installation of
GMU 44 and/or AHRS
OR
Excessive magnetic
interference
A GPS source has
lost communication
OR
A GPS source is
reporting failed
The PFD has not
received a pulse in
3 seconds or more
The AHRS has
reported that no
GPS data is being
received
A NAV source has
lost communication
OR
A NAV source is
reporting failed
An internal data
check has failed and
restarted the GDU
Corrective
Action
Corrective
Action
Corrective
Action
Corrective
Action
Corrective
Action
Corrective
Action
Perform Magnetic
Interference check
in section 3.7.2
Verify the GPS
source is on and
has a clear view of
the sky
Verify the GPS
source is on and
has a clear view of
the sky
Verify the GPS
source is on and
has a clear view of
the sky
Verify the NAV
source is on and
not reporting failed
Inspect GPS
antenna, wiring,
and connections
Inspect GPS
antenna, wiring,
and connections
Inspect GPS
antenna, wiring,
and connections
Verify GDU and
GPS configuration
settings
Verify GDU and
GPS configuration
settings
Verify GDU and
GPS configuration
settings
If reporting failed,
troubleshoot in
accordance with
NAV unit
maintenance
manual.
HDG Fail
Verify GMU 44
and AHRS
mounting locations
are within ±3° of
level and no more
than 6° of each
other (see LRU
installation
instructions in
G500H TXi AML
Installation Manual
for more
information)
Contact Garmin
Technical Support
Inspect NAV
wiring,
connections, and
configuration
settings
If fault still exists,
contact Garmin.
Figure 4-10 PFD Troubleshooting
190-02401-01
Rev. 1
G500H TXi Part 27 AML STC Maintenance Manual
Page 4-13
Terrain/TAWS Alert
Messages
Ext. TAWS
Fail
Ext. TAWS
N/A
TER FAIL
TER N/A
Service
TAWS.
Invalid
Config.
Maintenance
Log Message
Cause
Cause
Database corrupted
or missing
OR
Internal failure
Corrective
Action
See external
TAWS unit manual
for troubleshooting
instructions
Corrective
Action
See external
TAWS unit manual
for troubleshooting
instructions
Backup GPS is active TAWS/TER config not set
OR
OR
No Primary GPS signal External TAWS and GDU
OR
mismatch (rotorcraft /
Outside database region
fixed-wing)
Corrective
Action
Corrective
Action
Corrective
Action
Verify terrain
database is loaded
and current.
Verify primary
GPS is on and has
a clear view of the
sky
Check TAWS/
Terrain
configuration
settings
Reload helicopter
terrain database
Inspect GPS
antenna and wiring
Verify External
TAWS and GDU
have the same
aircraft type
configured
Verify Terrain
database coverage
If fault still exists,
contact Garmin.
Figure 4-11 Terrain Alert Troubleshooting
190-02401-01
Rev. 1
G500H TXi Part 27 AML STC Maintenance Manual
Page 4-14
Traffic Alert Messages
TAS/TCAS
function
inoperative
ADS traffic
alerting
function
inoperative
ADS traffic
function
inoperative
Traffic/FIS-B
functions
inoperative
UAT traffic/
data receiver
fault
1090ES
traffic
receiver fault
Corrective
Action
Corrective
Action
Corrective
Action
Corrective
Action
Corrective
Action
Corrective
Action
Troubleshoot
device failure in
accordance with
TAS/TCAS LRU
maintenance
manual
Troubleshoot
device failure in
accordance with
ADS-B LRU
maintenance
manual
Troubleshoot
device failure in
accordance with
ADS-B LRU
maintenance
manual
Troubleshoot device
failure in accordance
with UAT LRU
maintenance manual
Troubleshoot
device failure in
accordance with
ADS-B LRU
maintenance
manual
Troubleshoot
device failure in
accordance with
ADS-B LRU
maintenance
manual
If fault still exists,
contact Garmin.
