Garmin | G500 TXi | Garmin G500 TXi G500/G600 TXi Part 23 AML STC Maintenance Manual

Garmin G500 TXi G500/G600 TXi Part 23 AML STC Maintenance Manual
G500/G600 TXi Part 23 AML STC
Maintenance Manual
Contains Instructions for Continued Airworthiness
for STC SA02571SE
Aircraft make, model, registration number, and serial
number, along with the applicable STC configuration
information, must be completed in Appendix A and
saved with aircraft permanent records.
190-01717-B1
June 2019
Revision 3
© 2019
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190-01717-B1
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G500/G600 TXi Part 23 AML STC Maintenance Manual
Page i
INFORMATION SUBJECT TO EXPORT CONTROL LAWS
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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
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• 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
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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.
190-01717-B1
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G500/G600 TXi Part 23 AML STC Maintenance Manual
Page ii
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
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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
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rights in the Licensed Software.
190-01717-B1
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G500/G600 TXi Part 23 AML STC Maintenance Manual
Page iii
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
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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, reexport 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.
190-01717-B1
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G500/G600 TXi Part 23 AML STC Maintenance Manual
Page iv
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
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AS TO THE QUALITY AND PERFORMANCE OF THE LICENSED SOFTWARE AND
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OR LOSS CAUSED BY SUCH USE OF THE LICENSED SOFTWARE.
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PERMITTED BY APPLICABLE LAW, UNDER NO CIRCUMSTANCES AND
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(b) Licensee's breach of this Agreement.
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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
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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
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processes or materials (“Feedback”). Garmin may in connection with any of its products or
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any manner without any obligation, payment, royalty or restriction whether based on
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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.
f.
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.
g. 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.
h. 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
190-01717-B1
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Page vi
are cumulative and not exclusive of any rights or remedies that any Party would otherwise
have.
i.
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.
j.
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.
k. 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.
l.
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.
190-01717-B1
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Page vii
RECORD OF REVISIONS
Revision
Revision Date
Description
1
11/17/17
2
08/15/2018
Revised to address changes for the version 2.20 STC update.
3
06/25/19
Revised to address changes for the version 3.00 STC update.
Initial release.
DESCRIPTION OF CHANGES
Section
2.1
Description
Listed GEA 71B Enhanced as an engine sensor.
2.1.3
Updated section for included GEA 71B Enhanced installations.
2.1.7
Added GEA 71B Enhanced to Table 2-2 G500/600 TXi LRU Electrical Load.
2.2.1
Added restrictions for display of Turbine EIS on GDU 700P.
Added image of GDU 700P configured as Turbine EIS to Figure 2-2.
2.2.2
Added restrictions for display of Turbine EIS on GDU 700L.
2.2.3
Added image of GDU 1060 configured as MFD/PFD/EIS with Turbine EIS to
Figure 2-6.
2.2.14
Added Section 2.2.14 GEA 71B Enhanced Engine.
3.4.1
Added GEA 71B and GBB 54 to installations with aluminum foil tape.
3.5
4.2.9
Added GEA 71B Enhanced to Table 3-2 Electrical Bonding Requirements.
Added GEA 71B pinout.
5.8
Added Section 5.8 GEA 71B Enhanced.
A.2
Added GEA 71B to LRU Information form.
A.3
Added GEA 71B Equipment Location form.
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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.
WARNING
Failure to properly configure the EIS gauges per the POH/AFM and other approved data
could result in serious injury, damage to equipment, or death.
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 G500/G600 TXi components in or near water.
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TABLE OF CONTENTS
1 INTRODUCTION ............................................................................................................... 1-1
1.1
1.2
1.3
1.4
1.5
1.6
1.7
Purpose .......................................................................................................................................1-2
Scope ..........................................................................................................................................1-2
Organization ...............................................................................................................................1-2
Applicability...............................................................................................................................1-2
Publications ................................................................................................................................1-3
Revision and Distribution...........................................................................................................1-3
Terminology and Acronyms.......................................................................................................1-3
2 SYSTEM DESCRIPTION .................................................................................................. 2-1
2.1
2.2
System Overview .......................................................................................................................2-2
LRU Description, Control, and Operation .................................................................................2-6
3 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS .......................................... 3-1
3.1
3.2
3.3
3.4
3.5
3.6
3.7
3.8
3.9
3.10
3.11
Airworthiness Limitations..........................................................................................................3-2
Servicing Information ................................................................................................................3-2
Maintenance Intervals ................................................................................................................3-3
Visual Inspection........................................................................................................................3-5
Electrical Bonding Check...........................................................................................................3-6
RVSM Periodic Maintenance (Socata TBM 700/850 Only) .....................................................3-7
Overhaul Period..........................................................................................................................3-7
Special Inspection Requirements ...............................................................................................3-8
Application of Protective Treatments ........................................................................................3-9
Data Relative to Structural Fasteners .........................................................................................3-9
Additional Instructions ...............................................................................................................3-9
4 TROUBLESHOOTING ...................................................................................................... 4-1
4.1
4.2
4.3
General System Troubleshooting ...............................................................................................4-2
Connector Information ...............................................................................................................4-3
Troubleshooting Flow Charts...................................................................................................4-29
5 EQUIPMENT MAINTENANCE AND CHECKOUT PROCEDURES......................... 5-1
5.1
5.2
5.3
5.4
5.5
5.6
5.7
5.8
5.9
5.10
5.11
5.12
5.13
5.14
5.15
5.16
GDU 700/1060 ...........................................................................................................................5-3
GCU 485 ..................................................................................................................................5-11
EIS Annunciator.......................................................................................................................5-13
GDC 72 ...................................................................................................................................5-14
GSU 75( ), GRS 79 ..................................................................................................................5-16
GAD 43/43e .............................................................................................................................5-18
GEA 110...................................................................................................................................5-20
GEA 71B Enhanced .................................................................................................................5-23
GBB 54.....................................................................................................................................5-26
GMU 44....................................................................................................................................5-29
GTP 59 .....................................................................................................................................5-31
Backup GPS Antenna...............................................................................................................5-33
EIS Sensors ..............................................................................................................................5-35
Calibration ................................................................................................................................5-43
Uploading Software..................................................................................................................5-45
System Checks .........................................................................................................................5-46
APPENDIX A INSTALLATION-SPECIFIC INFORMATION ......................................... A-1
A.1 General Information ..................................................................................................................A-1
A.2 LRU Information.......................................................................................................................A-2
A.3 Equipment Location ..................................................................................................................A-3
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A.4
A.5
A.6
A.7
A.8
A.9
A.10
Wire Routing - Single Engine ...................................................................................................A-4
Wire Routing - Twin Engine .....................................................................................................A-5
Saved Configuration File ..........................................................................................................A-6
Print Configuration Log ............................................................................................................A-6
GDU 1060 EIS Gauge Layout Template ..................................................................................A-7
GDU 700P EIS Gauge Layout Template ..................................................................................A-8
GDU 700L EIS Gauge Layout Template ................................................................................A-10
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LIST OF FIGURES
Figure 2-1
Figure 2-2
Figure 2-3
Figure 2-4
Figure 2-5
Figure 2-6
Figure 2-7
Figure 2-8
Figure 2-9
Figure 2-10
Figure 2-11
Figure 2-12
Figure 2-13
Figure 2-14
Figure 2-15
Figure 2-16
Figure 2-17
Figure 2-18
Figure 2-19
Figure 2-20
Figure 2-21
Figure 2-22
Figure 2-23
Figure 2-24
Figure 4-1
Figure 4-2
Figure 4-3
Figure 4-4
Figure 4-5
Figure 4-6
Figure 4-7
Figure 4-8
Figure 4-9
Figure 4-10
Figure 4-11
Figure 4-12
Figure 4-13
Figure 4-14
Figure 4-15
Figure 4-16
Figure 4-17
Figure 4-18
Figure 4-19
Figure 4-20
Figure 4-21
Figure 4-22
Figure 4-23
Figure 4-24
Entering the Configuration Mode on the GDU ...................................................................2-3
GDU 700P Display Configurations .....................................................................................2-6
GDU 700P Features and Controls .......................................................................................2-7
GDU 700L Display Configurations.....................................................................................2-8
GDU 700L Features and Controls .......................................................................................2-9
GDU 1060 Display Configurations ...................................................................................2-10
GDU 1060 Features and Controls......................................................................................2-11
GCU 485 ............................................................................................................................2-12
Garmin Backup GPS Antenna ...........................................................................................2-12
GSU 75( ) ADAHRS Unit .................................................................................................2-13
GRS 79 AHRS Unit...........................................................................................................2-13
GDC 72 ADC Unit ............................................................................................................2-14
GMU 44 Magnetometer.....................................................................................................2-14
GTP 59 Outside Air Temperature Probe ...........................................................................2-14
GBB 54 Backup Battery ....................................................................................................2-15
GEA 110 Engine Interface.................................................................................................2-15
GEA 71B Enhanced Engine ..............................................................................................2-15
GAD 43 (Left) and GAD 43e (Right)................................................................................2-16
Engine Annunciator ...........................................................................................................2-17
Carburetor Temperature Probe ..........................................................................................2-17
Oil Temperature Probe ......................................................................................................2-17
Fuel Flow Sensor FT-60 (Left) and FT-90 (Right) ...........................................................2-18
Brass Pressure Sensor ........................................................................................................2-18
Stainless Steel Pressure Sensor..........................................................................................2-18
62 Pin D-sub Connectors Numbering Scheme for Female/Male Contacts .........................4-3
GDU 700P Connectors ........................................................................................................4-4
GCU 485 Connector ............................................................................................................4-9
View of J721 Connector Looking at GDC 72 ...................................................................4-10
View of J751 Connector Looking at GSU 75( ) ................................................................4-12
View of J791 Connector Looking at GRS 79 ....................................................................4-14
GAD 43/43e J431/P431 Connector Looking at Unit.........................................................4-16
GAD 43e J432/P432 Connector Looking at Unit..............................................................4-18
GAD 43e J433/P433 Connector Looking at Unit..............................................................4-20
GEA 110 Connectors .........................................................................................................4-21
GEA 110 J1101/P1101 Connector Looking at Unit ..........................................................4-21
GEA 110 J1102/P1102 Connector Looking at Unit ..........................................................4-22
GEA 71B Enhanced Connectors .......................................................................................4-24
GBB 54 J541/P541 Connector...........................................................................................4-27
J441/P441 Connector Looking at Pigtail ...........................................................................4-28
GDU Alert Message Troubleshooting ...............................................................................4-30
GDU Config and Battery Alert Message Troubleshooting ...............................................4-31
PFD Alert Message Troubleshooting ................................................................................4-32
AHRS/ADC Alert Message Troubleshooting ...................................................................4-33
Terrain Alert Message Troubleshooting ............................................................................4-34
Traffic Alert Message Troubleshooting.............................................................................4-35
Audio/Weather Alert Message Troubleshooting ...............................................................4-36
External LRU Failure Message Troubleshooting ..............................................................4-37
External LRU Service Message Troubleshooting .............................................................4-38
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page xii
Figure 4-25
Figure 4-26
Figure 4-27
Figure 5-1
Figure 5-2
Figure 5-3
Figure 5-4
Figure 5-5
Figure 5-6
Figure 5-7
Figure 5-8
Figure 5-9
Figure 5-10
Figure 5-11
Figure 5-12
Figure 5-13
Figure 5-14
Figure 5-15
Figure 5-16
Figure 5-17
Figure 5-18
Figure 5-19
Figure 5-20
Figure 5-21
Figure 5-22
Figure 5-23
Figure 5-24
Figure 5-25
Figure 5-26
Figure A-1
Figure A-2
Figure A-3
Figure A-4
Figure A-5
GAD Fault Message Troubleshooting ...............................................................................4-39
GAD Fault Message Troubleshooting Continued .............................................................4-40
EIS Gauge Troubleshooting ..............................................................................................4-41
GDU 1060 Installation.........................................................................................................5-3
GDU 700P Installation ........................................................................................................5-4
Integrated ADC Module Installation ...................................................................................5-7
Configuration Module Installation ......................................................................................5-8
GCU 485 Installation .........................................................................................................5-11
Panel Cutout for GCU 485 ................................................................................................5-12
EIS Caution and Warning Annunciator Installation ..........................................................5-13
GDC 72 Installation (Sheet Metal Shelf Example) ...........................................................5-14
GSU 75( ) Installation (Sheet Metal Shelf Example) ........................................................5-16
GAD 43 Installation (Sheet Metal Shelf Example) ...........................................................5-18
GEA 110 Installation (Mounted Directly to Airframe Example) ......................................5-20
GEA 110 Installation (Mounted on a Tray Example) .......................................................5-21
GEA 71B Enhanced (Metallic Example) ..........................................................................5-23
GEA 71B Enhanced (Sandwich Panel Example) ..............................................................5-24
GBB 54 Installation (Sheet Metal Shelf Example)............................................................5-26
GBB 54 Battery Cell Replacement....................................................................................5-28
GMU 44 Installation (Universal Mount Example) ............................................................5-30
GTP 59 Installation (Aircraft with Metallic Skin Example) .............................................5-31
Backup GPS Antenna Installation (Non-removable Installation Example) ......................5-33
Backup GPS Antenna Installation (Removable Installation Example) .............................5-34
Carburetor Temperature Sensor Installation Example ......................................................5-36
Oil Temperature Sensor Installation Example...................................................................5-37
Brass Sensor Installation (Coupling Mount Example) ......................................................5-39
Stainless Steel Sensor Installation (Housing Mount Example) .........................................5-40
Fuel Flow Transducer Installation .....................................................................................5-42
Airspeed Configuration Type ............................................................................................5-47
GDU 1060 EIS Gauge Template ........................................................................................A-7
GDU 700P EIS Gauge Layout Template............................................................................A-8
GDU 700P MFD/EIS Gauge Layout Template..................................................................A-9
GDU 700L EIS Gauge Layout Template .........................................................................A-10
GDU 700L MFD/EIS Gauge Layout Template................................................................A-11
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Page xiii
LIST OF TABLES
Table 1-1
Table 2-1
Table 2-2
Table 3-1
Table 3-2
Table 4-1
Table 4-2
Table 4-3
Table 4-4
Table 4-5
Table 4-6
Table 4-7
Table 4-8
Table 4-9
Table 4-10
Table 4-11
Table 4-12
Table 5-1
Table 5-2
Table 5-3
Table 5-4
Table 5-5
Table 5-6
Table 5-7
Reference Documentation ...................................................................................................1-3
AML STC Installed Sensors ................................................................................................2-3
G500/600 TXi LRU Electrical Load ...................................................................................2-5
Periodic Maintenance ..........................................................................................................3-3
Electrical Bonding Requirements ........................................................................................3-6
G500/G600 TXi Failures .....................................................................................................4-2
G500/G600 TXi - GDU 700/1060 Connectors....................................................................4-4
G500/G600 TXi - GCU 485 Connectors .............................................................................4-9
G500/G600 TXi - GDC 72 Connectors .............................................................................4-10
G500/G600 TXi - GSU 75 Connectors .............................................................................4-12
G500/G600 TXi - GRS 79 Connectors..............................................................................4-14
G500/G600 TXi - GAD 43 Connectors.............................................................................4-16
G500/G600 TXi - GAD 43e Connectors ...........................................................................4-18
G500/G600 TXi - GEA 110 Connectors ...........................................................................4-21
G500/G600 TXi - GEA 71B Enhanced Connectors..........................................................4-24
G500/G600 TXi - GBB 54 Connectors .............................................................................4-27
G500/G600 TXi - GMU 44 Connectors ............................................................................4-28
Pressure Sensor Equipment List ........................................................................................5-38
LRU Status Indicators........................................................................................................5-46
Airspeed Test Points ..........................................................................................................5-48
Advanced Airframe Specific Configuration Data – Arc Ranges.......................................5-49
Advanced Airframe Specific Configuration Data – Markings ..........................................5-51
Air Data Test Points...........................................................................................................5-53
Altitude Hold Check Log...................................................................................................5-55
190-01717-B1
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Page xiv
1 INTRODUCTION
1.1 Purpose..............................................................................................................................................1-2
1.2 Scope.................................................................................................................................................1-2
1.3 Organization......................................................................................................................................1-2
1.4 Applicability .....................................................................................................................................1-2
1.5 Publications.......................................................................................................................................1-3
1.6 Revision and Distribution .................................................................................................................1-3
1.7 Terminology and Acronyms .............................................................................................................1-3
1.7.1 Terminology ...............................................................................................................................1-3
1.7.2 Acronyms ...................................................................................................................................1-4
190-01717-B1
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G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 1-1
1.1 Purpose
This document is designed for use by the installing agency of the Garmin G500/G600 TXi PFD/MFD/EIS
system as a Maintenance Manual and Instructions for Continued Airworthiness in response to FAR
Part 23.1529 and Part 23 Appendix G. This ICA includes information required by the operator to
adequately maintain the Garmin G500/G600 TXi system installed under AML STC.
1.2 Scope
This document provides maintenance instructions and identifies the Instructions for Continued
Airworthiness for the modification of the aircraft for installation of the Garmin G500/G600 TXi PFD/
MFD/EIS system installed under the AML STC.
1.3 Organization
The following outline briefly describes the organization of this manual:
Section 2.1: System Overview
Provides a description of the G500/G600 TXi system equipment installed by this STC.
Section 2.2: LRU Description, Control, and Operation
Provides basic control and operation information specifically tailored to maintenance practices.
Section 3: Instructions for Continued Airworthiness
Provides Instructions for Continued Airworthiness of the G500/G600 TXi system LRUs.
Section 4: Troubleshooting
Provides troubleshooting information, including connector information, pinouts, and flowcharts to aid in
diagnosing and resolving problems with G500/G600 TXi system equipment.
Section 5: Equipment Maintenance and Checkout Procedures
Provides instructions for the removal and replacement of G500/G600 TXi system LRUs, including system
checkout procedures.
Appendix A: Installation-Specific Information
Provides a template to record aircraft-specific installation and configuration data for the G500/G600 TXi
system.
1.4 Applicability
This document applies to all aircraft with the G500/G600 TXi system installed in accordance with AML
STC SA02571SE. 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.
190-01717-B1
Rev. 3
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Page 1-2
1.5 Publications
In addition to this manual, the following documents are recommended for performing maintenance on the
G500/G600 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 G500/G600 TXi
system.
Table 1-1 Reference Documentation
Document
Garmin P/N
G500/G600 TXi Part 23 AML STC Equipment List
005-00795-D1
AFMS, G500/G600 TXi Part 23 AML STC
190-01717-B2
G500/G600 TXi Part 23 AML STC Installation Manual
190-01717-B3
1.6 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 website. Dealers are
notified of manual revision changes via Garmin Service Bulletins posted to the Dealer Resource Center.
Owners and operators may obtain the latest revision of this document at flyGarmin.com or by contacting a
Garmin dealer. Garmin contact information is available at flyGarmin.com.
1.7 Terminology and Acronyms
1.7.1
Terminology
Except where specifically noted, references made to the “GDU 700/1060” will apply to the GDU 700P,
GDU 700L, and GDU 1060 equally.
Except where specifically noted, references made to the “G500/G600 TXi system” will apply to an
installed system with one or more GDU 1060s or GDU 700s and all LRUs interfaced to the GDUs.
Except where specifically noted, references made to Garmin products with a “()” designation after the
model number refer to all sub-models in that series (e.g., a reference to GDU 700() refers to both the
GDU 700P and the GDU 700L variants).
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., wooden aircraft, aircraft with composite skin, or aircraft with tube-and-fabric construction).
Unless otherwise stated, all units of measure are US standard units.
190-01717-B1
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Page 1-3
1.7.2
Acronyms
The following terminology is used within this document.
AC
Alternating Current
ICA
Instructions for Continued Airworthiness
ADAHRS Air Data Attitude Heading Reference
System
ILS
Instrument Landing System
ADC
Air Data Computer
LCD
Liquid Crystal Display
ADF
Automatic Direction Finder
LOC
Localizer
ADS-B
Automatic Dependent Surveillance
Broadcast
LRU
Line Replaceable Unit
AFMS
Aircraft Flight Manual Supplement
MFD
Multi-Function Display
AHRS
Altitude and Heading Reference System NPT
National Pipe Taper
AML
Approved Model List
OAT
Outside Air Temperature
A/P
Autopilot
ODA
Organization Designation Authorization
ASI
Airspeed Indicator
PFD
Primary Flight Display
BIT
Built-In Test
POH
Pilot’s Operating Handbook
CFR
Code of Federal Regulations
PPS
Pulse Per Second
CHT
Cylinder Head Temperature
RNAV
Area Navigation
DC
Direct Current
RPM
Revolutions Per Minute
DME
Distance Measuring Equipment
RVSM
Reduced Vertical Separation Minimum
EGT
Exhaust Gas Temperature
SBAS
Satellite Based Augmentation System
EIS
Engine Indicating System
SD
Secure Digital
ES
Extended Squitter
SDI
Source/Destination Identifiers
FAA
Federal Aviation Administration
STC
Supplemental Type Certificate
FAR
Federal Aviation Regulation
TAS
Traffic Advisory System
FD
Flight Director
TAWS
Terrain Awareness System
FIS-B
Flight Information Services Broadcast
SSM
Sign/Status Matrix
GAD
Garmin Interface Adapter
TCAS
Traffic Collision Avoidance System
GBB
Garmin Backup Battery
TCAD
Traffic Collision Avoidance Device
GCU
Garmin Control Unit
TIS
Traffic Information Service
GDC
Garmin Data Computer
TSO
Technical Standard Order
GDU
Garmin Display Unit
UAT
Universal Access Transceiver
GEA
Garmin Engine Adapter
UTC
Coordinated Universal Time
GMU
Garmin Magnetometer Unit
VOR
VHF Omni-Directional Range
GPS
Global Position System
WAAS
Wide Area Augmentation System
GSR
Garmin Services
WXR
Weather Radar
GRS
Garmin Reference System
GTP
Garmin Temperature Probe
GWX
Garmin Weather Radar
HSI
Horizontal Situation Indicator
IAS
Indicated Air Speed
190-01717-B1
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G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 1-4
2 SYSTEM DESCRIPTION
2.1 System Overview..............................................................................................................................2-2
2.1.1 PFD Functionality ......................................................................................................................2-2
2.1.2 MFD Functionality.....................................................................................................................2-2
2.1.3 EIS Functionality........................................................................................................................2-2
2.1.4 Entering Configuration Mode ....................................................................................................2-3
2.1.5 SD Card Location Options .........................................................................................................2-4
2.1.6 Save/Load SD.............................................................................................................................2-4
2.1.7 Electrical Load Information .......................................................................................................2-5
2.2 LRU Description, Control, and Operation........................................................................................2-6
2.2.1 GDU 700P Display.....................................................................................................................2-6
2.2.2 GDU 700L Display ....................................................................................................................2-8
2.2.3 GDU 1060 Display...................................................................................................................2-10
2.2.4 GCU 485 Control Unit .............................................................................................................2-12
2.2.5 Backup GPS Antenna...............................................................................................................2-12
2.2.6 Integrated ADAHRS Unit ........................................................................................................2-12
2.2.7 GSU 75( ) ADAHRS Unit........................................................................................................2-13
2.2.8 GRS 79 AHRS Unit .................................................................................................................2-13
2.2.9 GDC 72 ADC Unit...................................................................................................................2-14
2.2.10 GMU 44 Magnetometer ...........................................................................................................2-14
2.2.11 GTP 59 OAT Probe..................................................................................................................2-14
2.2.12 GBB 54 Backup Battery...........................................................................................................2-15
2.2.13 GEA 110 Engine Interface .......................................................................................................2-15
2.2.14 GEA 71B Enhanced Engine .....................................................................................................2-15
2.2.15 GAD 43/43e Adapter ...............................................................................................................2-16
2.2.16 EIS Components.......................................................................................................................2-17
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Page 2-1
2.1 System Overview
The G500/G600 TXi installation can provide PFD, MFD, and EIS functions. Three display models, the
GDU 700P, GDU 700L, and GDU 1060, are used to convey the information. The G500/G600 TXi system
utilizes engine sensors and the GEA 71B/110 Engine Adapter to provide EIS functions.
