G5000™ Integrated Avionics System

Line Maintenance Manual

Bombardier Learjet 70/75

190-01386-00 February 2016 Revision C

 © Copyright 2016
Garmin Ltd. or its subsidiaries
All Rights Reserved

Except as expressly provided herein, no part of this manual may be reproduced, copied,
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without the express prior written consent of Garmin. Garmin hereby grants permission to
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Olathe, KS 66062 USA
Telephone: 913-397-8200

Garmin®, FliteCharts® and SafeTaxi® are registered trademarks of Garmin Ltd. or its subsidiaries.
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Inc.; Sirius®, XM®, and all associated trademarks or registered trademarks of Sirius XM Satellite
Radio, Inc. ©1984–2012.

i
 RECORD OF REVISIONS

Revision Date Section Pages Change Description

A 10/10/13 ------ ----- Initial Release
B 6/9/14 All All Comprehensive revision to support Phase IIA.
C 2/5/2016 All All Comprehensive revision to support GDU software
version 3.56

This manual reflects the configuration and operation of GDU software version 3.56.
The following are general safety precautions that are not related to any specific procedure and
therefore do not appear elsewhere in this maintenance manual. These are recommended
precautions that personnel should understand and apply during the many phases of
maintenance and repair.
KEEP AWAY FROM LIVE CIRCUITS. Maintenance personnel shall observe all safety regulations
at all times. Turn off system power before making or breaking electrical connections. Regard
any exposed connector, terminal board, or circuit board as a possible shock hazard.
Components which retain a charge shall be discharged only when such grounding does not
result in equipment damage. If a test connection to energized equipment is required, make the
test equipment ground connection before probing the voltage or signal to be tested.
DO NOT SERVICE ALONE. Personnel shall not under any circumstances reach into or enter any
enclosure for the purpose of servicing or adjusting the equipment without immediate presence
or assistance of another person capable of rendering aid.

ii
 INFORMATION SUBJECT TO EXPORT CONTROL LAWS
“This document may contain information which is subject to the Export Administration
Regulations (“EAR”) issued by the United States Department of Commerce (15 CFR, Chapter VII
Subchapter C) and which may not be exported, released or disclosed to foreign nationals inside
or outside the United States without first obtaining an export license. The preceding statement
is required to be included on any and all reproductions in whole or in part of this manual.”

WARNING
This product, its packaging, and its components contain chemicals known to the
State of California to cause cancer, birth defects, or reproductive harm. This
Notice is being provided in accordance with California's Proposition 65. If you
have any questions or would like additional information, please refer to the
Garmin web site at www.garmin.com/prop65.

CAUTION
The GDU lamps contain mercury and must be recycled or disposed of according
to local, state, or federal laws. If you have any questions or would like
additional information, please refer to our web site at the following website:
www.garmin.com/aboutGarmin/environment/disposal.jsp.

CAUTION
The GDU lens is coated with a special anti-reflective coating which is very
sensitive to skin oils, waxes and abrasive cleaners. CLEANERS CONTAINING
AMMONIA WILL HARM THE ANTI-REFLECTIVE COATING. It is very important to
clean the lens using a clean, lint-free cloth and a premium off the shelf LCD
screen cleaner that is anti-static, alcohol and sodium lauryl sulfate free and safe
for AR coatings.

iii
 WARNING

SAFE DISTANCE DETERMINATION- The following information establishes a minimum safe

distance from the antenna for personnel near an operating airborne weather radar. The
minimum safe distance is based upon the FCC’s exposure limit at 9.3 to 9.5 GHz for general
population/uncontrolled environments which is 10 mW/cm2. See Advisory Circular 20-68B for
more information on safe distance determination. The GWX 70 safe distance determination
given below in the table is based on lower exposure limits of 1 mW/cm2 than what is specified
in AC 20-68B.

Antenna Size Safe Distance

12” 9.6 ft.

iv
WARNING
MAXIMUM PERMISSIBLE EXPOSURE LEVEL (MPEL)- The zone in which the
radiation level exceeds the 1 mW/cm2, is the semi-circular area within a radius
of 9.6 ft from the 12” antenna as indicated in the illustration below. All
personnel must remain outside of this zone. The distance to the MPEL
boundary is calculated upon the basis of each antenna available with the GWX
70 (nominal average output power of the transmitter, and in the non-rotating
or bore sight position of the antenna (see example calculations above). With a
scanning or rotating beam, the averaged power density at the MPEL boundary
is significantly reduced.

WARNING
Airborne weather radar should be operated on the ground only by qualified
personnel. Installed airborne radar should not be operated while the aircraft is
in a hanger or other enclosure unless the radar transmitter is not operating, or
the energy is directed toward an absorption shield which dissipates the radio
frequency energy. Otherwise, radiation within the enclosure can be reflected
throughout the area.

v
 WARNING
BODY DAMAGE- TAKE THE FOLLOWING PRECAUTIONS TO PREVENT
HUMAN BODY DAMAGE:

 Never stand nearby or in front of a radar antenna which is

transmitting. The danger increases when the antenna is not
scanning.
 Follow the recommended safe distance. The distance from any
person to the radar should be greater than the recommended
safe distance.
 Avoid the end of an open waveguide unless the radar is turned
off.
 Avoid looking into a waveguide, or into the open end of a coaxial
connector or line connector to a radar transmitter output, as
severe eye damage may result.
 X-rays may be emitted when high power radar transmitters are
operated out of their protective cases. Stray X-rays can emanate
from the glass envelope type pulser, oscillator, clipper, or
rectifier tubes, as well as magnetrons.

vi
CONTENTS
SECTION 1 — INTRODUCTION
1.1 MAINTENANCE CONCEPT/SCOPE .......................................................................................... 1-1
1.2 SUPPLEMENTARY PUBLICATIONS .......................................................................................... 1-1
1.2.1 Bombardier/Learjet Documents ............................................................................................ 1-1
1.2.2 Garmin Documents ................................................................................................................ 1-1
1.2.2.1 Pilot’s Guides ......................................................................................................................... 1-1
1.2.2.2 Garmin Installation Manuals ................................................................................................. 1-2
1.3 TECHNICAL SUPPORT ............................................................................................................. 1-3
1.4 MANUAL ORGANIZATION ...................................................................................................... 1-3

SECTION 2 — G5000 DESCRIPTION

2.1 LINE REPLACEABLE UNITS ...................................................................................................... 2-1
2.1.1 GDU 1400W Display Unit ....................................................................................................... 2-1
2.1.2 GTC 570 .................................................................................................................................. 2-3
2.1.3 GCU 275 ................................................................................................................................. 2-3
2.1.4 GMA 36 .................................................................................................................................. 2-4
2.1.5 GIA 63W ................................................................................................................................. 2-4
2.1.6 GDC 7400 ............................................................................................................................... 2-5
2.1.7 GSC 46 .................................................................................................................................... 2-5
2.1.8 GEA 71.................................................................................................................................... 2-6
2.1.9 GSD 41.................................................................................................................................... 2-6
2.1.10 GTX 3000 ................................................................................................................................ 2-7
2.1.11 GRS 7800 ................................................................................................................................ 2-7
2.1.12 GMU 44 .................................................................................................................................. 2-8
2.1.13 GDL 69/GDL 69 SXM .............................................................................................................. 2-9
2.1.14 GMC 7250 ............................................................................................................................ 2-10
2.1.15 GSA 9000/GTA 82 ................................................................................................................ 2-11
2.1.16 GSM 9100 ............................................................................................................................ 2-11
2.1.17 GWX 70 ................................................................................................................................ 2-12

vii
SECTION 2 — G5000 DESCRIPTION (continued)
2.1.18 GTS 8000 .............................................................................................................................. 2-13
2.1.19 Iridium SATCOM System ...................................................................................................... 2-14
2.1.20 GDR 66 ................................................................................................................................. 2-15
SECTION 3 — G5000 CONTROL AND OPERATION
3.1 SYSTEM POWER-UP ............................................................................................................... 3-1
3.2 G5000 CONTROLS .................................................................................................................. 3-3
3.2.1 GDU Controllers ..................................................................................................................... 3-3
3.2.2 GDU Softkeys ......................................................................................................................... 3-4
3.2.3 Touchscreen Controller ......................................................................................................... 3-6
3.3 DATA ENTRY ......................................................................................................................... 3-21
3.4 SECURE DIGITAL (SD) CARDS .............................................................................................. 3-22
3.4.1 ReadyBoost .......................................................................................................................... 3-22
3.4.2.1 Disabling Ready Boost ......................................................................................................... 3-23
3.5 G5000 MODES OF OPERATION ........................................................................................... 3-23
3.5.1 Normal Mode ...................................................................................................................... 3-23
3.5.2 GDUs .................................................................................................................................... 3-23
3.5.3 Touchscreen Controllers ...................................................................................................... 3-23
3.5.4 Reversionary GDU Operation .............................................................................................. 3-24
3.5.5 Configuration Mode ............................................................................................................ 3-25
3.5.6 'SET' AND 'ACTIVE' Commands ............................................................................................ 3-25
3.5.7 SET and ACTIVE Softkeys ..................................................................................................... 3-26

viii
SECTION 4 — TROUBLESHOOTING
4.1 VISUAL HARDWARE INSPECTION ........................................................................................... 4-2
4.2 RED OR YELLOW X DISPLAY INDICATIONS ............................................................................. 4-2
4.3 G5000 SYSTEM MESSAGES .................................................................................................... 4-9
4.3.1 GCU 275 PFD Controller System Messages ........................................................................... 4-9
4.3.2 GDC 7400 Air Data Computer System Messages .................................................................. 4-9
4.3.3 GDL 59 System Messages .................................................................................................... 4-10
4.3.4 GDU 1400W System Messages ............................................................................................ 4-10
4.3.5 GIA 63W System Messages ................................................................................................. 4-13
4.3.6 GMA 36 System Messages................................................................................................... 4-17
4.3.7 GMC 7250 System Messages ............................................................................................... 4-17
4.3.8 GMU 44 System Messages .................................................................................................. 4-17
4.3.9 GRS 7800 System Messages ................................................................................................ 4-18
4.3.10 GTC 570 System Messages .................................................................................................. 4-20
4.3.11 GTS 8000 System Messages ................................................................................................ 4-22
4.3.12 GTX 3000 System Messages ................................................................................................ 4-22
4.3.13 GDR 66 Messages ................................................................................................................ 4-22
4.4 DATA LOGGING AND DIAGNOSTICS .................................................................................... 4-24
4.5 GIA AND GDU SERIAL CONFIGURATION PAGE DATA PATH INDICATIONS .......................... 4-26
4.6 CONFIGURATION PAGES ...................................................................................................... 4-27
4.6.1 General System Awareness ................................................................................................. 4-27
4.6.2 Configuration Page Security and General Information ....................................................... 4-27
4.6.3 Configuration Unlock Card................................................................................................... 4-28
4.6.4 Configuration Mode............................................................................................................. 4-28
4.6.5 Configuration Page Groups and Descriptions...................................................................... 4-29
4.6.5.1 System Group ...................................................................................................................... 4-31
4.6.5.2 GDU Page Group .................................................................................................................. 4-49
4.6.5.3 GIA Group ............................................................................................................................ 4-69
4.6.5.4 GSD Page Group................................................................................................................... 4-77
4.6.5.5 GEA Page Group ................................................................................................................... 4-82
4.6.5.6 GTX Page Group ................................................................................................................... 4-86

ix
SECTION 4 — TROUBLESHOOTING (continued)
4.6.5.7 GRS Page Group ................................................................................................................... 4-89
4.6.5.8 ADC Page Group................................................................................................................... 4-92
4.6.5.9 GFC Page Group ................................................................................................................... 4-93
4.6.5.10 GMA Page Group ................................................................................................................. 4-97
4.6.5.11 GDL Page Group ................................................................................................................. 4-104
4.6.5.12 RMT Group ......................................................................................................................... 4-112
4.6.5.13 GWX Page Group ............................................................................................................... 4-114
4.6.5.14 GTS Page Group ................................................................................................................. 4-116
4.6.5.15 GDR Page Group ................................................................................................................ 4-119
4.6.5.16 Cal Page Group .................................................................................................................. 4-122
4.6.6 GWX 70 RADAR TROUBLESHOOTING ................................................................................ 4-123
4.6.6.1 GWX 70 Troubleshooting Table ......................................................................................... 4-123
4.6.6.2 Miscellaneous Radar Faults ............................................................................................... 4-126
4.7 COMMON G5000 ISSUES AND CORRECTIVE ACTIONS ..................................................... 4-127
4.7.1 GDU 1400W ...................................................................................................................... 4-127
4.7.2 GIA 63W ............................................................................................................................. 4-129
4.7.2.1 WAAS GPS ......................................................................................................................... 4-130
4.7.2.2 NAV .................................................................................................................................... 4-134
4.7.3 GRS 7800 AHRS .................................................................................................................. 4-135
4.7.3.1 Common AHRS Issues and Possible Solutions ................................................................... 4-135
4.7.3.2 GRS 7800 Operational Modes ........................................................................................... 4-136
4.7.3.3 GRS 7800 Troubleshooting Questions ............................................................................... 4-137
4.7.3.4 GRS Aircraft Troubleshooting ............................................................................................ 4-139
4.7.4 GMA 36 .............................................................................................................................. 4-141
4.7.5 XM Weather Receiver ........................................................................................................ 4-143
4.8 AUTOMATIC FLIGHT CONTROL SYSTEM (AFCS) TROUBLESHOOTING ............................... 4-144
4.9 DOWNLOADING GIA AND GSA MAINTENANCE LOGS ....................................................... 4-145
4.10 LRU EXTERNAL CONNECTOR INFORMATION..................................................................... 4-147

x
SECTION 5 — LRU REPLACEMENT PROCEDURES
5.1 GCU 275 PFD CONTROLLER ................................................................................................... 5-2
5.2 GDC 7400 AIR DATA COMPUTER ........................................................................................... 5-3
5.3 GDL 59 WI-FI DATALINK AND FLIGHT PARAMETER RECORDER ............................................ 5-4
5.4 GDL 69 XM WEATHER DATA LINK .......................................................................................... 5-6
5.5 GDU 1400W DISPLAY UNIT .................................................................................................... 5-7
5.6 GEA 71 ENGINE AND AIRFRAME INTERFACE UNIT ................................................................ 5-8
5.7 GIA 63W INTEGRATED AVIONICS UNIT.................................................................................. 5-9
5.8 GMA 36 AUDIO PROCESSOR AND MARKER BEACON RECEIVER ......................................... 5-10
5.9 GMC 7250 AUTOPILOT MODE CONTROLLER ...................................................................... 5-11
5.10 GRS 7800 AHRS AND GMU 44 MAGNETOMETER ............................................................... 5-11
5.11 GSA 9000 SERVO ACTUATOR/GSM 9100 SERVO GEARBOX ................................................ 5-13
5.12 GTA 82 TRIM ADAPTER ........................................................................................................ 5-14
5.13 GSC 46 SIGNAL CONDITIONER ............................................................................................. 5-15
5.14 GSD 41 DATA CONCENTRATOR ........................................................................................... 5-16
5.15 GSR 56 IRIDIUM SATELLITE TRANSCEIVER ........................................................................... 5-16
5.16 GTC 570 TOUCH SCREEN CONTROLLER ............................................................................... 5-18
5.16.1 GTC 570 Touch Screen Controller Fans ............................................................................... 5-18
5.17 GTS 8000 TCAS II PROCESSOR.............................................................................................. 5-21
5.18 GTX 3000 TRANSPONDER .................................................................................................... 5-22
5.19 GWX 70 AIRBORNE WEATHER RADAR................................................................................. 5-22
5.20 CONFIGURATION MODULE REMOVAL AND REPLACEMENT ............................................... 5-24
5.21 GEA 71 BACKSHELL THERMOCOUPLE REMOVAL and REPLACEMENT ................................ 5-25
5.22 GDR 66 VHF DATALINK RADIO UNIT .................................................................................... 5-26
5.23 FLIGHT DATA RECORDER UNIT ............................................................................................ 5-27

xi
SECTION 6 — LRU SOFTWARE LOADING, CONFIGURATION, and TESTING
6.1 SUPPORTING PUBLICATIONS ................................................................................................. 6-2
6.2 SECURE DIGITAL CARDS ......................................................................................................... 6-2
6.3 SOFTWARE LOADING PROCEDURES ...................................................................................... 6-2
6.3.1 GCU 275 PFD Controller ........................................................................................................ 6-2
6.3.2 GDC 7400 Air Data Computer ................................................................................................ 6-3
6.3.3 GDL 59 WI-FI Datalink And Flight Parameter Recorder ......................................................... 6-4
6.3.4 GDL 69 XM Weather Data Link .............................................................................................. 6-5
6.3.5 GDU 1400W Display Unit ....................................................................................................... 6-6
6.3.6 GEA 71 Engine and Airframe Interface Unit ......................................................................... 6-7
6.3.7 GIA 63W Integrated Avionics Unit ........................................................................................ 6-8
6.3.8 GMA 36 Audio Processor And Marker Beacon Receiver ....................................................... 6-9
6.3.9 GMC 7250 AFCS Mode Controller ....................................................................................... 6-10
6.3.10 GRS 7800 AHRS .................................................................................................................... 6-11
6.3.11 GMU 44 Magnetometer ...................................................................................................... 6-12
6.3.12 GSA 9000 Servo Actuator .................................................................................................... 6-13
6.3.13 GSC 46 Signal Conditioner ................................................................................................... 6-14
6.3.14 GSD 41 Data Concentrator .................................................................................................. 6-15
6.3.15 GSM 9100 Servo Gearbox .................................................................................................... 6-16
6.3.16 GTA 82 Trim Adaptor ........................................................................................................... 6-17
6.3.17 GTC 570 Touch Screen Controller........................................................................................ 6-18
6.3.18 GTS 8000 TCAS II System ..................................................................................................... 6-19
6.3.19 GTX 3000 Transponder ........................................................................................................ 6-20
6.3.20 GWX 70 Airborne Weather Radar ....................................................................................... 6-21
6.3.21 GDR 66 VHF Digital Radio .................................................................................................... 6-22