Figure 4-12 Traffic Troubleshooting
190-02401-01
Rev. 1
G500H TXi Part 27 AML STC Maintenance Manual
Page 4-15
5. EQUIPMENT, MAINTENANCE, AND CHECKOUT PROCEDURES
This section provides the procedures to remove, replace, or install required and optional LRUs that are part of the G500H
TXi system. Before performing any maintenance on the G500H TXi system all information in Appendix A must be filled
out. It is highly recommended to save the system configuration to an SD card and print the configuration log before
replacing any system LRUs.
NOTE
A GDU 1060/700( ) may be removed, replaced with a new GDU, or the old GDU reinstalled without an
installer unlock card if the configuration module is not replaced.
NOTE
Any AHRS unit may be removed or replaced without using an installer unlock card if the unit mounting
brackets or support structure (i.e. mounting bracket, avionics shelf) is not loosened or removed. If the mounting
is loosened, additional calibrations and configurations will be necessary that require the use of an installer
unlock card.
5.1 GDU 1060/700
Figure 5-1 GDU 1060 Installation
190-02401-01
Rev. 1
G500H TXi Part 27 AML STC Maintenance Manual
Page 5-1
Figure 5-2 GDU 700P Installation
NOTE
The GDU 700L uses the same fastener and torque specifications as the GDU 700P in Figure 5-2 above.
5.1.1
Removal
Remove the GDU 1060/700 using the following procedure:
1.
2.
Ensure the current configuration is saved to an SD card in accordance with the instructions contained in Section
4.1.1.
Turn off the GDU and remove power for the GDU.
190-02401-01
Rev. 1
G500H TXi Part 27 AML STC Maintenance Manual
Page 5-2
3.
4.
5.
5.1.2
Remove the four (1) screws retaining the GDU in the instrument panel.
Gently pull the GDU out from the instrument panel far enough to access the cable connectors and ADC module
(if installed).
Remove the cable connectors from the back of the GDU.
Cooling Fan Replacement
NOTE
The GDU cooling fan replacement kit (P/N: K00-01080-00) must be obtained from an authorized Garmin
dealer. In order for the GDU warranty to remain valid this procedure must be accomplished by an authorized
Garmin dealer.
NOTE
Resetting the fan operation hours requires the use of an Installer unlock card.
The GDU 1060/700 cooling fan has a recommended replacement interval of 3000 hours. After 3000 hours of operation
the cooling fan should be replaced using the following procedure:
1.
2.
3.
4.
5.
6.
Remove the GDU from the instrument panel.
Remove the four(4) screws securing the fan module to the rear of the GDU and discard the O-rings.
Grasp the fan module and gently pull the module out of the GDU.
Visually inspect the inside of the fan module receptacle on the back of the GDU for the following:
• Verify that the four rubber gaskets around the fan screw mounting holes and are not torn, damaged, or
missing. If any of these conditions are found replace all four gaskets (not included in fan replacement kit).
• Inspect the 4-pin electrical connector for the fan module for damage or corrosion. If any
• damage is found, return the GDU to Garmin for service.
Place the new O-rings included in the fan replacement kit on the four fan mounting screws.
Place the new cooling fan module in the fan well of the GDU with the electrical connector oriented on the upper
side near the J7 connector.
CAUTION
It may be necessary to slightly move the fan module within the fan well to align the connector pins and
connector body. If the module does not press into the back of the GDU with slight pressure, the connector may
not be aligned. If the connector cannot be aligned, remove the module again and inspect the pins on the fan
module and the connector on the GDU for straightness or damage. Applying too much pressure to the fan
module with the connector out of alignment could cause damage to the fan module, GDU connector, or both.
7.
Slide the fan module evenly into the fan well on the GDU and gently press the module into the back of the
GDU.
8. Insert the four fan mounting screws with O-rings into the mounting holes on the fan module and tighten evenly
to 8 ± 1 LBF-IN.
9. Install the GDU.
10. Once GDU installation and checkout has been accomplished, reset the GDU cooling fan hour counter using the
following procedure:
• Power on the GDU 1060/700 in configuration mode.
• Navigate to Diagnostics → Temp & Power Stats.
• Press Reset Fan Hours.
190-02401-01
Rev. 1
G500H TXi Part 27 AML STC Maintenance Manual
Page 5-3
5.1.3
Configuration Module Replacement
To replace a GDU 1060/700 configuration module, perform the following procedure:
NOTE
Ensure the current configuration is saved to an SD card in accordance with the instructions contained in
Section 4.1.1.