2.1.1
PFD Functionality
The primary flight display provides attitude, heading, airspeed, altitude, and vertical speed. Optional
features, such as Synthetic Vision, autopilot control and annunciation, HSI map overlays, and more, can
also be provided by the PFD. The minimum PFD installation consists of:
• GDU 700/1060 display
• ADAHRS capability (must have one of the following):
◦ GRS 77 AHRS and GDC 74() ADC
◦ GRS 79 AHRS and GDC 72() ADC
◦ GSU 75() ADAHRS
◦ Internal ADAHRS (part of the GDU)
• GMU 44 Magnetometer
• GTP 59 Temperature Probe
• External WAAS GPS navigation source
2.1.2
MFD Functionality
The multi-function display provides at a minimum a moving map display. The display can optionally
provide traffic, terrain, audio, and weather functions depending on installed equipment. Additionally, the
MFD can be used as an integrated standby PFD when installed in accordance with the integrated standby
configuration described in G500/G600 TXi Part 23 AML STC Installation Manual (P/N 190-01717-B3).
The MFD minimum system installation consists of:
• GDU 700P or GDU 1060 display
• External WAAS GPS navigation source
2.1.3
EIS Functionality
EIS is applicable to single-engine turboprop aircraft as well as single and twin-engine reciprocating engine
equipped aircraft. For reciprocating engine aircraft, the EIS will display 4 and 6 cylinder engine data and
select airframe parameters. The EIS can display engine and airframe operating parameters on the GDU.
The EIS gauges include optional gauges and those required by the aircraft POH and manufacturer.
This manual only provides information for the EIS sensors installed per the G500/G600 TXi AML STC.
Table 2-1 lists the sensors that are maintained in this manual. Refer to the applicable maintenance data
and/or TSO manual for other sensors that are interfaced to the EIS.
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Page 2-2
Table 2-1 AML STC Installed Sensors
Function
Manufacturer P/N
Garmin P/N
Garmin 150 PSIG pressure, (Brass)
011-04202-30
Kulite APT-20GX-1000-150G (Stainless)
494-30032-00
UMA T3B3-2.5G
494-70009-00
Garmin 30 PSIA Press, (Brass)
011-04202-00
Kulite APT-20GX-1000-25A
494-30030-00
Garmin 75 PSIG Press, (Brass)
011-04202-20
Garmin 15 PSIG Press, (Brass)
011-04202-10
Kulite APT-20GX-1000-50G
494-30031-00
Kulite APT-20GX-1000-15G
494-30029-00
EI FT-60
494-10001-00
EI FT-90
494-10001-01
RPM
N/A (Magneto P-lead)
N/A
Carb Air Temp
UMA T3B10-SG
494-70010-00
Oil Press
Oil Temp
Manifold Press
Fuel Press
Fuel Flow
2.1.4
Entering Configuration Mode
The Configuration mode of the GDU 700/1060 can be accessed by holding down the inner knob located at
the bottom-right of the unit, as shown in Figure 2-1, upon initial power-up. The knob must be pressed until
the splash screen shown in Figure 2-1 disappears and the configuration menu appears.
Figure 2-1 Entering the Configuration Mode on the GDU
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G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 2-3
2.1.5
SD Card Location Options
The GDU 700/1060 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
◦ Screen shots (if a card is present in both slots, the screen shot will print to the top slot only)
◦ Update databases
• 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)
2.1.6
Save/Load SD
The aircraft configuration settings can be saved to an SD card, as well as loaded from an SD card using the
following procedures:
To save your aircraft configuration settings to an SD card:
1. Insert an SD card into the top/left slot of any GDU 700/1060 in the system.
2. Power on all GDUs in the G500/G600 TXi system in Configuration mode.
3. From the Home screen, select SD save.
4. Enter the name you would like the configuration saved as.
5. Select Enter.
To load your aircraft configuration settings from an SD card:
NOTE
An Installer Unlock Card is required to load configuration settings to an SD card.
NOTE
Loading the system configuration from an SD card will overwrite the current system
configuration and is not reversible. It is recommended to always save your current
configuration to the SD card first before loading a new configuration.
1.
2.
3.
4.
5.
6.
Insert an SD card into the top/left slot of any GDU 700/1060 in the system.
Power on all GDUs in the G500/G600 TXi system in Configuration mode.
Ensure you have set the GDU IDs, SYS ID Sources, 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.
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G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 2-4
NOTE
Information not contained in the selected Aircraft Configuration File will be grayed out
and cannot be selected.
7.
8.
9.
10.
Select the check box next to the configuration to be loaded.
Select SD Load.
Verify the loaded configuration(s) is identical to those recorded in the aircraft’s permanent records.
Perform the Configuration Ground Check in Section 5.16.1. 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.
2.1.7
Electrical Load Information
Electrical load information for the G500/G600 TXi system LRUs is provided below. Appendix A of this
document contains details specific to the load changes for the specific aircraft installation.
Table 2-2 G500/600 TXi LRU Electrical Load
LRU
14 Volt Current Draw
Typical
Maximum
28 Volt Current Draw
Typical
Maximum
GDU 700( )
3.0 A
6.0 A
1.5 A
3.0 A
GDU 1060
5.0 A
8.0 A
2.5 A
4.0 A
GRS 79/GMU 44
480 mA
958 mA
240 mA
479 mA
GRS 77/GMU 44
600 mA
1.0 A
300 mA
1.0 A
GSU 75( )/GMU 44/GTP 59
760 mA
958 mA
380 mA
479 mA
GDC 72/GTP 59
420 mA
958 mA
210 mA
479 mA
GDC 74( )/GTP 59
410 mA
480 mA
200 mA
235 mA
GAD 43
410 mA
720 mA
210 mA
350 mA
GAD 43e
790 mA
1.22 A
390 mA
590 mA
GCU 485
120 mA
357 mA
64 mA
179 mA
GEA 110
0.30 A
0.60 A
0.15 A
0.30 A
GEA 71B
0.34 A
1.08 A
0.15 A
0.54 A
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Page 2-5
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, MFD, EIS, or MFD/EIS display. The GDU 700P cannot be configured for
Turboprop EIS with the MFD/EIS configuration. Turboprop EIS is only available on the GDU 700P EIS
configuration. The GDU 700P is available with or without an integrated ADAHRS. The GDU 700P
requires a compatible GPS/SBAS navigator for MFD and PFD functionality.
Figure 2-2 GDU 700P Display Configurations
(Clockwise from top left: MFD, PFD, Reciprocating EIS, Turboprop EIS, and MFD/EIS)
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The GDU 700P has numerous features and controls, as shown in Figure 2-3. These features and controls
are as follows:
• 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 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
Power Button
Photocell
Top Card Slot
Bottom Card Slot
Dual Concentric Knob
Figure 2-3 GDU 700P Features and Controls
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G500/G600 TXi Part 23 AML STC Maintenance Manual
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2.2.2
GDU 700L Display
The GDU 700L is a 7-inch LCD landscape-oriented panel mount control and display unit. The GDU 700L
can be configured as a PFD, EIS, or MFD/EIS split display. The GDU 700L cannot be configured for
Turboprop EIS (only reciprocating engine EIS at this time). The GDU 700L is available with or without an
integrated ADAHRS. The GDU 700L requires a compatible GPS/SBAS navigator for MFD and PFD
functionality.
Figure 2-4 GDU 700L Display Configurations
(Clockwise from top left: PFD, EIS, and MFD/EIS)
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G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 2-8
The GDU 700L has numerous features and controls, as shown in Figure 2-5. These features and controls
are as follows:
• 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
Power Key
Photocell
Left Card Slot
Right Card Slot
Dual Concentric Knob
Figure 2-5 GDU 700L Features and Controls
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G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 2-9
2.2.3
GDU 1060 Display
The GDU 1060 is a 10.6-inch LCD panel mount control and display unit capable of displaying PFD and
MFD data with optional EIS display. The GDU 1060 may be optionally equipped with an integrated
ADAHRS or must be interfaced to an external ADC/AHRS LRU. Shown below is a combined PFD/MFD/
EIS display. The GDU 1060 requires interface with a compatible GPS/SBAS navigator.
Figure 2-6 GDU 1060 Display Configurations
(MFD/PFD and MFD/PFD/EIS with both Reciprocating EIS and Turboprop EIS shown)
190-01717-B1
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G500/G600 TXi Part 23 AML STC Maintenance Manual
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The GDU 1060 has numerous features and controls, as shown in Figure 2-7. These features and controls
are as follows:
• 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 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
Power Key
Photocell
Top Card Slot
Bottom Card Slot
Left Dual
Concentric
Knob
Right Dual
Concentric Knob
Figure 2-7 GDU 1060 Features and Controls
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2.2.4
GCU 485 Control Unit
The GCU 485 is a panel mount remote control unit that provides an alternate method of controlling the
G500/G600 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.
The GCU 485 installation is optional.
Figure 2-8 GCU 485
(P/N 011-03582-01 Shown)
2.2.5
Backup GPS Antenna
GDU 1060 and GDU 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 glareshield.
Figure 2-9 Garmin Backup GPS Antenna
2.2.6
Integrated ADAHRS Unit
The GDU 700/1060 has an optional integrated ADAHRS unit that provides flight altitude, vertical speed,
airspeed, attitude, OAT, and heading data for flight instrumentation. The AHRS portion is contained
internally within the GDU 700/1060. An Integrated ADC module is then plugged into the AHRS board and
attached to the back of the GDU 700/1060. The internal ADAHRS receives data from the GMU 44 and
GTP 56 that are connected to the GDU 700/1060. The integrated ADAHRS utilizes GPS signals sent from
the GPS/SBAS navigator. Attitude, heading, and air data can be sent using ARINC 429 digital signals to
external LRUs and the GAD43/43e.
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2.2.7
GSU 75( ) ADAHRS Unit
The GSU 75/75B ADAHRS is a remote LRU that provides flight altitude, vertical speed, airspeed, attitude,
OAT, and heading data for flight instrumentation. The GSU 75/75B receives data from the GMU 44
Magnetometer and GTP 59 OAT Probe. The GSU 75/75B 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
and GAD 43/43e. An RS-232 digital connection is used for maintenance and configuration information.
The GSU 75B is configured through the GDU 700P/1060 using a feature unlock card that contains
airframe specific air data corrections suitable for RVSM functionality in select applications.
Figure 2-10 GSU 75( ) ADAHRS Unit
2.2.8
GRS 79 AHRS Unit
The GSU 79 AHRS is a remote LRU that provides attitude and heading data for flight instrumentation. The
GSU 79 receives data from the GMU 44 Magnetometer. The GSU 79 utilizes GPS signals sent from the
GPS/SBAS navigator. Attitude and heading data is sent using ARINC 429 digital signals to the
GDU 700P/1060 and GAD 43/43e. An RS-232 digital connection is used for maintenance and
configuration information.
Figure 2-11 GRS 79 AHRS Unit
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2.2.9
GDC 72 ADC Unit
The GDC 72 Air Data Computer receives information from the existing aircraft pitot-static system and the
GTP 59 OAT Probe. The GDC 72 provides pressure altitude, airspeed, vertical speed, and OAT data to the
G500/G600 TXi system. The GDC 72 provides data to the G500/G600 TXi using ARINC 429 digital
interfaces, as well as RS-232 for maintenance and configuration information.
Figure 2-12 GDC 72 ADC Unit
2.2.10 GMU 44 Magnetometer
The GMU 44 Magnetometer senses magnetic field information and sends the data to the GSU 75/75B,
integrated ADAHRS, or GRS 77/79 AHRS to determine aircraft magnetic heading. This unit receives
power directly from the AHRS source and communicates with the AHRS using an RS-485 digital
interface.
Figure 2-13 GMU 44 Magnetometer
2.2.11 GTP 59 OAT Probe
The GTP 59 is a remote mount temperature probe that interfaces to the ADC for OAT 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 2-14 GTP 59 Outside Air Temperature Probe
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2.2.12 GBB 54 Backup Battery
The GBB 54 supplies power to the GDU 700P, internal ADAHRS, essential EIS sensors, and a single
GEA 110 in the event of total electrical power loss.
Figure 2-15 GBB 54 Backup Battery
2.2.13 GEA 110 Engine Interface
The GEA 110 is a remote mount engine interfacing and monitoring module used for gathering sensor input
parameters from the engine and processing the signals for the G500/G600 TXi system. The GEA 110 can
be mounted to the back assembly of the GDU 1060 or it can be remotely mounted in the fuselage or in the
engine compartment. The GEA 110 communicates with the G500/G600 TXi using an RS-485 digital
interface.
Figure 2-16 GEA 110 Engine Interface
2.2.14 GEA 71B Enhanced Engine
The GEA 71B Enhanced is an engine interface and monitoring module for turboprop engines that collects
signals from the engine sensors and communicates the engine parameters to the GDU 700P/1060 display
via RS-485 digital interface. The GEA 71B Enhanced is remotely mounted.
Figure 2-17 GEA 71B Enhanced Engine
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2.2.15 GAD 43/43e Adapter
The GAD 43 Adapter is an optional adapter that provides attitude, heading, and yaw input information for
third-party autopilot systems. It also provides a synchro heading output that can be used to provide synchro
heading to other systems.
The GAD 43/43e can provide the following information in analog format:
• Pitch and roll for the autopilot (synchro)
• Pitch and roll for weather radar stabilization (50 and 200 mV/degree)
• Heading (synchro)
• Yaw rate (100, 200, 333, and 600 mV/degree/sec)
OR
• The GAD 43/43e can provide an analog baro-correction output like the Honeywell KEA 130/130A
and KEA 346 (P/Ns 006-0362-0008 through -0011 only) encoding altimeters
With the GDU 700/1060 in Configuration mode, the GAD 43/43e also allows the installer to set the analog
attitude and heading outputs to specific values without the need for removing any gyros and using a tilt
table.
The GAD 43e provides all of the functions of the GAD 43. In addition, it allows the G500/G600 TXi to
receive data from marker beacon receivers, synchro (ARINC 407) ADF receivers, DME systems, and
analog radar altimeters. It also allows the G500/G600 TXi to provide altitude preselect and vertical speed
control to compatible autopilots.
Figure 2-18 GAD 43 (Left) and GAD 43e (Right)
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2.2.16 EIS Components
2.2.16.1 Engine Annunciator
An engine annunciator will only be installed if the EIS display is not installed within 8 inches of the center
of the pilot’s field-of-view.
Figure 2-19 Engine Annunciator
2.2.16.2 Carburetor Temperature Probe
The carburetor temperature probe is a Type-K thermocouple (Chromel and Alumel) probe.
Figure 2-20 Carburetor Temperature Probe
2.2.16.3 Oil Temperature Probe
The oil temperature probe is a Type-K thermocouple (Chromel and Alumel) probe.
Figure 2-21 Oil Temperature Probe
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2.2.16.4 Fuel Flow Sensors
The fuel flow sensor is incorporated in an aluminum housing that is installed in-line to the engine fuel
supply. There are two STC approved options available for installation to suit most aircraft applications.
Figure 2-22 Fuel Flow Sensor FT-60 (Left) and FT-90 (Right)
2.2.16.5 Brass Pressure Sensors
The brass pressure sensors are small sensors that are supplied with a compatible plug. Depending on the
installation, these sensors may be used to measure oil, fuel, and manifold pressure.
Figure 2-23 Brass Pressure Sensor
2.2.16.6 Stainless Steel Pressure Sensors
The stainless pressure sensors are unamplified, high-reliability sensors for harsh installation environments.
There are four sensors available to measure oil, fuel, and manifold pressure.
Figure 2-24 Stainless Steel Pressure Sensor
2.2.16.7 P-Lead RPM Pickup
A wire with two parallel resistors in-line connects from each P-lead, at the Magneto or the ignition switch,
to the GEA 110 to sense RPM.
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3 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
3.1 Airworthiness Limitations ................................................................................................................3-2
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.......................................................................................................................3-3
3.4 Visual Inspection ..............................................................................................................................3-5
3.4.1 Aluminum Foil Tape (Non-metallic Aircraft Only)...................................................................3-5
3.5 Electrical Bonding Check .................................................................................................................3-6
3.6 RVSM Periodic Maintenance (Socata TBM 700/850 Only) ............................................................3-7
3.7 Overhaul Period ................................................................................................................................3-7
3.8 Special Inspection Requirements......................................................................................................3-8
3.9 Application of Protective Treatments ...............................................................................................3-9
3.10 Data Relative to Structural Fasteners................................................................................................3-9
3.11 Additional Instructions .....................................................................................................................3-9
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3.3 Maintenance Intervals
Table 3-1 Periodic Maintenance
Item
G500/G600 TXi
System Visual
Inspection
GBB 54 Backup
Battery Check
Description/ Procedure
All installed system LRUs, switches, knobs, and wiring
harnesses must be inspected to ensure continued integrity of
the installation. The inspection must be performed in
accordance with Section 3.4.
Perform a Backup Battery Check as described in
Section 5.14.5.
If the GBB 54 does not pass the Backup Battery Check, the
battery cell must be replaced using the procedure found in
Section 5.9.2.
Interval
12 Calendar
Months
12 Calendar
Months
If an EIS annunciator is installed, perform a check of the
annunciator lamps using the following procedure:
1. Power on the GDU 700/1060 in Configuration mode per the
instructions in Section 2.1.4.
EIS Annunciator
Lamp Check
2. Navigate to Diagnostics → Discrete Outputs.
3. Toggle the state of the Engine Caution and Engine Warning
discrete outputs to ON (the bar at the bottom of the State
button on the GDU will illuminate green).
4. Verify that the respective engine annunciator lights have
illuminated.
5. Toggle the state of the Engine Caution and Engine Warning
discrete outputs to OFF.
12 Calendar
Months
RVSM Checks
(TBM 700/850 Only)
Perform the air data checks and autopilot altitude hold checks
as specified in Section 3.6.
24 Calendar
Months
AHRS Magnetic
Field Model Update
The GSU 75( ), GRS 79, and GDU 700/1060 Integrated
ADAHRS utilize an Earth magnetic field model that is updated
once every 5 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 start-up indicating the model
has 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.
Every 5 years
Perform an electrical bonding check of the G500/G600 TXi
system LRUs in accordance with Section 3.5.
Every 2000
flight hours or
10 years,
whichever
comes first
Electrical Bonding
Check
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Item
Description/ Procedure
Interval
It is recommended that the cooling fan on the GDU 700/1060
be replaced every 3000 fan-operating hours. The number of
hours the fan has been operating can be viewed using the
following procedure:
GDU 700/1060
Cooling Fan
Replacement
1. Power on the GDU 700/1060 in Configuration mode per the
instructions in Section 2.1.4.
2. Navigate to Diagnostics → Temp & Power Stats.
3. The cooling fan operating hours can be found under Power
Statistics as “Fan OPER Hours”.
Recommended
every 3000 fanoperating hours
The cooling fan replacement procedure is contained in
Section 5.1.2.
Test according to 14 CFR §43 Appendix E.
Interval must be
in accordance
with Title 14
CFR §91.411
and 91.413
Altimeter Checks
See the pitot-static checkout procedure in Section 5.16.2 for
system specific checkout procedure.
Lightning Damage
Check
Conduct an inspection of the G500/G600 TXi system in
accordance with Section 3.8.
After a
suspected or
actual lightning
strike
Equipment Removal
and Replacement
Removal and replacement of the G500/G600 TXi system LRUs
can be accomplished by referring to Section 5 for instructions.
On Condition
Cleaning GDU 700/
1060 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.
On Condition
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 700/1060. Over time, the backlight lamp
may dim and the display may not perform as well in direct
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
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3.4 Visual Inspection
Operation of the G500/G600 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 G500/G600 TXi system LRUs and associated wiring harnesses to ensure installation integrity:
WARNING
Ensure the GBB 54 vent tube is not pointed towards personnel or equipment before blowing
shop air through the tube. Any obstructions in the tube will be ejected at high speed and can
cause serious injury or property damage.
1. Inspect all units for security of attachment, including visual inspection of brackets and other
supporting structure attaching all units to the airframe.
2. Inspect all switches, annunciators, knobs, and buttons for legibility.
3. Visually inspect each unit’s wiring (including electrical bonding straps), overbraid, and connectors
for chafing, deterioration, damage, or wear.
4. Visually check for any signs of corrosion.
5. Visually inspect the GBB 54 vent tube and connectors for damage/corrosion and ensure there are
no obstructions in the vent tube. The vent tube can be checked for obstructions by disconnecting
the vent tube from the GBB 54 and blowing shop air through the tube from the battery connector
side to the exterior of the aircraft.
3.4.1
Aluminum Foil Tape (Non-metallic Aircraft Only)
Any aluminum foil tape used in the G500/G600 TXi installation for grounding of a GSU 75/75B, GDC 72,
GRS 79, GAD 43/43e, GEA 110, GEA 71B Enhanced, or GBB 54 (refer to Appendix A of this document)
must be inspected every 12 calendar months.
The inspection must verify that the foil tape is not torn, damaged, or showing signs of corrosion. If any of
these conditions are found, the tape must be replaced in accordance with Section 4 of G500/G600 TXi
Part 23 AML STC Installation Manual.
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Page 3-5
3.5 Electrical Bonding Check
G500/G600 TXi LRU electrical bonding must be checked every 2,000 flight hours or 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. If the measured resistance is greater than applicable values in the following
table, bonding must be improved to meet applicable requirements for a new installation in accordance with
Section 4 of G500/G600 TXi Part 23 AML STC Installation Manual.
Table 3-2 Electrical Bonding Requirements
LRU
Maintenance Requirement
GDU 700/1060
GCU 485
20 mΩ
Engine Annunciator
GSU 75/75B
GDC 72
GRS 79
5 mΩ
GAD 43/43e
GEA 71B Enhanced
GEA 110
5 mΩ (remote-mounted)
N/A (GDU 1060 mounted)
GTP 59
5 mΩ (or electrically isolated per Appendix D of
G500/G600 TXi Part 23 AML STC Installation Manual)
GMU 44
10 mΩ (or electrically isolated per Appendix D of
G500/G600 TXi Part 23 AML STC Installation Manual)
Notes:
[1] For remote LRUs bonded to the back of the instrument panel via an installed aluminum foil
ground plane, the bonding measurement must be taken between the remote LRU and the
instrument panel.