xii
SECTION 7 — PERIODIC MAINTENANCE
7.1 GENERAL PROCEDURES ......................................................................................................... 7-1
7.1.1 Pitot/Static Leak Test ............................................................................................................. 7-1
7.1.2 Altimeter (GDC 7400 and PFD) .............................................................................................. 7-1
7.1.3 Airspeed Function Test (GDC 7400 and PFD) ........................................................................ 7-1
7.1.4 Vertical Speed Indicator (GDC 7400 and PFD) ....................................................................... 7-1
7.1.5 GTX 3000 Transponder .......................................................................................................... 7-1
7.1.6 GRS 7800 Earth Magnetic Field Updates ............................................................................... 7-1
7.1.7 GA 37...................................................................................................................................... 7-1
7.1.8 GIA 63W ................................................................................................................................. 7-1
7.1.9 GCU 275 ................................................................................................................................. 7-2
7.1.10 GDC 7400 ............................................................................................................................... 7-2
7.1.11 GDL 59 .................................................................................................................................... 7-2
7.1.12 GDL 69 .................................................................................................................................... 7-2
7.1.13 GDU 1400W ........................................................................................................................... 7-3
7.1.14 GEA 71.................................................................................................................................... 7-3
7.1.15 GMA 36 .................................................................................................................................. 7-3
7.1.16 GMC 7250 .............................................................................................................................. 7-3
7.1.17 GMU 44 .................................................................................................................................. 7-3
7.1.18 GRS 7800 ................................................................................................................................ 7-3
7.1.19 GSA 9000/GSM 9100 ............................................................................................................. 7-3
7.1.20 GSD 41.................................................................................................................................... 7-3
7.1.21 GSR 56 .................................................................................................................................... 7-3
7.1.22 GTA 82.................................................................................................................................... 7-3
7.1.23 GTC 570 .................................................................................................................................. 7-4
7.1.24 GTS 8000 ................................................................................................................................ 7-4
7.1.25 GTX 3000 ................................................................................................................................ 7-4
7.1.26 GWX 70 .................................................................................................................................. 7-4

xiii
SECTION 8 — REINSTALLING SYSTEM SOFTWARE .................................................................................. 8-1
APPENDIX A — LRU CONNECTOR PIN DESCRIPTIONS
A.1 GDU 1400W Display Unit ....................................................................................................... A-1
A.2 GTC 570 Touch Screen Controller.......................................................................................... A-4
A.3 GIA 63W Integrated Avionics Unit ......................................................................................... A-6
A.4 GDC 7400 Air Data Computer .............................................................................................. A-18
A.5 GEA 71 Engine and Airframe Interface Unit ........................................................................ A-20
A.6 GRS 7800 AHRS .................................................................................................................... A-24
A.7 GMU 44 Magnetometer ...................................................................................................... A-26
A.8 GMA 36 Audio Processor and Marker Beacon Receiver ..................................................... A-27
A.9 GDL 69 XM Weather Data Link ............................................................................................ A-31
A.10 GDL 59 Wi-Fi Datalink and Flight Parameter Recorder ....................................................... A-33
A.11 GSR 56 Iridium Satellite Transceiver.................................................................................... A-35
A.12 GMC 7250 Autopilot Mode Controller ................................................................................ A-36
A.13 GWX 70 Airborne Weather Radar ....................................................................................... A-37
A.14 GSD 41 Data Concentrator .................................................................................................. A-39
A.15 GSA 9000 Servo Actuator .................................................................................................... A-43
A.16 GTA 82 Trim Adaptor .......................................................................................................... A-44
A.17 GTS 8000 TCAS II System ..................................................................................................... A-45
A.18 GCU 275 PFD Controller ...................................................................................................... A-51
A.19 GDR 66 Data Link Transceiver.............................................................................................. A-52

APPENDIX B — AFM/AFMS/POH CONSIDERATIONS

B.1 GARMIN GNSS NAVIGATION SYSTEM EQUIPMENT APPROVALS .......................................... B-1
B.2 GARMIN GNSS NAVIGATION SYSTEM LIMITATIONS ............................................................. B-2

xiv
SECTION 1—INTRODUCTION

NOTE
All visual depictions contained within this manual, including screen
images of the G5000 panel and displays, are subject to change and may
not reflect the most current G5000 system and aviation databases.
Depictions of equipment may differ slightly from the actual equipment.
This manual provides basic line maintenance information for the Garmin G5000 Integrated
Avionics System installed and configured in Learjet 70 and 75 aircraft.
1.1 MAINTENANCE CONCEPT/SCOPE
Performing maintenance on the G5000 consists of the following:
• Troubleshooting to identify and replace faulty Line Replaceable Units (LRUs).
• Removing and replacing an LRU.
• Installing and configuring system level and individual LRU software.
• Performing periodic maintenance procedures.
• Performing return to service tests.
There is no component level repair on any part of the system or any repair of an individual LRU.
The manual contains no schematic diagrams. No special tools or equipment are needed to
perform maintenance. This Maintenance Manual does not reflect part numbers and should not
be used for ordering replacement parts. Spares and replacement parts should be ordered using
the current Learjet Parts Lists.
1.2 SUPPLEMENTARY PUBLICATIONS
The following publications supplement the information contained in this maintenance manual:
1.2.1 Bombardier/Learjet Documents
• Learjet 75 Maintenance Manual, P/N MM-107, Publication Number LR75MM, Revision 1
or later FAA-approved revision
• Learjet 70 Maintenance Manual, P/N MM-106, Publication Number LR70MM, Revision 1
or later FAA-approved revision
• Supplemental Maintenance Manual, Model 45 Avionics Upgrade, P/N SMM-107-45, Rev
NC or later FAA-approved revision
1.2.2 Garmin Documents
1.2.2.1 Pilot’s Guide
Garmin G5000 Pilot’s Guide for Learjet 70/75: Part Number 190-01401-XX

G5000 Line Maintenance Manual-Learjet 70/75 Page 1-1

190-01386-00 Revision C
1.2.2.2 Garmin Installation Manuals
• GCU 275 PFD Controller-Garmin Installation Manual Part Number: 190-00303-75
• GDC 7400 Air Data Computer-Garmin Installation Manual Part Number: 190-01100-00
• GDL 59 WI-FI Datalink and Flight Parameter Recorder-Garmin Installation Manual Part
Number: 190-00837-00
• GDL 69 XM Weather and Radio Data Link-Garmin Installation Manual Part Number:
190-00355-02 (also covers GDL 69 SXM)
• GDU 1400W Display Unit-Garmin Installation Manual Part Number: 190-00303-28
• GEA 71 Engine And Airframe Interface Unit-Garmin Installation Manual Part Number:
190-00303-40
• GIA 63W Integrated Avionics Unit-Garmin Installation Manual Part Number:
190-00303-05
• GMC 7250 Autopilot Mode Controller-Garmin Installation Manual Part Number:
190-00303-70
• GRS 7800 AHRS and GMU 44 Magnetometer-Garmin Installation Manual Part Number:
190-01091-00
• GSA 9000 Servo Actuator/GSM 9100 Servo Gearbox-Garmin Installation Manual Part
Number: 190-00303-85
• GSC 46 Signal Conditioner-Sandia Corp. P/N 305952-00-IM
• GSD 41 Data Concentrator-Garmin Installation Manual Part Number: 190-00303-26
• GSR 56 Iridium Satellite Transceiver-Garmin Installation Manual Part Number:
190-00836-00
• GTA 82 Trim Adaptor-Garmin Installation Manual Part Number: 190-00303-74
• GTC 570 Touch Screen Controller-Garmin Installation Manual Part Number:
190-00987-00
• GTS 8000 TCAS II Processor-Garmin Installation Manual Part Number: 190-00587-50
• GTX 3000 Transponder-Garmin Installation Manual Part Number: 190-00926-01
• GWX 70 Airborne Weather Radar-Garmin Installation Manual Part Number:
190-00829-01
• GDR 66 Digital Communications Transceiver-Installation Manual Part Number:
190-00303-24

Page 1-2 G5000 Line Maintenance Manual-Learjet 70/75

Revision C 190-01386-00
1.3 TECHNICAL SUPPORT
For technical support contact Garmin at the following:

Technical Support and Field Service Engineers

Phone: 888-606-5482
Phone: 913-397-8200
Fax: 913-397-8282
Email: avionics@garmin.com

For Asia/Australia( APAC):

Dealer Sales and Support
Phone: 1800 244 143
Fax: 02 9679 3450
Email: au.orders@garmin.com

For EMEA :
Aviation - Garmin Europe
Phone: +44 (0) 87 0850 1243 - Monday - Friday: 8:30 AM - 17:30 PM Western European Time
Fax: +44 (0) 23 8052 4004
1.4 MANUAL ORGANIZATION
Section 1 gives introductory manual information. Section 2 provides a basic description of the
G5000 configured for the Learjet 70/75. Section 3 describes basic G5000 operating procedures.
Section 4 contains troubleshooting information. Section 5 describes how remove and replace a
faulty LRU. Section 6 describes how to load, configure, and test LRU software. Section 7 contains
periodic maintenance requirements for LRUs. Section 8 explains how to reload and configure
system software should it become necessary. Appendix A contains LRU external connector pin
names and numbers. Appendix B contains pertinent AFM, AFMS, and/or POH information as it
relates to the G5000.

G5000 Line Maintenance Manual-Learjet 70/75 Page 1-3

190-01386-00 Revision C
 Blank Page

Page 1-4 G5000 Line Maintenance Manual-Learjet 70/75

Revision C 190-01386-00
SECTION 2—G5000 DESCRIPTION

This section provides an overview of the G5000 Integrated Avionics System installed in the
Learjet 70/75 aircraft. The G5000 is an integrated flight control system that presents flight
instrumentation, position, navigation, communication, and identification information to the
flight crew using flat-panel color displays and Touchscreen Controllers (Figure 2-1).
2.1 LINE REPLACEABLE UNITS
The G5000 consists of the Line Replaceable Units (LRUs) described in this section.
2.1.1 GDU 1400W Display Unit (DU)

The GDU 1400W features a 14-inch light emitting diode (LED) backlit widescreen display with a
1280 x 800 resolution. The unit installed on the left/pilot side is designated as GDU1. In normal
operations, it shows a Primary Flight Display (PFD), and may also show a display pane and a PFD.
The center unit is designated as GDU2. In normal operations it shows the Engine Indication and
Crew Alerting System (EICAS) display, in addition to one or two display panes. The unit installed
on the right/copilot side is designated as GDU3. In normal operations, it shows a PFD, and may
also show a display pane and a PFD. The GDUs communicate with each other, the Touchscreen
Controllers, and with the on-side GIA 63W Integrated Avionics Unit (IAU) through a High-Speed
Data Bus (HSDB) Ethernet connection.

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 Figure 2-1. Simplified G5000 System Block Diagram

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2.1.2 GTC 570 Touch Controller

The Touch Controller provides access to a wide variety of system capabilities including control of
GDU display panes, Flight Management System (FMS) functions, communications, navigation,
and surveillance systems, system status, and setup. The unit installed on the left/pilot side is
designated as GTC1, and the one installed on the right/copilot side is designated as GTC2. Each
Touchscreen Controller communicates with the on-side GDU in addition to GDU2 using an HSDB
connection.
2.1.3 GCU 275

The GDU Controller is a panel-mounted user interface which enables the flight crew to control
the on-side GDU PFD. The unit installed on the left/pilot side is designated as GCU1, and the
one installed on the right/copilot side is designated as GCU2. Each unit is connected to the on-
side GDU and to the GDU2 using an RS-232 connection.

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2.1.4 GMA 36 Audio Processor

The Remote Audio Unit integrates navigation/communication radio (NAV/COM) digital audio,
intercom, and marker beacon audio. Each unit is connected to the on-side Touchscreen
Controller using an HSDB interface and to the cross-side IAU using an RS-232 connection as a
backup path. Each GMA 36 is also connected to the Cockpit Voice Recorder (CVR) using a
digital/analog connection.

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2.1.5 GIA 63W Integrated Avionics Unit

The GIAs functions as the main communications hub, linking several LRUs with each on-side
GDU. Each GIA contains a Satellite-Based Augmentation System (SBAS) receiver, a very high
frequency (VHF) communication/navigation/glideslope (COM/NAV/GS) receiver, a flight director
(FD) and system integration microprocessors. The GIAs also communicate directly with each
other via the Controller Area Network (CAN) protocol in the event the HSDB communications
path has failed.

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2.1.6 GDC 7400 Air Data Computer

The Air Data Computer (ADC) processes data from the pitot/static system and outside air
temperature (OAT) sensor. The ADC provides pressure altitude, density altitude, vertical speed,
airspeed, Mach number, OAT, and total air temperature data. The pilot side ADC only is
connected to the on-side IAU, GDU, GRS 7800, and to the cross-side IAU via an HSDB
connection, and is direct wired to GDU2. An RS-232 path also connects each ADC to the on-side
IAU.
2.1.7 GSC 46 Signal Conditioning Unit
The Signal Conditioning Unit (not shown in the block diagram) supplies N1 and N2 engine data
to the GEAs. The unit installed on the left/pilot side is designated as GSC1, and the one installed
on the right/copilot side is designated as GSC2. Each GSC is connected to the on-side GEA via a
digital connection.

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2.1.8 GEA 71 Engine and Airframe Unit

The Engine Airframe Unit receives and processes signals from the engine and airframe sensors.
This unit communicates with both IAUs using an RS-485 digital interface.
2.1.9 GSD 41 Serial Data Concentrator

This unit is a data concentrator which expands the input and output capabilities of the system.
HSDB communications occur among Garmin LRUs. The ARINC 429 protocol connects non-
Garmin LRUs as shown in the Learjet Maintenance Manual.

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2.1.10 GTX 3000 ATC Transponder

The solid-state Transponder provides Modes A/C/S capability, 1090 MHz Extended Squitter
Automatic Dependent Surveillance - Broadcast (ADS-B) transmission, and communicates with
the on-side IAU through an RS-482/422 digital interface. Each transponder is also connected to
the GTS 8000 Traffic Alert and Collision Avoidance II (v7.1) system using the ARINC 429 protocol.

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2.1.11 GRS 7800 AHRS

The Attitude and Heading Reference System (AHRS) provides aircraft attitude and heading
information via ARINC 429 protocol to the on-side and cross-side IAU, the on-side GDU, and to
GDU2. An RS-232 backup path connects AHRS 1 to each IAU. The AHRS contains advanced
sensors (including accelerometers and rate sensors) and interfaces with the Magnetometer to
obtain magnetic field information, with the ADC to obtain air data, and with both IAUs to obtain
GPS information. AHRS operation is discussed in the Learjet Maintenance Manual.
2.1.12 GMU 44 Magnetometer

The Magnetometer measures the local magnetic field and sends data to the AHRS for processing
to determine aircraft magnetic heading. The magnetometer receives power directly from the
AHRS and communicates with it via an RS-485/422 and RS-232 digital interface.

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2.1.13 GDL 69/GDL 69 SXM

The GDL 69/69 SXM are SiriusXM Satellite Radio data link receivers. The SiriusXM Satellite Radio
antenna receives the SiriusXM satellite signal and passes it to the GDL 69/69 SXM. The GDL
69/69 SXM are weather data receivers only. The GDL 69 and GDL 69 SXM receivers use the same
antenna, have pin-for-pin compatibility and slide into the same unit rack.
2.1.14 GMC 7250 AFCS Mode Controller

The AFCS Mode Controller provides AFCS control through an RS-232 digital interface. The unit
connects to GDU1 and GDU3.

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2.1.15 GSA 9000 and GTA 82

GSA 9000 GTA 82

The GSA 9000 Servos provide automatic control of pitch and roll. The GTA 82 Pitch Trim Adapter
works with the existing motor to provide automatic pitch trim. These units interface with each
IAU using RS-482/422 connections.
2.1.16 GSM 9100
The GSM 9100 Servo Gearboxes are responsible for transferring the output torque of the GSA
9000 Aileron, Elevator, and Rudder servo actuators to the mechanical flight-control surface
linkages.

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2.1.17 GWX 70 Weather Radar System

The weather radar system is a single-unit X-band radar used for atmospheric moisture detection
and ground mapping. When the system is in the weather detection mode, it will detect and
locate various types of inclement weather conditions along the flight path of the aircraft and
provide a visual-color display of storm intensities. When the system is used for ground mapping,
the display will enable the crew to identify coastlines, hilly or mountainous regions, cities, or
large structures.
The weather radar system consists of a receiver/transmitter/antenna (RTA) unit (A22). The RTA
incorporates a 12-inch plate array antenna and is installed inside the radome on the forward
side of frame 1. Software and configuration is loaded through PFD 1 via a SD card. The RTA is a
solid state weather radar with 50-watt transmit power. The RTA has a azimuth sweep range of
±60 degrees and a elevation sweep of ±30 degrees. The display range is 2.5 to 320 NM. The
weather radar system has supported features as follows:
1. Weather target alert to annunciate the presence of significant weather
2. Automatic range limiting
3. Vertical scan
4. Altitude compensating tilt
5. Pilot-selectable receiver gain
6. Ground mapping capability
Operation of the weather radar system is described in Section 34-42-00 in the Learjet
Maintenance Manual, MM106.

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2.1.18 GTS 8000 TCAS II Processor

TCAS II is an airborne traffic alert, collision avoidance, and resolution advisory system. The TCAS
II system operates in conjunction with the transponder to interrogate the transponders of other
aircraft and monitor their replies. TCAS II tracks and continuously evaluates the threat potential
of the responding aircraft and can display them on all three DUs either on MFWs or inset maps
on the PFDs. During threat situations, TCAS II gives traffic advisories and resolution advisories to
assist the pilot in avoiding midair collisions. The TCAS II system consists of a processor and two
antennas. (1) The TCAS II processor (A60) is in the nose compartment at approximately FS
150.51. The processor interfaces with the TCAS antennas, controls, displays, and other aircraft
systems. (2) The TCAS II antennas (E41, upper; E42, lower) are attached along the centerline of
the fuselage at FS 274.51 (upper) and FS 253.51 (lower). The antennas are installed on the top
and bottom of the aircraft to prevent intruder aircraft from being shielded by the airframe. C.
The TCAS II processor transmits transponder interrogation signals and monitors all replies. The
range, bearing, and closure rate of the responding aircraft are then computed. If a responding
aircraft is equipped with an altitude-reporting transponder, its altitude and vertical speed are
also determined. D. The TCAS II antennas are located on the top and the bottom of the aircraft.
Each antenna is a four element, vertically polarized, monopole array, that can transmit in any
direction as selected, and receive from all directions simultaneously.