NOTE
All item numbers in this procedure reference Figure 5-3.
1.
2.
3.
4.
5.
6.
7.
8.
Remove the GDU.
Remove the backshell cover(7) from connector P2 by removing two screws(8).
Remove the screw(10) securing the configuration module(1) to the backshell(6).
Lift the configuration module(1) out of the backshell(6) and disconnect the wiring harness(3) from the module.
Inspect the wiring harness(3) and connector pins(4) for damage, loose wiring, or corrosion. Replace all
deficient components if any of these conditions are found.
Connect harness to new configuration module.
Install new configuration module in connector backshell(6) and re-install cover(7).
Re-Install GDU 1060/700.
Figure 5-3 Configuration Module Installation
NOTE
The GDU will automatically copy the system configuration to the new configuration module upon the first
power-up.
190-02401-01
Rev. 1
G500H TXi Part 27 AML STC Maintenance Manual
Page 5-4
5.1.4
Master Configuration Module Replacement
NOTE
Replacement of the G500H TXi system Master configuration module requires the use of an Installer unlock
card and must be performed by an authorized Garmin Dealer.
Physical replacement of the master configuration module is identical to the configuration module replacement procedure
provided in Section 5.1.4. Following the master configuration module replacement, the system ID will have changed. Any
feature unlocks and databases will need to be re-issued for the new system ID by a Garmin dealer. To return the system
to service from this condition perform the following steps:
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
11.
12.
13.
14.
15.
16.
5.1.5
If possible, save the system configuration as shown in section 4.1.1.
If multiple GDU 1060/700 displays are installed in the system, choose one GDU to act as the new master GDU.
Power on all LRUs in the G500H TXi system with all GDUs in configuration mode.
From the home screen on each GDU navigate to GDU Type.
Configure all GDU ID’s, locations, and unit configurations to match the recorded configuration settings in the
configuration log printout.
Ensure that Master is selected on the GDU that has been chosen to act as the master configuration module.
At this point the G500H TXi system will have a new system ID. System features will need to be unlocked and
the system databases will need to be re-installed. The System ID must be updated on Flygarmin.com and then
new databases can be downloaded.
Insert the feature unlock card in the bottom or right slot of any GDU in the system
Navigate to Home → System Management → Feature Enablement and enable system features.
If available, insert the SD card with the saved aircraft configuration file in the Top or left slot of any GDU in
the system. If not available, manually configure the system using the aircraft maintenance records and skip to
step 16.
Navigate to Home → SD Load
Select the aircraft configuration file you wish to load.
Select the GDU to configure, and the desired configuration settings to load.
Select SD Load.
Follow on screen commands.
Perform the Configuration Ground check in Section 5.9.1.
Re-installation
To replace the GDU 1060/700 perform the following procedure:
1.
2.
3.
4.
Connect the four wiring connectors and any installed antenna wires to the back of the GDU and tighten the
retaining screws.
Place the GDU in the instrument panel cutout.
Install the four screws (item 1) as shown in Figure 5-1 and Figure 5-2 and tighten to 8 ± 1 LBF-IN.
Perform the configuration mode ground check in Section 5.9.1.
190-02401-01
Rev. 1
G500H TXi Part 27 AML STC Maintenance Manual
Page 5-5
5.2 GCU 485
5.2.1
Removal
Remove the GCU 485 using the following procedure:
1. Remove power to the GCU 485.
2. Insert a 3/32” hex drive tool into the holes in the top and bottom of the front panel.
3. Turn counter-clockwise until the pawl-latches rotate to a horizontal position.
4. Remove the unit from the panel.
5. Disconnect the electrical connector from the back of the unit.
5.2.2
Re-Installation
NOTE
Electrical bond between the airframe and the GCU 485 is accomplished through direct metal-to-metal contact
between pawl latches and the back side of the panel. Areas as indicated in figure 5-5 must be free of any
surface coatings.
Figure 5-4 Panel Cutout for GCU 485
To re-install the GCU 485 perform the following procedure:
1.
2.
3.
4.
5.