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3.6 RVSM Periodic Maintenance (Socata TBM 700/850 Only)
Maintain all RVSM equipment in accordance with the manufacturer’s maintenance and performance
requirements. The encoding altimeter must be checked as specified in the Socata Maintenance Manual
Section 05-10-01, ATA Chapter 34. The RVSM critical areas must be inspected as specified in Socata
Maintenance Manual Section 05-10-01, ATA Chapter 53.
The air data systems must be checked within the preceding 24 months, as specified in the Socata
Maintenance Manual Section 34-11-00, except for the altitude displays and altitude alerter. The altitude
displays and altitude alerter must be checked in accordance with Section 5.16.3 of this manual. Socata
Maintenance Manual test procedures may be adapted to complete all other air data system checks required
in Section 5.16.2.
The autopilot altitude hold performance must be checked within the preceding 24 months in accordance
with the RVSM In-flight altitude hold check described in Section 5.16.3.3.
3.7 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 G500/G600 TXi system. If any LRU indicates an internal failure, the unit may be
removed and replaced. See Section 4 of this document for fault corrective actions.
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3.8 Special Inspection Requirements
After a suspected lightning strike, the following actions must be performed for the specified LRU.
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 the washer
if damaged. If there is evidence of lightning strike to the OAT or any lightning damage, replace the GTP 59
OAT.
Tube-and-fabric aircraft must replace the OAT bond strap (if installed) in accordance with Section 4.6.2 of
G500/G600 TXi Part 23 AML STC Installation Manual.
GMU 44
Aircraft with a GMU mounted in the wingtip of metallic aircraft with non-metallic wingtip covers must
inspect the magnetometer installation for the following conditions:
1. Check the GMU 44 Magnetometer body and mount for scorching, soot, melting, pitting, denting,
or discoloration.
2. Check P441 and J441 for melting or pin damage.
3. Check the cable overbraid for pinching, melting, or evidence of arcing.
4. Check the lug for evidence of arcing and verify that the lug is still secured to the overbraid.
5. Check electrical bonding between the GMU 44 overbraid and adjacent aircraft structure.
Resistance should be less than 5 mΩ.
6. If any of these checks shows evidence of a lightning strike, replace the overbraid assembly in
accordance with Figure 4-54 of G500/G600 TXi Part 23 AML STC Installation Manual.
Perform the Magnetic Interference Check in accordance with Section 6.6.4 of G500/G600 TXi Part 23
AML STC 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.
GBB 54 Battery Vent Tube
Aircraft with a GBB 54 battery must inspect the battery vent tube using the following procedure:
1. Gain access to the GBB 54 and both ends of the vent tube.
2. Check the battery vent grounding strap for evidence of arcing or damage.
3. Check the end of the vent tube that protrudes through the aircraft skin for scorching, soot, melting,
pitting, denting, or discoloration.
If any of these checks show evidence of a lightning strike, replace the vent tube and grounding strap in
accordance with Section 4.5.6 of G500/G600 TXi Part 23 AML STC Installation Manual.
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3.9 Application of Protective Treatments
None.
3.10 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.
3.11 Additional Instructions
None.
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4 TROUBLESHOOTING
4.1 General System Troubleshooting......................................................................................................4-2
4.1.1 System Maintenance Log ...........................................................................................................4-2
4.2 Connector Information......................................................................................................................4-3
4.2.1 GDU 700/1060 ...........................................................................................................................4-4
4.2.2 GCU 485 ....................................................................................................................................4-9
4.2.3 GDC 72 ....................................................................................................................................4-10
4.2.4 GSU 75( ) .................................................................................................................................4-12
4.2.5 GRS 79 .....................................................................................................................................4-14
4.2.6 GAD 43 ....................................................................................................................................4-16
4.2.7 GAD 43e ..................................................................................................................................4-18
4.2.8 GEA 110...................................................................................................................................4-21
4.2.9 GEA 71B Enhanced .................................................................................................................4-24
4.2.10 GBB 54.....................................................................................................................................4-27
4.2.11 GMU 44....................................................................................................................................4-28
4.2.12 GTP 59 .....................................................................................................................................4-28
4.3 Troubleshooting Flow Charts .........................................................................................................4-29
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 G500/G600 TXi system, refer to wire routing drawings and interconnect diagrams
retained in Appendix A of this document or with the aircraft’s permanent records.
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4.1 General System Troubleshooting
Before troubleshooting the G500/G600 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 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
G500/G600 TXi Part 23 AML STC Installation Manual (P/N190-01717-B3). Basic troubleshooting of the
G500/G600 TXi system can be accomplished using the instructions provided in Table 4-1.
Table 4-1 G500/G600 TXi Failures
Symptom
GDU 700/1060 Blank
Configuration mode pages grayed out
with an Installer Unlock Card
EIS Gauge Fault/Failure
Recommended Action
1) Check power/ground wiring for GDU.
2) Press the Power button until the Garmin logo is visible.
1) Ensure a GDU master configuration module is selected.
2) Ensure a functional configuration module is present.
3) Ensure the GDU IDs are set for all GDUs.
Troubleshoot the problem using the EIS gauge troubleshooting
flowchart provided in Section 4.3.
An Alert message is displayed on the
Troubleshoot the alert message using the flowcharts provided
GDU or present in the maintenance log in Section 4.3.
4.1.1
System Maintenance Log
The G500/G600 TXi system has a maintenance and error log that can be accessed or printed to assist with
system maintenance and troubleshooting.
The maintenance and error log can be accessed using the following procedure:
1. Power all GDU 700/1060 units into Configuration mode in accordance with Section 2.1.4.
2. On GDU #1, navigate to Diagnostics → Maintenance / Error Log → Maintenance Log.
The maintenance and error log can be printed using the following procedure:
1. Power all GDU 700/1060 units into Configuration mode in accordance with Section 2.1.4.
2. Insert an SD card into the top/left SD card slot.
3. Press the SD Save button.
4. Enter a name for the configuration file to be saved as, and then select Enter.
5. Once the save process is completed, eject the SD card from the GDU and insert it into a computer.
6. On the computer, navigate to the SD card drive and open the “maintenance_logs” directory.
7. Open the .htm file with the name that you entered in step 4.
8. The file should open in your computer internet browser and can be printed using your selected
internet browser print function (in most cases, pressing the Ctrl and P buttons simultaneously will
access this function).
The maintenance log will display reported system faults. The alert message that is displayed on the GDU
for that fault (if any) will display frequency, most recent occurrence time of the fault, and any additional
information about the fault that might be helpful. If any faults are reported on the maintenance log, refer to
the troubleshooting flowcharts contained in Section 4.3.
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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 G500/G600 TXi STC.
All D-sub connectors follow a similar pin numbering scheme as that shown in Figure 4-1.
(view is from the contact side of the connector)
Figure 4-1 62 Pin D-sub Connectors Numbering Scheme for Female/Male Contacts
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4.2.1
GDU 700/1060
NOTE
GDU 700 and GDU 1060 displays have identical connectors and pin functions.
The GDU 700/1060 has seven connectors. The mating designators, part numbers, and associated connector
kits are listed in Table 4-2.
Table 4-2 G500/G600 TXi - GDU 700/1060 Connectors
REF. DES.
DESCRIPTION
CONN P/N
KIT P/N
P1
Conn, HD D-Sub, Male, Str, Mil Crmp Pins, 26 Ckt
330-00626-26
011-03527-00
P2
Conn, HD D-Sub, Male, Str, Mil Crmp Pins, 44 Ckt
330-00626-44
011-03527-00
P3
Conn, HD D-Sub, Male, Str, Mil Crmp Pins, 62 Ckt
330-00626-62
011-03527-00
P4
Conn, HD D-Sub, Male, Str, Mil Crmp Pins, 78 Ckt
330-00626-78
011-03527-00
P5
TNC, Male
P6
TNC, Male
P7
TNC, Male
Supplied with antenna
*36
+'9,'(2
+'9,'(2
Figure 4-2 GDU 700P Connectors
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J1/P1 Connector
Pin
Function
I/O
Pin
Function
I/O
1
AIRCRAFT POWER 2
IN
14
BATTERY CHARGE OUT
OUT
2
AIRCRAFT POWER 2
IN
15
BATTERYGND
3
AIRCRAFT POWER 2
IN
16
BATTERY RS-232 GND
4
AIRCRAFT POWER 2
IN
17
USE BATTERY OUT
OUT
5
BATTERY CHARGE OUT
OUT
18
BATTERY POWER IN
IN
6
BATTERY GROUND
--
19
AIRCRAFT POWER 1
IN
7
BATTERY RS-232 IN
IN
20
AIRCRAFT POWER 1
IN
8
BATTERY GROUND
--
21
AIRCRAFT POWER 1
IN
9
BATTERY POWER IN
IN
22
AIRCRAFT POWER 1
IN
10
AIRCRAFT GND
--
23
BATTERY GND
--
11
AIRCRAFT GND
--
24
BATTERY RS-232 OUT
12
AIRCRAFT GND
--
25
STANDBY POWER IN
IN
13
AIRCRAFT GND
--
26
BATTERY POWER IN
IN
---
OUT
J2/P2 Connector
Pin
Function
I/O
Pin
Function
23
ETHERNET OUT 4A
I/O
1
RS-485 1A
I/O
OUT
2
RS-485 1B
I/O
24
GND
--
3
LIGHTING BUS HI
IN
25
RESERVED
--
4
LIGHTING BUS LO
IN
26
MAGNETOMETER GND
--
5
OAT POWER
OUT
27
RS-232 IN 2
IN
6
OAT PROBE IN HI
IN
28
RS-232 IN 1
IN
7
OAT PROBE IN LO
IN
29
CONFIG MODULE GND
--
8
COMPOSITE VIDEO IN 2
IN
30
CONFIG MODULE CLOCK
9
AUDIO OUT LO
OUT
31
ETHERNET IN 1B
10
AUDIO OUT HI
OUT
32
ETHERNET OUT 1B
11
GND
--
33
ETHERNET IN 2B
12
RS-232 GND 2
--
34
ETHERNET OUT 2B
13
RS-232 GND 1
--
35
ETHERNET IN 3B
14
COMPOSITE VIDEO IN 1
IN
36
ETHERNET OUT 3B
15
CONFIG MODULE PWR
OUT
37
ETHERNET IN 4B
16
ETHERNET IN 1A
IN
38
ETHERNET OUT 4B
17
ETHERNET OUT 1A
OUT
39
DEMO MODE SELECT*
18
ETHERNET IN 2A
19
ETHERNET OUT 2A
20
ETHERNET IN 3A
21
ETHERNET OUT 3A
22
ETHERNET IN 4A
OUT
IN
OUT
IN
OUT
IN
OUT
IN
OUT
IN
IN
40
LRU POWER OUT 1
OUT
OUT
41
MAGNETOMETER PWR OUT
OUT
IN
42
RS-232 OUT 2
OUT
OUT
43
RS-232 OUT 1
OUT
IN
44
CONFIG MODULE DATA
I/O
* Indicates Active-Low
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-5
J3/P3 Connector
Pin
Function
I/O
Pin
Function
I/O
1
DISC OUT 3 HI
OUT
32
LATERAL - FLAG OUT
OUT
2
DISC OUT 4 HI
OUT
33
VERTICAL - FLAG OUT
OUT
3
RS-232 OUT 3
OUT
34
DISC IN 1 LO
IN
4
RS-232 IN 3
IN
35
DISC IN 2 LO
IN
5
RS-232 OUT 4
OUT
36
DISC IN 3 LO
IN
6
RS-232 IN 4
IN
37
DISC IN 4 LO
IN
7
VERTICAL SUPERFLAG OUT
OUT
38
ANALOG IN 1B
IN
8
LATERAL SUPERFLAG OUT
OUT
39
ANALOG IN 1A
IN
9
LATERAL +LEFT OUT
OUT
40
A/P AC REF LO
IN
10
LATERAL + RIGHT OUT
OUT
41
A/P AC REF HI
IN
11
LATERAL +FLAG OUT
OUT
42
FD PITCH UP
12
VERTICAL +FLAG OUT
OUT
43
DISC OUT 1 LO
13
VERTICAL +UP OUT
OUT
44
RS-485 2A
I/O
14
VERTICAL +DOWN OUT
OUT
45
RS-485 2B
I/O
IN
OUT
15
A/P COURSE ERROR LO
--
46
RS-485 3A
I/O
16
A/P COURSE ERROR HI
OUT
47
RS-485 3B
I/O
17
A/P HEADING ERROR LO
--
48
DISC OUT 7 LO
OUT
18
A/P HEADING ERROR HI
OUT
49
DISC OUT 2 LO
OUT
19
FD ROLL LEFT
IN
50
DISC OUT 5 LO
OUT
20
FD ROLL RIGHT
IN
51
DISC OUT 6 LO
OUT
21
FD PITCH DOWN
IN
52
RESERVED
22
LRU POWER OUT 2
OUT
53
DISC OUT 2 HI
OUT
23
GND
--
54
DISC OUT 1 HI
OUT
24
GND
--
55
DISC OUT 3 LO
OUT
25
RS-232 GND 3
--
56
DISC OUT 4 LO
OUT
26
RS-232 GND 4
--
57
DISC IN 1 HI
--
IN
27
LRU POWER OUT 3
OUT
58
DISC IN 2 HI
IN
28
TIME MARK IN 2A
IN
59
DISC IN 3 HI
IN
29
TIME MARK IN 2B
IN
60
DISC IN 4 HI
IN
30
TIME MARK IN 1A
IN
61
RS-485 4A
I/O
31
TIME MARK IN 1B
IN
62
RS-485 4B
I/O
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-6
J4/P4 Connector
Pin
Function
I/O
Pin
Function
I/O
1
ARINC 429 IN 1A
IN
40
GLIDESLOPE #2 +FLAG
IN
2
ARINC 429 IN 2A
IN
41
GLIDESLOPE #2 -FLAG
IN
3
ARINC 429 IN 3A
IN
42
GLIDESLOPE #1 +FLAG
IN
4
ARINC 429 IN 4A
IN
43
GLIDESLOPE #1 -FLAG
IN
5
ARINC 429 IN 5A
IN
44
ANALOG OUT 1B
OUT
6
ARINC 429 IN 6A
IN
45
ANALOG OUT 1A
OUT
7
ARINC 429 IN 7A
IN
46
RS-485 5A
I/O
8
ARINC 429 IN 8A
IN
47
ARINC 708/453 IN 1A
IN
9
ARINC 429 IN 9A
IN
48
ARINC 708/453 IN 1B
IN
10
ARINC 429 IN 10A
IN
49
ARINC 708/453 IN TERM A
11
ARINC 429 IN 11A
IN
50
ARINC 708/453 IN TERM B
12
RS-232 GND 7
--
51
DISC OUT 9 LO
OUT
13
RS-232 IN 7
IN
52
DISC OUT 10 LO
OUT
14
RS-232 OUT 7
OUT
53
ARINC 429 OUT 1A
OUT
15
RS-232 GND 6
--
54
ARINC 429 OUT 2A
OUT
16
RS-232 IN 6
IN
55
ARINC 429 OUT 3A
OUT
17
RS-232 OUT 6
OUT
56
ARINC 429 OUT 4A
OUT
18
RS-232 GND 5
--
57
ADF X/COS IN
19
RS-232 IN 5
20
RS-232 OUT 5
21
--
IN
IN
58
ADF Y/SIN IN
IN
OUT
59
ADF DC REF IN
IN
ARINC 429 IN 1B
IN
60
DISC OUT LOW 13
OUT
22
ARINC 429 IN 2B
IN
61
DISC OUT LOW 8
OUT
23
ARINC 429 IN 3B
IN
62
GLIDESLOPE #2 +UP IN
IN
24
ARINC 429 IN 4B
IN
63
GLIDESLOPE #2 +DN IN
IN
25
ARINC 429 IN 5B
IN
64
GLIDESLOPE #1 +UP IN
IN
26
ARINC 429 IN 6B
IN
65
GLIDESLOPE #1 +DN IN
IN
27
ARINC 429 IN 7B
IN
66
RS-485 5B
I/O
28
ARINC 429 IN 8B
IN
67
VOR/LOC COMPOSITE #1 LO
IN
29
ARINC 429 IN 9B
IN
68
VOR/LOC COMPOSITE #1 HI
IN
30
ARINC 429 IN 10B
IN
69
VOR/LOC COMPOSITE #2 LO
IN
31
ARINC 429 IN 11B
IN
70
VOR/LOC COMPOSITE #2 HI
IN
32
RESERVED
--
71
DISC OUT LO 11
33
RS-232 GND 8
--
72
DISC OUT LO 12
OUT
34
RS-232 IN 8
IN
73
ARINC 429 OUT 1B
OUT
35
RS-232 OUT 8
OUT
74
ARINC 429 OUT 2B
OUT
36
DISC IN 5 LO
IN
75
ARINC 429 OUT 3B
OUT
37
DISC IN 6 LO
IN
76
ARINC 429 OUT 4B
OUT
38
DISC IN 7 LO
IN
77
ARINC 429 OUT 5A
OUT
39
DISC IN 8 LO
IN
78
ARINC 429 OUT 5B
OUT
190-01717-B1
Rev. 3
OUT
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-7
J5/P5 Connector
Pin
N/A
Name
HD VIDEO IN 1
I/O
--
J6/P6 Connector
Pin
N/A
Name
HD VIDEO IN 2
I/O
--
J7/P7Connector
Pin
N/A
190-01717-B1
Rev. 3
Name
BACKUP GPS ANT
I/O
--
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-8
4.2.2
GCU 485
The GCU 485 has one connector. The mating designator, part number, and associated connector kit are
listed in Table 4-3.
Table 4-3 G500/G600 TXi - GCU 485 Connectors
REF. DES.
P4851
DESCRIPTION
Conn, Male, HD D-Sub, 15 Ckt
CONN P/N
330-00366-15
KIT P/N
011-01824-00
Figure 4-3 GCU 485 Connector
J4851/P4851 Connector
Pin
190-01717-B1
Rev. 3
Function
I/O
1
RS-232 OUT 1
OUT
2
RS-232 IN 1
3
RS-232 OUT 2
4
RS-232 IN 2
IN
5
POWER GROUND
--
IN
OUT
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
--
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-9
4.2.3
GDC 72
The GDC 72 has one connector. The mating designator, part number, and associated connector kit are
listed in Table 4-4.
Table 4-4 G500/G600 TXi - GDC 72 Connectors
REF. DES.
P721
DESCRIPTION
CONN P/N
Conn, HD D-Sub, Male, Str, Mil Crp, Sealed,
w/ GND Indents, 78 Pin
60
40
61
62
41 42
21
1
22
2
63
43
23
3
64
44
24
4
65
45
25
5
66
26
6
67
46
47
27
7
68
48
28
8
69
49
29
9
10
70
50
30
11
71
72
51 52
31
12
32
330-00776-78
73
53
33
13
14
74
54
34
15
75
55
35
16
76
77
56
36
17
58
38
18
011-03735-00
78
57
37
KIT P/N
59
39
19
20
Figure 4-4 View of J721 Connector Looking at GDC 72
J721/P721 Connector
Pin
Function
I/O
Pin
OUT
40
Function
RESERVED
I/O
1
ARINC 429 OUT 1A
--
2
ARINC 429 OUT 1B
OUT
41
RESERVED
--
3
ARINC 429 OUT 2A
OUT
42
ARINC 429 IN 1A
IN
4
OAT LO
IN
43
ARINC 429 IN 1B
IN
5
OAT HI
IN
44
ARINC 429 IN 2A
IN
6
OAT POWER
OUT
45
RESERVED
--
7
ARINC 429 OUT 1B
OUT
46
RESERVED
--
8
ARINC 429 OUT 3A
OUT
47
RESERVED
--
9
ARINC 429 OUT 3B
OUT
48
SIGNAL GROUND
--
10
RESERVED
--
49
ARINC 429 OUT 2A
OUT
11
RESERVED
--
50
ARINC 429 OUT 2B
OUT
12
RESERVED
--
51
RESERVED
--
13
RESERVED
--
52
RESERVED
--
14
AIRCRAFT POWER 1
IN
53
CONFIG MODULE POWER
15
SIGNAL GROUND
--
54
CONFIG MODULE DATA
16
AIRCRAFT POWER 2
IN
55
CONFIG MODULE CLOCK
17
RS232 OUT 2
OUT
56
DISCRETE IN 1*
IN
OUT
I/O
OUT
18
RS232 IN 2
IN
57
SYS ID 2*
IN
19
RESERVED
--
58
RESERVED
--
20
RESERVED
--
59
RESERVED
--
21
ARINC 429 OUT 3A
OUT
60
RESERVED
--
22
ARINC 429 OUT 3B
OUT
61
RESERVED
--
23
ARINC 429 OUT 2B
OUT
62
ARINC 429 IN 3A
IN
24
SIGNAL GROUND
--
63
ARINC 429 IN 3B
IN
25
RESERVED
--
64
ARINC 429 IN 2B
IN
26
SIGNAL GROUND
--
65
RESERVED
--
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-10
27
ARINC 429 OUT 1A
OUT
66
RESERVED
--
28
RESERVED
--
67
RESERVED
--
29
RESERVED
--
68
SIGNAL GROUND
30
SIGNAL GROUND
--
69
RS 232 OUT 1
31
SIGNAL GROUND
--
70
RS 232 IN 1
IN
32
SIGNAL GROUND
--
71
RESERVED
--
33
SIGNAL GROUND
--
72
RESERVED
--
34
AIRCRAFT GROUND 1
--
73
SIGNAL GROUND
--
35
SPARE
--
74
CONFIG MODULE GROUND
--
36
AIRCRAFT GROUND 2
--
75
SYS ID 1*
IN
37
SIGNAL GROUND
--
76
DISCRETE IN 3*
IN
38
RESERVED
--
77
DISCRETE IN 4
IN
39
RESERVED
--
78
DISCRETE IN 2*
IN
-OUT
*Indicates Active-Low
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-11
4.2.4
GSU 75( )
The GSU 75 has one connector. The mating designator, part number, and associated connector kit are listed
in Table 4-5.
Table 4-5 G500/G600 TXi - GSU 75 Connectors
REF. DES.