NOTE: Operation of the TCAS II system is described in Section 34-43-00 in the Learjet
Maintenance Manual, MM106.

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2.1.19 Iridium SATCOM System

GDL 59 Wireless Datalink Unit GSR 56 Iridium SATCOM Transceiver

The Iridium SATCOM System consists of an Iridium transceiver (A5225), maintenance data
recorder and wireless datalink unit (A18) and a SATCOM antenna (A5189). (1) The Iridium
transceiver (A5225) is in the left side of the avionics nose compartment at FS 142 and supports
cockpit integrated phone and in-air remote maintenance datalink through a low-speed RS232 to
the flight parameter recorder unit. (2) The Iridium SATCOM antenna (A5189) is on the top of the
aircraft at FS 318. (3) The maintenance data recorder and wireless datalink unit is in the aircraft
nose at FS 168. The unit provides a flight parameter recorder function and a high speed data link
between the aircraft systems and ground computers using 802.11g (“Wi-Fi”) while the aircraft is
on the ground. (Refer to 45-45-00 in the Learjet MM.) Power for the Iridium SATCOM system is
supplied through the WI-FI/IRIDIUM circuit breaker on the left main bus on the pilot circuit
breaker panel. Phone numbers can be dialed through the GTCs through the Iridium phone. An
aural alert is heard to indicate an incoming call is being received. The transceiver interfaces with
the maintenance data recorder and wireless datalink unit through RS232. The GSR 56 also
provides a data link to receive the optional Garmin Connext Weather service.

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2.1.20 GDR 66 Digital Radio Unit

The Digital Radio Unit is a transceiver for sending and receiving Controller Pilot Data Link
Communications (CPDLC) messages by using the Touchscreen Controllers. It also supports
analog voice communications. It communicates with each GSD 41 unit using an RS-485/422
interface. Description and operation of the GDR 66 is in the Controller Pilot Datalink
Communication System - Description And Operation, Learjet Supplemental Maintenance
Manual, M100544ICT-SMM-0200, section 23-25-00.

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SECTION 3—G5000 CONTROL AND OPERATION

A basic knowledge on how to operate the G5000 is needed to perform maintenance. Refer to
the G5000 Pilot’s Guide for Learjet 70/75 (P/N 190-01401-00) if more detailed information is
required.
3.1 SYSTEM POWER-UP
The G5000 System is integrated with the aircraft electrical system and receives power directly
from electrical busses. The GDUs, Touchscreen Controllers, and supporting sub-systems include
both power-on and continuous built-in test features that exercise the processors, memory,
external inputs, and outputs.
During system power-up (Figures 3-2 and 3-3) the system displays test annunciations on the
GDUs. The Touchscreen Controllers display the Initialization Screen.
On the PFDs, the AHRS initializes and displays “AHRS ALIGN: Keep Wings Level”. The AHRS
should display valid attitude and heading fields typically within the first minute of power-up.
The AHRS can align itself both while taxiing and during level flight.
When the MFD powers up, the splash display (Figure 3-3) shows the following information:
• System Version
• Copyright
• Checklist name and version
• Basemap Land database and version
• Safe Taxi database information
• Terrain database name and version
• Obstacle database name and version
• Navigation database name, version, and effective dates
• Airport Directory name, version and effective dates
• ChartView database information

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 Figure 3-1. MFD Splash Screen with Database Information

Current database information includes database type, cycle number, or valid operating dates.
Review the listed information for currency (to ensure no databases have expired).
Pressing the right-most softkey on the MFD acknowledges this information, and then shows the
EICAS (Engine Indication and Crew Alerting System) Display, the Summary Pane (in Half Mode),
and the Navigation Map Pane (in Half Mode). When the system has acquired a sufficient number
of satellites to determine a position, the system displays the aircraft’s current position on the
Navigation Map Pane.

Figure 3-2. PFD1 Power Up Figure 3-3. MFD Power Up

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 Figure 3-4. Touchscreen Controller Initialization Screen

3.2 G5000 CONTROLS

Controls are located on the GDU bezels and controllers, the Touchscreen Controllers, and the
AFCS Controller. GDU controls and the Touchscreen Controllers are discussed in this section.
AFCS controls are described in the AFCS section. See the Audio and CNS Section in the Pilot’s
Guide for detailed information about NAV/COM, intercom, and transponder controls.
3.2.1 GDU Controllers
The GDU Controllers are a panel-mounted user interface allowing for ease of data entry, PFD
operation, and NAV/COM tuning (refer to the Audio and CNS Section in the Pilot’s Guide for
detailed information about NAV/COM tuning). Many procedures in this maintenance manual
can be performed using the GDU Controller. The pilot’s side GDU Controller controls PFD1 and
the copilot’s GDU controller controls PFD2.

Figure 3-5. GCU 275 GDU Controller

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3.2.2 GDU Softkeys
Press the selection softkey key to perform the function shown above the bezel key on the GDU.
The MFD uses Softkeys to scroll up or down through Crew Alerting System (CAS) messages when
more messages are present than can be displayed simultaneously in the CAS window; refer to
the EAS section in the Pilot’s Guide for more information about CAS operation.

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 Figure 3-6. GDU Softkeys on GDU1 in Full Mode and Split Mode
GDU2 uses softkeys to scroll up or down through Crew Alerting System (CAS) messages when
more messages are present than can be displayed simultaneously in the CAS window, refer to
the EAS section in the Pilot’s Guide for more information on CAS operation.

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3.2.3 Touchscreen Controller
The Touchscreen Controllers are pedestal-mounted user interfaces allowing for ease of data
entry, display pane operation, and NAV/COM tuning. The CNS Bar at the top of the Touchscreen
Controller screen provides radio tuning capability (refer to the Audio and CNS Section for more
information about NAV/COM tuning).

Figure 3-7. GTC 570 Touchscreen Controller

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The Touchscreen Controller’s functions are arranged by screen. Each screen has a title which
appears at the top of the screen area (and below the CNS bar). The contents of each screen
change dynamically in response to flight crew or system input. All of the Touchscreen
Controller’s available functions are accessible from the Home Screen. This screen is displayed
after the Initialization Screen.
The Home Screen may also be accessed any time it is not currently displayed by touching the
Home button in the Button Bar below the screen area. Procedures generally begin from the
Home Screen as a reference point; however it is not necessary to return to the Home Screen
before performing each procedure if the appropriate screen is already displayed.

Figure 3-8. Touchscreen Controller Screen Navigation

As the Touchscreen Controller is used, certain selections will cause another screen to be
displayed. To return to the previous screen, touch the Back Button or the Cancel Button (shown
during data input), or touch the Home Button to return to the Home Screen. If the Home Screen
was the previous screen, pressing either the Back or Home Button will also return to the Home
Screen. The CNS Bar, positioned above the screen area, is always displayed during system
operation and is accessible at any time regardless of what is displayed in the screen area below.
Some functions on the CNS Bar will cause another screen to be displayed in the screen area
below the CNS Bar; however, touching the Back or Cancel Button will return to the previous
screen.

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 Figure 3-9. Accessing Screens with the CNS Bar

The Button Bar, displayed below the screen area, displays the system-level buttons which are
context-sensitive. For example, if scrolling is available on a screen, the Button Bar includes
corresponding Up and Down Scroll Arrow buttons.

Figure 3-10. Button Bar Displays System-Level Buttons

The Button Bar is also where the Home, Cancel, and Back buttons are displayed. If the system
issues a message, the MSG button is shown. Touching this button will display the Messages
Screen. The Button Bar also contains buttons for controlling the size of map displays on the
MFD.

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 Table 3-11. Button Bar Buttons with Functions

The Label Bar, near the bottom of the Touchscreen Controller and above the Joystick and Knobs
displays the current function of each control as a reference. These functions include Map Range
adjustment, display pane selection, radio volume/squelch adjustment, COM radio tuning, and
alphanumeric data entry.

Figure 3-12. Label Bar Indicates Context-Sensitive Joystick

The labels change based on the context of the options being performed. The Touchscreen
Controller recognizes input based on a touch, a gesture (such as sliding a finger), or by pressing
or turning the Knobs or Joystick.
On-screen buttons can be ‘pressed’ by momentarily touching them and then releasing. It is not
necessary to apply pressure, as the infrared touchscreen surface detects the only the presence
and movement of the finger, not pressure. When touched, the button background is highlighted
in blue until the touch is released. If enabled, an aural ‘click’ sound confirms the system has
detected the button touch.

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When releasing the touch, make sure it released within the boundary of the button, otherwise
the input is considered invalid. If enabled, an aural tone then indicates the touch input was not
accepted. Some adjustments are made using horizontal or vertical sliders. To use, simply touch
within the slider box and slide in the desired slider bar direction, then release. The finger may
move outside of the slider box during adjustment; slider movement stops when either the finger
is released or the slider has reached its maximum travel.

Figure 3-13. Sliders on the Touchscreen Controller

Map Detail Adjustment Slider

When a Touchscreen Controller screen window contains more information than the window can
currently show, a scroll bar and scroll buttons appear. To scroll the contents of the window,
touch the controller while moving the finger up or down accordingly within the window. To
scroll more quickly, move the finger up or down rapidly in a flicking motion. Scrolling can also be
performed by pressing the Up or Down scroll buttons. If additional scrolling is required to view
all information in the window, each touch of the scroll button will display one ‘page’ of
information Some screens provide tabs as a means to group multiple categories of information
or buttons. Touch the desired tab to display its contents and manage settings or information.
The Touchscreen Controller highlights the selected tab.

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 Figure 3-14. Touchscreen Controller with Tabs and Scroll Arrows
Elements on the Touchscreen Controller screens (such as buttons and sliders) appear subdued
(dimmed) to indicate their functions are currently not available.

Figure 3-15. Subdued Buttons on Touchscreen Controller

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In some cases, the screen area of the Touchscreen controller (including the buttons) may also
appear subdued to indicate functions on that screen are unavailable while the other
Touchscreen Controller is controlling a particular system resource.
Button Types
Annunciator Buttons operate in an on/off state. An ‘on’ or enabled button displays a green
annunciator; an ‘off’ or disabled button displays a gray annunciator. Touch the annunciator
button to change its state.

Figure 3-16. Touchscreen Controller Annunciator Buttons

Data field Buttons can be modified based on information the flight crew can enter or edit, and
often contain light blue alphanumeric text. Touching data field button will either display a pop-
up window from which a selection can be made, or display a keypad to supply the data. See the
Data Entry discussion in the Pilot’s Guide for more information.

Figure 3-17. Touchscreen Controller Datafield Buttons

In the CNS bar and the Audio and Radios Screen, if a system failure causes a button’s function to
be inaccessible, a yellow ‘X’ appears over the button. The system does not respond when these
buttons are touched.

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 Figure 3-18. Failed Buttons on Touchscreen Controller

Screens
Home Screen

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Aircraft Systems Screen

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Services Screen

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Utilities Screen

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Note: the ‘Mark Event’ button is optional.

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Setup Screen

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3.3 DATA ENTRY
Three methods exist for directly entering alphanumeric data (e.g., waypoint identifiers,
barometric minimum descent altitude) into the system: using the Touchscreen Controller’s
alphanumeric keypad, the large and small right knob on the bottom of the Touchscreen
Controller, or the PFD Knob on the GDU Control Unit. In some instances, such as when entering
an identifier, the system will try to predict the desired identifier based on the characters being
entered. In this case, if the desired identifier appears, use the ENTER Button to confirm the
entry without entering the rest of the identifier manually. This can save the pilot from entering
all the characters of the identifier.
Besides character-by-character data entry, the system also provides a shortcut for entering
waypoint identifiers. When the cursor is on a field awaiting entry of a waypoint identifier,
touching the Find button accesses four different lists of waypoint identifiers for quick selection:
Recent, Nearest, Flight Plan (if active flight plan waypoints are available), and a Favorite
waypoints list. In addition, the system provides the ability to search by Facility Name or by City.
The system will automatically fill in the identifier, facility, and city fields with the information for
the selected waypoint.
Using the Touchscreen Controller keyboard to enter alphanumeric data:
1. Select a Datafield Button the Touchscreen Controller for which data entry is required
(i.e. waypoint, radio frequency, etc.). A keypad will appear, and the Datafield Button
will be highlighted in light blue.
2. Touch the desired letters or numbers, one at a time.
3. If an alphabetic keypad is displayed and numbers are desired, touch the 123... Button.
4. If the numeric keypad is displayed and letters are desired, touch the ABC... Button.
5. To accept the entry, touch the Enter Button. Otherwise, touch the Back, Cancel, or
Home Button (on the Button Bar) to exit the datafield without saving the entry.

Figure 3-19. Entering a Waypoint on the Touchscreen Controller’s Alphanumeric Keypads

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Using the Touchscreen Controller’s large and small right knob to enter data:
1. Select a data field button on the Touchscreen Controller for which data entry is required
(i.e. waypoint, radio frequency, etc.). A keypad will appear, and the data field will be
highlighted in light blue.
2. Begin entering data by turning the small right Knob to select a character for the first
placeholder.
3. Turning the knob to the right scrolls through the alphabet (where appropriate) toward
the letter Z, starting in the middle at K, and the digits zero through nine. Turning the
knob to the left scrolls in the opposite direction.
4. Turn the large right knob to move the cursor to the next placeholder in the field.
5. Repeat, using the small right knob to select a character and the large right knob to move
the cursor, until the field is complete.
6. Press the right knob to confirm entry. Otherwise, touch the Back or Home button to exit
the field without saving the entry.
3.4 SECURE DIGITAL (SD) CARDS
Garmin recommends following the procedures and detailed information regarding Secure Digital
Cards found in the following Learjet AMM Maintenance Manual sections:
SECURE DIGITAL CARDS - DESCRIPTION AND OPERATION
• General: 31-40-01
• Description: 31-40-01
• Operation: 31-40-01
SECURE DIGITAL CARD SYSTEM - MAINTENANCE PRACTICES
• Adjustment/Test: 31-40-02
• Software Loading with the Secure Digital (SD) Card: 31-40-02
3.4.1 ReadyBoost
The Secure Digital (SD) memory cards used in Garmin displays can potentially be harmed by a
feature of the Windows operating system. The ReadyBoost feature available in Windows Vista,
Windows 7 and Windows 8 is a disk caching feature allowing an external flash memory device
such as a USB flash drive or SD card to be used to speed up system operation. ReadyBoost writes
frequently used PC data to the external flash memory device for faster access.

Garmin has determined that ReadyBoost can potentially overwrite required data on any Garmin
SD card installed in a computer with ReadyBoost enabled. A Garmin SD card inserted in to a
computer with ReadyBoost enabled may be rendered unusable. Garmin advises disabling the
ReadyBoost feature if you are using a computer with Windows Vista, 7 and 8 operating systems
to update your Garmin SD cards.

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To disable ReadyBoost:
1. Plug a flash drive or other removable media device (non-Garmin SD card) into your
computer.
2. In the AutoPlay dialog box, under General Options, click Speed up my system.
3. In the Properties dialog box for the removable media device, click the ReadyBoost tab,
and then click Do not use this device to disable ReadyBoost OFF.
4. Click OK.
3.5 G5000 MODES OF OPERATION
The following section describes the various modes of operation for the G5000.
3.5.1 Normal Mode
Normal mode refers to normal operating mode. To start the G5000 system in normal mode,
apply power to the G5000 system. If the displays are already operating in configuration mode
and normal mode is desired, cycle power for the affected displays to restart in normal mode.
3.5.2 GDUs
In normal operations, PFD1 and PFD2 present graphical flight instrumentation (such as heading,
airspeed, altitude, vertical speed) on Primary Flight Displays (PFD) in either Full Mode or Half
Mode. In Full Mode, the PFD (including its softkeys) occupies the entire display portion of the
GDU. In Split Mode, the PFD is condensed to accommodate a display pane on the outboard
portion of the GDU. The reversion/dim panel, mounted in the cockpit, controls the selection of
these operating modes; refer to the AFM for detailed information about this equipment. MFD
shows an Engine Indication and Crew Alerting System (EICAS) display on the left portion of the
GDU. It also shows either a single display pane in Full Mode, or two display panes side-by-side in
Half Mode. The #1 and #2 Touchscreen Controllers select the Full and Half Modes for MFD.
3.5.3 Touchscreen Controllers
In normal operations, the #1 or pilot’s side Touchscreen Controller controls the PFD1 display
pane (in Split Mode), and the MFD left display pane (in Half Mode). The #2 or copilot’s
Touchscreen Controller controls the PFD2 display pane (in Split Mode) and the right display pane
MFD. Either Touchscreen Controller may also control a single MFD display pane in Full Mode. A
button on the Touchscreen Controller indicates when Full Mode or Half Mode is available for
the currently selected MFD display pane. The Touchscreen Controller joysticks select display
panes for control. Refer to the ‘Controlling GDU Display Panes’ discussion in this section for
more information.

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 Figure 3-20. G5000 Normal Operation
3.5.4 Reversionary GDU Operation

NOTE: The system alerts the pilot when the LRUs are communicating using backup paths. Refer
to the Learjet Maintenance Manual for further information regarding system-specific alerts.

If a GDU fails or is off-line, the system provides the capability to show a PFD, an EICAS display,
and a display pane on another GDU in Reversionary Mode.

• GDU1 failure – GDU2 enters reversionary mode if Split Mode is selected for GDU2 on
the cockpit-mounted reversionary/dim panel, otherwise GDU2 continues to operate
normally.
• GDU2 failure – GDU1 and GDU3 enter reversionary mode if Split Mode is selected for
GDU1/GDU3 on the cockpit-mounted reversionary/dim panel, otherwise GDU1 and
GDU3 continue to operate normally.
• GDU3 failure – GDU2 enters reversionary mode if Split Mode is selected for GDU2 on
the cockpit-mounted reversionary/dim panel, otherwise GDU2 continues to operate
normally.

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 Figure 3-21. Reversionary Mode Operation

If GDU2 is operating in Reversionary Mode (e.g. GDU1 or GDU3 failure), the Touchscreen
Controller on the failed GDU side controls the Reversionary Mode display pane. If GDU1 or
GDU3 is in Reversionary Mode, the on-side Touchscreen Controller controls the Reversionary
Mode display pane.