Connect the electrical connector to the back of the GCU 485.
Place the unit in the panel cutout, ensuring that the pawl latches are fully retracted and in the horizontal
position.
Tighten the pawl latches with a 3/32” hex drive tool inserted through holes in GCU 485 face plate.
Torque the latches to 20 +/-2 in-lbs.
Restore power to the unit.
190-02401-01
Rev. 1
G500H TXi Part 27 AML STC Maintenance Manual
Page 5-6
5.3 GSU 75H
This section provides instructions for removal, re-installation, and installation, and checkout of the GSU 75H.
Figure 5-5 GSU 75H Installation (Sheet Metal Shelf Example)
NOTE
The GRS 79 has the same case and mounting hardware as the GSU 75H with the exception of the Pitot-static
ports, which are not present on the GRS 79. Removal and installation procedures are similar for both units.
NOTE
Loosening of the unit mounting rack and/or the shelf to which the mounting plate is attached requires recalibration of the AHRS, which requires an installer unlock card.
190-02401-01
Rev. 1
G500H TXi Part 27 AML STC Maintenance Manual
Page 5-7
5.3.1
Removal
Removal of the GSU 75H can be accomplished using the following procedure:
1.
2.
3.
4.
5.
5.3.2
1.
2.
3.
4.
5.
6.
7.
5.3.3
Remove power to the unit.
Disconnect electrical connector.
Disconnect Pitot-Static lines.
Loosen the two mounting screws on the connector end of the unit.
Lift the connector side of the unit and slide the unit towards the connector to remove.
Installation
Place the unit on the remote rack.
Slide the unit back until the feet are fully engaged with the remote rack.
Push down and simultaneously turn each retention screw clockwise.
Torque each retention screw to 15-20 in-lbs.
Connect Pitot-Static Lines.
Connect electrical connector.
Restore unit power.
Checkout
If the mounting bracket bolts have been loosened or bracket mounting (i.e. instrument panel, avionics shelf) has been moved
in any way the following AHRS calibration procedures must be performed as described in Section 6 of the G500H TXi Part
27 AML STC Installation Manual:
1.
2.
3.
4.
5.
Pitch/Roll Offset Compensation.
Magnetometer Calibration.
Compass Swing.
Heading offset compensation if required by the previous step.
Engine Run-up Vibration check.
Perform a static and pitot system leak test in accordance with the aircraft manufacturers specification and/or applicable
regulations. In accordance with 14 CFR 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-paragraphs (iv) (Friction) and
(vi) (Barometric Scale Error) are not applicable because the digital outputs of the GSU 75H are not susceptible to these
types of errors.
Perform checkout procedures in Section 5.9.3.
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Page 5-8
5.4 GMU 44( )
This section provides instructions for removal, re-installation, and installation, and checkout of the GMU 44( ). Do not
use magnetic tipped tools for servicing the magnetometer. Actual installations may differ from the examples shown
below.
Figure 5-6 GMU 44B Installation
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G500H TXi Part 27 AML STC Maintenance Manual
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•
GARMIN~
-
1
10
2
3
9
8
MS51957-28
M$35214-23
SCREW, MACHI NE, PAN HEAD, CROSs-RECESSED, CORROSION RESISTANT STEEL, .1380-32 UNC-2A, 0.375 LONG
SCREW, MACHINE, PAN HEAD, CROss-RECESSED, BRASS, 0.1380-32 UNC-2A, 0.25 IN LONG
2
7
MS21069L06
NUT, SELF-LOCKING, PlATE, lWO-LUG, REDUCED RNET SPACING, LOW HEIGHT, STEEL.138-32 UNJC-3B
6
4
6
5
RNET, SOUD, COUNTERSUNK 100 DEG, PRECISSION HEAD, 5/32 IN OD, 4/ 16 IN LONG
RNET, SOUD, COUNTERSUNK 100 DEG, PRECISION HEAD, 3/32 IN OD, 3/16 IN LONG
1
4
MS20426AD5-4
MS20426AD3-3
115-00481-10
1
2
BRACKET, GMU 44
RACK, INSTALL, MODIFIED, GMU 44
011-00870-20
GMU 44 MAGNETOMETER
011-00870-10
QTY. ITEM PART NUMBER DESCRIPTION
NOTES
ffi DIMENSIONS
ARE IN INCHES UNLESS OTHERWISE SPECIFIED. MAXIMUM DISTANCE FROM MOUNTING FACE TO CENTER OF GMU 44
UNIT IS S.O INCHES.