P751
DESCRIPTION
CONN P/N
Conn, HD D-Sub, Male, Str, Mil Crp, Sealed,
w/ GND Indents, 78 Pin
60
40
61
62
41 42
21
1
22
2
63
43
23
3
64
44
24
4
65
45
25
5
66
26
6
67
46
47
27
7
68
48
28
8
69
49
29
9
10
70
50
30
11
71
72
51 52
31
12
32
330-00776-78
73
53
33
13
14
74
54
34
15
75
55
35
16
76
77
56
36
17
58
38
18
011-03109-00
78
57
37
KIT P/N
59
39
19
20
Figure 4-5 View of J751 Connector Looking at GSU 75( )
J751/P751 Connector
Pin
1
Function
ARINC 429 OUT ADC 1A
I/O
Pin
OUT
40
Function
I/O
PPS IN 1 B
IN
2
ARINC 429 OUT ADC 1B
OUT
41
PPS IN 2 A
IN
3
ARINC 429 OUT ADC 2A
OUT
42
ARINC 429 IN ADC 1A
IN
4
OAT LO
IN
43
ARINC 429 IN ADC 1B
IN
5
OAT HI
IN
44
ARINC 429 IN ADC 2A
IN
6
OAT POWER
OUT
45
ARINC 429 IN AHRS 1A
IN
7
ARINC 429 OUT ADAHRS 1B
OUT
46
ARINC 429 IN AHRS 1B
IN
8
ARINC 429 OUT ADAHRS 3A
OUT
47
ARINC 429 IN AHRS 3A
IN
9
ARINC 429 OUT ADAHRS 3B
OUT
48
SIGNAL GROUND
--
10
RS-422 IN A
IN
49
ARINC 429 OUT ADAHRS 2A
OUT
11
RS-422 IN B
IN
50
ARINC 429 OUT ADAHRS 2B
OUT
12
RS-232 OUT AHRS 3
OUT
51
RS-232 OUT AHRS 1
OUT
13
MAGNETOMETER POWER
OUT
OUT
52
RS232 IN AHRS 1
14
AIRCRAFT POWER 1
IN
53
CONFIG MODULE POWER
15
SIGNAL GROUND
--
54
CONFIG MODULE DATA
16
AIRCRAFT POWER 2
17
RS-232 OUT ADC 2
18
19
IN
OUT
I/O
IN
55
CONFIG MODULE CLOCK
OUT
56
DISCRETE IN 1*
OUT
IN
RS-232 IN ADC 2
IN
57
SYS ID 2*
IN
RESERVED
--
58
RESERVED
IN
20
RESERVED
--
59
RESERVED
I/O
21
ARINC 429 OUT ADC 3A
OUT
60
PPS IN 1A
IN
22
ARINC 429 OUT ADC 3B
OUT
61
PPS IN 2B
IN
23
ARINC 429 OUT ADC 2B
OUT
62
ARINC 429 IN ADC 3A
IN
24
SIGNAL GROUND
--
63
ARINC 429 IN ADC 3B
IN
25
PPS SELECT
IN
64
ARINC 429 IN ADC 2B
IN
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-12
26
SIGNAL GROUND
--
65
ARINC 429 IN AHRS 2A
IN
27
ARINC 429 OUT ADAHRS 1A
OUT
66
ARINC 429 IN AHRS 2B
IN
28
ARINC 429 OUT ADAHRS 3A
OUT
67
ARINC 429 IN AHRS 3B
IN
29
ARINC 429 OUT ADAHRS 3B
OUT
68
RS-232 ADC 1 GROUND
--
30
SIGNAL GROUND
--
69
RS-232 OUT ADC 1
31
RS-232 AHRS 3 GROUND
--
70
RS-232 IN ADC 1
32
RS-232 AHRS 1 GROUND
--
71
RS-232 OUT AHRS 2
33
MAGNETOMETER GROUND
--
72
RS-232 IN AHRS 2
IN
34
AIRCRAFT GROUND 1
--
73
RS-232 AHRS 2 GROUND
--
35
RESERVED
--
74
CONFIG MODULE GROUND
--
36
AIRCRAFT GROUND 2
--
75
SYS ID 1*
IN
37
RS-232 ADC 2 GROUND
--
76
DISCRETE IN 3*
IN
38
RESERVED
--
77
DISCRETE IN 4
IN
39
RESERVED
I/O
78
DISCRETE IN 2*
IN
OUT
IN
OUT
*Indicates Active-Low
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-13
4.2.5
GRS 79
The GRS 79 has one connector. The mating designator, part number, and associated connector kit are listed
in Table 4-6.
Table 4-6 G500/G600 TXi - GRS 79 Connectors
REF. DES.
P791
DESCRIPTION
CONN P/N
Conn, HD D-Sub, Male, Str, Mil Crmp, Sealed,
w/ GND Indents, 78 Pin
60
40
61
62
41 42
21
1
22
2
63
43
23
3
64
44
24
4
65
45
25
5
66
46
26
6
67
47
27
7
68
48
28
8
69
49
29
9
10
70
50
30
11
71
72
51 52
31
12
32
330-00776-78
73
53
33
13
14
74
54
34
15
75
55
35
16
76
77
56
36
17
58
38
18
011-03733-00
78
57
37
KIT P/N
59
39
19
20
Figure 4-6 View of J791 Connector Looking at GRS 79
J791/P791 Connector
Pin
Function
I/O
Pin
Function
I/O
1
ARINC 429 OUT 1A
OUT
40
PPS IN 1 B
IN
2
ARINC 429 OUT 1B
OUT
41
PPS IN 2 A
IN
3
ARINC 429 OUT 2A
OUT
42
RESERVED
--
4
RESERVED
--
43
RESERVED
--
5
RESERVED
--
44
RESERVED
--
6
RESERVED
--
45
ARINC 429 IN 1A
IN
7
ARINC 429 OUT 1B
OUT
46
ARINC 429 IN 1B
IN
8
ARINC 429 OUT 3A
OUT
47
ARINC 429 IN 3A
IN
9
ARINC 429 OUT 3B
OUT
48
SIGNAL GROUND
--
10
RS-422 IN A
IN
49
ARINC 429 OUT 2A
OUT
11
RS-422 IN B
IN
50
ARINC 429 OUT 2B
OUT
12
RS-232 OUT 3
OUT
51
RS-232 OUT 1
OUT
13
MAGNETOMETER POWER
OUT
OUT
52
RS-232 IN 1
14
AIRCRAFT POWER 1
IN
53
CONFIG MODULE POWER
15
SIGNAL GROUND
--
54
CONFIG MODULE DATA
16
AIRCRAFT POWER 2
IN
55
CONFIG MODULE CLOCK
17
RESERVED
--
56
DISCRETE IN 1*
IN
18
RESERVED
--
57
SYS ID 2*
IN
19
RESERVED
--
58
RESERVED
IN
IN
OUT
I/O
OUT
20
RESERVED
--
59
RESERVED
I/O
21
ARINC 429 OUT 3A
OUT
60
PPS IN 1A
IN
22
ARINC 429 OUT 3B
OUT
61
PPS IN 2B
IN
23
ARINC 429 OUT 2B
OUT
62
RESERVED
--
24
SIGNAL GROUND
--
63
RESERVED
--
25
PPS SELECT
IN
64
RESERVED
--
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-14
26
SIGNAL GROUND
--
65
ARINC 429 IN 2A
IN
27
ARINC 429 OUT 1A
OUT
66
ARINC 429 IN 2B
IN
28
RESERVED
--
67
ARINC 429 IN 3B
IN
29
RESERVED
--
68
SIGNAL GROUND
--
30
SIGNAL GROUND
--
69
RESERVED
--
31
SIGNAL GROUND
--
70
RESERVED
--
32
SIGNAL GROUND
--
71
RS-232 OUT 2
33
MAGNETOMETER GROUND
--
72
RS-232 IN 2
OUT
IN
34
AIRCRAFT GROUND 1
--
73
SIGNAL GROUND
--
35
SPARE
--
74
CONFIG MODULE GROUND
--
36
AIRCRAFT GROUND 2
--
75
SYS ID 1*
IN
37
SIGNAL GROUND
--
76
DISCRETE IN 3*
IN
38
RESERVED
--
77
DISCRETE IN 4
IN
39
RESERVED
I/O
78
DISCRETE IN 2*
IN
*Indicates Active-Low
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-15
4.2.6
GAD 43
The GAD 43 has one connector. The mating designator, part number, and associated connector kit are
listed in Table 4-7.
Table 4-7 G500/G600 TXi - GAD 43 Connectors
REF. DES.
P431
DESCRIPTION
CONN P/N
Conn, D-Sub, Mil Crimp Socket, 50 Ckt
17 16 15 14 13 12 11 10
9
8
330-00502-50
7
6
5
4
3
2
KIT P/N
011-01990-00
1
33 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18
50
49 48 47 46 45 44 43 42 41 40 39 38 37 36 35 34
Figure 4-7 GAD 43/43e J431/P431 Connector Looking at Unit
J431/P431 Connector
Pin
Function
1
RESERVED
2
HEADING VALID OUT*
3
I/O
Pin
Function
I/O
--
26
WXR ROLL OUT LO (50 mV/deg)
--
OUT
27
SPARE DISC IN* 2
IN
ATTITUDE VALID RELAY NO
--
28
WXR ROLL OUT HI (50 mV/deg)
OUT
4
ATTITUDE VALID RELAY NC
--
29
ROLL DC OUT
OUT
5
AP INTERLOCK RELAY COMMON
--
30
ROLL SYNCHRO OUT X
OUT
6
+26 VDC OUT
OUT
31
PITCH SYNCHRO OUT X
OUT
7
HDG SYNCHRO OUT Y
OUT
32
ARINC 429 IN B
8
HDG SYNCHRO OUT X
OUT
33
RS-232 OUT
IN
OUT
9
10VAC REF IN HI
IN
34
26VAC LO
--
10
10VAC REF IN LO
IN
35
5VAC OUT LO
--
11
SPARE DISC OUT* 2
OUT
36
5VAC OUT HI
OUT
12
WXR PITCH OUT HI (50mV/deg)
OUT
37
115VAC REF IN LO
IN
13
PITCH DC OUT
OUT
38
115VAC REF IN HI
IN
14
ROLL SYNCHRO OUT Y
OUT
39
26VAC REF IN HI
IN
15
PITCH SYNCHRO OUT Y
OUT
40
YAW RATE / BARO CORRECTION
GND
--
16
ARINC 429 IN A
IN
41
HDG SYNCHRO OUT Z
17
RS-232 IN
IN
42
PITCH AC OUT LO
(60 Mv/DEG OR 200 Mv/DEG)
--
18
26VAC OUT HI
OUT
43
WXR PITCH OUT LO (50 mV/deg)
--
19
YAW RATE / BARO CORRECTION
OUT
OUT
44
ROLL SYNCHRO OUT Z
--
20
ATTITUDE VALID RELAY COMMON
--
45
PITCH SYNCHRO OUT Z
OUT
21
AP INTERLOCK RELAY VALID NC
--
46
RS-232 GND
--
22
AP INTERLOCK RELAY VALID NO
--
47
AIRCRAFT GROUND
--
23
ROLL AC OUT HI
(54 mV/deg or 200 mV/deg)
OUT
48
AIRCRAFT GROUND
--
190-01717-B1
Rev. 3
OUT
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-16
24
PITCH AC OUT HI
(60 mV/deg or 200 mV/deg)
OUT
49
AIRCRAFT POWER 1
IN
25
ROLL AC OUT LO
(54 mV/deg or 200 mV/deg)
--
50
AIRCRAFT POWER 2
IN
*Indicates Active-Low
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-17
4.2.7
GAD 43e
The GAD 43e has three connectors. The mating designators, part numbers, and associated connector kit
are listed in Table 4-8. Refer to Section 4.2.6 for J431/P431 pinout.
Table 4-8 G500/G600 TXi - GAD 43e Connectors
REF. DES.
DESCRIPTION
CONN P/N
KIT P/N
P431
Conn, D-Sub, Mil Crimp Socket, 50 Ckt
330-00502-50
011-02350-00
P432
Conn, HD D-Sub, Male, Str, Mil Crmp Pins, 78 Ckt
330-00626-78
011-02350-00
P433
Conn, HD D-Sub, Male, Str, Mil Crmp Pins, 26 Ckt
330-00626-26
011-02350-00
60
40
61
41
1
2
3
64
5
66
46
26
25
24
4
65
45
44
43
23
22
21
63
62
42
6
67
47
8
69
49
29
28
27
7
68
48
9
70
50
30
10
71
31
11
72
33
32
12
73
53
52
51
13
74
54
35
34
14
75
55
15
76
56
36
16
37
17
78
77
57
58
38
18
59
39
19
20
Figure 4-8 GAD 43e J432/P432 Connector Looking at Unit
J432/P432 Connector
Pin
Function
I/O
Pin
Function
I/O
1
ALTITUDE PRESELECT DATA
I/O
40
DME RQST HI / DME SYNC IN HI
I/O
2
GROUND
--
41
DME RQST LO / DME SYNC IN LO
I/O
3
RS-232 IN 2
IN
42
DME RNAV RQST OUT
OUT
4
RS-232 OUT 2
OUT
43
ARINC 429 OUT 1A
OUT
5
RS-232 GND 2
--
44
ARINC 429 OUT 1B
OUT
6
OUTER MARKER EXT LAMP IN
IN
45
GROUND
--
7
MIDDLE MARKER EXT LAMP IN
IN
46
ILS ENERGIZE #1 IN*
IN
8
INNER MARKER EXT LAMP IN
IN
47
ILS ENERGIZE #2 IN*
IN
9
RADAR ALT VALID IN
IN
48
GLIDESLOPE #1 VALID IN
IN
10
GROUND
--
49
GLIDESLOPE #2 VALID IN
IN
11
RESERVED
--
50
DME EXT TUNE K50 IN
IN
12
RESERVED
--
51
DME SUPERFLAG IN
IN
13
RESERVED
--
52
DME HOLD OUT*
OUT
14
RESERVED
--
53
ALT HOLD*
OUT
15
GROUND
--
54
GROUND
--
16
RESERVED
--
55
RESERVED
--
17
VS CMD
OUT
56
RESERVED
--
18
GROUND
--
57
RESERVED
--
19
ALTITUDE ERROR OUT +
OUT
58
PRESELECT MON+ POWER
IN
20
ALTITUDE ERROR OUT -
OUT
59
PRESELECT MON+ OUT
21
ALTITUDE PRESELECT CLOCK
I/O
60
DME CLOCK HI
I/O
22
GROUND
--
61
DME CLOCK LO
I/O
23
DME ARINC 429 IN A
IN
62
DME DATA HI
I/O
24
DME ARINC 429 IN B
IN
63
DME DATA LO
I/O
25
GROUND
--
64
AIRCRAFT GROUND
--
26
RESERVED
--
65
DME EXT TUNE M8/MA/M0 IN
IN
190-01717-B1
Rev. 3
OUT
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-18
27
RESERVED
--
66
DME EXT TUNE M4/ME/M1 IN
IN
28
RESERVED
--
67
DME EXT TUNE M2/MC/M2 IN
IN
29
RESERVED
--
68
DME EXT TUNE M1/MD/M3 IN
IN
30
PRESELECT ADDR 0 / AP DISC SW
IN
69
DME EXT TUNE K800/KA/K0 IN
IN
31
PRESELECT ADDR 1
IN
70
DME EXT TUNE K400/KE/K1 IN
IN
32
GROUND
--
71
DME EXT TUNE K200/KC/K2 IN
IN
33
RESERVED
--
72
DME EXT TUNE K100/KD/K3 IN
IN
34
VS SELECT CTRL* / KNOB IN
MOTION*
OUT
73
GROUND
--
35
DME COM NAV 1* / CH 1-2
SELECT*
I/O
74
RESERVED
--
36
DME COM NAV 2*
I/O
75
RESERVED
--
37
RESERVED
--
76
GROUND
--
38
GROUND
--
77
RESERVED
--
39
RESERVED
--
78
RESERVED
--
*Indicates Active-Low
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-19
9
8
18
7
17
26
6
16
25
5
15
24
3
4
14
23
13
22
1
2
12
21
11
20
10
19
Figure 4-9 GAD 43e J433/P433 Connector Looking at Unit
J433/P433 Connector
Pin
190-01717-B1
Rev. 3
Function
I/O
1
VOR/LOC COMPOSITE #1 HI
IN
2
VOR/LOC COMPOSITE #1 LO
IN
3
VOR/LOC COMPOSITE #2 HI
IN
4
VOR/LOC COMPOSITE #2 LO
IN
5
GROUND
--
6
GLIDESLOPE #1 +UP IN
IN
7
GLIDESLOPE #1 +DN IN
IN
8
GLIDESLOPE #2 +UP IN
IN
9
GLIDESLOPE #2 +DN IN
IN
10
RESERVED
--
11
GROUND
--
12
ADF BEARING X
IN
13
ADF BEARING Y
IN
14
ADF BEARING Z (GND)
--
15
RADAR ALT IN HI
IN
16
RADAR ALT IN LO
IN
17
GROUND
--
18
GROUND
--
19
FD PITCH UP OUT/GS #2 VALID OUT
20
FD PITCH DOWN OUT (GND)
21
FD ROLL RIGHT OUT/GS #1 VALID OUT
22
FD ROLL LEFT OUT (GND)
--
23
FD PITCH UP IN/GS #2 +FLAG
IN
24
FD PITCH DOWN IN/GS #2 -FLAG
IN
25
FD ROLL RIGHT IN/GS #1 +FLAG
IN
26
FD ROLL LEFT IN/GS #2 -FLAG
IN
OUT
-OUT
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-20
4.2.8
GEA 110
The GEA 110 has two connectors. The mating designators, part numbers, and associated connector kits are
listed in Table 4-9.
Table 4-9 G500/G600 TXi - GEA 110 Connectors
REF. DES.
P1101
P1102
DESCRIPTION
CONN P/N
KIT P/N
Conn, Hi Dens, D-Sub, Mil Crmp, 15 Ckt
330-00185-15
011-03527-50
Conn, HD D-Sub, Male, Str, Mil Crp contacts
included, sealed, 15 Pin
330-01384-00
011-03527-51
Conn, Hi Dens, D-Sub, Mil Crp, 78 Ckt
330-00185-75
011-03527-50
Conn, HD D-Sub, Male, Str, Mil Crp, Sealed,
w/ GND Indents, 78 Pin
330-00776-78
011-03527-51
Figure 4-10 GEA 110 Connectors
5
4
3
10
15
9
14
2
7
8
13
1
12
6
11
Figure 4-11 GEA 110 J1101/P1101 Connector Looking at Unit
J1101/P1101 Connector
Pin
190-01717-B1
Rev. 3
Function
I/O
1
AV PWR IN 1
IN
2
RESERVED
--
3
DISCRETE OUT 1
4
RS 485 2A
I/O
5
RS 485 1A
I/O
6
AV PWR IN 2
IN
7
RESERVED
--
8
DISCRETE OUT 2
9
RS 485 2B
I/O
10
RS 485 1B
I/O
OUT
OUT
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-21
20
19
39
59
18
38
58
78
17
37
57
77
DISCRETE IN 5
IN
12
SYS ID #1
IN
13
SYS ID #2
IN
14
GND
--
15
GND
--
16
36
56
76
11
15
34
35
55
75
14
54
74
13
32
33
52
53
73
12
72
11
31
51
71
30
50
70
10
9
28
29
48
49
69
8
68
7
27
47
67
64
3
23
43
44
45
65
4
24
25
26
46
66
5
6
63
1
2
21
22
42
62
41
61
40
60
Figure 4-12 GEA 110 J1102/P1102 Connector Looking at Unit
J1102/P1102 Connector
Pin
Function
I/O
Pin
Function
I/O
1
CHT 1 (+)
IN
40
EGT 1 (+)
IN
2
CHT 2 (+)
IN
41
EGT 2 (+)
IN
3
CHT 3 (+)
IN
42
EGT 3 (+)
IN
4
CHT 4 (+)
IN
43
EGT 4 (+)
IN
5
CHT 5 (+)
IN
44
EGT 5 (+)
IN
6
CHT 6 (+)
IN
45
EGT 6 (+)
IN
7
GENERAL PURPOSE 1 (+)
IN
46
CARB TEMP (+)
IN
8
GENERAL PURPOSE 2 (+)
IN
47
OIL TEMP (+)
IN
9
+10 VDC
OUT
48
OIL PRESSURE (+)
IN
10
FUEL PRESSURE (+)
IN
49
GND
--
11
DISCRETE IN 1
IN
50
MANIFOLD PRESSURE (+)
IN
12
FUEL QUANTITY 1 /
GENERAL PURPOSE 3 (+)
IN
51
DISCRETE IN 3
IN
13
FUEL QUANTITY 3 /
GENERAL PURPOSE 5 (+)
IN
52
FUEL QUANTITY 2 /
GENERAL PURPOSE 4 (+)
IN
14
GND
IN
53
FUEL QUANTITY 4 /
GENERAL PURPOSE 6 (+)
IN
15
FUEL FLOW 1
IN
54
GND
--
16
FUEL FLOW 2
17
+12 VDC
IN
55
SHUNT 1 (-)
IN
OUT
56
SHUNT 2 (-)
IN
18
RPM IN 1 (+)
IN
57
BUS 1
IN
19
RPM IN 2 (+)
IN
58
BUS 2
IN
20
CONFIG. MOD PWR
OUT
59
CONFIG MOD CLOCK
21
CHT 1 (-)
IN
60
EGT 1 (-)
IN
22
CHT 2 (-)
IN
61
EGT 2 (-)
IN
23
CHT 3 (-)
IN
62
EGT 3 (-)
IN
190-01717-B1
Rev. 3
OUT
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-22
24
CHT 4 (-)
IN
63
EGT 4 (-)
IN
25
CHT 5 (-)
IN
64
EGT 5 (-)
IN
26
CHT 6 (-)
IN
65
EGT 6 (-)
IN
27
GENERAL PURPOSE 1 (-)
IN
66
CARB TEMP (-)
IN
28
GENERAL PURPOSE 2 (-)
IN
67
OIL TEMP (-)
IN
29
+5 VDC
OUT
68
OIL PRESSURE (-)
IN
30
FUEL PRESSURE (-)
IN
69
+12 VDC
31
DISCRETE IN 2
IN
70
MANIFOLD PRESSURE (-)
IN
32
FUEL QUANTITY 1 /
GENERAL PURPOSE 3 (-)
IN
71
DISCRETE IN 4
IN
33
FUEL QUANTITY 3 /
GENERAL PURPOSE 5 (-)
IN
72
FUEL QUANTITY 2 /
GENERAL PURPOSE 4 (-)
IN
34
GND
--
73
FUEL QUANTITY 4 /
GENERAL PURPOSE 6 (-)
IN
35
SHUNT 1 (+)
IN
74
GND
--
36
SHUNT 2 (+)
IN
75
SPARE
--
37
RPM IN 1 (-)
IN
76
+5 VDC
OUT
38
RPM IN 2 (-)
IN
77
BUS 3
IN
39
CONFIG MOD DATA
I/O
78
CONFIG MOD GND
--
190-01717-B1
Rev. 3
OUT
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-23
4.2.9 GEA 71B Enhanced
The GEA 71B Enhanced has two connectors. The mating designators, part numbers, and associated
connector kits are listed in Table 4-10.
Table 4-10 G500/G600 TXi - GEA 71B Enhanced Connectors
REF. DES.