If both GDU1 and GDU3 fail or are off-line, the #1 Touchscreen Controller controls the
Reversionary Mode display pane on GDU2. The #2 Touchscreen Controller’s functions (with the
exception of display pane control) continue to be available in the event of GDU1 and GDU3
failure.
3.5.5 Configuration Mode
Section 4 contains information on configuration mode.
3.5.6 'SET' AND 'ACTIVE' Commands
The SET and ACTIVE commands which are displayed on various configuration pages are used for
setting system input/output conditions.

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 Figure 3-22. SET and ACTIVE Softkeys and Columns

3.5.7 SET and ACTIVE Softkeys

Look for inequalities (configuration mismatches) between the SET and ACTIVE columns during
troubleshooting. Certain problems can be resolved by pressing the SET>ACTV softkey which
reloads settings to the specific LRU (this can also be accomplished by reloading the configuration
files for the LRU using the system software loader card). Use the ACTV>SET softkey with care. If
an improperly configured unit is installed, this softkey causes the wrong configuration to replace
the correct one.
Definitions:
SET—refers to a setting or group of settings that reside in the PFDs internal memory and/or
master configuration module.
ACTIVE—refers to a current setting stored and used in a LRU. LRUs store the ‘active’ settings
within internal memory.
Data can be manually copied from one column to the other by using the following two softkeys:
SET>ACTV (Set to Active) — sends the information in the SET column (data stored in the master
configuration module) to the ACTV column (data used by the LRU).
ACTV>SET (Active to Set)—copies the current settings of the LRU to the master configuration
module as SET items.

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SECTION 4—TROUBLESHOOTING

NOTE
All references in this section made to the GDL 69 also include the GDL 69 SXM.
This section contains system-level troubleshooting information involving one or more of the
following methods:
• Visual Hardware Inspection
• Red/Yellow X Display Indications
• G5000 System Messages
• Maintenance Information System
• GIA And GDU Serial Configuration Page Data Path Indications
• Configuration Pages
• Common G5000 Issues And Recommended Actions
• Autopilot Troubleshooting
• LRU External Connector Information

NOTE
The following table shows the various types of data status indications and their
definitions. These indications are referred to throughout this troubleshooting
section and may help troubleshoot a fault.

INDICATION DESCRIPTION
The LRU is online and reports that the item located next to the indicator box is
communicating.
The LRU is online, and reports that the item located next to the indicator box is
not communicating.
Same as red x (display indications only; does not appear on any configuration
page).
The LRU is not reporting a status for the item located next to the indicator box.
This may be because the data is not available, not applicable, or not expected.

The LRU is not reporting status for the item located next to the indicator box. This
? may be due to the fact that the data is not available or is not expected.

“True” condition; i.e., necessary conditions have met in order to activate the
T item.

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 “False” condition; i.e., necessary conditions have not been met in order to
F activate the item.

INDICATION DESCRIPTION
“High” condition; i.e., the system expects a high voltage or a high resistance input
H to trigger the item (fan operation, etc.).

“Low” condition; i.e., the system expects a low voltage or a low resistance input
L to trigger the item (fan operation, etc.).

4.1 VISUAL HARDWARE INSPECTION

Begin troubleshooting with a visual inspection. Check for corrosion, damage, or other defects.
Replace any damaged parts as required. Inspection may require the temporary removal of an
LRU to gain access to connectors. Follow the instructions given in Section 5 for LRU removal and
replacement.
4.2 RED OR YELLOW X DISPLAY INDICATIONS
When an LRU or an LRU function fails, a large ‘X’ is typically displayed on windows associated
with the failure (Figure 4-1). Depending on the LRU, the ‘X’ may be yellow or red. The following
section describes various red/yellow x’s, their associated LRU(s), and recommended actions to
take.

NOTE
During the time the G5000 is powering up, certain windows remain invalid as
the equipment begins to initialize. All windows should be operational within one
minute of power-up. If any window continues to be flagged, begin
troubleshooting.

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 Figure 4-1. G5000 Major System Failure Annunciations (GDU in Reversionary Mode)
Table 4-1. Red/Yellow X Fields and Recommended Actions
Marking Location/LRU Recommended Actions
GIA1
1. Check the GTC 570 and the PFD for GIA1 configuration,
(see Figure 4-1)
software or failed data path error messages. Correct any
errors before proceeding.
2. Swap GIA1 and GIA2 and reconfigure for their new positions to
verify location of problem.
3. If problem follows GIA1, replace GIA1.
4. Check Ethernet interconnect from GIA1 to PFD1 and unit
connector pins for faults.
5. If problem persists, replace PFD1.
GIA2
1. Check the GTC 570 and the PFD for GIA2 configuration,
(see Figure 4-1)
software or failed data path error messages. Correct any
errors before proceeding.
2. Swap GIA2 and GIA1 and reconfigure for their new positions to
verify location of problem:
• If problem follows GIA2, replace GIA2. Check Ethernet
interconnect from GIA2 to PFD2 and unit connector pins
for faults.
• If problem persists, replace PFD2.

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 GIA1 or 2
1. Check the GTC 570 and the PFD for GIA1/2 configuration, software
(see Figure 4-1)
or failed data path error messages. Correct any errors before
proceeding.
2. Verify the aircraft is located where the GPS antennas have a clear
view of the sky. Check for possible external interference to the GPS
receivers.
3. Check the GPS strength bars on both GPS receivers on the GPS 1 or
GPS 2 STATUS Display on the MFD and the GPS Status Screen on the
Touchscreen Controller. If the signal strength levels are erratic,
disappear and reappear rapidly, or switch between a solid and
hollow bar frequently there is an external device interfering with the
GPS receivers. Turn off any devices that radiate a signal in the local
area or move the aircraft to another location to remove the
interference.
4. Verify the aircraft is not parked in close proximity to a hanger with
the doors open and equipped with a GPS repeater. Verify the GIA’s
are online by checking for a green checkmark next to the GIA on the
GTC 570 avionics status page.
5. If a GIA is not online (a red-x will be present instead of a green check
mark), check for power input faults.
Marking Location/LRU Recommended Actions
XPDR/GTC 570
1. Check the PFD and the GTC 570 for GIA1/2 and GTX 3000
configuration, software or failed data path error messages. Correct
any errors before proceeding.
2. Perform a SET>ACTV configuration reset on the GTX Transponder
LRU: GTX 3000 Configuration page for each installed GTX.
3. Verify the aircraft registration is entered for the transponders on the
GTX Transponder Configuration page.
4. Check the GIA and GTX racks for connector pin faults (push-back or
bent) on the RS-232 interconnect lines.
5. Replace the GTX 3000.

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AIRSPEED
1. Check the GTC 570 and the PFD for PFD1/2, MFD or GDC1/2
ALTITUDE
configuration, software or failed data path error messages. Correct
VERT SPEED
any errors before proceeding.
(see Figure 4-1)
2. Verify the GDC’s are online by checking for a green checkmark next
LRU: GDC 7400 to the GDC on the GTC 570 avionics status page.
3. Swap the GDCs to see if the problem follows the unit.
4. If the GDC is not online (a red-x will be present instead of a green
check mark), check for wiring/power faults and GDC connector
security.
5. Replace the GDC 7400.
6. Inspect GDC 7400 pitot/static ports and plumbing for blockage.
7. Replace the GDC 7400 configuration module.
8. For TAS failures only, replace the GTP 59.

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Marking Location/LRU Recommended Actions
ATTITUDE
1. Check PFD and GTC 570 for PFD, MFD or GRS configuration, software
(see Figure 4-1)
or failed data path error messages. Correct any errors before
proceeding.
LRU: GRS 7800
2. For an attitude failure while parked, check the following:
3. Is the aircraft stationary if GPS is not available? Aircraft movement
(rocking the wings or moving the tail) may cause the attitude and
heading to fail if it believes the aircraft is in motion without GPS
input.
4. Check if the GPS has acquired at least four satellites, has a 3D
navigation solution, and a DOP of less than 5.0.
5. Check for metal objects (tool boxes, power carts, nearby large steel
structures, etc.) around the aircraft that could be interfering with the
magnetometer.
6. Cycle GRS 7800 power to restart initialization.
7. Check the GRS 7800 connecter for security and that proper wire
harness strain relief is provided.
8. Check the GRS 7800 is fastened down tightly in its mounting rack and
that the mounting rack is not loose (CAUTION - do not loosen the
mounting rack hardware to the airframe shelf or the aircraft will need
to be re-leveled and the PITCH/ROLL OFFSET procedure performed).
9. Perform an Engine Run-Up Test to check if engine vibration is causing
the GRS 7800 to go offline.
10. Replace GRS 7800.
11. If problem persists replace the GRS 7800 configuration module.
12. Contact Garmin Aviation Product Support if condition continues after
replacing the GRS 7800 and config module for additional assistance.

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 Marking Location/LRU Recommended Actions
HDG
1. Check PFD and GTC 570 for PFD1/2, MFD, GMU or GRS configuration,
(see Figure 4-1)
software or failed data path error messages. Correct any errors before
proceeding.
LRUs: GRS 7800 and GMU 44
2. Ensure metal objects (tool boxes, power carts, etc.) are not interfering
with the magnetometer and aircraft is not in hangar, near other buildings,
parked over metal drainage culverts or on hard surfaces that may contain
steel reinforcements
3. Cycle power after moving aircraft away from metal objects to determine
if metal objects were the source of the interference. Allow up to five
minutes for the heading to reinitialize.
4. Perform a Magnetometer Interference Test to check for interference
from onboard electrical system components (e.g. NAV lights). Pay
particular attention to any new electrical devices that have been installed
since the aircraft was new. Correct any discrepancies that do not allow
this test to pass before continuing.
5. Ensure GRS 7800 and GMU 44 connectors are secure.
6. Check the wiring and any inline connectors between the GRS and GMU
for faults.
7. Recalibrate the GMU 44.
8. Replace the GMU 44. If problem persists, replace the GRS 7800.

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 Annunciation Recommended Actions
Engine/Airframe Sensors
1. Check GTC 570 and PFD for GIA1/2 or GEA1/2 configuration,
(see Figure 4-1)
software or failed data path error messages. Correct any errors
before proceeding.
LRUs: GEA 71 and
GIA 63W 2. On the PFD in Configuration Mode, turn to the GEA STATUS page
and verify that the GEA internal power supply, configuration,
and calibration status boxes are green.
3. If the internal power supply box is red, check for shorted sensors
that receive 5V, 10V or 12V power from the GEA.
4. Configuration and calibration boxes should be green. If the
calibration status boxes are red, replace the GEA 71.
5. Verify internal, external, and reference voltages listed in the
Main Analog and I/O Analog boxes are not dashed out (does not
include Aircraft Power 1 and 2). If any voltages are dashed out,
replace the GEA.
6. Check the GTC avionics status page to verify GEA is online (green
checkmark on the AUX – SYSTEM STATUS page is present). If GEA
is not online (red-x is present), verify the unit is receiving power
at the GEA rack connector.
7. Replace the GEA 71.
8. If problem persists, check the GIA/GEA interconnects wiring and
unit connector pins for faults.
GRS 7800 Config Module
This indication is displayed if the AHRS/MAG system has been
replaced and has not been calibrated. It also is displayed if there are
problems with the GRS 7800 Config Module and/or associated
wiring.

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4.3 G5000 SYSTEM MESSAGES
In the normal mode of operation the G5000 displays a variety of system messages which will
alert the technician to a problem. System messages are displayed on the GTC 570 notifications
page (Figure 4-2) and are viewed by pressing the MSG softkey. The G5000 displays other
messages, alerts, and annunciations which are pilot related. These are described in detail in the
Garmin G5000 Pilot’s Guide for the Learjet 70/75, P/N 190-01401.

Figure 4-2. G5000 System Messages

The following describes messages pertinent to maintenance, their causes and recommended
actions to take. The messages are in LRU alphabetical order.

4.3.1 GCU 275 PFD Controller System Messages

GCU1 KEYSTK – GCU1 [key name] key is stuck. A key is stuck on the #1 GCU bezel.
• Attempt to free the stuck key by pressing it several times.
GCU2 KEYSTK – GCU2 [key name] key is stuck. A key is stuck on the #2 GCU bezel.
• Attempt to free the stuck key by pressing it several times.

4.3.2 GDC 7400 Air Data Computer System Messages

ADC1 SERVICE – ADC1 needs service. Return unit for repair. A failure has been detected in the
#1 GDC and/or #2 GDC2.
• Replace GDC1 or GDC2.
ADC2 SERVICE – ADC2 needs service. Return unit for repair. A failure has been detected in the
#1 GDC and/or #2 GDC2.
• Replace GDC1 or GDC2.

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4.3.3 GDL 59 System Messages
GDL59 FAIL – GDL 59 has failed. A failure has been detected in the GDL 59. The receiver is
unavailable. The system should be serviced.
• Replace GDL 59.
GDL59 SERVICE – GDL 59 needs service. Return unit for repair. A failure has been detected in
the GDL 59. The system should be serviced.
• Replace GDL 59.
GDL59 RTR FAIL – The GDL 59 router has failed. A failure has been detected in the GDL 59
router. The system should be serviced.
• Replace router.
4.3.4 GDU 1400W System Messages
PFD1 SERVICE-The G5000 has determined PFD1 needs service.
1. Ensure PFD1 connector is fully seated and locked.
2. Disregard the message if the CCFT level rises.
3. Replace the PFD if the CCFT level does not rise.
4. Replace PFD1.
PFD2 SERVICE-the G5000 has determined PFD2 needs service.
1. Ensure PFD2 connector is fully seated and locked.
2. Disregard the message if the CCFT level rises.
3. Replace the PFD if the CCFT level does not rise.
4. Replace PFD2.
MFD1 SERVICE-the G5000 has determined the MFD needs service.
1. Ensure MFD connector is fully seated and locked.
2. Disregard the message if the CCFT level rises.
3. Replace the MFD if the CCFT level does not rise.
4. Replace the MFD.
PFD1 COOLING – PFD1 has poor cooling. Reducing power usage. The PFD and/or MFD is
overheating and is reducing power consumption by dimming the display.
1. Check the cooling fan and wiring.
2. Replace the cooling fan.
3. Replace the display if the problem persists.

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PFD2 COOLING – PFD2 has poor cooling. Reducing power usage. The PFD and/or MFD is
overheating and is reducing power consumption by dimming the display.
1. Check the cooling fan and wiring.
2. Replace the cooling fan.
3. Replace the display if the problem persists.
MFD1 COOLING – MFD1 has poor cooling. Reducing power usage. The PFD and/or MFD is
overheating and is reducing power consumption by dimming the display.
1. Check the cooling fan and wiring.
2. Replace the cooling fan.
3. Replace the MFD if the problem persists.
PFD1 FAN FAIL – PFD1 internal fan failure. The PFD and/or MFD internal cooling fan has failed.
• Replace the fan.
PFD2 FAN FAIL – PFD2 internal fan failure. The PFD and/or MFD internal cooling fan has failed.
• Replace the fan.
MFD1 FAN FAIL – MFD1 internal fan failure.
• Replace the fan.
PFD1 BKLT CAL INV – PFD1 bklt cal lost or mismatch. The PFD and/or MFD backlight calibration
cannot be found or found or is invalid.
• Reload GDU software
• Replace GDU
PFD2 BKLT CAL INV – PFD2 bklt cal lost or mismatch. The PFD and/or MFD backlight calibration
cannot be found or found or is invalid.
• Reload GDU software
• Replace GDU
MFD1 BKLT CAL INV – MFD1 bklt cal lost or mismatch.
• Reload GDU software
• Replace GDU
PFD1 KEYSTK – PFD1 [key name] is stuck. A key is stuck on the PFD and/or MFD bezel.
1. Attempt to free the stuck key by pressing it several times.
2. Select the GDU test page and verify key is stuck (if key is stuck the corresponding
indicator will be green).
3. Exercise suspected stuck key and reset GDU test page to see if indicator remains green
without pressing the key.
4. Replace the display if the problem persists.

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PFD2 KEYSTK – PFD2 [key name] is stuck. A key is stuck on the PFD and/or MFD bezel.
1. Attempt to free the stuck key by pressing it several times.
2. Select the GDU test page and verify key is stuck (if key is stuck the corresponding
indicator will be green).
3. Exercise suspected stuck key and reset GDU test page to see if indicator remains green
without pressing the key.
4. Replace the display if the problem persists.
MFD1 KEYSTK – MFD1 [key name] is stuck.
1. Select the GDU test page and verify key is stuck (if key is stuck the corresponding
indicator will be green).
2. Exercise suspected stuck key and reset GDU test page to see if indicator remains green
without pressing the key.
3. Replace the display if the problem persists.
CNFG MODULE – PFD1 configuration module is inoperative. The PFD1 configuration module
backup memory has failed.

NOTE
The various optional features will need to be reinstalled if the master
configuration module is changed. The G5000 System ID number will change to a
new number when installing a new master config module.
1. Check the master configuration module connector and wiring for damage inside the
GDU connector back plate.
2. Replace the master configuration module wiring and pins.
3. Replace the master configuration module if the problem persists.
PFD1 VOLTAGE – PFD1 has low voltage. Reducing power usage. The PFD1 voltage is low.
1. Check the input voltage to PFD1.
2. Replace PFD1 if the input voltage is correct.
PFD2 VOLTAGE – PFD2 has low voltage. Reducing power usage. The PFD2 voltage is low.
1. Check the input voltage to PFD2.
2. Replace PFD2 if the input voltage is correct.
MFD1 VOLTAGE – MFD1 has low voltage. Reducing power usage. The MFD voltage is low.
1. Check the input voltage to the MFD.
2. Replace the MFD if the input voltage is correct.
NAV DB UPDATED – Active navigation database updated. The standby navigation database has
been copied to the active navigation database.
• No maintenance required.