.ffi FASTENER HOLES ARE LOCATED TO MATCH GMU 44 1NSTALL RACK ITEM 4.
ffi FASTENER HOLES ARE LOCATED TO MATCH GMU 44 BRACKET ITEM 10.
& FASTENER HOLES ARE LOCATED TO MATCH NUTPLATE ITEM 7.
& RIVETS
ARE INSTALLED PER MIL-R-47196 (NASM47196) RIVET, BUCK TYPE, PREPARATION FOR AND INSTALLATION, OR PER M IL-ST0-403
PREPARA nON FOR AND INSTALLATION OF RIVETS AND SCREWS, ROCKET MISSILE, AND AIRFRAME STRUCTURES.
& SCREW
IS A PART OF 011-00871-00 GMU 44 CONNECTOR KIT. INSTALL WITH MEDIUM STRENGTH THREAD LOCKER. TORQUE .1380·32
UNC-2A BRASS SCREWS 7.0 ±0.5 LBF-IN.
&. TORQUE .138D-32 UNC·2A STEEL SCREWS 11.0 ±:1.0 LBF-IN.
Figure 5-7 GMU 44 Installation
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G500H TXi Part 27 AML STC Maintenance Manual
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NOTE
Removal, re-installation, or replacement of the GMU 44( ) will require a recalibration of the AHRS which
requires the use of a GDU installer unlock card. In addition, any removal or addition of electrical components
or ferrous materials within 10 ft of the GMU 44( ) will require recalibration of the AHRS.
5.4.1
Removal
To remove the GMU 44( ) perform the following procedure:
1.
2.
3.
4.
5.4.2
Remove power to the AHRS unit.
Disconnect the GMU 44( ) connector.
Remove the three screws shown in Figure 5-6 (4) or Figure 5-7 (8).
Remove the GMU 44( ) from the mounting bracket.
Re-Installation
NOTE
If re-using the original mounting screws, 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 are reused,
coat screw threads with Loctite 242 (blue) thread-locking compound, Garmin PN 291-00023-02, or equivalent.
To re-install the GMU 44( ) perform the following procedure:
1.
2.
3.
4.
5.
5.4.3
Place the GMU 44( ) in the mounting bracket.
Install the three screws in Figure 5-6 (4) or Figure 5-7 (8) and torque to the specifications shown.
Connect the GMU 44( ) electrical connector.
Restore power to the AHRS unit.
Perform the Checkout procedure in Section 5.9.3.
Checkout
Perform the following calibration procedures and checks found in Section 6 of the G500H TXi Part 27 AML STC
Installation Manual to return the aircraft to service:
1.
2.
3.
4.
5.
Magnetometer Calibration.
Compass Swing.
Heading offset compensation if required by the previous step.
Engine Run-up Vibration check.
Configuration mode ground checks.
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5.5 GTP 59
Figure 5-8 GTP 59 Installation
5.5.1
Removal
To remove the GTP 59, perform the following procedure:
1. Remove power to the ADC unit.
2. Remove mounting nut(1) shown in Figure 5-8.
5.5.2
1.
2.
5.5.3
1.
2.
Re-Installation
Place GTP 59 in previous installation hole
Install washer(2) and nut(1) and torque to specifications in Figure 5-8.
Checkout
Restore power to the GDU 700/1060 and AHRS unit.
Verify the correct units (Celsius or Fahrenheit) and temperature reference (SAT, TAT, ISA) are displayed on
the PFD.
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Page 5-12
5.6 Backup GPS Antenna
The backup GPS antenna is designed for installation on top of an existing instrument panel glare shield. The selected
location must offer good visibility of the sky through the windshield. The optimal antenna position is horizontal, or as
close to horizontal as practical given the shape of the glare shield.