DESCRIPTION
CONN P/N
KIT P/N
J701
Conn, Hi Dens, D-Sub, Mil Crp, 78 Ckt
330-00185-78
011-00797-03
J702
Conn, Hi Dens, D-Sub, Mil Crp, 78 Ckt
330-00185-78
011-00797-03
-
-
Figure 4-13 GEA 71B Enhanced Connectors
60
40
61
41
1
2
3
64
66
46
26
25
24
4
65
45
44
43
23
22
21
63
62
42
6
5
67
47
9
8
69
49
29
28
27
7
68
48
70
50
30
10
71
31
11
72
33
32
12
73
53
52
51
13
74
54
35
34
14
75
55
15
76
56
36
16
37
17
78
77
57
58
38
18
59
39
19
20
J701/P701 Connector
Pin
Function
I/O
Pin
Function
I/O
1
CONFIG MODULE GROUND
--
40
CONFIG MODULE DATA
I/O
2
DIGITAL IN* 1
IN
41
DIGITAL IN*3
IN
3
DIGITAL IN* 2
IN
42
ANALOG IN 3 HI
IN
4
SIGNAL GROUND
--
43
ANALOG IN 3 LO
IN
5
RS-485 1 A
I/O
44
ANALOG IN 4 HI
IN
6
RS-485 1 B
I/O
45
ANALOG IN 4 LO
IN
7
RS-485 2 A
I/O
46
ANALOG IN 5 HI
IN
8
RS-485 2 B
I/O
47
ANALOG IN 5 LO
IN
9
RESERVED
--
48
ENGINE TEMP ANALOG IN 7 HI
IN
10
RESERVED
--
49
ENGINE TEMP ANALOG IN 7 LO
IN
11
TRANSDUCER PWR OUT LO (GND)
--
50
ENGINE TEMP ANALOG IN 8 HI
IN
12
TRANSDUCER PWR OUT LO (GND)
--
51
ENGINE TEMP ANALOG IN 8 LO
IN
13
TRANSSUCER PWR OUT LO (GND)
--
52
ENGINE TEMP ANALOG IN 9 HI
IN
14
+10 VDC TRANSDUCER PWR OUT
OUT
53
ENGINE TEMP ANALOG IN 9 LO
IN
15
+5 VDC TRANSDUCER PWR OUT
OUT
54
ENGINE TEMP ANALOG IN 10 HI
IN
16
+12 VDC TRANSDUCER PWR OUT
OUT
55
ENGINE TEMP ANALOG IN 10 LO
IN
17
ENGINE TEMP ANALOG IN 6 HI
IN
56
ENGINE TEMP ANALOG IN 11 HI
IN
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-24
18
ENGINE TEMP ANALOG IN 6 LO
IN
57
ENGINE TEMP ANALOG IN 11 LO
IN
19
SIGNAL GROUND
--
58
ENGINE TEMP ANALOG IN 12 HI
IN
20
POWER GROUND
--
59
ENGINE TEMP ANALOG IN 12 LO
IN
21
CONFIG MODULE POWER
OUT
60
CONFIG MODULE CLOCK
22
ANALOG IN 1 HI
IN
61
DIGITAL IN* 4
IN
23
ANALOG IN 1 LO
IN
62
ANALOG IN 6 HI
IN
24
ANALOG IN 2 HI
IN
63
ANALOG IN 6 LO
IN
25
ANALOG IN 2 LO
IN
64
ANALOG IN 7 HI
IN
26
ENGINE TEMP ANALOG IN 1 HI
IN
65
ANALOG IN 7 LO
IN
27
ENGINE TEMP ANALOG IN 1 LO
IN
66
ANALOG IN 8 HI
IN
28
ENGINE TEMP ANALOG IN 2 HI
IN
67
ANALOG IN 8 LO
IN
29
ENGINE TEMP ANALOG IN 2 LO
IN
68
THERMOCOUPLE REF IN HI
IN
30
ENGINE TEMP ANALOG IN 3 HI
IN
69
THERMOCOUPLE REF IN LO
IN
31
ENGINE TEMP ANALOG IN 3 LO
IN
70
DISCRETE IN* 1
IN
32
SIGNAL GROUND
--
71
DISCRETE IN* 2
IN
33
ENGINE TEMP ANALOG IN 4 HI
IN
72
ANALOG IN 9 HI
IN
34
ENGINE TEMP ANALOG IN 4 LO
IN
73
ANALOG IN 9 LO
IN
35
AIRCRAFT POWER 1
IN
74
ANALOG IN 10 HI
IN
36
ENGINE TEMP ANALOG IN 5 HI
IN
75
ANALOG IN 10 LO
IN
37
AIRCRAFT POWER 2
IN
76
DISCRETE IN* 3
IN
38
ENGINE TEMP ANALOG IN 5 LO
IN
77
RESERVED
--
39
SIGNAL GROUND
--
78
POWER GROUND
--
OUT
* Indicates Active-Low
20
19
39
59
18
38
58
78
17
37
57
77
16
36
56
76
15
55
75
14
34
35
54
74
13
33
52
53
73
12
32
72
11
31
51
71
10
30
50
70
9
49
69
8
29
48
68
7
27
28
47
67
6
46
66
5
25
26
44
45
65
4
24
64
43
63
3
42
62
1
2
22
23
21
41
61
40
60
J702/P702 Connector
Pin
Function
I/O
Pin
Function
I/O
1
ANNUNCIATE* 1A
OUT
40
DISCRETE IN* 17A
IN
2
ANNUNCIATE* 2A
OUT
41
DISCRETE IN* 18A
IN
3
ANNUNCIATE* 3A
OUT
42
DISCRETE IN* 19A
IN
4
ANNUNCIATE* 4A
OUT
43
DISCRETE IN* 20A
IN
5
ANNUNCIATE* 5A
OUT
44
ANLG/CURRENT MONITOR IN 1A HI
IN
6
ANNUNCIATE* 6A
OUT
45
ANLG/CURRENT MONITOR IN 1A LO
IN
7
ANNUNCIATE* 7A
OUT
46
ANLG/CURRENT MONITOR IN 2A HI
IN
8
EXTNDED CMN MDE ANLG IN 1A HI
IN
47
ANLG/CURRENT MONITOR IN 2A LO
IN
9
EXTNDED CMN MDE ANLG IN 1A LO
IN
48
ANLG/CURRENT MONITOR IN 3A HI
IN
10
ANNUNCIATE* 8A
OUT
49
ANLG/CURRENT MONITOR IN 3A LO
IN
11
TRANSDUCER PWR OUT LO (GND)
--
50
ANLG/CURRENT MONITOR IN 4A HI
IN
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-25
12
TRANSDUCER PWR OUT LO (GND)
--
51
ANLG/CURRENT MONITOR IN 4A LO
IN
13
TRANSDUCER PWR OUT LO (GND)
--
52
ANALOG IN 1A HI
IN
14
+10 VDC TRANSDUCER PWR OUT A
OUT
53
ANALOG IN 1A LO
IN
15
+5 VDC TRANSDUCER PWR OUT A
OUT
54
ANALOG IN 2A HI
IN
16
+12 VDC TRANSDUCER PWR OUT A
OUT
55
ANALOG IN 2A LO
IN
17
SPARE
--
56
ANALOG IN 3A HI
IN
18
EXTNDED CMN MDE ANLG IN 2A HI
IN
57
ANALOG IN 3A LO
IN
19
EXTNDED CMN MDE ANLG IN 2A LO
IN
58
ANALOG IN 4A HI
IN
20
ANNUNCIATE* 9A
OUT
59
ANALOG IN 4A LO
IN
21
DIFF COUNTER IN 1A HI
IN
60
DISCRETE IN* 1A
IN
22
DIFF COUNTER IN 1A LO
IN
61
DISCRETE IN* 2A
IN
23
DIFF COUNTER IN 2A HI
IN
62
DISCRETE IN* 3A
IN
24
DIFF COUNTER IN 2A LO
IN
63
DISCRETE IN* 4A
IN
25
DISCRETE IN* 11A
IN
64
DISCRETE IN* 5A
IN
26
DISCRETE IN* 12A
IN
65
DISCRETE IN* 6A
IN
27
DISCRETE IN* 13A
IN
66
DISCRETE IN* 7A
IN
28
DISCRETE IN* 14A
IN
67
DIGITAL IN* 5A
IN
29
DISCRETE IN* 15A
IN
68
DIGITAL IN* 6A
IN
30
DISCRETE IN* 16A
IN
69
DIGITAL IN* 7A
IN
31
SIGNAL GROUND
--
70
DIGITAL IN* 8A
IN
32
SIGNAL GROUND
--
71
DISCRETE IN* 8A
IN
33
SIGNAL GROUND
--
72
DISCRETE IN* 9A
IN
34
SIGNAL GROUND
--
73
DISCRETE IN* 10A
IN
35
SIGNAL GROUND
--
74
DIGITAL IN* 1A
IN
36
SIGNAL GROUND
--
75
DIGITAL IN* 2A
IN
37
SIGNAL GROUND
--
76
DIGITAL IN* 3A
IN
38
SIGNAL GROUND
--
77
DIGITAL IN* 4A
IN
39
SIGNAL GROUND
--
78
SIGNAL GROUND
--
* Indicates Active-Low
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-26
4.2.10 GBB 54
The GBB 54 has one connector. The mating designator, part number, and associated connector kit are listed
in Table 4-11.
Table 4-11 G500/G600 TXi - GBB 54 Connectors
REF. DES.
P541
DESCRIPTION
CONN P/N
Conn, Std D-Sub, Male, Crimp, No Contacts, 15 Pos
8
6
7
15
14
5
13
4
12
3
11
KIT P/N
330-01437-00 011-03527-70
2
1
10
9
Figure 4-14 GBB 54 J541/P541 Connector
J541/P541 Connector
Pin
190-01717-B1
Rev. 3
Function
I/O
1
POWER IN
IN
2
POWER IN
IN
3
GROUND
--
4
STANDBY
OUT
5
GROUND
--
6
GROUND
--
7
BATTERY POWER
OUT
8
BATTERY POWER
OUT
9
POWER IN
IN
10
GROUND
--
11
RS-232 TX
OUT
12
RS-232 RX
IN
13
PWR ON REQ
IN
14
GROUND
--
15
BATTERY POWER
OUT
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-27
4.2.11 GMU 44
The GMU 44 has one connector. The mating designator, part number, and associated connector kit are
listed in Table 4-12.
Table 4-12 G500/G600 TXi - GMU 44 Connectors
REF. DES.
P441
DESCRIPTION
CONN P/N
Conn, Circular, Female, 9 Ckt
KIT P/N
330-00360-00 011-00871-00
Figure 4-15 J441/P441 Connector Looking at Pigtail
J441/P441 Connector
Pin
Function
I/O
1
SIGNAL GROUND
2
RS-485 OUT B
--
3
SIGNAL GROUND
4
RS-485 OUT A
5
SPARE
--
6
POWER GROUND
--
7
SPARE
--
8
RS-232 IN
IN
9
+12 VDC POWER
IN
OUT
-OUT
4.2.12 GTP 59
The GTP 59 Temperature Probe does not have a connector. Rather, a 3-conductor shielded cable extends
from the sensor for interface with a GDU or GDC unit.
3-Conductor Shielded Cable
Conductor Color
190-01717-B1
Rev. 3
Name
I/O
White
Probe Power Lead
IN
Blue
Resistive Element HI
OUT
Orange
Resistive Element LO
OUT
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-28
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.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-29
G D U A le r t M e s s a g e s
D is p la y h o t,
d is p la y
d im m e d
C o o lin g fa n
fa ile d
B a c k lig h t
c a lib ra tio n
lo s t
D em o m ode,
d o n o t u s e in
flig h t
M a in te n a n c e
Log M essage
M a in te n a n c e
Log M essage
The G D U has
e x c e e d e d its
o v e rte m p th re s h o ld
G D U S o ftw a re
M is m a tc h
C ause
C ause
G D U c o o lin g fa n
fa ilu re
OR
G D U c o o lin g fa n
o b s tru c tio n
C o rr e c tiv e
A c tio n
J 2 P in 3 9 o n th e
G D U is g ro u n d e d
C o r re c tiv e
A c tio n
R e p la c e c o o lin g
fa n in a c c o rd a n c e
w ith S e c tio n 5 .1 .2
C ause
O n e o r m o re
G D U s in th e
s y s te m h a v e a
d iffe re n t s o ftw a re
v e rs io n
C o rre c tiv e
A c tio n
C o r re c tiv e
A c tio n
C o rre c tiv e
A c tio n
R e tu rn th e G D U to
G a rm in fo r s e rv ic e
In s p e c t G D U
c o n n e c to rs a n d
w irin g to re m o v e
th e s ig n a l fro m th e
D em o M ode
S e le c t P in
E n s u re a ll G D U s
h a v e th e s a m e
s y s te m s o ftw a re
in s ta lle d
V e rify c o o lin g fa n
p o rts a re c le a r
If m e s s a g e is in
c o n ju n c tio n w ith
“F a n F a ilu re
d e te c te d ”
m e s s a g e , re p la c e
c o o lin g fa n in
a c c o rd a n c e w ith
S e c tio n 5 .1 .2
S e rv ic e
R e q u ire d
If fa u lt s till e x is ts ,
c o n ta c t G a rm in .
Figure 4-16 GDU Alert Message Troubleshooting
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-30
Battery/Configuration
Alert Messages
Battery
unavailable:
fault
detected
Battery
unavailable:
communication
lost
Battery
unavailable:
power output
failed
Battery
unavailable:
capacity test
required
Internal config module
has been overwritten
by harness config
module
External config
module has been
overwritten by internal
config module
Service
Soon
Service
Required
Maintenance
Log Message
Maintenance
Log Message
Maintenance
Log Message
Maintenance
Log Message
Internal config module
has been overwritten
External config
module has been
overwritten
System configuration
module has failed or
is missing
Multiple master
config modules
detected
Cause
Cause
Cause
Cause
Cause
The battery capacity
test has not been
successfully completed
or
Capacity test not run in
last 392 days
This message is
expected if a GDU
has been replaced
This message is
expected if a
configuration
module has been
replaced
External config
module cannot be
written to, read
from, or is not
detected in the
system
More than one
GDU is configured
as “Master”
Corrective
Action
Corrective
Action
Corrective
Action
Corrective
Action
Corrective
Action
Corrective
Action
Corrective
Action
Corrective
Action
Return GBB 54 to
Garmin for service
Verify GBB 54 and
GDU wiring and
connections
Verify GBB 54 and
GDU wiring and
connections
Verify that the
GBB 54 battery
cell is fully charged
Verify GDU
configuration
matches printed
configuration log
Verify GDU
configuration
matches printed
configuration log
Inspect config
module wiring and
connector for bent,
damaged, missing
pins/wires
Verify GDU
configuration
Verify that GBB 54
battery cell is
charged
If configuration
does not match
printed log, load
GDU configuration
from saved SD
card
If configuration
does not match
printed log, load
GDU configuration
from saved SD
card
Replace external
configuration module
in accordance with
Section 5.1.4 or
Section 5.1.5
Run the battery
capacity test in
accordance with
Section 5.13.8
Ensure only one
GDU is configured
as “Master” under
the “GDU Type”
configuration
window
If fault still exists,
contact Garmin.
Figure 4-17 GDU Config and Battery Alert Message Troubleshooting
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-31
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 6.6.4 of
installation manual
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
G500/G600 Txi
Part 23 AML
Installation Manual
(P/N 190-01717B3) for more
information)
Contact Garmin
Technical Support
Inspect NAV
wiring,
connections, and
configuration
settings
If fault still exists,
contact Garmin.
Figure 4-18 PFD Alert Message Troubleshooting
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-32
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
ADC 1/2 reports
SSEC unavailable or
failed
AHRS 1/2 is not
receiving true
airspeed
ADC 1/2 reports
configuration
error
Cause
Cause
Cause
Cause
The alert flag has
been set by the
ADC
Wrong RVSM
aircraft configuration
OR
ADC 2 selected on
PFD 1
ADC loss of
communication
OR
No GTP 59 signal
Corrective
Action
Corrective
Action
Verify ADC power
If RVSM is
expected, ensure
RVSM feature is
enabled in Feature
Enablement page.
Cause
Cause
Cause
Cause
The AHRS has
detected an intarmac 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 6.6.4 of
the G500/G600
Txi Part 23 AML
STC Installation
Manual (P/N 19001717-B3)
If this error shows
up repeatedly,
conduct the
magnetic
interference check
in Section 6.6.4 of
the G500/G600
TXi Part 23 AML
STC Installation
Manual (P/N 19001717-B3)
Perform AHRS
magnetic model
maintenance in
accordance with
Table 3-1
Inspect GMU 44
wiring and
connections
If other ADC or
AHRS faults are
present, correct
those faults first.
Verify ADC 1/2
configuration and
wiring
Ensure GMU 44
installation is
within ±3° of level
and less than 6°
difference from the
AHRS unit in
accordance with
G500/G600 TXi
AML STC
Installation Manual
Verify ADC 1/2
configuration and
wiring.
Inspect ADC/
AHRS wiring and
connections
ADC reports config
error
OR
RVSM is not enabled
in the system but the
ADC is expecting
RVSM
Replace ADC
config module
Inspect GTP 59,
connections, and
wiring.
If fault still exists,
contact Garmin.
Figure 4-19 AHRS/ADC Alert Message Troubleshooting
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-33
T errain /TA W S A lert
M essages
T A W S F A IL
T A W S N /A
E xt. T A W S
F ail
E xt. T A W S
N /A
T E R F A IL
T E R N /A
S ervice
TAW S.
In valid
C o nfig .
M ainten an ce
Lo g M essage
C au se
C au se
C au se
C a us e
A udio F ailed
OR
D atabase error
OR
Internal failure
G D U is operating
from backup G P S
OR
P rim ary G P S is not
receiving a signal
D atabase corrupted
or m issing
OR
Internal failure
B ackup G P S is active
OR
N o P rim ary G P S signal
OR
O utside database region
T A W S /TE R config not set
OR
E xternal TA W S and G D U
m ism atch (rotorcraft /
fixed-w ing)
C orrective
A ctio n
C orrective
A ction
C orrective
A ctio n
C orrective
A ctio n
C o rrective
A ction
V erify audio
system is online
and terrain
database is loaded
V erify prim ary
G P S is on and has
a clear view of the
sky
V erify terrain
database is loaded
and current.
V erify prim ary
G P S is on and has
a clear view of the
sky
C heck TA W S /
T errain
configuration
settings
V erify terrain
alerting
configuration
Inspect G P S
antenna and w iring
R eload terrain
database
Inspect G P S
antenna and w iring
C orrective
A ction
S ee external
T A W S unit m anual
for troubleshooting
instructions
C orrective
A ction
S ee external
T A W S unit m anual
for troubleshooting
instructions
R eload Terrain
database
V erify E xternal
TA W S and G D U
have the sam e
aircraft type
configured
V erify T errain
database coverage
If fau lt s till exists ,
c on tact G arm in .
Figure 4-20 Terrain Alert Message Troubleshooting
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-34
T r a ff ic A le r t M e s s a g e s
T A S /T C A S
fu n c tio n
in o p e ra tiv e
A D S tra ffic
a le rtin g
fu n c tio n
in o p e ra tiv e
A D S tra ffic
fu n c tio n
in o p e ra tiv e
T ra ffic /F IS -B
fu n c tio n s
in o p e ra tiv e
U A T tra ffic /
d a ta re c e iv e r
fa u lt
1090ES
tra ffic
re c e iv e r fa u lt
C o r r e c tiv e
A c tio n
C o r r e c tiv e
A c tio n
C o r r e c tiv e
A c tio n
C o r r e c tiv e
A c tio n
C o r r e c tiv e
A c tio n
C o r r e c t iv e
A c tio n
T r o u b le s h o o t
d e v ic e fa ilu re in
a c c o rd a n c e w ith
T A S /T C A S L R U
m a in te n a n c e
m anual
T ro u b le s h o o t
d e v ic e fa ilu re in
a c c o rd a n c e w ith
A D S -B L R U
m a in te n a n c e
m anual
T ro u b le s h o o t
d e v ic e fa ilu re in
a c c o rd a n c e w ith
A D S -B L R U
m a in te n a n c e
m anual
T r o u b le s h o o t d e v ic e
fa ilu re in a c c o r d a n c e
w ith U A T L R U
m a in te n a n c e m a n u a l
T r o u b le s h o o t
d e v ic e fa ilu re in
a c c o rd a n c e w ith
A D S -B L R U
m a in te n a n c e
m anual
T ro u b le s h o o t
d e v ic e fa ilu re in
a c c o rd a n c e w ith
A D S -B L R U
m a in te n a n c e
m anual
If fa u lt s till e x is ts ,
c o n ta c t G a r m in .
Figure 4-21 Traffic Alert Message Troubleshooting
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-35
Audio/WX Radar Fault
Messages
TAWS audio
data missing
or corrupt
Weather
radar needs
service
Audio
Inoperative
Weather
radar
inoperative
Maintenance
Log Message
Cause
Cause
Audio Failed
OR
Database Failed
OR
Internal failure
Audio device failed
OR
Audio clip failed to
play
Corrective
Action
Corrective
Action
Verify audio
system is online
and terrain
database is loaded
Verify audio device
is online
Verify terrain
alerting
configuration
Troubleshoot in
accordance with
audio device
maintenance
manual
Inspect audio
device
connections and
wiring
GWX requires
service
ARINC 708
weather radar
requires service
Weather radar is
not receiving one
or more inputs
Cause
Cause
Cause
Cause
See maintenance
log message for
specific failure
condition
See A708 weather
radar maintenance
manual for specific
failure
Display failure
OR
Attitude in failure
OR
Control fault
Connection to WX
radar lost
OR
Improper
configuration
Corrective
Action
Corrective
Action
Corrective
Action
Corrective
Action
Remove GWX and
contact Garmin to
return unit for
service
Remove A708
weather radar and
contact
appropriate
company for repair
Inspect WX radar
wiring and
connections
Check power and
wiring to WX radar
Verify WX radar
and GDU
configuration
Verify correct WX
radar configuration
Troubleshoot in
accordance with
audio device
maintenance
manual
If fault still exists,
contact Garmin.
Figure 4-22 Audio/Weather Alert Message Troubleshooting
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-36
E x te r n a l L R U A le r t
M essages
S a te llite
w e a th e r
in o p e r a tiv e
S a te llite
w e a th e r n o t
r e g is te r e d
M a in te n a n c e
Log M essage
M a in t e n a n c e
Log M essage
C o m u n ic a tio n lo s t
w ith G S R 5 6
G S R 5 6 w e a th e r
n o t r e g is te r e d
Cause
C ause
C o m u n ic a tio n lo s t
w ith G S R 5 6
The G SR 56
w e a th e r fu n c tio n
has not been
re g is te re d
C o r r e c tiv e
A c t io n
In s p e c t G S R 5 6
w irin g a n d
c o n n e c to rs .
S to r m s c o p e
in o p e r a tiv e
S ir iu s X M
r e c e iv e r
in o p e r a tiv e
C o n tr o lle r
U n a v a ila b le
M a in t e n a n c e
Log M essage
M a in t e n a n c e
Log M essage
S to r m s c o p e is n o t
c o n fig u r e d o r
o p e r a tin g p r o p e r ly
C o m m u n ic a tio n
lo s t w ith
s to r m s c o p e
G C U 485
c o m m u n ic a tio n lo s t
C ause
Cause
C ause
C ause
G D L 6 9 /6 9 a h a s e ith e r
lo s t c o m m u n ic a tio n w ith
G D U o r is r e p o r tin g a
fa ile d c o n d itio n
S to rm s c o p e is
r e p o rtin g fa ile d
T h e G D U h a s lo s t
c o m m u n ic a tio n
w ith th e
s to r m s c o p e
T h e G D U h a s lo s t
c o m m u n ic a tio n w ith
th e G C U 4 8 5
C o r r e c t iv e
A c tio n
C o r r e c tiv e
A c t io n
C o r r e c t iv e
A c t io n
C o r r e c tiv e
A c t io n
C o r r e c t iv e
A c tio n
R e g is te r th e
G S R 5 6 w e a th e r
fu n c tio n a s
d e s c rib e d in
G 5 0 0 /G 6 0 0 T X i
AM L STC
In s ta lla tio n M a n u a l
In s p e c t G D L 6 9 /
6 9 a w ir in g a n d
c o n n e c to rs .