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TERRAIN DSP – [PFDx or MFD1] Terrain awareness display unavailable. A terrain or
obstacle database required for TAWS in the specified PFD or MFD is missing or invalid.
• Reload database
4.3.5 GIA 63W System Messages
COM1 RMT XFR – COM1 remote transfer key is stuck. The COM1 and/or COM2 transfer switch is
stuck in the enabled (or “pressed”) position.
1. Press the transfer switch again to cycle its operation.
2. Press the COM1 external remote transfer switch again to cycle its operation.
3. Check COM1 remote transfer switch and wiring.
4. Switch GIA1 and GIA2, to verify location of problem.
5. If problem follows the unit, replace GIA1.
COM2 RMT XFR – COM2 remote transfer key is stuck. The COM1 and/or COM2 transfer switch is
stuck in the enabled (or “pressed”) position.
1. Press the transfer switch again to cycle its operation.
2. Press the COM2 external remote transfer switch again to cycle its operation.
3. Check COM2 remote transfer switch and wiring.
4. Switch GIA1 and GIA2, to verify location of problem.
5. If problem follows the unit, replace GIA2.
RAIM UNAVAIL – RAIM is not available from FAF to MAP waypoints. GPS satellite coverage is
insufficient to perform Receiver Autonomous Integrity Monitoring (RAIM) from the FAF to the
MAP waypoints.
• No maintenance required.
LOI – GPS integrity lost. Crosscheck with other NAVS. Loss of GPS integrity monitoring.
• No maintenance required.
GPS NAV LOST – Loss of GPS navigation. Insufficient satellites. Loss of GPS navigation due to
insufficient satellites.
• No maintenance required.
GPS NAV LOST – Loss of GPS navigation. Position error. Loss of GPS navigation due to position
error.
• No maintenance required.

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GPS NAV LOST – Loss of GPS navigation. GPS fail. Loss of GPS navigation due to GPS failure.
1. Verify the area the aircraft was traveling through did not have loss of GPS coverage.
FAA NOTAMs may be issued for periods of outages, or the US Coast Guard website
http://www.navcen.uscg.gov/gps/gpsnotices/default.htm will have notices posted.
2. Using the MFD AUX - GPS status page, verify the signal strength bars are not erratic. If
so, this indicates outside interference is affecting the GPS receivers. Find and remove
the source of interference.
3. Check GPS antenna and cabling.
ABORT APR – Loss of GPS navigation. Abort approach. Abort approach due to loss of GPS
navigation.
• No maintenance required.
TRUE APR – True north approach. Change HDG reference to true. Displayed after passing the
first waypoint of a true north approach when the nav angle is set to ‘AUTO’.
• No maintenance required.
GPS1 FAIL – GPS1 is inoperative. A failure has been detected in the GPS1 and/or GPS2 receiver.
The receiver is unavailable.
1. Switch GIA1 and GIA2, to verify location of problem.
2. If problem follows the unit, replace GIA1.
3. If problem does not follow the unit, check GPS1 antenna and cabling.
GPS2 FAIL – GPS2 is inoperative. A failure has been detected in the GPS1 and/or GPS2 receiver.
The receiver is unavailable.
1. Switch GIA1 and GIA2, to verify location of problem.
2. If problem follows the unit, replace GIA2.
3. If problem does not follow the unit, check GPS2 antenna and cabling.
GPS1 SERVICE – GPS1 needs service. A failure has been detected in the GPS1 and/or GPS2
receiver. The receiver may still be available.
• Replace GIA1.
GPS2 SERVICE – GPS2 needs service.
• Replace GIA2.
NAV1 SERVICE – NAV1 needs service. A failure has been detected in the NAV1 and/or NAV2
receiver. The receiver may still be available.
• Replace GIA1.
NAV2 SERVICE – NAV2 needs service. A failure has been detected in the NAV1 and/or NAV2
receiver. The receiver may still be available.
• Replace GIA2.

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NAV1 RMT XFR – NAV1 remote transfer key is stuck. The remote NAV1 and/or NAV2 transfer
switch is stuck in the enabled (or “pressed”) state.
1. Press the transfer switch again to cycle its operation.
2. Check NAV1 remote transfer switch and wiring.
3. Switch GIA1 and GIA2, to verify location of problem.
4. If problem follows the unit, replace GIA1.
NAV2 RMT XFR – NAV2 remote transfer key is stuck. The remote NAV1 and/or NAV2 transfer
switch is stuck in the enabled (or “pressed”) state.
1. Press the transfer switch again to cycle its operation.
2. Check NAV2 remote transfer switch and wiring.
3. Switch GIA1 and GIA2, to verify location of problem.
4. If problem follows the unit, replace GIA2.
G/S1 FAIL – G/S1 is inoperative. A failure has been detected in glideslope receiver 1 and/or
receiver 2.
1. Switch GIA1 and GIA2 to verify location of problem:
2. If problem follows the unit, replace GIA.
3. If problem does not follow unit, check G/S1 antenna and cabling.
G/S2 FAIL – G/S2 is inoperative. A failure has been detected in glideslope receiver 1 and/or
receiver 2.
1. Switch GIA1 and GIA2 to verify location of problem
2. If problem follows the unit, replace GIA.
3. If problem does not follow unit, check G/S2 antenna and cabling.
G/S1 SERVICE – G/S1 needs service. A failure has been detected in glideslope receiver 1 and/or
receiver 2. The receiver may still be available.
1. Switch GIA1 and GIA2 to verify location of problem:
2. If problem follows the unit, replace GIA.
3. If problem does not follow unit, check G/S1 antenna and cabling.
G/S2 SERVICE – G/S2 needs service. A failure has been detected in glideslope receiver 1 and/or
receiver 2. The receiver may still be available.
1. Switch GIA1 and GIA2 to verify location of problem:
2. If problem follows the unit, replace GIA.
3. If problem does not follow unit, check G/S2 antenna and cabling.
HW MISMATCH – GIA1 hardware mismatch, GIA1 communication halted. A GIA mismatch has
been detected, where only one is WAAS capable.

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 • Replace GIA1 with a WAAS unit.
HW MISMATCH – GIA hardware mismatch, GIA2 communication halted. A GIA mismatch has
been detected, where only one is WAAS capable.
• Replace GIA 2 with a WAAS unit.
COM1 TEMP – COM1 over temp. Reducing transmitter power. The system has detected an over
temperature condition in COM1 and/or COM2. The transmitter operates at reduced power.
1. Check fan, wiring and air tubing for proper operation (if applicable).
2. Replace cooling fan if unable to determine if operating correctly.
3. Replace GIA1.
COM2 TEMP – COM2 over temp. Reducing transmitter power. The system has detected an over
temperature condition in COM1 and/or COM2. The transmitter operates at reduced power.
1. Check fan, wiring and air tubing for proper operation (if applicable).
2. Replace cooling fan if unable to determine if operating correctly.
3. Replace GIA2.
COM1 SERVICE – COM1 needs service. The system has detected a failure in COM1 and/or
COM2. COM1 and/or COM2 may still be usable.
• Replace GIA1.
COM2 SERVICE – COM2 needs service. The system has detected a failure in COM1 and/or
COM2. COM1 and/or COM2 may still be usable.
• Replace GIA2.
LOI – GPS integrity lost. Crosscheck with other NAVS. GPS integrity is insufficient for the current
phase of flight.
• No maintenance required.
APR DWNGRADE – Approach downgraded. Vertical guidance generated by SBAS is unavailable.
Use only LNAV minimums.
• No maintenance required.
RAIM UNAVAIL – RAIM is not available from FAF to MAP waypoints. GPS satellite coverage is
insufficient to perform Receiver Autonomous Integrity Monitoring (RAIM) from the FAF to the
MAP waypoints.
• No maintenance required.
UNABLE RNP – Estimated position error exceeds RNP. The estimated GPS position error exceeds
the RNP limits.
• No maintenance required.
UNABLE RNP APR – GPS integrity lost. The estimated GPS position error exceeds the
requirements for the current approach.
• No maintenance required.

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APR ADVISORY – SBAS VNAV not available. Using Baro VNAV. SBAS VNAN not available.
• No maintenance required.
4.3.6 GMA 36 System Messages
GMA1 FAIL - GMA 1 is inoperative. The G5000 has detected a failure in GMA1.
1. Ensure GMA1, both GIAs and all GDUs are receiving power.
2. Troubleshoot for a failed data path.
3. Replace GMA1.
GMA2 FAIL - GMA 2 is inoperative. The G5000 has detected a failure in GMA2.
1. Ensure GMA2, both GIAs and all GDUs are receiving power.
2. Troubleshoot for a failed data path.
3. Replace GMA2.
GMA1 SERVICE – GMA1 needs service. Return unit for repair. The audio panel self-test has
detected a problem in the unit. Certain audio functions may still be available, and the audio
panel may still be usable. The system should be serviced when possible.
• Replace GMA1.
GMA2 SERVICE – GMA 2 needs service. Return unit for repair. The audio panel self-test has
detected a problem in the unit. Certain audio functions may still be available, and the audio
panel may still be usable. The system should be serviced when possible.
• Replace GMA2
4.3.7 GMC 7250 System Messages
GMC FAIL – GMC is inoperative. A failure has been detected in the GMC 7250. The GMC 7250 is
unavailable.
• Replace GMC.
GMC KEYSTK – GMC [key name] key is stuck. A key is stuck on the GMC 7250 bezel. The system
should be serviced if the problem persists.
1. Attempt to free the stuck key by pressing it several times.
2. Replace the GMC if problem persists.
4.3.8 GMU 44 System Messages
HDG FAULT – AHRS1 magnetometer fault has occurred. A fault has occurred in the #1 GMU 44.
Heading is flagged as invalid. The AHRS uses GPS for backup mode operation.
1. Check GMU 44/GRS 7800 interconnect for faults.
2. Replace GMU 44 #1.
3. If problem persists, replace GRS 7800 #1.
HDG FAULT – AHRS2 magnetometer fault has occurred. A fault has occurred in the #2 GMU 44.
Heading is flagged as invalid. The AHRS uses GPS for backup mode operation.

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 1. Check GMU 44/GRS 7800 interconnect for faults.
2. Replace GMU 44 #2.
3. If problem persists, replace GRS 7800 #2.
GMU1 MANIFEST - GMU1 software mismatch, communication halted. The GMU 44 has incorrect
software installed.
• Reload correct software.
GMU2 MANIFEST - GMU2 software mismatch, communication halted. The GMU 44 has incorrect
software installed.
• Reload correct software.
4.3.9 GRS 7800 System Messages
AHRS1 TAS – AHRS1 not receiving valid airspeed. The #1 AHRS is not receiving true airspeed
from the air data computer. The AHRS relies on GPS information to augment the lack of
airspeed.
1. Check GRS1/GDC1 interconnect.
2. Replace GDC1.
3. If problem persists, replace GRS1.
AHRS2 TAS – AHRS2 not receiving valid airspeed. The #2 AHRS is not receiving true airspeed
from the air data computer. The AHRS relies on GPS information to augment the lack of
airspeed.
1. Check GRS2/GDC2 interconnect.
2. Replace GDC2.
3. If problem persists, replace GRS2.
AHRS1 GPS – AHRS1 using backup GPS source. The #1 AHRS is using the backup GPS path.
Primary GPS path has failed.
1. Check GPS status for GIA 1 and 2. If one or both GPS receivers cannot acquire a position
lock, troubleshoot the GPS.
2. Replace the GRS 7800.
AHRS2 GPS – AHRS2 using backup GPS source. The #2 AHRS is using the backup GPS path.
Primary GPS path has failed.
1. Check GPS status for GIA 1 and 2. If one or both GPS receivers cannot acquire a position
lock, troubleshoot the GPS.
2. Replace the GRS 7800.
AHRS1 GPS – AHRS1 not receiving any GPS information. The #1 AHRS is not receiving any or any
useful GPS information.
1. Check AFMS limitations.

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 2. Check GPS status for GIA 1 and 2. If one or both GPS receivers cannot acquire a position
lock, troubleshoot the GPS.
3. Replace the GRS 7800.
AHRS2 GPS – AHRS2 not receiving any GPS information. The #2 AHRS is not receiving any or any
useful GPS information.
1. Check AFMS limitations.
2. Check GPS status for GIA 1 and 2. If one or both GPS receivers cannot acquire a position
lock, troubleshoot the GPS.
3. Replace the GRS 7800.
AHRS1 GPS – AHRS1 not receiving backup GPS information. The #1 AHRS is not receiving backup
GPS information.
1. Check GPS status for GIA 1 and 2. If one or both GPS receivers cannot acquire a position
lock, troubleshoot the GPS.
2. Replace the GRS 7800.
AHRS2 GPS – AHRS2 not receiving backup GPS information. The #2 AHRS is not receiving backup
GPS information.
1. Check GPS status for GIA 1 and 2. If one or both GPS receivers cannot acquire a position
lock, troubleshoot the GPS.
2. Replace the GRS 7800.
AHRS1 GPS – AHRS1 operating exclusively in no-GPS mode. The #1 AHRS is operating exclusively
in no-GPS mode.
1. Check GPS status for GIA 1 and 2. If one or both GPS receivers cannot acquire a position
lock, troubleshoot the GPS.
2. Replace the GRS 7800.
AHRS2 GPS – AHRS2 operating exclusively in no-GPS mode. The #2 AHRS is operating exclusively
in no-GPS mode.
1. Check GPS status for GIA 1 and 2. If one or both GPS receivers cannot acquire a position
lock, troubleshoot the GPS.
2. Replace the GRS 7800.
AHRS MAG DB – AHRS magnetic model database version mismatch. The #1 AHRS and #2 AHRS
magnetic model database versions do not match.
• Update magnetic field model when practical.
AHRS1 SRVC – AHRS1 Magnetic-field model needs update. The #1 AHRS earth magnetic field
model is out of date.
• Update magnetic field model when practical.
AHRS2 SRVC – AHRS2 Magnetic-field model needs update. The #2 AHRS earth magnetic field
model is out of date.

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 • Update magnetic field model when practical.
GEO LIMITS – AHRS1 too far north/south, no magnetic compass. The aircraft is outside
geographical limits for approved AHRS operation. Heading is annunciated as invalid.
• No maintenance required.
GEO LIMITS – AHRS2 too far north/south, no magnetic compass.
• No maintenance required.
GRS1 MANIFEST – GRS1 software mismatch, communication halted. The #1 AHRS has incorrect
software installed.
• Install correct software.
GRS2 MANIFEST – GRS2 software mismatch, communication halted. The #2 AHRS has incorrect
software installed.
• Install correct software.
4.3.10 GTC 570 System Messages
GTC1 SERVICE – GTC1 needs service.
• Replace GTC1.
GTC2 SERVICE – GTC2 needs service.
• Replace GTC2.
GTC1 COOLING – GTC1 has poor cooling. Reducing power usage. The GTC 570 has insufficient
cooling.
1. Check fan, wiring and air tubing for proper operation (if applicable).
2. Replace cooling fan if unable to determine if operating correctly.
3. Replace GTC1.
GTC2 COOLING – GTC2 has poor cooling. Reducing power usage. The GTC 570 has insufficient
cooling.
1. Check fan, wiring and air tubing for proper operation (if applicable).
2. Replace cooling fan if unable to determine if operating correctly.
3. Replace GTC2.
GTC1 FAN FAIL – GTC1 internal fan failure.
• Replace GTC1 fan.
GTC2 FAN FAIL – GTC2 internal fan failure.
• Replace GTC2 fan.
GTC1 VOLTAGE – GTC1 has low voltage. Reducing power usage. The GTC 570 is operating with
reduced power.
1. Check input voltage to GTC1.

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 2. If input voltage is ok, replace GTC1.
GTC2 VOLTAGE – GTC2 has low voltage. Reducing power usage. The GTC 570 is operating with
reduced power.
1. Check input voltage to GTC2.
2. If input voltage is ok, replace GTC2.
GTC1 CARD1 ERR – GTC1 card 1 is invalid. The internal SD card in the GTC 570 contains invalid
data.
1. Confirm supplemental data card is inserted fully in the bottom slot of the display.
2. Move the data card to the top slot of the display.
3. If the error clears, the problem is with the bottom slot. Insert and remove a SD card
multiple times to clean the contacts. If the card still does not work in the bottom slot,
leave the card in the top slot or replace the display.
4. Swap with a supplemental data card from another display in the same system.
5. If problem moves to the other display, reload the database on the data card or replace
the supplemental data card. You may need to replace all data cards as a set to keep the
database cycles the same and prevent database mismatch errors.
6. If problem remains in the same GTC, replace that GTC.
GTC2 CARD1 ERR – GTC2 card 1 is invalid. The internal SD card in the GTC 570 contains invalid
data.
1. Confirm supplemental data card is inserted fully in the bottom slot of the display.
2. Move the data card to the top slot of the display.
3. If the error clears, the problem is with the bottom slot. Insert and remove a SD card
multiple times to clean the contacts. If the card still does not work in the bottom slot,
leave the card in the top slot or replace the display.
4. Swap with a supplemental data card from another display in the same system.
5. If problem moves to the other display, reload the database on the data card or replace
the supplemental data card. You may need to replace all data cards as a set to keep the
database cycles the same and prevent database mismatch errors.
6. If problem remains in the same GTC, replace that GTC.
GTC KEYSTK – GTC1 [key name] key is stuck. A knob or joystick is stuck on the GTC 570 bezel.
• Attempt to free the stuck control by pushing or turning it several times.
GTC KEYSTK – GTC2 [key name] key is stuck. A knob or joystick is stuck on the GTC 570 bezel.
• Attempt to free the stuck control by pushing or turning it several times.

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4.3.11 GTS 8000 System Messages
GTS CONFIG – GTS Config error. Config service req'd. The GTS 8000 and GDU have different
copies of the GTS 8000 configuration, or the Mode S address is invalid.

NOTE
Option and unlock card will need to be replaced if the master configuration
module is changed. The G5000 System ID number will change to a new number
when installing a new master config module.
1. Perform a SET>ACTV configuration reset on the GTS configuration page.
2. If error is still present, reload config files from a loader card.
3. If problem persists, replace master configuration module, check config module harness
for faults and replace if necessary.
4.3.12 GTX 3000 System Messages
XPDR1 ADSB-B FAIL – XPDR1 is inoperative. There is no communication with the #1 transponder.
1. Troubleshoot for a failed data path.
2. Check communication paths.
3. Replace GTX1.
XPDR2 ADSB-B FAIL – XPDR2 is inoperative. There is no communication with the #2 transponder.
1. Troubleshoot for a failed data path.
2. Check communication paths.
3. Replace GTX2.
4.3.13 GDR 66 System Messages
CPDLC – CPDLC connection lost. Data link connection has been lost.
• Establish new connection.
CPDLC – CPDLC facility logon failed. Logon failed.
• Check pertinent entries for accuracy.
CPDLC – CPDLC data link available. Logon is still required. The data link is ready for use, but
logon to the facility has not yet taken place.
• Logon.
GDR TEMP – GDR over temp. Reducing transmitter power. The system has detected an over
temperature condition in the GDR. The transmitter operates at reduced power.
• If the problem persists, replace the GDR 66.
GDR FAIL – GDR is inoperative. A failure has been detected in the GDR.
• Replace the GDR 66.