Figure 5-9 Backup GPS Antenna Installation (Non-removable Installation Example)
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G500H TXi Part 27 AML STC Maintenance Manual
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Figure 5-10 Backup GPS Antenna Installation (Removable Installation Example)
5.6.1
Removal
Use the following procedure to remove the backup GPS antenna:
1. Power off the GDU 1060/700 connected to the backup battery antenna.
2. Remove the two screws(6) securing the antenna (if installed with screws).
3. Lift up on the Backup GPS antenna to remove it.
4. Disconnect the connector from the GDU. If necessary, remove the GDU per Section 5.1.1).
5.6.2
Installation
Install the backup GPS antenna in the reverse order of the removal procedure.
5.6.3
1.
2.
3.
4.
5.
Checkout
Ensure the TXi system is in Normal mode and the aircraft has an unobstructed view of the sky or GPS repeater.
Ensure GPS #1 and GPS #2 (if equipped) are powered on.
Wait at least 5 minutes to allow GPS to acquire a position.
Power off GPS #1 and GPS #2 (if equipped).
Verify position on the map and “Backup GPS” message is annunciated on PFD.
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5.7 Calibration
This section provides guidance for calibrating the G500H TXi system if the previous calibration has become invalid.
Most calibrations require the use of an installer unlock card and must be performed by a Garmin dealer.
5.7.1
Attitude/Heading
Attitude and heading calibration requires the use of an Installer unlock card. If it becomes necessary to re-calibrate an
installed ADAHRS, refer to the calibration procedure contained in Sections 5 and 6 of the G500H TXi Part 27 AML STC
Installation Manual.
5.7.2
Analog NAV Calibration
Analog Nav calibration requires the use of an Installer unlock card. If it becomes necessary to re-calibrate the Analog
Nav, refer to the calibration procedure contained in Section 5.6.3 of the G500H TXi Part 27 AML STC Installation
Manual.
5.8 Uploading Software
The Software Upload page is used to update the software for the GDU 700/1060 and any LRUs directly interfaced to the
GDU 700( )/1060. The approved software version and part numbers can be found in the most recent revision of G500H
TXi Part 27 AML STC, Equipment List. Software updates must be accomplished using the following procedure:
1.
Create a Software Update SD card using approved software and instructions available on the
Dealer Resource Center.
NOTE
All software updates must be contained in a region file named “file.rgn” on the root directory of the Software
Update SD card.
2.
3.
4.
5.
Insert a Software Update SD card into the appropriate slot of the GDU 700/1060 as specified in
Section 2.1.4.
Power on the display in configuration mode.
Navigate to System Management → Software Upload.
Select the LRUs to upload software to from the list of available LRUs.
NOTE
Only LRUs that are configured in the system and currently online will be selectable for software updates.
6.
7.
Select the Update button.
Follow the on-screen display instructions.
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G500H TXi Part 27 AML STC Maintenance Manual
Page 5-15
5.9 System Checks
Periodic system checks that do not require a Garmin dealer to perform are contained in this section. For complete system
checkout procedures see Section 6 of the G500H TXi Part 27 AML STC Installation Manual.
5.9.1
Configuration Ground Check
The configuration ground check procedures are intended to verify each LRU and interface in the G500H TXi system has
been properly configured. Steps not applicable to a particular installation may be skipped.
NOTE
Throughout the configuration ground check section, references are made to particular functions and screens. If
a function or screen is not available, ensure that the system has been configured correctly.
The configuration ground checks must be performed on every GDU 700( )/1060. Before starting the configuration
mode checkout, the following conditions must be met:
1.
2.
3.
5.9.2
All GDU 700()/1060 displays in the system must be powered on in configuration mode.
All system LRUs must be powered on.
All installed LRUs must be configured per the printed configuration log contained in Appendix A.
LRU Status check
The Home page in the configuration mode of the GDU 700P/1060 shows the Devices Online that reports the status of
installed LRUs. The icon next to each LRU reports one of three colors to indicate the status of each LRU as described in
Table 5-1. Verify that all LRUs connected or configured to each display have a green indicator.
Table 5-1 LRU Status Indicators
Status Color
5.9.3
LRU Condition
Green
Red
The LRU is online. No faults are detected.