In s p e c t
s to r m s c o p e w ir in g
a n d c o n n e c tio n s
V e r ify p o w e r to
s to r m s c o p e is o n
V e rify p o w e r to
G C U 4 8 5 is o n
V e r ify s to r m s c o p e
c o n fig u ra tio n
s e ttin g s
In s p e c t
s to r m s c o p e w ir in g
a n d c o n n e c tio n s
In s p e c t G C U 4 8 5
w irin g a n d
c o n n e c tio n s
E n s u r e a ll L R U s in
th e s y s te m a re
o n lin e .
If f a u lt s t ill e x is t s ,
c o n t a c t G a r m in .
Figure 4-23 External LRU Failure Message Troubleshooting
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-37
E xte rn al L R U S ervice
A lerts
S e rvice
Soon
S e rvice
R e q uire d
M ainten an ce
L o g M e ssag e
M ainten an ce
L o g M e ssag e
S to rm scope is
reportin g in valid
he ading
E xtern a l L R U rep o rts
co n fig m od u le n e e ds
service
C h eck G A D 4 3/
4 3e co nfig u ra tion
se tting s
E xte rn a l LR U
re p o rts service
re q u ire d
R e ce ivin g d a ta
fro m th e w ro n g
sid e L R U .
A D C 1 /2 o r A H R S 1 /2
co n fig d oe s n ot m a tch
the G D U co n fig
G E A d id no t
a cce pt
co nfig u ra tion
C au se
C au se
C au s e
Cause
C au se
Cause
C au s e
A H R S does n ot
ha ve va lid h eadin g
OR
Im proper
configuratio n
T he externa l LR U
config m odule is
m issing or h as
fa ile d
T he G D U
configuratio n d oes
not m atch the
G A D 4 3 /43e
configuratio n
Incorrect S D I on
externa l L R U
OR
Incorrect G D U
con figu ration se ttings
G D U a nd external
A H R S /A D C LR U repo rt
d iffere nt configuratio n
version s
T h e G E A 110 did
not a ccept the
GDU
configuration .
C o rrective
A c tio n
C orrectiv e
A c tio n
C o rrectiv e
A ctio n
C o rre ctive
A ctio n
C orrectiv e
A c tio n
C o rre ctive
A ction
C o rrectiv e
A ctio n
T his m e ssa ge is
exp ected if in
co njunction w ith
“H D G F A IL”
m e ssage , “H D G
F A IL” m ust be
trou bleshooted
an d correcte d first
In spe ct conn ector
p ins and w iring to
externa l L R U
con fig m odu le
V erify the correct
G A D 4 3 /43 e
configuratio n
se ttings on th e
G D U in te rface s
pag e
R eturn E xte rnal
LR U to G a rm in for
service .
Inspect exte rnal
LR U S D I strappin g
p in s to e nsu re
correct S D I
V e rify A D C /A H R S
interface settin gs
on G D U and copy
the con figu ration
to th e A D C /A H R S
E nsure the proper
E IS configu ration
pro ced ure is b eing
fo llo w ed in
G 500 /G 6 00 T X i
AM L STC
In sta llatio n
M an u al S e ction 5
In spe ct w iring an d
co nnectors for
d am aged o r
m issing
conn ections
R epla ce E xternal
LR U con fig
m odule
U pda te the G A D
43/43 e
co nfigura tion o n
the G D U “G A D 43
In te rface setting s
page ”
T he exte rnal LR U
is re porting that
se rvice is re quire d
V erify G D U
co nfig ura tion
m atches
installation w iring/
port configura tio n
V erify G D U
co nfig ura tion
se ttings
If fa u lt still e x is ts ,
co n ta ct G arm in .
Figure 4-24 External LRU Service Message Troubleshooting
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-38
G A D F a u lt M e s s a g e s
M a in te n a n c e
Log M essage
G A D re p o rts
p itc h
d e v ia tio n
G A D re p o rts
ro ll d e v ia tio n
G A D re p o rts
y a w ra te
d e v ia tio n
G A D re p o rts
AH R S A429
a tt tim e o u t
G A D re p o rts
AH R S A429
a tt in v a lid
G A D re p o rts
A H R S p itc h
o u t o f ra n g e
G A D re p o rts
AHRS
a ttitu d e
in v a lid
Cause
C ause
C ause
C ause
C ause
Cause
Cause
E rro r d e te cte d in o n e
o r m o re a n a lo g p itc h
o u tp u ts
OR
A C re fe re n ce is n o t
b e in g p ro vid e d
E rro r d e te c te d in o n e
o r m o re a n a lo g ro ll
o u tp u ts
OR
A C re fe re n c e is n o t
b e in g p ro vid e d
E rro r d e te cte d in
o n e o r m o re
a n a lo g y a w ra te
o u tp u ts
A R IN C 4 2 9
h e a d in g d a ta fro m
th e A H R S h a s
tim e d o u t
T h e A H R S h a s fla g g e d
th e h e a d in g o u tp u t a s
in va lid d u e to a n in te rn a l
A H R S m o n ito r fa u lt
G A D 4 3 /4 3 e h a s
re c e ive d a p itch v a lu e
g re a te r th a n ± 9 0 d e g
fro m th e A H R S
T h e A H R S h a s fla g g e d
th e h e a d in g o u tp u t a s
in va lid d u e to a n in te rn a l
A H R S m o n ito r fa u lt
C o rre c tiv e
A c tio n
C o rre c tiv e
A c tio n
C o rre c tiv e
A c tio n
C o rre c tiv e
A c tio n
C o rre c tiv e
A c tio n
C o rre c tiv e
A c tio n
C o rre c tiv e
A c tio n
V e rify c o rre ct
w irin g fo r a n a lo g
p itc h o u tp u ts fro m
G A D 4 3 /4 3 e
V e rify co rre c t
w irin g fo r a n a lo g
ro ll o u tp u ts fro m
G A D 4 3 /4 3 e
V e rify c o rre ct
w irin g fo r a n a lo g
y a w ra te o u tp u ts
fro m G A D 4 3 /4 3 e
V e rify A H R S is
p o w e re d o n
If th e e rro r
p e rsists, re tu rn th e
A H R S to G a rm in
fo r s e rvic e
If th e e rro r
p e rs is ts , re tu rn th e
A H R S to G a rm in
fo r se rv ice
If th e e rro r
p e rsists , re tu rn th e
A H R S to G a rm in
fo r s e rvic e
V e rify A C
re fe re n ce v o lta g e
is o n a n d w irin g is
co rre c t
V e rify A C
re fe re n c e vo lta g e
is o n a n d w irin g is
c o rre ct
In s p e ct A R IN C
4 2 9 d a ta b u s
w irin g fro m A H R S
to G A D 4 3 /4 3 e
If fa u lt s till e x is ts ,
c o n ta c t G a rm in .
Figure 4-25 GAD Fault Message Troubleshooting
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-39
G A D F a u lt M e s s a g e s
C o n t.
M a in te n a n c e
Log M essage
G A D re p o rts
pow er
s u p p ly fa u lt
G A D re p o rts
AC
re fe re n c e
lo s t
G A D re p o rts
a p p lic a tio n
S C I in te g rity
fa u lt
G A D re p o rts
c o n fig u ra tio n
in te g rity fa u lt
G A D re p o rts
c a lib ra tio n
in te g rity fa u lt
G A D re p o rts
u n it fa u lt
C heck
R S -2 3 2
w irin g to
G A D 4 3 /4 3 e
C ause
Cause
C ause
C ause
C ause
Cause
C ause
O n e o r m o re
in te rn a l p o w e r
s u p p ly h a s
re p o rte d a fa u lt
A C re fe re n c e v o lta g e
is n o t b e in g p ro v id e d
to th e G A D 4 3 /4 3 e
T h e in te rn a l G A D 4 3 /
4 3 e c o n fig u ra tio n d a ta
does not pass C R C
check
G A D 4 3 /4 3 e in te rn a l
c a lib ra tio n h a s b e c o m e
c o rru p te d
A n in te rn a l
com ponent has
fa u lte d
C o m m u n ic a tio n w ith
G A D 4 3 /4 3 e h a s b e e n
lo s t
C o r re c tiv e
A c tio n
C o r re c tiv e
A c tio n
C o rr e c tiv e
A c tio n
C o rr e c tiv e
A c tio n
C o r re c tiv e
A c tio n
C o rr e c tiv e
A c tio n
C o rr e c tiv e
A c tio n
If th e e rro r
p e rs is ts , re tu rn th e
A H R S to G a rm in
fo r s e rv ic e
In s p e c t A C
re fe re n c e to G A D
4 3 /4 3 e w irin g a n d
e n s u re A C
re fe re n c e s o u rc e
is p o w e re d o n
R e lo a d G A D 4 3 /
4 3 e s o ftw a re
U p d a te G A D 4 3 /
4 3 e c o n fig u ra tio n
fro m th e in te rfa c e
s e ttin g s s c re e n
R e tu rn th e G A D
4 3 /4 3 e to G a rm in
fo r s e rv ic e
R e tu rn th e G A D
4 3 /4 3 e to G a rm in
fo r s e rv ic e
In s p e c t G A D 4 3 /
4 3 e to G D U
R S -2 3 2 w irin g a n d
G A D 4 3 /4 3 e
p o w e r w irin g .
In te rn a l s o ftw a re
h a s fa ile d a C R C
check
If th e e rro r
p e rs is ts , re tu rn th e
G A D 4 3 /4 3 e to
G a rm in fo r s e rv ic e
If th e e rro r
p e rs is ts , re tu rn th e
G A D 4 3 /4 3 e to
G a rm in fo r s e rv ic e
If th e e rro r
p e rs is ts , re tu rn th e
G A D 4 3 /4 3 e to
G a rm in fo r s e rv ic e
If fa u lt s till e x is ts ,
c o n ta c t G a rm in .
Figure 4-26 GAD Fault Message Troubleshooting Continued
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-40
EIS Gauges
Unstable
RPM
Loss of RPM
during mag.
check
RPM is
erratic during
engine start/
cranking
Fuel quantity
gauge
inaccurate
Fuel totalizer
inaccurate
Fuel flow
indication
unstable
Manifold
pressure
unstable
Manifold
pressure
inaccurate
Cause
Cause
Cause
Cause
Cause
Cause
Cause
Cause
Resistor failure
OR
Poor connection
OR
Interference
Resistor failure
OR
Poor connection
Starting vibrator is
installed. Normal
operation with
P-Lead RPM
input.
Pressure line
blocked
OR
Sensor out of cal.
OR
Sensor failure
Corrective
Action
Corrective
Action
Poor connection
OR
Air/contamination in the
sensor
OR
Incorrect sensor config.
OR
Interference
Pressure line drain
plugged/line blocked
OR
Sensor failure
Corrective
Action
Poor connection
OR
Fuel probe
malfunction
OR
Probe out of
calibration
Fuel flow requires
calibration
Corrective
Action
Corrective
Action
Disconnect P-Lead
signal wires at
both ends. Verify
wire is more than
400 KOhms.
Replace wire and
parallel resistors if
less than
400 KOhms
Verify wiring and
connections
Route signal wires
away from spark
plug leads and
power wires
Disconnect P-Lead
signal wire at both
ends of suspect mag.
Verify wire is more
than 400 KOhms.
Replace wire and
parallel resistors if less
than 400KOhms.
Verify wiring and
connections
None
Verify wiring and
connections
Calibrate fuel flow.
Limited to 15% in
GDU Normal
mode. More
adjustment will
require a different
K-Factor
Replace fuel probe
Recalibrate fuel
tank probes
Replace fuel flow
transducer
Corrective
Action
Verify wiring and
connections
Purge fuel lines of
air, verify sensor
orientation, clean
the sensor
Configure sensor with
‘Hi’ filtering option
Corrective
Action
Verify manifold
pressure line vent
(if installed) is
clear.
Verify fuel is not
trapped in the
manifold pressure
line
Corrective
Action
Verify manifold
pressure line is
clear
Recalibrate
manifold pressure
sensor (brass
sensor only)
Replace manifold
pressure sensor
Replace manifold
pressure sensor
Route wires away
from spark plug leads
and power wires,
install EMI shield
Replace fuel flow
transducer
If fault still exists,
contact Garmin.
Figure 4-27 EIS Gauge Troubleshooting
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 4-41
5 EQUIPMENT MAINTENANCE AND CHECKOUT PROCEDURES
5.1 GDU 700/1060..................................................................................................................................5-3
5.1.1 Removal .....................................................................................................................................5-5
5.1.2 Cooling Fan Replacement ..........................................................................................................5-5
5.1.3 Integrated ADC Module Replacement .......................................................................................5-7
5.1.4 Configuration Module Replacement ..........................................................................................5-8
5.1.5 Master Configuration Module Replacement ..............................................................................5-9
5.1.6 Re-installation ..........................................................................................................................5-10
5.2 GCU 485 .........................................................................................................................................5-11
5.2.1 Removal ...................................................................................................................................5-11
5.2.2 Re-installation ..........................................................................................................................5-12
5.3 EIS Annunciator .............................................................................................................................5-13
5.3.1 Removal ...................................................................................................................................5-13
5.3.2 Re-installation ..........................................................................................................................5-13
5.4 GDC 72 ..........................................................................................................................................5-14
5.4.1 Removal ...................................................................................................................................5-15
5.4.2 Re-installation ..........................................................................................................................5-15
5.4.3 Checkout...................................................................................................................................5-15
5.5 GSU 75( ), GRS 79 .........................................................................................................................5-16
5.5.1 Removal ...................................................................................................................................5-17
5.5.2 Re-installation ..........................................................................................................................5-17
5.5.3 Checkout...................................................................................................................................5-17
5.6 GAD 43/43e....................................................................................................................................5-18
5.6.1 Removal ...................................................................................................................................5-19
5.6.2 Re-installation ..........................................................................................................................5-19
5.6.3 Checkout...................................................................................................................................5-19
5.7 GEA 110 .........................................................................................................................................5-20
5.7.1 Removal ...................................................................................................................................5-22
5.7.2 Re-installation ..........................................................................................................................5-22
5.7.3 Checkout...................................................................................................................................5-22
5.8 GEA 71B Enhanced........................................................................................................................5-23
5.8.1 Removal ...................................................................................................................................5-25
5.8.2 Re-installation ..........................................................................................................................5-25
5.8.3 Checkout...................................................................................................................................5-25
5.9 GBB 54 ...........................................................................................................................................5-26
5.9.1 Removal ...................................................................................................................................5-27
5.9.2 Battery Cell Replacement.........................................................................................................5-27
5.9.3 Re-installation ..........................................................................................................................5-28
5.9.4 Checkout...................................................................................................................................5-28
5.10 GMU 44 ..........................................................................................................................................5-29
5.10.1 Removal ...................................................................................................................................5-29
5.10.2 Re-installation ..........................................................................................................................5-29
5.10.3 Checkout...................................................................................................................................5-29
5.11 GTP 59............................................................................................................................................5-31
5.11.1 Removal ...................................................................................................................................5-32
5.11.2 Re-installation ..........................................................................................................................5-32
5.11.3 Checkout...................................................................................................................................5-32
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-1
5.12 Backup GPS Antenna .....................................................................................................................5-33
5.12.1 Removal ...................................................................................................................................5-34
5.12.2 Re-installation ..........................................................................................................................5-34
5.12.3 Checkout...................................................................................................................................5-34
5.13 EIS Sensors .....................................................................................................................................5-35
5.13.1 Carburetor/Induction Air Temperature ....................................................................................5-36
5.13.2 Oil Temperature Sensor ...........................................................................................................5-37
5.13.3 Pressure Sensors .......................................................................................................................5-38
5.13.4 Fuel Flow..................................................................................................................................5-41
5.13.5 RPM .........................................................................................................................................5-42
5.14 Calibration ......................................................................................................................................5-43
5.14.1 Attitude/Heading ......................................................................................................................5-43
5.14.2 Autopilot Calibration................................................................................................................5-43
5.14.3 Analog NAV Calibration .........................................................................................................5-43
5.14.4 Fuel Level Calibration..............................................................................................................5-43
5.14.5 Backup Battery Check..............................................................................................................5-44
5.14.6 External Systems (Weather Radar) Calibration .......................................................................5-44
5.15 Uploading Software ........................................................................................................................5-45
5.16 System Checks................................................................................................................................5-46
5.16.1 Configuration Ground Check ...................................................................................................5-46
5.16.2 Pitot-Static and Airspeed Tape Settings Checks ......................................................................5-47
5.16.3 RVSM System Checkouts (Socata TBM 700/850 only)..........................................................5-52
This section provides the procedures to remove, replace, or install required and optional LRUs that are part
of the G500/G600 TXi system. Refer to Section 4 for the definition of connectors and pin functions for
G500/G600 TXi system LRUs. Before performing any maintenance on the G500/G600 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 700/1060 without an integrated ADAHRS may be removed, replaced with a new
GDU, or have the old GDU re-installed without an Installer Unlock Card as long as the
configuration module is not replaced.
NOTE
Any AHRS unit (including a GDU with an integral ADAHRS) may be removed or replaced
without using an Installer Unlock Card as long as the unit mounting brackets or support
structure (e.g., instrument panel, mounting bracket, avionics shelf) is not loosened or
removed. If the mounting is loosened, additional calibrations and configurations that
require the use of an Installer Unlock Card will be necessary.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-2
5.1 GDU 700/1060
3
4
1
4
2
8
06
1876(/)/2&.,1*3/$7(21(/8*5('8&('5,9(763$&,1*/2:+(,*+767((/81-&%
06$'
5,9(762/,'&2817(5681.'(*35(&,6,21+($',12',1/21*
06%
6&5(:&$362&.(7+($'+(;$*21&25526,215(6,67$1767((/81&$,1/21*
QTY ITEM PART NUMBER
DESCRIPTION
NOTES
5,9(76$5(,167$//('3(50,/5 1$60 5,9(7%8&.7<3(35(3$5$7,21)25$1',167$//$7,21253(5
0,/67'35(3$5$7,21)25$1',167$//$7,212)5,9(76$1'6&5(:652&.(7 0,66,/($1'$,5)5$0(6758&785(6
72548(81&$6&5(:6 /%),1
Figure 5-1 GDU 1060 Installation
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-3
3
4
2
8
1
4
06/
1876(/)/2&.,1*3/$7(7:2/8*5('8&('5,9(763$&,1*/2:+(,*+767((/81-&%
06$'
5,9(762/,'&2817(5681.'(*35(&,6,21+($',12',1/21*
06%
6&5(:&$362&.(7+($'+(;$*21&25526,215(6,67$1767((/81&$,1/21*
QTY
ITEM PART NUMBER DESCRIPTION
NOTES
5,9(76$5(,167$//('3(50,/5 1$60 5,9(7%8&.7<3(35(3$5$7,21)25$1'
,167$//$7,21253(50,/67'35(3$5$7,21)25$1',167$//$7,212)5,9(76$1'6&5(:652&.(7 0,66,/($1'$,5)5$0(6758&785(6
72548(81&$6&5(:6 /%),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.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-4
5.1.1 Removal
Remove the GDU 700/1060 using the following procedure:
1. Ensure the current configuration is saved to an SD card in accordance with the instructions
contained in Section 2.1.6.
2. Turn off the GDU and remove power to the GDU.
3. Remove the four screws retaining the GDU in the instrument panel, shown as item 1 in
Figure 5-1 or Figure 5-2 above.
4. Gently pull the GDU out from the instrument panel far enough to access the cable connectors and
ADC module (if installed).
5. Remove the cable connectors from the back of the GDU.
6. If an integrated ADAHRS is installed in the GDU, loosen the four thumbscrews securing the ADC
module to the rear of the GDU, as shown in Figure 5-3, and gently separate the module from the
GDU. If the ADC module is being replaced, proceed to Section 5.1.3.
5.1.2
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 700/1060 cooling fan has a recommended replacement interval of 3,000 hours. After
3,000 hours of operation, the cooling fan should be replaced using the following procedure:
1. Remove the GDU from the instrument panel in accordance with Section 5.1.1.
2. Remove the four screws securing the fan module to the rear of the GDU and discard the
O-rings.
3. Grasp the fan module and gently pull the module out of the GDU.
4. 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
5. Place the new O-rings included in the fan replacement kit on the four fan mounting screws.
6. 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.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-5
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 in-lbf.
9. Install the GDU in accordance with Section 5.1.6.
10. Once the GDU installation and checkout has been accomplished, reset the GDU cooling fan hour
counter using the following procedure:
a. Power on the GDU 700/1060 in Configuration mode per the instructions in Section 2.1.4.
b. Navigate to Diagnostics → Temp & Power Stats.
c. Press Reset Fan Hours.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-6
5.1.3 Integrated ADC Module Replacement
To replace the integrated ADC module, perform the following procedure:
1. Remove the GDU 700/1060 in accordance with Section 5.1.1.
2. Mark pitot and static lines with “P” and “S” (if not already marked) near ADC connections.
REF. FITTING, 1/8-27 ANPT
TYP. 2 PLCS
REF. 011-03457-00 ADC MODULE, GDU 700/1060 DISPLAY
REF. THUMB SCREW
Figure 5-3 Integrated ADC Module Installation
3. Remove pitot and static line from 1/8-27 fittings, shown in Figure 5-3 above.
4. Install pitot and static lines in the new ADC module 1/8-27 fittings.
5. Install the GDU 700/1060 in accordance with Section 5.1.6.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-7
5.1.4 Configuration Module Replacement
To replace a GDU 700/1060 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 2.1.6.
NOTE
All item numbers in this procedure reference Figure 5-4.
1.
2.
3.
4.
5.
6.
7.
8.
Remove the GDU in accordance with Section 5.1.1.
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 the harness to the new configuration module.
Install the new configuration module in the connector backshell (6) and re-install the cover (7).
Re-install the GDU 700/1060 in accordance with Section 5.1.6.
Figure 5-4 Configuration Module Installation
NOTE
The GDU will automatically copy the system configuration to the new configuration
module upon the first power-up.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-8
5.1.5
Master Configuration Module Replacement
NOTE
Replacement of the G500/G600 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:
NOTE
Ensure the current configuration is saved to an SD card in accordance with the
instructions contained in Section 2.1.6.
1. If multiple GDU 700/1060 displays are installed in the system, choose one GDU to act as the new
master GDU.
2. Power on all LRUs in the G500/G600 TXi system with all GDUs in Configuration mode.
3. From the Home screen on each GDU, navigate to GDU Type.
4. Configure all GDU IDs, locations, and unit configurations to match the recorded configuration
settings in the configuration log printout.
5. Ensure that Master is selected on the GDU that has been chosen to act as the master configuration
module.
6. At this point, the G500/G600 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
at flyGarmin.com and then new databases can be downloaded.
7. Insert the feature unlock card in the bottom or right slot of any GDU in the system.
8. Navigate to Home → System Management → Feature Enablement and enable system features.
9. Insert the SD card with the saved aircraft configuration file in the top or left slot of any GDU in the
system.