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GDR TX FAIL – GDR transmitter is inoperative.
1. Check antenna for faults and unit for extreme temperatures.
2. Replace the GDR 66.
GDR PTT – GDR push-to-talk key is stuck. The GDR push-to-talk switch is stuck in the enable (or
“pressed”) position.
1. Press the PTT switch again to cycle its operation.
2. If the problem persists, replace the GDR 66.
GDR RMT XFR – GDR remote transfer key is stuck. The GDR transfer switch is stuck in the
enabled (or “pressed”) position.
1. Press the transfer switch again to cycle its operation.
2. If the problem persists, replace the GDR 66.
GDR SERVICE – GDR needs service.
• Replace the GDR 66.
GDR CONFIG – GDR config error. Config service req’d. GDR configuration settings do not match
those of backup configuration memory.
• Replace the GDR 66.
GDR MANIFEST – GDR software mismatch, communication halted. The GDR has incorrect
software installed.
1. Install the correct software.
2. If problem persists, replace the GDR 66.
GDR AUX MANIFEST – GDR AUX software mismatch, communication halted. The GDR secondary
processor has incorrect software installed.
1. Install the correct software.
2. If problem persists, replace the GDR 66.

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4.4 MAINTENANCE INFORMATION SYSTEM (DATA LOGGING AND DIAGNOSTICS)
Data logging and diagnostics acquires aircraft system information through the engine and
airframe units, data concentrators, and integrated avionics units by the high-speed data bus
(HSDB). Line replaceable units transfer information directly to DU 2 for storage. The
maintenance information system (MIS) allows for the line replaceable units that follow.
 Data logging and diagnostics of fault and CMC messages
 Continuous data logging, configurable continuous data logging
 Exceedance capture
 Trend capture
 Service messages
 Life cycle data
Figure 4-3 shows the maintenance information top level functionality.

Figure 4-3. Overview of Data Logging and Transfer

The maintenance information system gives four methods for data transfer.
• Data/logs can be copied to the SD card in the top slot of the MFD.
• Data/logs can be transferred by wire to a laptop through the maintenance connector
panel.
• The GDL 59 is used for transferring a selected report via Wi-Fi. This is possible when the
aircraft is near a Wi-Fi hotspot on the ground.

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 • The GSR 56 is used for data transfer via Iridium satellite link. The GSR 56 allows for in-
flight or on-ground transfer of logs.
Refer to the following sections in the Learjet AMM for instructions on the Maintenance
Information System:
MAINTENANCE INFORMATION SYSTEM - DESCRIPTION AND OPERATION
• Description-Section 45-45-00
• Operation-Section 45-45-00
MAINTENANCE INFORMATION SYSTEM - MAINTENANCE PRACTICES
• Adjustment/Test-Section 45-45-00
• Functional Test of the Iridium Satcom System-Section 45-45-00
MAINTENANCE DATA RECORDER AND WIRELESS DATALINK UNIT-MAINTENANCE PRACTICES
• Removal/Installation-Section 45-45-02
• Removal of the Maintenance Data Recorder and Wireless Datalink Unit-Section 45-45-
02
• Installation of the Maintenance Data Recorder and Wireless Datalink Unit-Section 45-
45-02
WIRELESS DATALINK ANTENNA - MAINTENANCE PRACTICES
• Removal/Installation-Section 45-45-03
• Removal of the Wireless Datalink Antenna-Section 45-45-03
• Installation of the Wireless Datalink Antenna-Section 45-45-03

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 4.5 GIA AND GDU SERIAL CONFIGURATION PAGE DATA PATH INDICATIONS
The GIA and GDU Serial Configuration pages can be used to troubleshoot possible LRU faults by
observing the data indicators.
SELECT UNITS—MFD/PFD1/PFD2/GIA1/GIA2
ARINC 429/RS-232/RS-485 WINDOW

Data Status/Recommended Actions

Indicator
 SELECT UNIT/LRU data path is functioning correctly.
1. SELECT UNIT/LRU data path is not functioning correctly.
2. Check GTC 570 avionics status page for SELECT UNIT or LRU configuration or
software error messages. Correct any errors before proceeding.
3. If applicable, check the SELECT UNIT/LRU interconnect wiring and unit
connector pins for faults.
4. Replace LRU.
5. Reload SELECT UNIT config file.
6. If problem remains, replace SELECT UNIT.
7. Remove SELECT UNIT and verify power and ground are present at the
appropriate connector.
• If power or ground is not present, troubleshoot aircraft wiring for faults.
• If power and ground are present, check the select unit and LRU
connector for damaged or pushback pins.
8. Swap PFD1 and PFD2 to confirm if the problem is in the original PFD1.
9. Replace original PFD1 if box displays green check after swapping displays.
10. Ensure LRU connecter is secure and proper wire harness strain relief is
provided.
11. Swap LRU #1 and LRU #2 to confirm if the problem is in the original LRU #1.
12. Replace original LRU #1 if box displays green check after swapping units.
1. SELECT UNIT/LRU data path functionally is unknown.
2. Reload SELECT UNIT configuration file.

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4.6 CONFIGURATION PAGES
4.6.1 General System Awareness
Configuration pages can help identify a fault by observing the values and symbology in the data
fields for various G5000 subsystems and LRUs. This section describes the configuration pages
and gives a basic definition of their various fields. Configuration data is loaded to the LRUs from
an aircraft-specific Garmin software loader card. Settings are typically are predetermined for a
specific aircraft. Different security levels exist for configuration pages. Most pages contain flight
critical information and cannot be accessed using normal methods.
4.6.2 Configuration Page Security and General Information
The following levels of security apply to the configuration pages.
LEVEL ACCESS DATA SECURITY MEASURE
1 Pilot Access Pilot profiles, etc. None
1 Line Techs (day- Basic configuration and Hold down <ENT> key on
to-day) statuses (non- the GDU at power- up.
catastrophic)
2* Line Techs GDL 69 antenna Hold down <ENT> key on
(experienced) configuration, GDL 69 the GDU at power- up,
present configuration, and AND enter key
Fuel sequence** on protected
pages.
3 Line Techs GEA, GRS, and ADC Hold down <ENT> key on
(experienced) configuration and the GDU at power- up,
calibration AND enter key
sequence** on protected
pages.
4*, 5, 6* OEM/Dealer Airframe/alert Insert special card into
(STC/TC) configuration and GDU before power-up,
diagnostics AND hold down <ENT>
key on the GDU at power-
up.

*Pages with level 2 security allow limited page modification prior to entering a key sequence.
Pages with level 4 security allow limited page modification without a special card inserted. Pages
with level 6 security will be hidden when the special card is not present at power up.
**For security level and passwords on individual configuration pages, refer to each page's
requirements, security section. If not specified, pages have level 1 configuration security. No
configuration changes are allowed on any configuration mode page while the aircraft is in flight
unless a specified key sequence of softkeys 12, 11, 10, 12 is entered on the System Status page.
A yellow message with the text "IN-AIR CONFIGURATION LOCKOUT" is displayed in the extreme
upper right corner of the display when in configuration mode and changes are prohibited due to
the aircraft being in flight.

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4.6.3 Configuration Enable Card
A configuration enable card allows configuration changes on pages with all security levels,
without requiring any passwords. To prevent configuration changes on GDUs other than PFD1,
only the following configuration pages are enabled on GDUs other than PFD1 when a
configuration unlock card is not present:
• SYSTEM - SYSTEM STATUS
• SYSTEM - OEM DIAGNOSTICS
• GDU - GDU STATUS
• GDU - GDU TEST
• GDU - SERIAL / ETHERNET I/O
• GDU - ALERT CONFIGURATION
• GRS - GRS / GMU CALIBRATION
Configuration mode changes on GDUs other than PFD1 are not prevented if a configuration
unlock card is present.
4.6.4 Configuration Mode
To start the G5000 system in configuration mode (all displays), do the following:
1. Apply power to the G5000 system by applying aircraft EXT power and energizing all
electrical buses.
2. Select displays OFF using the DU reversion knobs on the pedestal.
3. Press and hold the far right softkey on PFD2 while applying power by using the DU3
reversion knob on the pedestal.
4. Release the softkey after ‘INITIALIZING SYSTEM’ appears in the upper left corner of
PFD2.
5. Press and hold the far right softkey on the MFD while applying power by using the DU2
reversion knob on the pedestal.
6. Release the softkey after ‘INITIALIZING SYSTEM’ appears in the upper left corner of the
MFD.
7. Press and hold the far right softkey on PFD1 while applying power by using the DU1
reversion knob on the pedestal.
8. Release the ENT key after ‘INITIALIZING SYSTEM’ appears in the upper left corner of
PFD1.
If the display(s) are already operating in normal mode and configuration mode is desired for
PFD1 only, do the following:
1. Select DU1 off by using the DU1 reversion knob.
2. Press and hold the far right softkey on PFD1 while applying power by using the DU1
reversion knob.

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 3. Release the softkey after ‘INITIALIZING SYSTEM’ appears in the upper left corner
of PFD1. A configuration page groups menu ceases to show (timeout) when no
page navigation attempt has occurred in five seconds.
Configuration pages are selected by using the PFD knob on the GCU 275 controller (Figure 4-5).
To select the page groups use the large knob, to select pages within a group, turn the small
knob.

Figure 4-4. GCU 275 Controller PFD Knob

4.6.5 Configuration Page Groups and Descriptions

Figure 4-5. Configuration Pages and Page Groups

Figure 4-6. Configuration Page Title

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When the associated LRUs are configured, the configuration pages are grouped and ordered
according to the following (Figure 4-5):

• SYSTEM
• GDU
• GIA
• GSD
• GEA
• GTX
• GRS
• ADC
• GFC
• GMA
• GDL
• RMT
• GWX
• GTS
• CAL

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The following sections describe various configuration pages and their basic definition.
4.6.5.1 System Group
System Status Page

NOTE: The System Status page is protected by a boot disk. The page does not allow softkey
operations when the
boot disk is not present.
Data
The System Status page displays the following data:
• Indications that show the presence or non-presence of LRUs (green checkmark, red x).
The System Status page displays a list of LRUs that are configured. The following data is
displayed for a selected LRU:
• Part Number
• Version
• Product
• Copyright
• Serial Number
• Model Number
• Functions Present
• Status

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Time Configuration Page

Data
The Date/Time Setup Configuration page displays the following data:
• UTC date
• UTC time
Operations
The Date/Time Setup Configuration page allows the following operations:
• Set the system UTC date by highlighting the date field and using PFD knob entry
• Set the system UTC time by highlighting the time field and using PFD knob entry

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Lighting Configuration Page

Data
The Lighting Configuration page displays the following data when a GDU is selected:
• Current GDU unit selected
• Current display and key backlight source input value and current display and key
backlight intensity
• Automatic display and key backlight source
• Display and key backlight filter response time and display and key backlight filter
minimum value
The Lighting Configuration page displays the following data when a remote controller is
selected:
• Current remote controller unit selected
• Current annunciator and backlight source input value and current annunciator and
backlight intensity
• Set and active automatic annunciator and backlight source, filter response time, and
filter minimum value
Note: The filter minimum value defines the minimum lighting intensity for the display and key
backlight. The filter minimum overrides the lighting curve settings when the minimum provides
a greater intensity than the lighting curve.
• GMA annunciator and key backlight intensity (if a GMA associated with the selected
GDU is configured to be present)
• GMA annunciator and key offset (if a GMA associated with the selected GDU is
configured to be present)

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 • Display and key curve vertices and key photo curve vertices
Note: The filter minimum value defines the minimum lighting intensity for the annunciator and
backlight. The filter minimum overrides the lighting curve settings when the minimum provides
a greater intensity than the lighting curve.
• Annunciator and backlight vertex selected
• Set and active annunciator and backlight curve vertices
• Set and active annunciator and backlight photo curve vertices

System Audio

Data
The System Audio page displays the following data:
• Audio clip name
• Audio clip volume
• Altitude alerter threshold clip (tone 1, tone 2, off)
• Altitude alerter deviation limit clip (tone 1, tone 2, off)
• Altitude alerter beyond limit clip (tone 1, tone 2, off)
Operations
The Audio Clip Configuration page allows the following operations:
• Change audio clip volume with the volume field highlighted
• Change audio alert voice type (male or female) with the voice field highlighted
• Test playback of any available audio clips via selection from the audio clip drop-down list
and highlighting the "PLAY?" or "TEST?" field and pressing ENT
• Stop playback of any available audio clips via highlighting the "STOP?" field and pressing
ENT

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 • Change altitude alerter threshold clip (tone 1, tone 2, off)
• Change altitude alerter deviation limit clip (tone 1, tone 2, off)
• Change altitude alerter beyond limit clip (tone 1, tone 2, off)

System Upload Page

Data
The System Upload Configuration page displays the following data:
• Group List
• Item List
• Product List
The System Upload page compares the software part numbers on the loader card and in the LRU
and performs the following operations:
• Inhibit both software and configuration upload by denoting "N/A" on both fields if the
part numbers are mismatched
• Allow software and configuration (if available) upload with checkbox(es) if the part
numbers are matching
• Display the product in the product list and allow software and configuration (if available)
upload with checkbox(es) if the reported serial number is less than or equal to the
specified maximum and greater than or equal to the specified minimum

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 • Display the product in the product list but mark the software and configuration fields
with the text "INV", displayed in yellow, if the serial number is not being reported by the
LRU
Configuration Items
The System Upload page supports the configuration of the following products:
• Airframe
• System
• MFD 1
• PFD 1
• PFD 2
• GIA 1
• GIA 2
• Pilot GMA
• Co-pilot GMA
• GTX 1
• GTX 2
• GEA 1
• GEA 2
• GEA 3
• Pilot GDC
• Copilot GDC
• GDL69
• GWX
• GCU
• GMC
• Audio
• GSD 1
• GSD 2
• GDL59
• GTS
• COM 1
• COM 2
• Digital GMA 1

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 • Digital GMA 2
Commands
The System Upload page supports the following commands:
• Clear Configuration
• The Clear Configuration command supports the following options:
• Clear all configuration data
• Clear airframe configuration data
• Clear configuration data for airframe alerts and triggers
• Clear configuration data for CMC alerts and triggers
Summary
• A list of attempted uploads and their result in the Summary window
• A visual result next to an item's checkbox (could be both software and configuration)
with a result of PASS (in green text) or FAIL (in red text)
• If serial number checking is enabled for a product and a serial number is not being
reported by the LRU, an attempt to load the product fails immediately and display the
text "NO SERIAL REPORTED" in the Summary window
Status
• The upload status is displayed using the progress pop-up window
Configuration ID
• The configuration ID is displayed in the upper left corner
• The configuration ID is updated after a load configuration or a clear configuration
operation is completed.
Operations
The System Upload Configuration page allows the following operations:
• Selecting an airframe and configuration/software to load
• Checking or unchecking a checkbox which determines if the page will attempt to load
that particular
• product's software/configuration by highlighting the software/configuration checkbox
for a product and pressing ENT
• Starting an upload by pressing the LOAD softkey
• Canceling an upload by pressing the CANCEL softkey
• Using the SMRY UP and SMRY DN softkeys to scroll through the summary window
• Updating the configuration backup module with the internal configuration values using
the UPDT CFG Softkey

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 • When an unlock card is inserted, CLR CFG softkey is displayed on tier #1
• Accessing tier #2 softkeys when CLR CFG softkey is pressed
• Clear all configuration data when CLR ALL softkey is pressed
• Clear airframe configuration data when CLR AFRM softkey is pressed
• Clear configuration data for airframe alerts and triggers when CLR CAS softkey is pressed
• Clear configuration data for CMC alerts and triggers when CLR CMC softkey is pressed
Aircraft Configuration Page

LRU Configuration Status

A green checkbox indicates that the unit is properly configured and is communicating normally.
A yellow question mark symbol indicates that the unit configuration is invalid. A red X indicates
or that the unit is not communicating properly.
Aircraft Configuration
• Aircraft Registration: Enter the aircraft’s tail number here.
• ICAO Address: Enter the aircraft’s 24 bit ICAO address here.
• IATA Airline Designator: If applicable, enter the airline’s 2 digit airline designator code.
• Country Code: Not used at this time.
• VFR Code: A pre-programmed code which will become active when the VFR key on the
GDU is pressed. Pressing the VFR key again restores the previous code.

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File Manager Page

NOTE: The File Manager page is protected by a boot disk. The page is hidden when the boot disk
is not present.
Data
The File Manager Configuration page displays the following data:
• The current device
• The current directory that is being viewed
• A list of files and sub-directories in the current directory that shows the mode, name,
size, and date modified
Operations
The File Manager Configuration page allows the following operations:
• Change the current directory that is being viewed by pressing ENT with a directory
highlighted
• Copy the highlighted file to another directory via the COPY and PASTE softkeys
• Copy the highlighted directory to another directory via the COPY and PASTE softkeys
• Clear the highlighted file if the file is permitted to be cleared via the CLEAR softkey
• Delete the highlighted file if the file is permitted to be deleted via the DELETE softkey
• Delete the highlighted directory if the directory is empty and permitted to be deleted
via the DELETE softkey
• Clear the highlighted directory of all subdirectories and files if the directory is permitted
to be cleared via the CLEAR softkey

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Diagnostics Terminal Page

The Diagnostics Terminal page is only be available in Diagnostics Mode.

Data
The Diagnostics Terminal page displays the following data:
• Currently selected LRU
• Currently selected command
• Output data received from the selected LRU
Operations
• The Diagnostics Terminal page allows the following operations for each field on the
page:
• Selecting an LRU to review from the list by highlighting the LRU field or selecting the
"Select LRU Window" menu option
• Changing the command to execute by highlighting the Command field or selecting the
"Select Command Window" menu option
• Executing the selected command by pressing ENT once the command has been entered
• Scrolling through the output from the selected LRU by pressing the OUTPUT softkey or
selecting the "Select Output Window" menu option, then turning the FMS inner knob.
• Freeze the output of the selected LRU by pressing the FREEZE softkey or selecting the
"Freeze Diagnostics Data" menu option.