The LRU is online. A fault, warning, and/or error is detected.
Black
The LRU is not online.
Pitot-Static, Airspeed Setting, and Altimeter Checks
The following section verifies the correct operation of the GDU 700P/1060 altitude and airspeed tapes, standby
altimeter, and standby airspeed indicator using a Pitot-static ramp tester. When using a Pitot-static ramp tester, only
simulate normal aircraft operating conditions as defined in the aircraft Type Data (POH/ AFM) or other approved STC
to avoid component damage.
NOTE
The ADC may require a warm-up period of 15 minutes to reach full accuracy, however 30 minutes may be
required if the environmental temperature is below 0º C.
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G500H TXi Part 27 AML STC Maintenance Manual
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Verify correct operation of the altimeter and airspeed indicator configuration as follows.
1.
2.
3.
Print the configuration log from the multimedia card saved in the aircraft permanent records (refer to
Appendix A.5). If the configuration log is not available, refer to the RFM.
Verify the G500H TXi system is in Normal mode.
Verify all self-tests pass on the main startup screen.
NOTE
If the ADC and standby airspeed indicator are on separate Pitot-static systems, it is recommended to set up the
test set so that both systems can be tested at the same time, or separate tests must be completed for each
system.
4.
5.
6.
7.
8.
Using a Pitot-Static test set, increase the airspeed until the PFD airspeed tape pointer is at the bottom of the first
airspeed arc limit or marking. If an ESI-500 standby indicator is installed, refer section 5.5.3 of the G500H TXi
Part 27 AML STC Installation Manual for acceptable yellow markings.
a. Verify the PFD airspeed arc limit/marking matches the printed configuration log or RFM (±5 kt).
b. Verify the PFD airspeed and the standby airspeed indicator arc limit values are the same.
Increase the airspeed and stop at each arc limit and marking. Repeat the verifications of steps 4(a) and 4(b).
The last value verified should be the bottom of the red Vne arc.
The following applies to Variable Vne aircraft only:
a. Decrease the airspeed to 25 kt below Power-On Vne (i.e. bottom of the red arc). Increase the
indicated altitude to decrease Vne. Decrease the airspeed as needed so airspeed does not exceed Vne
during the simulated climb. Verify the indicated Vne at three individual altitudes match the RFM Vne
at the indicated altitude.
b. Decrease the indicated altitude (do not exceed vertical speed limitations) back to ambient static
pressure.
c. If variable Power-Off Vne is variable, repeat steps a. and b. using the red/white bar instead of PowerOn Vne.
Starting at the current airspeed, decrease the airspeed to zero, stopping at the airspeeds listed in Table 5-2. Do
not check airspeeds above Vne. Verify that the PFD and standby airspeed indicator values are within the
tolerances indicated.
Table 5-2 Airspeed Test Points
Test Set Airspeed (kt)
PFD Allowed
Tolerance (kt)
Recommended Standby
Airspeed Indicator
Tolerance (kt) [1]
50
80
100
120
150
180
210
250
290
±5.0
±3.5
±2.0
±2.0
±2.0
±2.0
±2.0
±2.0
±3.0
±5
±4
±3
±3
±3
±5
±5
±5
±6
Notes:
[1] If available, the aircraft or instrument manufacturer’s data should be referenced for standby tolerances.
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G500H TXi Part 27 AML STC Maintenance Manual
Page 5-17
Table 5-3 Typical Airspeed Arc Ranges
Arc Color
Description
YELLOW
Cautionary range
GREEN
Standard operational
range
Vne
Never exceed speed
RFM Section
Note
2-Limitations, see If an ESI-500 standby indicator is installed, refer
note.
to the G500H TXi Part 27 AML STC
Installation Manual for the acceptable yellow
arc below the green arc.
2-Limitations
2-Limitations
Could be configured as variable or fixed.
Variable configurations will typically decrease
at higher altitudes and/or lower temperatures.
Table 5-4 Typical Airspeed Markings
Marking
Description
RFM Section
Note
BLUE BAR
Typically marks PowerOff Vne in aircraft
certified by CAR 6.