10. Navigate to Home → SD Load.
11. Select the aircraft configuration file you wish to load.
12. Select the GDU to configure and the desired configuration settings to load.
13. Select SD Load.
14. Follow on-screen commands.
15. Perform the Configuration Ground check in Section 5.16.1.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-9
5.1.6 Re-installation
To replace the GDU 700/1060, perform the following procedure:
1. If equipped with an integrated ADAHRS, align the ADC module with the back of the GDU as
shown in Figure 5-3 and gently press the module into place.
2. Tighten the four thumb screws that secure the ADC module to the back of the GDU to
10 ± 1 in-lbf.
3. Connect the four wiring connectors and any installed antenna wires to the back of the GDU and
tighten the retaining screws.
4. Place the GDU in the instrument panel cutout.
5. Install the four screws (1), as shown in Figure 5-1 and Figure 5-2, and tighten to 8 ± 1 in-lbf.
6. Perform the Configuration mode Ground Check in Section 5.16.1.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-10
5.2 GCU 485
DOWN
LATCH DETAIL
UP
LOCKED
Figure 5-5 GCU 485 Installation
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 counterclockwise until the pawl latches are able to rotate to a horizontal position.
4. Remove the unit from the panel.
5. Disconnect the electrical connector from the back of the unit.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-11
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
indicated in Figure 5-6 must be free of any surface coatings.
1.73in 44mm
R0.06in 1.6mm MAX.
TYP. 4 PLCS
1.780in 45.2mm
0.15in 3.8mm TYP. 2 PLCS
0.50in 12.7mm TYP. 2 PLCS
SURFACE FOR ELECTRICAL BOND
PANEL BACK SIDE TYP. 2 PLCS
0.64in 16.3mm
4.970in 126.2mm
Figure 5-6 Panel Cutout for GCU 485
To re-install the GCU 485, perform the following procedure:
1. Connect the electrical connector to the back of the GCU 485.
2. Place the unit in the panel cutout, ensuring that the pawl latches are fully retracted and in the
horizontal position.
3. Tighten the pawl latches with a 3/32” hex drive tool inserted through holes in GCU 485 face plate.
4. Torque the latches to 20 ± 2 in-lbf.
5. Restore power to the unit.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-12
5.3 EIS Annunciator
5.3.1 Removal
The EIS caution and warning annunciator can be removed using the following procedure:
1. Using an Aerospace Optics cap extraction tool (P/N 17-150), locate the two extraction slots
positioned on either side of the pushbutton cap.
2. Insert the tool into the extraction slots and pull the cap out from the module.
NOTE
The cap will rotate 90° on two hinged slide retainer pins to allow access to the module
mounting screws.
3. Loosen the two small flat head module mounting screws located behind the pushbutton cap until
the module can be removed from the housing.
4. Insert an Aerospace Optics connector extraction tool (P/N 18-234) into the slots at the top and
bottom of the electrical connector.
5. Push to release the snap tabs in the switch housing and gently pull the connector out of the module.
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5.3.2 Re-installation
Re-installation of the annunciator is accomplished using the following procedure:
1. Orient the keyed electrical connector to the module and press together until locked.
2. Orient the annunciator for proper viewing and gently slide the module into the housing until
seated.
3. Tighten the mounting screws until the module is fully seated in the housing.
4. Rotate the cap back into position on the module and gently press until secured.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-13
5.4 GDC 72
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190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-14
5.4.1 Removal
Removal of the GDC 72 Air Data Computer can be accomplished using the following procedure:
1. Remove power to the GDC 72.
2. Disconnect the electrical connector.
3. Disconnect the pitot-static lines.
4. Loosen the single mounting screw in the endplate mount bracket.
5. Lift the side of the GDC 72 where the endplate mount bracket is attached and slide the unit
towards the bracket to disengage mounting pawls and remove the unit.
5.4.2
1.
2.
3.
4.
Re-installation
Place the unit flat on the mounting bracket and slide it back to engage the mounting pawls.
Engage the mounting screw and torque the screw to 15-20 in-lbf.
Connect the pitot-static lines.
Connect the electrical connector.
5.4.3 Checkout
Perform a static and pitot system leak test in accordance with the aircraft manufacturer’s 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 GDC 72
are not susceptible to these types of errors.
Perform checkout procedures in Section 5.16.2.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-15
5.5 GSU 75( ), GRS 79
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NOTE
The GRS 79 has the same case and mounting hardware as the GSU 75( ) 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 plate and/or the shelf to which the mounting plate is
attached requires re-calibration of the AHRS, which requires an Installer Unlock Card.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-16
5.5.1 Removal
Removal of the GSU 75( ) or GRS 79 can be accomplished using the following procedure:
1. Remove power to the unit.
2. Disconnect the electrical connector.
3. Disconnect the pitot-static lines (GSU75( ) only).
4. Loosen the two mounting screws on the connector end of the unit.
5. Lift the connector side of the unit and slide the unit towards the connector to remove.
5.5.2
1.
2.
3.
4.
5.
6.
7.
Re-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-lbf.
Connect the pitot-static lines (GSU 75( ) only).
Connect the electrical connector.
Restore unit power.
5.5.3 Checkout
If the mounting bracket bolts have been loosened or bracket mounting (e.g., instrument panel, avionics
shelf) has been moved in any way, the following AHRS calibration procedures must be performed as
described in Section 6 of G500/G600 TXi Part 23 AML STC Installation Manual (P/N 190-01717-B3):
1. Pitch/Roll Offset Compensation.
2. Magnetometer Calibration.
3. Compass Swing.
4. Heading Offset Compensation (if required by the previous step).
5. Engine Run-up Vibration Check.
For the GSU 75( ) only:
Perform a static and pitot system leak test in accordance with the aircraft manufacturer’s 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 75( )
are not susceptible to these types of errors.
Perform checkout procedures in Section 5.16.2.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-17
5.6 GAD 43/43e
NOTE
The GAD 43/43e may be removed and re-installed without a GDU Installer Unlock Card.
If the unit is replaced with a new GAD 43/43e, or if the software is updated, a GDU
Installer Unlock Card is necessary to configure the new unit.
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Figure 5-10 GAD 43 Installation (Sheet Metal Shelf Example)
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-18
5.6.1 Removal
The GAD 43/43e can be removed using the following procedure:
1. Remove power from the GAD 43/43e.
2. Disconnect the electrical connector(s) from the GAD 43/43e.
3. Unscrew the four mounting screws.
5.6.2 Re-installation
Re-installation of the GAD 43/43e is accomplished by performing the removal process in reverse. Torque
the mounting screws to the specifications provided in Figure 5-10.
5.6.3 Checkout
If the GAD 43/43e has been replaced, perform the following procedure:
1. Insert the Installer Unlock Card into the GDU connected to the GAD.
2. Power the G500/G600 TXi system up on Configuration mode.
3. Navigate to Interfaces → Adapter → Settings.
4. Configure interface settings per the printed configuration log.
5. Perform checkout procedures in Section 6.2 and Section 6.7 of G500/G600 TXi Part 23 AML STC
Installation Manual (P/N 190-01717-B3).
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-19
5.7 GEA 110
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190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-20
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Figure 5-12 GEA 110 Installation (Mounted on a Tray Example)
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-21
5.7.1 Removal
To remove the GEA 110, perform the following procedure:
1. Remove power to the GEA 110.
2. Disconnect the two electrical connectors.
3. If the unit is mounted on a tray, as shown in Figure 5-12, pull out on the mounting knob and turn
counterclockwise to loosen it enough to rotate the arm down and away from the unit.
4. If the unit is mounted to the airframe or back of the GDU using screws, as shown in Figure 5-11,
loosen the four screws securing the unit to the airframe or GDU.
5.7.2 Re-installation
To re-install the GEA 110, perform the removal procedures in reverse. If the unit is mounted to the
airframe or back of the GDU, torque the screws to the specification in Figure 5-11. For units that are
mounted in a mounting tray, tighten the mounting screw by hand until the unit is secure.
If the GEA 110 was replaced, the sensor configurations must be loaded to the new unit using the following
procedure:
1. Insert saved configuration SD card in the top or left SD card slot of any GDU 700/1060 directly
connected to the GEA 110.
2. Power on the GDU that is physically wired to the GEA 110 in Configuration mode.
3. Press SD Load.
4. Select the appropriate Aircraft Configuration File.
5. Select the current GDU as the From SD and To GDU.
6. Select the EIS Sensor Configuration check box.
7. Select SD Load.
5.7.3 Checkout
Perform the following checkout procedures:
1. Configuration Mode Ground Checks as described in Section 5.16.1. If the GEA 110 does not pass
the checks in this step, load the sensor configurations using the procedure in Section 5.7.2 and
perform the checkout procedure again.
Perform the following checkout procedure only if the GEA was replaced or did not initially pass the
checkout procedure above:
1. EIS Ground Checks as described in Section 6.5 of G500/G600 TXi Part 23 AML STC Installation
Manual (P/N 190-01717-B3).
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-22
5.8 GEA 71B Enhanced
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190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-23
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Figure 5-14 GEA 71B Enhanced (Sandwich Panel Example)
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-24
5.8.1 Removal
The GEA 71B Enhanced can be removed using the following procedure:
1. Remove power from the GEA 71B Enhanced.
2. Disconnect the electrical connectors from the GEA 71B Enhanced.
3. On the GEA 71B unit, unlatch the handle. Rotate the handle to unlock the GEA 71B Enhanced unit
from the mounting bracket.
4. Slide the GEA 71B Enhanced unit from the mounting bracket.
5.8.2 Re-installation
Re-installation of the GEA 71B Enhanced is accomplished by performing the removal process in reverse.
If the GEA 71B Enhanced was replaced, the sensor configurations must be loaded to the new unit using the
following procedure:
1. Insert saved configuration SD card in the top or left SD card slot of any GDU 700/1060 directly
connected to the GEA 71B Enhanced.
2. Power on the GDU that is physically wired to the GEA 71B Enhanced in Configuration mode.
3. Press SD Load.
4. Select the appropriate Aircraft Configuration File.
5. Select the current GDU as the From SD and To GDU.
6. Select the EIS Sensor Configuration check box.
7. Select SD Load.
5.8.3 Checkout
Perform the following checkout procedures:
1. Configuration Mode Ground Checks as described in Section 5.16.1. If the GEA 71B Enhanced
does not pass the checks in this step, load the sensor configurations using the procedure in
Section 5.8.2 and perform the checkout procedure again.
Perform the following checkout procedure only if the GEA was replaced or did not initially pass the
checkout procedure above:
• EIS Ground Checks as described in Section 6.5 of G500/G600 TXi Part 23 AML STC Installation
Manual (P/N 190-01717-B3).
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-25
5.9 GBB 54
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Figure 5-15 GBB 54 Installation (Sheet Metal Shelf Example)
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-26
5.9.1
Removal
NOTE
All item numbers in this section refer to Figure 5-15.
To remove the GBB 54, utilize the following procedure:
1. Ensure the GDU connected to the GBB 54 is powered off.
2. Disconnect the electrical connector.
3. Loosen the tube nut (3) and disconnect the vent tube (2) from the battery (1).
4. Remove the four screws (7) holding the GBB 54.
5.9.2
Battery Cell Replacement
NOTE
The GBB 54 Battery Cell Replacement Kit (P/N 010-01331-02) must be obtained from an
authorized Garmin dealer.
If access is available to remove four bolts (1) on connector side, unit removal is not required. Refer to
Figure 5-16.
Removal Steps
1. Remove the four bolts (1) and four nuts (7).
2. Pull battery cover (2) from the housing (5).
3. Discard the gasket (3).
4. Remove the four bolts (8) that secure the battery to the battery cover.
5. Pull the battery pack (4) from the cover receptacle (2).
Replacement Steps
1. Apply Dow Corning 4 dielectric grease, or equivalent, to the pins in the battery pack connector (6).
2. Push the battery pack connector (6) into the cover receptacle (2).
3. Apply Loctite 242 (blue) thread-locking compound, or equivalent, to the bolts (8).
4. Secure the battery (4) to the cover (2) with bolts (8).
5. In a cross-tightening sequence, torque bolts (8) to 20-25 in-lbf.
6. Place the gasket (3) over the battery pack (4) until flush with the battery cover (2).
7. Insert the battery cover (2) with the gasket (3) and the battery pack (4) into the housing (5).
8. Insert the four bolts (1) and nuts (7).
9. In cross-tightening sequence, torque bolts (1) to 40 to 60 in-lbf.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-27
1
3
4
2
5
1
3
4
2
7 x4
CROSS-TIGHTENING SEQUENCE CROSS-TIGHTENING SEQUENCE
FOR BOLTS (STEP 5)
FOR BOLTS (STEP 9)
4
3
8 x4
2
6
1 x4
FRONT OF
BATTERY
BATTERY CELL INSERTION
(STEP 7)
Figure 5-16 GBB 54 Battery Cell Replacement
5.9.3 Re-installation
To re-install the GBB 54, perform the following procedure:
1. Install four screws (7) securing the GBB 54 and torque to the specification in Figure 5-15.
2. Connect the vent tube to the GBB 54 and tighten the tube nut.
3. Connect the electrical connector.
4. Perform the checkout in Section 5.9.4.
5.9.4 Checkout
1. Perform a Configuration Mode Ground Check as described in Section 5.16.1.
2. Perform the Backup Battery Check as described in Section 5.14.5.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-28
5.10 GMU 44
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. Additionally, any removal
or addition of electrical components or ferrous materials within 10 feet of the GMU 44
will require recalibration of the AHRS.
5.10.1 Removal
To remove the GMU 44, perform the following procedure:
1. Remove power to the AHRS unit.
2. Disconnect the GMU 44 connector.
3. Remove the three screws (9) shown in Figure 5-17.
4. Remove the GMU 44 from the mounting bracket.
5.10.2 Re-installation
NOTE
If reusing 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
P/N 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. Place the GMU 44 in the mounting bracket.
2. Install the three screws (9) and torque to the specifications shown in Figure 5-17.
3. Connect the GMU 44 electrical connector.
4. Restore power to the AHRS unit.
5. Perform the checkout procedure in Section 5.10.3.
5.10.3 Checkout
Perform the following calibration procedures and checks found in Section 6 of G500/G600 TXi Part 23
AML STC Installation Manual (P/N 190-01717-B3) to return the aircraft to service:
1. Magnetometer Calibration.
2. Compass Swing.
3. Heading Offset Compensation (if required by the previous step).
4. Engine Run-up Vibration Check.
5. Configuration Mode Ground Checks.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-29
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Figure 5-17 GMU 44 Installation (Universal Mount Example)
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-30
5.11 GTP 59
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Figure 5-18 GTP 59 Installation (Aircraft with Metallic Skin Example)
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-31
5.11.1 Removal
To remove the GTP 59, perform the following procedure:
1. Remove power to the ADC unit.
2. Remove the mounting nut (1) shown in Figure 5-18.
3. Remove the GTP 59 from the hole.
5.11.2 Re-installation
1. Place the GTP 59 in the previous installation hole.
2. Install washer (2) and nut (1) and torque to specifications in Figure 5-18.
5.11.3 Checkout
Perform the checkout procedure in Section 6.3.2 of G500/G600 TXi Part 23 AML STC Installation Manual
(P/N 190-01717-B3).
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-32
5.12 Backup GPS Antenna
The backup GPS antenna is designed for installation on top of an existing instrument panel glareshield.
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
glareshield.
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190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-33
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Figure 5-20 Backup GPS Antenna Installation (Removable Installation Example)
5.12.1 Removal
Use the following procedure to remove the backup GPS antenna:
1. Power off the GDU 700/1060 connected to the backup battery antenna.
2. Remove the two screws (6) securing the antenna (if installed per Figure 5-19 only).
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).
5.12.2 Re-installation
Install the backup GPS antenna in the reverse order of the removal procedure.
5.12.3 Checkout
Perform the backup GPS checkout procedure as described in Section 6.3.6 of G500/G600 TXi Part 23
AML STC Installation Manual (P/N 190-01717-B3).
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-34
5.13
EIS Sensors
In addition to the data in this manual, replacement or re-installation of each probe/sensor and wire must be
accomplished in accordance with the sensor manufacturer instructions or as recommended by the engine
manufacturer. Wire routing and clamping must follow procedures defined in the aircraft maintenance
manual, standard practices manual, or practices defined in Chapter 11, Electrical Systems, of advisory
circular AC 43.13-1B, Aircraft Inspection and Repair.
Sensors must be connected using hoses and fittings approved as part of aircraft or engine type certificated
design or standard aircraft parts (AN/MS).
After removing or replacing any EIS sensor, perform the EIS ground checkout procedure for the specific
sensor that was affected in Section 6.5 of G500/G600 TXi Part 23 AML STC Installation Manual
(P/N 190-01717-B3).
CAUTION
Check hose routing for sharp bends. Check sensors and fittings for leaks during engine
run-up and correct prior to flight.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-35
5.13.1 Carburetor/Induction Air Temperature
The sensor location will vary for different carburetors. Refer to the engine or carburetor manufacturer data
for temperature sensor location, if required.
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CAUTION
Fuel and air passages must remain free of contaminants during work near and around the
carburetor.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-36
5.13.2 Oil Temperature Sensor
When installing the oil temperature sensor, the unbroken side of the crush washer must face the sensor
flange. The sensor is torqued finger tight plus one-half turn and safety wired in accordance with practices
defined in Section 7, Safetying, of Chapter 7, Aircraft Hardware, Control Cables and Turnbuckles, of
advisory circular AC 43.13-1B, Aircraft Inspection and Repair.
Figure 5-22 Oil Temperature Sensor Installation Example
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-37
5.13.3 Pressure Sensors
Manifold pressure, oil pressure, and fuel pressure sensor installations are similar. Garmin pressure sensors
with a brass housing are limited to aircraft with operational ceilings up to 25,000 feet. Garmin pressure
sensors with a stainless steel housing may be used on all aircraft on the AML.
When replacing existing sensors:
• Do not remove engine and fuel fittings with an intentionally reduced orifice. It may limit fluid loss
and fire damage in the event of a hose failure
• Inspect the condition of all existing tubes, hoses, and fittings that are being reused; replace if
necessary
When installing pressure sensors:
1. Fuel and oil hoses in the engine compartment must meet TSO-C53a Type C or D (fire resistant).
2. Do not install sensors directly below fittings or components that may leak flammable fluid.
3. Thread sealant or tape must be used for the NPT threads. To reduce the risk of system
contamination, a minimal amount of sealant should be applied leaving at least two threads at the
end of the fitting clear of sealant/tape.
4. Sensors must be routed as far away from the aircraft exhaust system as practical and no closer than
6 inches.
Table 5-1 Pressure Sensor Equipment List
Function
Manufacturer P/N, Description
Kavlico P4055-5020-4, Press (Brass)
Oil Press
Kulite APT-20GX-1000-150G,
Press (Stainless)
Kavlico P4055-5020-1, Press (Brass)
Manifold Press
Kulite APT-20GX-1000-25PSIA,
Press (Stainless)
Kavlico P4055-5020-3, Press (Brass)
Fuel Press
190-01717-B1
Rev. 3
Kavlico P4055-5020-2, Press (Brass)
Garmin P/N
Authorization
011-04202-30
(494-30027-30)
TXi STC
494-30032-00
011-04202-00
(494-30027-00)
TXi STC
494-30030-00
011-04202-20
(494-30027-20)
011-04202-10
(494-30027-10)
APT-20GX-1000-50PSIG, Press (Stainless)
494-30031-00
APT-20GX-1000-15PSIG, Press (Stainless)
494-30029-00
TXi STC
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-38
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190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-39
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Figure 5-24 Stainless Steel Sensor Installation (Housing Mount Example)
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-40
5.13.4 Fuel Flow
The fuel flow transducer can be mounted using the bracket or clamping hoses connected to the transducer.
If mounting with clamps, the placement must be no further than 6 inches from the clamp to the nearest face
of the transducer.
• The transducer can be oriented with the wires pointing up, or the cap with five bolts pointing up, or
the output port pointing up, or any combination thereof
• The hose connected to the IN port must be straight for a minimum 4 inches
• The hose connected to the OUT port should be level or slope up. It must not slope down more than
4 inches per foot
Hoses and fittings connected to fuel flow transducer must meet the following:
1. New hoses must have the same internal diameter as the hose being replaced and meet TSO-C53a
Type C or D (fire resistant) specifications.
2. Fuel compatible thread sealant or tape must be used for the NPT threads. To reduce the risk of fuel
system contamination, a minimal amount of sealant should be applied leaving at least two threads
at the end of the fitting clear of sealant/tape.
3. Fitting torque must not exceed 12 ft-lbf or two full turns past finger tight, whichever occurs first.
4. The transducer and fuel hoses must be routed as far away from the aircraft exhaust system as
practical. The transducer must be protected with Aeroquip AE102-( ) fire-sleeve if within
6 inches of any exhaust component.
WARNING
Ensure the fuel flow transducer installation does not introduce thread sealant or debris into
the fuel system.
CAUTION
Do not blow pressurized air through the flow transducer.
If the fuel flow transducer bracket must be replaced, the replacement bracket must be fabricated from
300 series austenitic stainless steel (annealed per AMS 5901 or ½ hard per AMS 5517), sheet thickness
19 gauge minimum (0.044 inches) and installed as provisioned by the aircraft structural repair manual or
standard practices manual. Methods, techniques, and practices defined in Chapter 4, Metal Structure,
Welding and Brazing, of advisory circular AC 43.13-1B, Aircraft Inspection and Repair, are acceptable.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-41
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5.13.5 RPM
The TXi system can use the electrical signal generated by the primary magneto coils or “P-Lead” to
display RPM. When used, the left and right magneto P-Lead signals must both be connected to the
GEA 110. The connection can be made at the magneto or the ignition switch.
To replace the P-Lead wire, remove the old section of wire and replace the entire wire and parallel resistors
in accordance with the P-Lead installation instructions contained in G500/G600 TXi Part 23 AML STC
Installation Manual (P/N 190-01717-B3).
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-42
5.14 Calibration
This section provides guidance for calibrating the G500/G600 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.
5.14.1 Attitude/Heading
Attitude and heading calibration requires the use of an Installer Unlock Card. If it becomes necessary to
re-calibrate any installed AHRS, refer to the calibration procedure contained in Section 5 and Section 6 of
G500/G600 TXi Part 23 AML STC Installation Manual (P/N 190-01717-B3).
5.14.2 Autopilot Calibration
Autopilot calibration requires the use of an Installer Unlock Card. If it becomes necessary to re-calibrate
the autopilot, refer to the calibration procedure contained in G500/G600 TXi Part 23 AML STC Installation
Manual (P/N 190-01717-B3).
5.14.3 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 G500/G600 TXi Part 23 AML
STC Installation Manual (P/N 190-01717-B3).
5.14.4 Fuel Level Calibration
Fuel level calibration requires the use of an Installer Unlock Card. If it becomes necessary to re-calibrate
the fuel level, refer to the calibration procedure contained in G500/G600 TXi Part 23 AML STC
Installation Manual (P/N 190-01717-B3).
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-43
5.14.5 Backup Battery Check
This procedure will analyze the voltage and discharge qualities of the installed backup battery. The
procedure is required to be completed on initial installation and every 12 calendar months when a backup
battery is installed in the system. A yellow “X” will be displayed over the battery level indicator and a fault
indication message will be displayed in Normal mode until this procedure is completed.