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 • Clear the output data received thus far by pressing the CLEAR softkey or selecting the
"Clear Diagnostics Data" menu option.
• Copy the output data received to the card by pressing the CP2CRD softkey or selecting
the "Copy Diagnostics Data to Card" menu option.
• Log the data to the card by pressing the LG2CRD softkey or by selecting the "Start Log
Diagnostics to Card" menu option.
• Move the highlight to the LRU selection field by pressing the LRU softkey.
• Move the highlight to the command entry field by pressing the COMMAND softkey.
• Move the highlight to the output window by pressing the OUTPUT softkey.

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OEM Diagnostics Page

The OEM Diagnostics (OEMD) can be accessed with the GTC thru the Maintenance icon and
using DU 2.
Data
The OEM Diagnostics page displays the following data:
• Contents of index.htm file located in "html" directory on card (html\index.htm).
Operations
The OEM Diagnostics page allows the following operations:
• The Save Screen operation is done by pushing both the GDU softkeys 2 and 9. The SAVE
IMG softkey will not be used when OEMD is accessed through the GTC. Traversing fields
defined by data on the card using the FMS knob.
• Selecting items using the ENT key.

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System Configuration Page

NOTE: The System Configuration page is protected by a boot disk. The page allows only GDL
present to be configured without a boot disk present.
Data
• Indicates the presence (green check mark) or non-presence (red x) of LRUs.

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System Data Path Configuration Page

The System Data Paths Configuration page displays the following data when the A429, CAN, RS-
232, or RS-485 data path softkey is selected.
A table containing one row for each configured LRU with the following data per row, ordered
from left to right:
• A text field indicating the LRU name in the column
• A text field indicating the channel name
A status indicator showing:
• An N/A indication if the monitor is on and data path status is "N/A"
• A positive indication if the monitor is on and data path status is "OK"
• A negative indication if the monitor is on and data path status is "FAIL"
• An unknown indication if the monitor is off or the monitor is "ON" and data path
status is "UNKNOWN"
A text field indicating the port monitor status:
• "ON" if the monitor is turned on
• "OFF" if the monitor is turned off
A text field indicating the port status with the following possible values:
• "OK" if the port is communicating
• "FAIL" if the port is not communicating
• "N/A" if the port is not applicable

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 • "UNKNOWN" if the port status is unknown
Data
The System Data Paths Configuration page displays the following data when the HSDB data path
softkey is selected.
A table containing one row for each configured LRU with the following data per row, ordered
from left to right:
• A text field indicating the LRU name in the column
• A drop down selectable field indicating the expected LRU for each HSDB port
• A white text field indicating the current LRU for each HSDB port
A status indicator for each HSDB port:
• An N/A indicator if the expected LRU is configured to none and there is no actual LRU
online
• A positive indicator if the expected LRU matches actual LRU online
• A negative indicator if the expected LRU does not match actual LRU online
Operations
The System Data Path Configuration page allows the following operations:
• Turn on/off port monitor on A429, CAN, RS-232, or RS485 page
• Configure port on HSDB page
• Display ARINC-429 port monitoring information by pressing the A429 softkey
• Display CAN port monitoring information by pressing the CAN softkey
• Display HSDB path monitoring information by pressing the HSDB softkey
• Display RS-232 port monitoring information by pressing the RS-232 softkey
• Display RS-485 port monitoring information by pressing the RS-485 softkey

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System Setup Page

In addition to the field definitions that are described in the Pilot’s Guide, the following
additional fields exist:
Fuel Type
• Displays the currently configured system fuel type.
• Allows the user to set the currently configured fuel type for the system, which will result
in the configuration for the GDU, GIA 1, GIA 2, GSD 1, and GSD 2 to be set to the
selected fuel type, by highlighting the currently allowed system fuel type setting.
Flight Director
• Displays the currently allowed system flight director setting(s).
• Allows the user to set the currently allowed system flight director setting(s) by
highlighting the currently allowed system flight director setting and turning the small
GCU 275 PFD Knob if more than one flight director option is allowed per the airframe
specific requirements document.
GFDS Data Request
The GFDS Data Request section of the System Setup page is only be available when GFDS
Weather is configured. The GFDS Data Request Section displays the following data:
• Fastest Update Rate
Operations
• The user is able to set the Fastest Update Rate by highlighting the current setting using
the large GCU 275 PFD knob and using the small GCU 275 PFD Knob to select from the
following list (Default, 5 Min, 10 Min, 15 Min, 20 Min, 30 Min, 45 Min, 60 Min).

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 • Pilot profile data and operations is not available on the configuration mode System
Setup page.

Manifest Configuration Page

The Manifest Configuration page is protected by a boot disk. The page does not allow
operations when the boot disk is not present.
Data
• Software Card
• Part number
• Version number
• LRUs
• Part number
• Version number
Operations
• Changing an LRU part number
• Changing an LRU version number

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Maintenance Log Page

Data
The Maintenance Log Configuration Page displays a list of log entries with the following
information for each entry:
• Entry alert ID
• Date & Time
• Set or Clear
• Inhibit state
The Maintenance Log Configuration page displays the log data points for the selected log entry.
Operations
The Maintenance Log Configuration Page allows the following operations:
• Clear the maintenance log by pressing the CLEAR softkey and then confirming a popup
dialog.
• Save the maintenance log to an SD card by pressing the CP2CRD softkey
• Select log section to view by pressing the SECTION softkey and the subsequent number
softkeys

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4.6.5.2 GDU Page Group
GDU Serial Configuration Page

Data
The GDU RS-232/ARINC 429 Configuration page displays the following data:
• Current GDU unit selected
• Set and active speeds for ARINC 429 inputs 1 and 2
• Set and active data for ARINC 429 inputs 1 and 2
• ARINC 429 SDI
• Set and active inputs for RS-232 channels 1 and 2
• Set and active outputs for RS-232 channels 1 and 2
• Port status indication for each ARINC 429 input
• Port status indication for each RS-232 input
Operations
The GDU RS-232/ARINC 429 Configuration page allows the following operations:
• Select GDU unit
• Select set speeds for ARINC 429 inputs 1 and 2
• Select set data for ARINC 429 inputs 1 and 2
• Select ARINC 429 SDI

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 • Select set input for RS-232 channels 1 through 2
• Select set output for RS-232 channels 1 through 2

GDU Status Page

Data
'STATUS' Window:
• RAM―Indicates condition of GDU 104X RAM memory. If it does not pass, the unit may
not initialize.
• XILINX―Indicates condition of GDU 104X XILINX processor. If it does not pass, the unit
may not initialize.
• BASE MAP―Indicates condition of stored basemap in the GDU 104X. A green box
indicates the basemap has been installed. If the box is black, the basemap will need to
be loaded. Contact Garmin for assistance.
• ETHERNET 1, 2, 3―Indicates status of the GDU 104Xs Ethernet channel. A green box
indicates the ETHERNET loopback tests passed. A red or black box indicates it may not
be used or a wiring fault is present.
• RS-232 1, 2―Indicates status of the GDU 104X’s RS-232 channel. A green box indicates
the RS-232 loopback tests passed. A red or black box indicates it may not be used or a
wiring fault is present.

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 • IRDA―Indicates status of GDU 104X IrDA infrared port. Used for Garmin testing, it is
not activated at this time
• ETHERNET 4―Indicates status of GDU 104Xs Ethernet channel 5. Used for Garmin
testing, it is not activated at this time
'ANALOG' Window:
• BEZEL THERM―Displays the temperature of the GDU bezel, expressed in degrees
Celsius (Example: 2064 = 20.64 degrees Celsius)
• CCFT CRNT 1, 2―Displays an indication of current flowing through the display backlight
bulbs. Number does not reflect actual current value and is not useful for
troubleshooting.
• LGHT BUS AC―Displays the input value of the AC lighting bus, if enabled. Disregard
number if it is not used in the installation.
• LGHT BUS DC―Displays the input value of the DC lighting bus, if enabled. Disregard
number if not used in the installation.
• POWER (1.3V, 2.5V, 3.3V, 28 V 1/2)―Displays power input voltages of various internal
components. Should be within 10% of the desired voltage. (example: for 2.5V field,
2500 = 2.500 Vdc; for 28V Field, 3633 = 36.33 Vdc). Replace the display if these values
are more than 10% from the desired voltage.
• INTRNL TEMP 1, 2―Displays the internal temperature sensor values of the display, in
degrees Celsius. (Example: 45267 = 45.267°C)
'DISCRETE' Window:
GDU System ID 1 GDU System ID 2 GDU System ID 3 Display Mode
Black Black Green MFD
Black Black Black PFD #1
Green Black Black PFD #2
• SYS ID 1, 2, 3―Displays the current system ID assigned to the display. Green indicates
that the System ID pin is strapped to ground. Black indicates that the System ID pin is
left ‘open’ and not strapped to ground.
• RVRSNRY MODE 1, 2―Displays the current status of the reversionary modes.
Reversionary Mode 1 is activated by the GMA 1347 reversion button. Reversionary
Mode 2 is activated by a second GMA 1347, if installed. Reversionary 1 input is a ground
on Pin 58, reversionary 2 input is a ground on Pin 15.
• SPARE INPUT―A green box indicates Pin 14 is grounded. This input should have a black
box, if it is green check for connector miswiring or a bent pin.
• TEST/DEMO MODE SLCT―A green box indicates Pin 53/54 is grounded. These inputs
should have a black box, if either box is green check for connector miswiring or a bent
pin.
• PULSE PER SEC 1, 2―Displays status of GPS time synchronization inputs (from GIA) to
the GDU. Used for Garmin testing, not useful for troubleshooting.

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The ‘Discrete' Window displays the current configuration of discrete inputs into the display.
These settings are loaded with the G5000 Loader Card and must not be changed. The input box
is green if it is receiving the input, black if no input is expected, or red for a missing input. If the
active column does not match the set column, load PFD/MFD configuration files. These settings
are loaded with the G5000 Loader Card and must not be changed.
GDU Key Test Page

The GDU key Test Page shows a graphical layout of all display buttons in red. Each red button
turns green when the button is pressed indicating correct operation of the button.
GDU Test Page Window Descriptions
'DISPLAY-NEC®' Window:
• DUTY PWM 1―Displays the display brightness duty pulse width modulation. Value
range is between 0 and 9999 and corresponds to the display brightness value shown.
Not useful for troubleshooting.
• CRNT PWM―Displays percentage of current pulse-width-modulation to backlight bulbs.
Value is between 0 and 10,000, showing the percentage of the maximum allowable
current to the backlight. Not useful for troubleshooting.
• TOGGLE PWM TO MANL?― Allows the technician to manually adjust the display
brightness.
• TOGGLE CCFT OFF?― Allows the technician to turn off the backlight current controller.
• 'KEY' Window:

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 • KEY PWM―Displays the keypad pulse width modulation brightness value. Range is
between 0 and 9999 and corresponds to the keypad brightness value shown. Not useful
for troubleshooting.
• TOGGLE KEY BKLT OFF?―Allows the technician to toggle the keyboard backlight off.
• REINIT PAGE INFO?―Allows technician to re-initialize all information on the test page.
'ADC' Window:
• BEZEL THERM―Displays the temperature of the GDU bezel, expressed in degrees
Celsius.
• CCFT CRNT 1, 2―Displays an indication of current flowing through the display backlight
bulbs. Number does not reflect actual current value and is not useful for
troubleshooting.
• POWER (2.5V, 3.3V, 28 V 1, 2; 1.3V)―Displays power input voltages of various internal
components. (Example: for 2.5V field, 2500 = 2.500 Vdc; for 28V Field, 3633 = 36.33
Vdc) They need to be within 10% of desired voltages. Replace the display if these
values are more than 10% from the desired voltage.
• LGHT BUS DC, AC―Displays input value of AC and DC lighting bus inputs, depending on
which is configured. Disregard number if not used in the installation.
• INTRNL TEMP 1, 2―Displays the internal temperature of the GDU, expressed in degrees
Celsius.
'TEST' Window:
• IIC EEPROM―Displays the condition of the GDU configuration module EEPROM chip,
located in the backplate connector. It should be green for the PFD and red for the MFD.
If it is red on the PFD, check configuration module wiring and pins for damage before
replacing the configuration module.
• DATACARD CHKSUM 1, 2―Requires the use of a special datacard. Tests the datacard
reader interface function. Used for Garmin testing, not useful for troubleshooting.
• NAND, NOR FLASH, SDRAM―Displays the condition of various GDU internal
components.
• A429 LOOP 1, 2―Indicated the status of the GDU 104Xs ARINC 429 channels. A green
box indicates the ARINC 429 loopback tests passed. A red or black box indicated it may
not be used or a wiring fault is present.
• ETHERNET 1, 2, 3―Indicates status of the GDU 104Xs Ethernet channel. A green box
indicates the ETHERNET loopback tests passed. A red or black box indicates it may not
be used or a wiring fault is present.
• RS-232 1, 2―Indicates status of the GDU 104X’s RS-232 channel. A green box indicates
the RS-232 loopback tests passed. A red or black box indicates it may not be used or a
wiring fault is present.
• IRDA―Indicates status of GDU 104X IrDA infrared port. Used for Garmin testing, it is
not activated at this time.

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 • BKUP CAPS―Indicates status of the Backup Capacitor Test. A green box indicates the
test passed, a red box indicates it failed.
'DISCRETE' Window:
GDU System ID 1 GDU System ID 2 GDU System ID 3 Display Mode
Black Black Green MFD
Black Black Black PFD #1
Green Black Black PFD #2
• RVRSNRY MODE 1, 2―Displays the current status of the reversionary modes.
Reversionary Mode 1 is activated by the GMA 1347 reversion button. Reversionary
Mode 2 is activated by a second GMA 1347, if installed. Reversionary 1 input is a ground
on Pin 58, reversionary 2 input is a ground on Pin 15.
• PULSE PER SEC 1, 2―Displays status of GPS time synchronization inputs (from GIA 63W)
to the GDU. Used for Garmin testing, not useful for troubleshooting.
• TEST, DEMO MODE SELECT―A green box indicates Pin 53/54 is grounded. These inputs
should have a black box, if either box is green check for connector miswiring or a bent
pin.
• FPGA―Displays the condition of the GDU FPGA processor. If it does not pass the unit
may not initialize.
• SYS ID 1, 2, 3―Displays the current system ID assigned to the display. Green indicates
that the System ID pin is strapped to ground. Black indicates that the System ID pin is
left ‘open’ and not strapped to ground. (See Table below) PFD #2 is not used in certain
aircraft.
• REMOTE OFF―Allows the display to control power of a remote system. Not used in any
installation at this time.

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LED BKLT Test Page

Refer to Learjet maintenance documentation for information regarding the LED BKLT Test Page.

LED BKLT Calib Page

Consult with Garmin Field Service Engineering for information regarding the LED BKLT Calib
Page.

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Diagnostics Page

NOTE: The Diagnostics page is protected by a boot disk. The page is hidden when the boot disk is
not present.
Data
• A list of up to the 99 most recent exceptions for the processor that describes the type of
exception and the day and time for each exception
• Source module, file, and line number of assert, if assert is selected
• Task if applicable
• Registers R0 through R12
• SP register
• LR register
• CPSR register
• PC register
• FSR register
• FADDR register
• CPU trace
• Stack dump
• Power cycles
• Power hours

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 • Fault
• Temperature Maximum, Minimum, and Average
Operations
• Scroll through the list of exceptions using the FMS knob
• Scroll through the CPU trace by pressing the CPU TRCE softkey then using the FMS knob
• Scroll through the stack dump by pressing the STCK DMP softkey then using the FMS
knob
• Delete an exception by highlighting the exception and pressing CLR
• Save the error log to a data card by pressing the SAVE LOG softkey
• Clear the error log by pressing the CLR LOG softkey
• Toggle between viewing the CPU trace and stack dump by pressing the CPU TRCE or
STCK DMP softkeys
• Selecting to scroll through the Exceptions or CPU trace/stack dump windows by pressing
the EXCEPTNS or MEMORY softkeys when an exception has been selected

Ethernet Test Page

The Ethernet Test page is protected by a boot disk. The page does not allow operations when
the boot disk is not present.

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Data
The Serial / Ethernet I/O Configuration page displays the following Ethernet statistics for the
selected Ethernet port:
• Good frames received • Good frames transmitted
• Receive collision detections • Transmit max collision errors
• Receive alignment errors • Transmit late collision errors
• Receive overrun errors • Transmit underrun errors
• Receive resource errors • Transmit lost carrier sense
• Receive CRC errors • Transmit frames deferred
• Receive short frame errors • Transmit single collisions
• Number of Flow Control frames • Transmit multiple collisions
received that are not Flow Control
• Number of Flow Control frames
Pause Frames
transmitted
• Number of Flow Control frames
• Transmit total collisions
received
HSDB Statistics
The Serial / Ethernet I/O Configuration page displays the following HSDB statistics:
• Pings transmitted • Number of received periodic
packets
• Number of transmitted periodic
packets • Number of received
acknowledgement request packets
• Number of transmitted
acknowledgement request packets • Number of received
acknowledgement packets
• Number of transmitted
acknowledgement packets • Minimum acknowledgement time
in milliseconds
• Number of transmitted retry
packets • Maximum acknowledgement time
in milliseconds
• Number of aborted transmission
packets • Number of packets pending
• Number of write fails • Number of LRU online changes
• Number of overruns
The Serial / Ethernet I/O Configuration page allows the following operations:
• Change the selected Ethernet port using the FMS knob
• Show non-volatile statistics log by pressing the NONVOL softkey
• Clear non-volatile statistics log by pressing the CLR LOG softkey

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Video Test Page

The Video Test page is only present when the number of available video decoder sources is
greater than zero.
Data
• An image of the selected video source scaled to the available display space.
• Identification of the selected video source in the upper-left corner of the image, as
determined by configuration.
• If the selected video signal is not available, the page displays "NO DATA AVAILABLE".
• Current source configuration information
• Text identifier description for the video source (0-19 characters)
• Source number (1, 2)
• Whether or not the source is configured
• Source standard (NTSC, PAL, AUTO)
• Rotation (0°, 90°, 180°, 270°)
• Original dimensions (width and height)
• Crop (0-49% for each side)
• Size of inset window (a percentage of the main window, 10%-50%)
• Text timeout (0-10s)
• Current source settings

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 • Brightness (0-100%)
• Contrast (0-100%)
• Saturation (0-100%)
• Digital zoom level (1x, 2x, 4x, 8x, 10x)
The Video Test Configuration page allows the following operations:
• Switching to the VIDEO 1 source, by pressing the VIDEO 1 softkey.
• Switching to the VIDEO 2 source, by pressing the VIDEO 2 softkey.
• Changing the video format standard to AUTO mode, by pressing the AUTO softkey.
• Changing the video format standard to NTSC mode, by pressing the NTSC softkey.
• Changing the video format standard to PAL mode, by pressing the PAL softkey.
• Rotating the video image, by pressing the ROTATE softkey.
• Increasing the contrast of the video image, by pressing the CNTRST + softkey.
• Decreasing the contrast of the video image, by pressing the CNTRST - softkey.
• Increasing the brightness of the video image, by pressing the BRIGHT + softkey.
• Decreasing the brightness of the video image, by pressing the BRIGHT - softkey.
• Increasing the saturation of the video image, by pressing the SAT + softkey.
• Decreasing the saturation of the video image, by pressing the SAT - softkey.
• Increasing the zoom level of the video image, by pressing the ZOOM IN softkey.
• Decreasing the zoom level of the video image, by pressing the ZOOM OUT softkey.
• Hiding or showing the video image, by pressing the HIDE softkey.
• Modification of saved configuration settings (when an unlock card is inserted)
• Saving modified configuration settings, by pressing the SAVE softkey.
• Discarding modified configuration settings (and restoring the last saved settings), by
pressing the DISCARD softkey.