2-Limitations
Blue radial on airspeed indicator of light twins
Set to OFF for single engine aircraft
RED/WHITE
BAR
Typically marks PowerOff Vne in aircraft
certified by Part 27.
2-Limitations
Could be configured as variable or fixed.
Variable configurations will typically decrease
at higher altitudes and/or lower temperatures.
5.9.3.1 Altimeter Check
The GDU 700P/1060 and standby altitude displays must be verified per Title 14 of the CFR 91.411 and
Part 43 Appendix E, with the following exception to 14 CFR Part 43 Appendix E, paragraph (b)(1); sub-paragraphs (iv)
(Friction) and (vi) (Barometric Scale Error) are not applicable to the GDU 700P/1060 due to the ADC interface and
instrument display being digital.
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G500H TXi Part 27 AML STC Maintenance Manual
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APPENDIX A
INSTALLATION SPECIFIC INFORMATION
This manual and the completed data in this appendix must be retained with the permanent aircraft maintenance records.
A.1
GENERAL INSTALLATION INFORMATION
Installation Date:__________/___________/____________
By (Installer):
___________________________________
Aircraft Year:
___________________________________
Aircraft Make: ___________________________________
Aircraft Model: ___________________________________
Aircraft Serial #: __________________________________
Aircraft Reg. #: ___________________________________
Installed System
GDU1
1060
700P
700L
MFD
PFD
GDU2
1060
700P
700L
MFD
PFD
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G500H TXi Part 27 AML STC Maintenance Manual
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A.2
LRU INFORMATION
The table below is a record of installed equipment.
Unit
Part Number
GDU #1
011-0330____ - ____
GDU #2
011-0330____ - ____
GSU 75H #1
011-03094-_____
GSU 75H #2
011-03094-_____
GMU 44 #1 or
011-00870-_____
GMU 44B #1
011-04201-_____
GMU 44 #2 or
011-00870-_____
GMU 44B #2
011-04201-_____
GTP 59 #1
011-00978-_____
GTP 59 #2
011-00978-_____
GCU 485
011-03582-_____
Flight Stream 510
011-03595-_____
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G500H TXi Part 27 AML STC Maintenance Manual
Page A-2
A.3 EQUIPMENT LOCATION
The table below is record of the equipment locations.
Unit
Fuselage Station (CG) Description of Location
GDU #1
in.
GDU #2
in.
GSU 75H #1
in.
GSU 75H #2
in.
GMU 44 #1
in.
GMU 44 #2
in.
GTP 59 #1
in.
GTP 59 #2
in.
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G500H TXi Part 27 AML STC Maintenance Manual
Page A-3
A.4 WIRE ROUTING
The medium body or small body diagrams are a record of wire routing for the GDU 700/1060, ADAHRS, GMU 44( ),
GTP 59, and interfaces throughout the aircraft structure.
(Option 1- Medium Body Rotorcraft)
Additional wire routing notes (e.g. bulkhead or interposing connector locations):
__________________________________________________________________________________________
__________________________________________________________________________________________
__________________________________________________________________________________________
__________________________________________________________________________________________
__________________________________________________________________________________________
__________________________________________________________________________________________
__________________________________________________________________________________________
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G500H TXi Part 27 AML STC Maintenance Manual
Page A-4
(Option 2- Small Body Rotorcraft)
Additional wire routing notes (e.g. bulkhead or interposing connector locations):
__________________________________________________________________________________________
__________________________________________________________________________________________
__________________________________________________________________________________________
__________________________________________________________________________________________
__________________________________________________________________________________________
__________________________________________________________________________________________
__________________________________________________________________________________________
__________________________________________________________________________________________
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G500H TXi Part 27 AML STC Maintenance Manual
Page A-5
A.5 GDU 700/1060 CONFIGURATION FILES
The affixed memory card includes a record of the G500H TXi configuration. The data was created in accordance with
Section 4.1.1.
Saved with GDU 700/1060 System Software Version: _________________
Aircraft
Configuration
Card
(Affix Here)
NOTE
The GDU 700/1060 software version used to create the card should be the same version, or an earlier
compatible version, that is currently installed on the GDU 700/1060.
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G500H TXi Part 27 AML STC Maintenance Manual
Page A-6
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