NOTE
The battery rundown test may take up to 60 minutes to complete.
NOTE
The battery rundown test date is reported in UTC.
To complete the backup battery test, complete the following steps:
1. Power the GDU 700P in Configuration mode and navigate to Calibration/Test → Backup Battery
Test.
2. Verify that the Backup Battery status icon is green.
3. Verify that the battery state is not “Discharging” annunciated under Battery State.
4. Complete the on-screen Before Test instructions. Once all checklist items have a green check
mark, the Start selection will become active.
5. Select Start and follow the on-screen commands.
6. The GDU 700P will power off automatically when the test is complete.
7. Power-up the unit in Configuration mode and verify a PASS was achieved.
5.14.6 External Systems (Weather Radar) Calibration
Weather radar calibration requires the use of an Installer Unlock Card. If it becomes necessary to
re-calibrate the weather radar, refer to the calibration procedure contained in G500/G600 TXi Part 23 AML
STC Installation Manual (P/N 190-01717-B3).
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-44
5.15
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 G500/G600 TXi Part 23 AML STC Equipment List (P/N 005-00795-D1). 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. Insert a Software Update SD card into the appropriate slot of the GDU 700/1060, as specified in
Section 2.1.5.
3. Power on the display in Configuration mode.
4. Navigate to System Management → Software Upload.
5. 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. Select the Update button.
7. Follow the on-screen display instructions.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-45
5.16
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 G500/G600 TXi Part 23 AML STC Installation
Manual (P/N190-01717-B3).
5.16.1 Configuration Ground Check
The configuration ground check procedures are intended to verify that each LRU and interface in the
G500/G600 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. All GDU 700/1060 displays in the system must be powered on in Configuration mode.
2. All system LRUs must be powered on.
3. All installed LRUs must be configured per the printed configuration log contained in Appendix A.
5.16.1.1 LRU Status check
The Home page in the Configuration mode of the GDU 700P/1060 shows 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 5-2. Verify that all LRUs connected or configured to each display have a
green indicator.
Table 5-2 LRU Status Indicators
Status Color
LRU Condition
Green
The LRU is online. No faults are detected.
Red
The LRU is online. A fault, warning, and/or error is detected.
Black
The LRU is not online.
5.16.1.2 System Summary
The Home page in Configuration mode of the GDU 700P/1060 contains a Summary button that provides
information for each configured LRU as part of the G500/G600 TXi system.
1. Open the system summary (Home → Summary).
2. Verify that all configuration settings listed are consistent with the printed configuration log.
3. Verify that if any LRU sections have a yellow warning triangle present the configuration is valid.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-46
5.16.1.3 Capturing and Saving Screen Shots
Screen shots can be captured and saved to an SD card on any GDU in Normal or Configuration mode.
1. Insert an SD card into either slot on the GDU 700/1060.
2. Navigate to the desired screen image.
3. Hold down the right knob and momentarily press the Power button.
4. A small camera icon will appear on the annunciator bar when in Normal mode, or the upper-left
corner when in Configuration mode, indicating an image has been captured.
5. Remove the SD card after all desired images have been captured.
6. Images will be saved to a \print file on the SD card.
5.16.2 Pitot-Static and Airspeed Tape Settings 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.
The GDU 700P/1060 airspeed tape display and settings must be verified using the procedures in
Section 5.16.2.1 or Section 5.16.2.2 depending on the airspeed tape configuration (Basic or Advanced,
respectively). The airspeeds referenced in the following steps must match those shown in the printed
configuration log.
5.16.2.1 Basic Airspeed Tape Setting
If the airspeed Configuration Type is set to Basic, verify correct operation of the ADC as follows:
Figure 5-26 Airspeed Configuration Type
1. Verify the TXi system is in Normal mode.
2. Verify all self-tests pass on the main start-up 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.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-47
3. Using a pitot-static test set, increase the airspeed until the PFD airspeed tape pointer is at the
bottom of the white band (Vs0).
4. Verify that the bottom of the white arc/band on the standby ASI and PFD airspeed tape are at the
same airspeed value.
5. For twin-engine aircraft with a minimum control speed: Increase the airspeed to the lower red
radial (Vmca). Verify that the red radial on the standby ASI and PFD airspeed tape are at the same
airspeed value.
6. Change the airspeed until the PFD airspeed tape pointer is at the bottom of the green band (Vs1).
7. Verify that the bottom of the green arc/band on the standby ASI and PFD airspeed tape are at the
same airspeed value.
8. For twin-engine aircraft only: Increase the airspeed to the blue radial (Vyse). Verify that the blue
radial on the standby ASI and PFD airspeed tape are at the same airspeed value.
9. Change the airspeed until the PFD airspeed tape pointer is at the top of the white band (Vfe).
10. Verify that the top of the white arc/band on the standby ASI and PFD airspeed tape are at the same
airspeed value.
11. Change the airspeed until the PFD airspeed tape pointer is at the top of the green band/bottom of
the yellow band (Vno).
12. Verify that the top of the green arc/band on the standby ASI and PFD airspeed tape are at the same
airspeed value.
13. Increase the airspeed to the upper red radial/top of yellow arc (Vne).
14. Verify that the red radial on the standby ASI and PFD airspeed tape are at the same airspeed value.
15. Starting at the current airspeed, decrease the airspeed to zero, stopping at each of the airspeeds
listed in Table 5-3 (airspeeds above Vne should not be checked), verifying that the PFD and
standby ASI airspeed values are within the tolerances indicated in Table 5-3.
Table 5-3 Airspeed Test Points
Test Set Airspeed (kt)
PFD Allowed Tolerance (kt)
Recommended Standby ASI
Tolerance (kt) [1]
50
±5.0
±5
80
±3.5
±4
100
±2.0
±3
120
±2.0
±3
150
±2.0
±3
180
±2.0
±5
210
±2.0
±5
250
±2.0
±5
290
±3.0
±6
Notes:
[1] If available, the aircraft or instrument manufacturer’s data should be referenced for
standby tolerances.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-48
5.16.2.2 Advanced Airspeed Tape Setting
If the Configuration Type is set to Advanced, verify correct operation of the ADC as follows:
1. Verify the TXi system is in Normal mode.
2. Verify all self-tests pass on the main start-up 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.
3. Using a pitot-static test set, increase the airspeed until the PFD airspeed tape pointer is at the
bottom of the white band (Vs0).
4. Verify that the bottom of the white arc/band on the standby ASI and PFD airspeed tape are at the
same airspeed value.
5. Increase the IAS throughout the range of the ASI – stop at the limits of all Arc Ranges, and at all
Marking values configured per the instructions in Table 5-4 and Table 5-5 and listed in the printed
configuration log.
6. Verify that the ranges and markings on the standby ASI and PFD are located at the same airspeed
values. The last value verified should be the beginning of the barber pole (Vne/Vmo/Mmo).
7. The following applies to Variable Vne/Vmo/Mmo aircraft only:
a. Decrease the IAS to 25 kt below the barber pole on the PFD. Increase the indicated altitude to
the maximum operating altitude or service ceiling. Verify that the barber pole on the PFD and
standby ASI are at the same airspeed (±5 kt). Decrease the airspeed as needed to ensure the
IAS does not exceed the barber pole during the simulated climb.
b. Decrease the indicated altitude (do not exceed vertical speed limitations) back to ambient
static pressure.
8. Starting at the current airspeed, decrease the airspeed to zero, stopping at all of the relevant
airspeeds listed in Table 5-3 (airspeeds above Vne should not be checked). Verify that the PFD
and standby ASI values are within the tolerances indicated.
Table 5-4 Advanced Airframe Specific Configuration Data – Arc Ranges
Arc Color
RED
(LOW SPEED)
Description
Low speed
awareness
POH/AFM
Section
2 - Limitations
Notes
If the aircraft has a defined WHITE or
GREEN arc, set the RED arc to ON. Set
the MAX value of the RED arc to the
lowest value of the WHITE or GREEN arc
(Vs0). A RED low-speed awareness arc
will appear below the lowest marked stall
speed.
If the aircraft does not have defined white
or green arc, set the red arc to OFF, and
enter the lowest stall speed in the STALL
SPEED setting at the bottom of the page.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-49
Arc Color
Description
POH/AFM
Section
Notes
Set the Min value to the bottom of the
POH/AFM defined range.
If WHITE and GREEN arcs overlap, set the
Max value to the beginning of the WHITE/
GREEN arc.
WHITE
HALF WHITE
WHITE/
GREEN
Full flap operational
range
Standard operational
range
Overlap between
standard operational
and flaps operational
ranges
2 - Limitations
If WHITE and GREEN arcs do not overlap,
set the Max value to the top of the POH/
AFM or aircraft specification defined range.
If a WHITE arc is not defined by the AFM/
POH or aircraft specifications, set both the
Min and Max values to the aircraft stall
speed in the landing configuration (Vs0).
This setting will not display a white arc, but
the system needs it to characterize aircraft
performance.
2 - Limitations
If the HALF WHITE arc range is not
defined by the AFM/POH or aircraft
specification, set to OFF.
This may sometimes be called a “narrow
WHITE arc.”
2 - Limitations
If a WHITE/GREEN arc is not defined by
the AFM/POH or aircraft specification, set
to OFF.
If WHITE and GREEN arcs overlap,
configure to the range they overlap within.
If the GREEN arc is not defined by the
AFM/POH or aircraft specification, set to
OFF.
GREEN
Standard operational
range
2 - Limitations
If WHITE and GREEN arcs overlap, set
Min value to the Max of WHITE/GREEN.
If the YELLOW arc is defined, set to the
Min of the YELLOW arc (Vno).
If the YELLOW arc is not defined, set Max
value to Vno/Vne.
YELLOW
Caution / smooth air
operational range
2 - Limitations
If the YELLOW arc is defined by the AFM/
POH or aircraft specification, set to ON
with Min value equal to Maximum
structural speed (Vno). Max value should
be configured to Vne, or the highest value
of Vne if variable.
If the YELLOW arc is not defined, set to
OFF.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-50
Arc Color
Vne/Vmo/Mmo
POH/AFM
Section
Description
Never exceed speed/
max operating speed/
max operating mach
number
Notes
If defined as a fixed value, set to Fixed,
and enter POH/AFM defined Vne/Vmo as
the Min value.
2 - Limitations
If variable with altitude, set to Variable, and
set overspeeds in accordance with
Appendix Section E.5 in G500/G600 TXi
Part 23 AML STC Installation Manual.
Table 5-5 Advanced Airframe Specific Configuration Data – Markings
Marking
Description
POH/AFM
Section
Note
WHITE TRIANGLE
A small white triangle –
meaning varies by airframe
2 - Limitations
If defined in POH/AFM, set to
given value. Else, set to OFF.
RED BAR
Typically marks the minimum
controllable airspeed for twinengine aircraft with only one
engine operational (Vmca)
3 - Emergency
Procedures
Lower red radial on ASI of
light twins.Set to OFF for
single-engine aircraft.
BLUE BAR
Typically marks the single
engine best rate-of-climb
speed for a twin-engine aircraft
3 - Emergency
Procedures
RED/WHITE BAR
Varies – sometimes used as a
fixed point Vne marking
2 - Limitations
If a fixed RED/WHITE bar,
(not a barber pole) is shown
in the POH/AFM, set to given
value. Else, set to OFF.
Vle
Maximum landing gear
extended speed
2 - Limitations
Set to OFF for fixed gear
aircraft.
Blue radial on ASI of light
twins.
Set to OFF for single-engine
aircraft.
5.16.2.3 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):
• The tests of 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
NOTE
For aircraft being configured for RVSM operations, refer to Section 5.16.3 for altimeter
check procedures.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-51
5.16.3 RVSM System Checkouts (Socata TBM 700/850 only)
Pitot-static system #1, pitot-static system #2, and calibration of the AM-250 must meet the criteria in the
following sections. The air data tests and surface checks are required within the previous 24 months.
5.16.3.1 Air Data Test
The air data systems must be tested and maintained in accordance with the Socata Maintenance Manual,
except as follows.
The following altimeter checks must be used in lieu of Socata Maintenance Manual 34-11-00,
Table 503, and Section 5.16.2.3, with the following exceptions:
• For paragraph (b)(1)(i) Scale Error, use of Table 5-6 instead of 14 CFR 43, Appendix E, Table I
• Do not perform paragraph (b)(1)(iv), Friction
• Do not perform paragraph (b)(1)(vi), Barometric Scale Error
The following Air Data and Altitude Alerter Tests are to be performed in conjunction with any other
regulated tests. The Air Data test must be performed on both pilot and co-pilot systems with a calibrated
pitot-static test set with a combined accuracy/repeatability specification of less than ±20 feet for the test
altitude range.
NOTE
The standby altimeter is connected to the co-pilot side static system and it is not SSEC
corrected.
1. Connect the pitot-static tester to the aircraft left and right pitot and static ports in accordance with
Socata Maintenance Manual Section 34-11-00.
2. Perform a pitot-static system leak check of each system as described in Socata Maintenance
Manual Section 34-11-00.
3. File the results with the aircraft maintenance records.
4. Verify that the altimeter baro-setting is 29.92 in Hg (1013.25 millibar) on both sides.
5. Verify the Altitude Alerter annunciation and alert tones at test level of 29,000 feet during the Air
Data Test.
a. To set the altitude alerter to the current altitude, navigate to the ALT menu and press the inner
PFD knob.
6. Simulate the altitudes and airspeeds for each condition shown in Table 5-6.
7. Record the altitude displayed on the GDU 700P/1060 and AM-250 for each condition on
Table 5-6.
8. Verify that the indicated altitudes are within allowable tolerances.
9. File the results with the aircraft maintenance records.
If either the pilot or co-pilot air data system does not meet the tolerances specified, maintenance checks
should be performed on the air data system or the pitot-static system.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-52
Table 5-6 Air Data Test Points
Test Point
Altitude
(ft)
Nominal
Altitude
(ft)
Airspeed
(kts)
0
0
150
44*
1000
40
1000
2000
120
2032
4000
120
4034
120
8038
300
8219
10000
150
10059*
11000
120
11042
13000
150
13065
14000
150
14067
16000
180
16100
18000
210
18145
120
20056
150
20082*
300
20324
120
29077
150
29113*
300
29447
0
8000
20000
29000
190-01717-B1
Rev. 3
Altitude Tolerance Range (ft)
Air Data 1
GSU 75B
Air Data 2
GDC 74B
AM 250
-20 to 20
-20 to 20
-20 to 20
24 to 64
24 to 64
24 to 64*
980 to 1020
980 to 1020
980 to 1020
2007 to 2057
2007 to 2057
2007 to 2057
4009 to 4059
4009 to 4059
4009 to 4059
8008 to 8068
8008 to 8068
8013 to 8063
8129 to 8249
8129 to 8249
8194 to 8244
10029 to 10089
10029 to 10089
10034 to 10084*
11007 to 11077
11007 to 11077
11012 to 11072
13025 to 13105
13025 to 13105
13035 to 13095
14027 to 14107
14027 to 14107
14037 to 14097
16055 to 16145
16055 to 16145
16070 to 16130
18100 to 18190
18100 to 18190
18115 to 18175
20009 to 20103
20009 to 20103
20026 to 20086
20035 to 20129
20035 to 20129
20052 to 20112*
20277 to 20371
20277 to 20371
20294 to 20354
29005 to 29149
29005 to 29149
29042 to 29112
29041 to 29185
29041 to 29185
29078 to 29148*
29375 to 29519
29375 to 29519
29412 to 29482
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-53
Table 5-6 Air Data Test Points
Test Point
Altitude
(ft)
33000
Airspeed
(kts)
Nominal
Altitude
(ft)
120
33090
150
33131*
300
33519
Altitude Tolerance Range (ft)
Air Data 1
GSU 75B
Air Data 2
GDC 74B
AM 250
33018 to 33162
33018 to 33162
33049 to 33131
33059 to 33203
33059 to 33203
33090 to 33172*
33447 to 33591
33447 to 33591
33478 to 33560
* Test points and tolerances correspond with Socata Maintenance Manual 34-11-00,
Table 503.
5.16.3.2 Surface Checks
The TBM700 series aircraft with RVSM privileges require external checks per Socata Maintenance
Manual 05-10-01, ATA 53 for Standard and Progressive inspection intervals. Refer to Socata Maintenance
Manual 53-00-00 for fuselage surface check procedures.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-54
5.16.3.3 RVSM In-Flight Altitude Hold Check
In addition to the autopilot performance checks specified in this manual, RVSM operation requires that the
autopilot system accurately maintain the acquired altitude during non-turbulent, non-gust cruise
conditions. The autopilot must be shown to meet the performance specification of the following in-flight
altitude hold test:
1. Verify the following conditions (normal RVSM cruise flight):
◦ Altitude FL290 to FL310
◦ Altimeter setting 29.92 in Hg (1013 HPA)
◦ Autopilot altitude hold engaged
◦ Non-turbulent, non-gust conditions
2. Record the data specified in Table 5-7 from the primary cockpit displays every 5 minutes for a
minimum flight segment of 30 minutes in length. The maximum altitude deviation shown on the
display throughout the test should not exceed ±65 feet.
If the aircraft fails to hold altitude to this tolerance, repeat the check ensuring that the airspeed remains
constant and the air remains stable during the entire test. If the test still fails, perform maintenance checks
on the G600 TXi system, then repeat the test. RVSM operations are prohibited until the autopilot is capable
of maintaining altitude within ±65 feet of the selected cruise altitude.
Table 5-7 Altitude Hold Check Log
Aircraft S/N:
Date:
Time (hr:min)
Pilot
Altitude (ft)
Airspeed (kt)
Pilot:
En route to:
Co-pilot
Altitude (ft)
Airspeed (kt)
0:00
0:05
0:10
0:15
0:20
0:25
0:30
0:35
0:40
0:45
0:50
0:55
1:00
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page 5-55
APPENDIX A: INSTALLATION-SPECIFIC INFORMATION
A.1 General Information
Date:_______ /_________ /__________
By:_____________________________________________
AIRCRAFT
AIRCRAFT YEAR:
_________________________________________________________________
AIRCRAFT MAKE:
_________________________________________________________________
AIRCRAFT MODEL:
_________________________________________________________________
AIRCRAFT SERIAL #: _________________________________________________________________
AIRCRAFT REG. #:
_________________________________________________________________
Installed System
 G500TXi
 G600TXi
 GDU1
 1060  700P  700L
 MFD  PFD  EIS
 GDU2
 1060  700P  700L
 MFD  PFD  EIS
 GDU3
 1060  700P  700L
 MFD  PFD  EIS
 GDU4
 1060  700P  700L
 MFD  PFD  EIS
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page A-1
A.2 LRU Information
For each unit included in the installation, record the LRU information in the table below.
Unit
Part Number
GDU #1
011-0330__-_______
GDU #2
011-0330__-_______
GDU #3
011-0330__-_______
GDU #4
011-0330__-_______
GSU 75( ) #1
011-03094-________
GSU 75( ) #2
011-03094-________
GRS 77 #1
011-00868-________
GRS 77 #2
011-00868-________
GRS 79 #1
011-03732-________
GRS 79 #2
011-03732-________
GMU 44 #1
011-00870-________
GMU 44 #2
011-00870-________
GDC 72( ) #1
011-03734-________
GDC 72( ) #2
011-03734-________
GDC 74( ) #1
011-0_____-_______
GDC 74( ) #2
011-0_____-_______
GTP 59 #1
011-00978-________
GTP 59 #2
011-00978-________
GAD 43/43e
011-0_____-_______
GEA 110 #1
011-03454-________
GEA 110 #2
011-03454-________
GEA 71B
011-03682-________
GCU 485
011-03582-________
GBB 54
011-03456-________
190-01717-B1
Rev. 3
Serial Number
Mod Level
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page A-2
A.3 Equipment Location
For each unit included in the installation, record the fuselage station and provide a brief description of
the location.
Unit
Station (CG)
GDU #1
in.
GDU #2
in.
GDU #3
in.
GDU #4
in.
GSU 75( ) #1
in.
GSU 75( ) #2
in.
GRS 77 #1
in.
GRS 77 #2
in.
GRS 79 #1
in.
GRS 79 #2
in.
GMU 44 #1
in.
GMU 44 #2
in.
GDC 72( ) #1
in.
GDC 72( ) #2
in.
GDC 74( ) #1
in.
GDC 74( ) #2
in.
GTP 59 #1
in.
GTP 59 #2
in.
GAD 43/43e
in.
GEA 110 #1
in.
GEA 110 #2
in.
GEA 71B
in.
GBB 54
in.
190-01717-B1
Rev. 3
Description of Location
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page A-3
A.4 Wire Routing – Single-Engine
The following diagram depicts the wire routing for the G500/G600 TXi LRUs throughout the
aircraft structure for a single-engine aircraft:
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page A-4
A.5 Wire Routing – Twin-Engine
The following diagram depicts the wire routing for the G500/G600 TXi LRUs throughout the
aircraft structure for a twin-engine aircraft:
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page A-5
A.6 Saved Configuration File
The G500/G600 TXi system configuration must be saved to an SD card and placed with the permanent
aircraft maintenance records. For instructions on saving the aircraft configuration file to an SD card,
refer to Section 2.1.6. It is recommended that the SD card be taped or otherwise secured to this page in
the location marked below.
Aircraft Configuration SD Card
A.7 Print Configuration Log
The G500/G600 TXi system configuration log must be printed out and included with the permanent
aircraft maintenance records. To print the system configuration log, perform the following
procedure:
1. Insert the SD card that was created in Appendix Section A.6 into a computer.
2. Open the "Summary" folder.
3. Print the .htm file corresponding to the save generated from Appendix Section A.6.
4. NOTE
It is recommended that the configuration log be attached to the back of this document for
continuity and ease of use. It is required that the MM/ICA, SD card, and configuration log
be included in the permanent aircraft maintenance records.
The configuration log printout contains configuration info for configured EIS gages, including
configured markings and gauge layout for each GDU displaying EIS gauges. The configuration log
will list the location number for each gauge, which can then be referenced to the GDU templates
provided in the following sections.
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page A-6
GDU 1060 Twin Engine Layout
GDU 1060 Single Engine Layout
A.8 GDU 1060 EIS Gauge Layout Template
(E G T /C H T )
(E G T /C H T )
Figure A-1 GDU 1060 EIS Gauge Template
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page A-7
GDU 700P Single Engine Layout
A.9 GDU 700P EIS Gauge Layout Template
GDU 700P Twin Engine Layout
(E G T /C H T )
( E G T /C H T )
Figure A-2 GDU 700P EIS Gauge Layout Template
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page A-8
Figure A-3 GDU 700P MFD/EIS Gauge Layout Template
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page A-9
GDU 700L Twin Engine Layout
GDU 700L Single Engine Layout
A.10 GDU 700L EIS Gauge Layout Template
(EGT/CHT)
(EGT/CHT)
Figure A-4 GDU 700L EIS Gauge Layout Template
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page A-10
Figure A-5 GDU 700L MFD/EIS Gauge Layout Template
190-01717-B1
Rev. 3
G500/G600 TXi Part 23 AML STC Maintenance Manual
Page A-11
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