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Alert Configuration Page

The Alert Configuration page has two display modes, List and Detail, described in the following
requirements.
List View Data
The Alert Configuration page displays the following data in List View:
A list of configurable alerts, including:
• Alert ID
• Alert Brief Text
• Alert State (set or cleared)
A list of configurable triggers, including:
• Trigger ID
• Trigger Description
Detail View Data
• The Alert Configuration page displays the following data in Detail View:
• ID of the selected alert
• Brief Text of the selected alert
• Descriptive Text of the selected alert
• Level of the selected alert
• Notify flags of the selected alert

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 • Acknowledge flags of the selected alert
• Flags value of the selected alert
• Maintenance log section(s) to notify on alert set
• Maintenance log section(s) to notify on alert clear
• Clear flags of the selected alert
• Set-audio of the selected alert
• Clear-audio of the selected alert
• Discrete out controlled by the selected alert
• OEM that created/configured the selected alert
• The OEM revision of the selected alert
• A list of the alert's nodes, each node displaying:
o Node number
o Trigger ID
o Parent node
o Operation
o State
• ID of the selected trigger
• Source of the selected trigger
• Data id of the selected trigger, and description (e.g. discrete id and discrete name)
• Data type of the selected trigger
• Data offset of the selected trigger
• Flags of the selected trigger
• Threshold and threshold operation of the selected trigger
• Extinguish and extinguish operation of the selected trigger
• Set time of the selected trigger
• Clear time of the selected trigger
• OEM that created/configured the selected trigger
• The OEM revision of the selected trigger
List View Operations
In LIST View mode, the Alert Configuration page allows the following operations:
• Switch to Detail View mode by pressing the DETAIL softkey
• Switch to Detail View mode by highlighting an alert or trigger and pressing ENT

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 • Select the Alerts list by pressing the ALERTS softkey
• Select the Triggers list by pressing the TRIGGERS softkey
Detail View Operations
In DETAIL View mode, the Alert Configuration page allows the following operations:
• Switch to List View mode by • Modify each node's Trigger ID by
pressing the LIST softkey pressing the NODE softkey and
using FMS knob entry on the trigger
• Select the alert to view using the
ID field
FMS inner knob on the alert field
• Modify each node's Parent node by
• Select the selected trigger to view
pressing the NODE softkey and
using the FMS inner knob on the
using FMS knob entry on the parent
trigger field
ID field
• Modify the selected alert's Brief
• Modify each node's Operation using
Text using FMS knob entry
the FMS inner knob and ENT to
• Modify the selected alert's select from a drop-down list
Descriptive Text using FMS knob
• Modify the selected trigger's Source
entry
using the FMS inner knob and ENT
• Modify the selected alert's Level to select from a dropdown list
using the FMS inner knob and ENT
• Modify the selected trigger's Data
to select from a drop-down list
id using FMS knob entry
• Modify the selected alert's Notify
• Modify the selected trigger's Data
flags using FMS knob entry
type using the FMS inner knob and
• Modify the selected alert's Flags ENT to select from a dropdown list
value using FMS knob entry
• Modify the selected trigger's Data
• Modify the selected alert's offset using FMS knob entry
Acknowledge flags using FMS knob
• Modify the selected trigger's Flags
entry
using FMS knob entry
• Modify the selected alert's Clear
• Modify the selected trigger's
flags using FMS knob entry
Threshold and threshold operation
• Modify the selected alert's Set- using the FMS inner knob and ENT
audio using FMS knob entry to select from a drop-down list
• Modify the selected alert's Clear- • Modify the selected trigger's
audio using FMS knob entry Extinguish and extinguish operation
• Modify the selected alert's Discrete using the FMS inner knob and ENT
Out using the FMS inner knob and to select from a drop-down list
ENT to select from a drop-down list • Modify the selected trigger's Set
• Modify the selected alert's OEM time using FMS knob entry
Revision using FMS knob entry • Modify the selected trigger's Clear
time using FMS knob entry

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 • Modify the selected trigger's OEM • Save the modifications to the
Revision using FMS knob entry trigger by pressing the SV TRGR
softkey
• Save the modifications to the alert
by pressing the SV ALRT softkey
Common Operations
The Alert Configuration page allows the following operations in both List and Detail views:
• Acknowledge all alerts by pressing the ACK softkey
• Switch between viewing CAS and LOG alerts by pressing the CAS and LOG softkeys,
respectively

DAT Configuration Page

Contact Garmin Field Service Engineering for questions and/or information regarding the DAT
Configuration Page.

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Airframe Configuration Page

Page Security
The Airframe Configuration page is protected by a boot disk. The page does not allow operations
when the boot disk is not present (level 5 security).
General
• The Airframe Configuration page displays and configure information relating to the
specific airframe per the airframe specific system requirements.
• For each airframe, the Airframe Configuration page displays and configures the
navigation center offset with a resolution of 1 foot or 0.1 meters depending on the units
configured in the system.
• For each airframe, the Airframe Configuration page displays all OEM Tag/Value Pairs for
which the Tag is defined.
• For each airframe, the Airframe Configuration page configures all OEM Values for which
the Tag is defined.

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TAWS Configuration Page

The TAWS Setup page is protected by a boot disk, allowing modifications only when a
configuration unlock card is not present (Level 4 security). The following annunciations, in
yellow text, is displayed if and only if a configuration unlock card is not present:
• AIRPORT CRITERIA FIELDS ARE LOCKED
• CLIMB ANGLE FIELDS ARE LOCKED
• AIRSPEEDS FIELDS ARE LOCKED

Data
The TAWS Setup Configuration page is titled based on the TAWS alerting configuration (“TAWS-
A SETUP”).
Terrain Alerting Configuration
The TAWS Setup Configuration page displays the current TAWS configuration.
Airport Criteria (TAWS-A, TAWS-B, TERRAIN-SVS only)
The TAWS Setup Configuration page displays the following data related to airport criteria:
• Runway surface type
• Minimum length (ft)
• Voice Callouts (TAWS-A, HTAWS-B)
The TAWS Setup Configuration page displays the following data related to voice callouts for
each voice callout:
• Whether the selected callout is enabled or disabled

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 • FLTA Climb Angles (TAWS-A)
The TAWS Setup Configuration page displays the following data related to climb angles:
• Selected entry's altitude (ft)
• Selected entry's angle (degrees)
Configurable Airspeed Parameters (TAWS-A)
The TAWS Setup Configuration page displays the following related to airspeeds:
• Approach speed (kt)
• Maximum gear/flap landing configuration speed (kt)
Audio Configuration
The TAWS Setup Configuration page displays the following related to audio messages:
• The text "No Audio Configuration Available" if the TAWS configuration is TERRAIN
PROXIMITY or HTERRAIN PROXIMITY
• The selected aural alert message for each alert type if the TAWS configuration is not
TERRAIN PROXIMITY or HTERRAIN PROXIMITY

Operations
The TAWS Setup Configuration page allows the following operations, if the data fields are
available:
The following operations is allowed for the TAWS Setup Configuration page softkeys (if
applicable):
• Advance highlight to the first field of the Airport Criteria group by pressing the APT
softkey
• Advance highlight to the first field of the Voice Callouts group by pressing the VCO
softkey
• Advance highlight to the first field of the Climb Angle group by pressing the CLIMB
softkey
• Advance highlight to the first field of the Airspeeds group by pressing the AIRSPD
softkey
Airport Criteria
The following operations is allowed for the TAWS Setup Configuration page airport criteria fields
(if applicable):
• Select a minimum runway surface (Any, Hard only, Hard/Soft, Water)
• Select a minimum runway length

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Voice Callouts
The following operations is allowed for the TAWS Setup Configuration page voice callout fields
(if applicable):
• Select a voice callout to modify
• Enable or Disable the given voice callout
• Set the given voice callout allow or disallow user configurability (HTAWS-B only).
• The VCO 500 callout is not modifiable (always enabled) for TAWS-A configurations.
Climb Angle
The following operations is allowed for the TAWS Setup Configuration page climb angle fields (if
applicable):
• Select a climb angle entry to modify
• Select an altitude for the given climb angle entry
• Select a climb angle for the given climb angle entry
Airspeeds
The following operations is allowed for the TAWS Setup Configuration page airspeed fields (if
applicable):
• Select an approach speed
• Select a maximum landing configuration speed
Audio Configuration

CAUTION
Do not attempt to change the TAWS audio configuration. Doing so may put the
airplane in a configuration that is not consistent with type design.

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4.6.5.3 GIA Group
GIA Serial Configuration Page

Data
The GIA RS-232 / ARINC 429 Configuration page displays the following data:
• Current GIA unit selected
• Set and active speeds for ARINC 429 inputs 1 through 8
• Set and active speeds for ARINC 429 outputs 1 through 3
• Set and active data for ARINC 429 inputs 1 through 8
• Set and active data for ARINC 429 outputs 1 through 3
• ARINC 429 SDI
• Set and active inputs for RS-232 channels 1 through 8
• Set and active outputs for RS-232 channels 1 through 8
• Port status indication for each ARINC 429 input
• Port status indication for each RS-232 input
Operations
The GIA RS-232 / ARINC 429 Configuration page allows the following operations:
• Select GIA unit

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 • Select set speeds for ARINC 429 inputs 1 through 8
• Select set speeds for ARINC 429 outputs 1 through 3
• Select set data for ARINC 429 inputs 1 through 8
• Select set data for ARINC 429 outputs 1 through 8
• Select ARINC 429 SDI
• Select set input for RS-232 channels 1 through 8
• Select set output for RS-232 channels 1 through 8
• Copy set information to the active information by pressing the SET>ACTV softkey
• Copy the active information to the set information by pressing the ACTV>SET softkey
• Clear the non-volatile registry data for the serial configurations by pressing the CLR
softkey

GIA RS-485 Configuration Page

Data
The GIA RS-485 Configuration page displays the following data:
• Current GIA unit selected
• Set and active inputs for RS-485 channels 1 through 5
• Set and active outputs for RS-485 channels 1 through 5
• Clocked data interface set and active input/output data type
• Port status indication for each RS-485 input
Operations
The GIA RS-485 Configuration page allows the following operations:
• Select GIA unit
• Select set input for RS-485 channels 1 through 5

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 • Select set output for RS-485 channels 1 through 5
• Copy set information to the active information by pressing the SET>ACTV softkey
• Copy the active information to the set information by pressing the ACTV>SET softkey
• Select set data for clocked data interface input/output

GIA I/O Configuration Page

Data
The GIA I/O Configuration page displays the following data:
• Current GIA unit selected
• Current input / output type selected
• List of discrete I/O channel configurations or analog I/O function configurations
Discrete I/O Channel Configurations
The list of discrete I/O channel configurations displays the following data for each item:
• Discrete I/O channel's set data type
• Discrete I/O channel's active data type
• Discrete I/O channel's current status
• Discrete I/O channel's set inversion status
• Discrete I/O channel's active inversion status
• Discrete input channel's set active debounce time (if discrete in selected)
• Discrete input channel's active debounce time (if discrete in selected)

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 • Discrete input channel's set inactive debounce time (if discrete in selected)
• Discrete input channel's active inactive debounce time (if discrete in selected)
Analog I/O Function Configurations
The list of analog I/O function configurations displays the following data for each item:
• Analog I/O function
• Analog I/O function's set and active status
Operations
The GIA I/O Configuration page allows the following operations:
• Select a GIA unit
• Select input / output type (discrete in, discrete out, analog in, analog out)
• Copy set information to the active information by pressing the SET>ACTV softkey
• Copy active information to the set information by pressing the ACTV>SET softkey
Discrete I/O Channel Configurations
The list of discrete I/O channels allows the following operations for each item:
• Select a discrete I/O channel's set data type
• Select a discrete I/O channel's set inversion status (true or false) (if its data type is
defined)
• Modify a discrete input channel's set active debounce time (if its data type is defined)
• Modify a discrete input channel's set inactive debounce time (if its data type is defined)
• Toggle the signal of a discrete output channel (true or false) (if its data type is defined)
Analog I/O Channel Configurations
The list of analog I/O functions allows the following operations for each item:
• Toggle an analog I/O function's enabled status (true or false)

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GIA COM Setup Page

Data
The COM Setup Configuration page displays the following data:
• Current GIA unit selected
• Calibration communication frequency
• Communication frequency kHz spacing selection
• Communication volume
• Emergency communication volume (set and active data)
• 25 kHz squelch adjustment (set and active data)
• kHz squelch adjustment (set and active data)
• Sidetone adjustment (set and active data)
• Microphone gain adjustment (set and active data)
Operations
The COM Setup Configuration page allows the following operations:
• Select GIA unit
• Select calibration communication frequency
• Select communication frequency spacing (8.33 kHz, 25.0 kHz)
• Select communication volume
• Select emergency communication volume
• Select 25.0 kHz squelch adjustment
• Select 8.33 kHz squelch adjustment

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 • Select sidetone adjustment
• Select microphone gain adjustment
• Store current calibration settings by pressing the STORE softkey (Calibration Method)
• Copy set information to the active information by pressing the SET>ACTV softkey
(Configuration Method)
• Copy the active information to the set information by pressing the ACTV>SET softkey
(Configuration Method)

GIA Status Page

Data
The GIA Status Configuration page displays the following data reported from GIA 1 or GIA 2:
GPS Status
• GIA with Non-WAAS Capable GPS Receiver
• ROM status
• RAM status
• ASIC status
• Receiver status
GIA with WAAS Capable GPS Receiver
• RTC Battery

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 • Battery
• PLL Locked
• EEPROM
Glideslope Status
• ROM status
• EEPROM status
• Synthesizer lock status
COM Status
• ROM status
• EEPROM status
• Receive status
• Transmit status
• Synthesizer lock status
• Low Power status
• Over temperature status
VLOC Status
• ROM status
• EEPROM status
• XILINX status
• Synthesizer lock status
Main GIA Status
• ROM status • -5V power range status
• Analog calibration status • -12V power range status
• EEPROM 1, 2 status • Aircraft power range A and B status
• FPGA 1, 2 status • Over temperature status
• +28V power range status • Low temperature status
• +12V power range status • +5V backed power status
• +5V power range status • 3V battery status
• +3.3V power range status • BKUP CAPS Backup capacitor status
Analog Status
• Aircraft power A and B
• Temperature

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Discrete Status
• System ID Program 1 and 2
Fuel
• System Fuel Type
Operations
The GIA Status Configuration page allows the following operations:
• Select which GIA to display data for

GIA CAN Configuration Page

Data
The GIA CAN Configuration page displays the following data:
• Current GIA unit selected
• Current CAN channel selected
• Set and active input data type for CAN channels 1 and 2
• Set and active output data type for CAN outputs on channels 1 and 2
• Set and active speeds for CAN channels 1 and 2
• Set and active on/off status for five left, two center, and five right fuel packets for CAN
channels 1 and 2

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4.6.5.4 GSD Page Group
GSD ARINC Configuration Page

Data
The GSD ARINC Configuration page displays the following data:
• Current GSD unit selected
• Set and active speeds for ARINC inputs 1 through 24
• Set and active speeds for ARINC outputs 1 through 16
• Set and active data type for ARINC inputs 1 through 24
• Set and active data type for ARINC outputs 1 through 16
• Port status indication for each ARINC input
Operations
The GSD ARINC Configuration page allows the following operations:
• Select GSD unit
• Select set speeds for ARINC inputs 1 through 24
• Select set speeds for ARINC outputs 1 through 16
• Select set data type for ARINC inputs 1 through 24
• Select set data type for ARINC outputs 1 through 16
• Copy set information to the active information by pressing the SET>ACTV softkey

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 • Copy the active information to the set information by pressing the ACTV>SET softkey
• Clear the non-volatile registry data for the serial configurations by pressing the CLR NV
softkey

GSD RS-485 Configuration Page

Data
• The GSD RS-485 Configuration page displays the following data:
• Current GSD unit selected
• Set and active inputs for RS-485 channels 1 through 16
• Set and active outputs for RS-485 channels 1 through 16
• Port status indication for each RS-485 input
Operations
The GSD RS-485 Configuration page allows the following operations:
• Select GSD unit
• Select set input for RS-485 channels 1 through 16
• Select set output for RS-485 channels 1 through 16
• Copy set information to the active information by pressing the SET>ACTV softkey
• Copy the active information to the set information by pressing the ACTV>SET softkey

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GSD I/O Configuration Page

Data
• The GSD I/O Configuration page displays the following data:
• Current GSD unit selected
• Current input type selected
• List of discrete input channel configurations
• Discrete I/O Channel Configurations
The List Of Discrete Input Channel Configurations Displays The Following Data For Each Item:
• Discrete input channel's set data type
• Discrete input channel's active data type
• Discrete input channel's current status
• Discrete input channel's set inversion status
• Discrete input channel's active inversion status
• Discrete input channel's set active debounce time
• Discrete input channel's active debounce time
• Discrete input channel's set inactive debounce time
• Discrete input channel's active inactive debounce time

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Operations
The GSD I/O Configuration page allows the following operations:
• Select a GSD unit
• Copy set information to the active information by pressing the SET>ACTV softkey
• Copy active information to the set information by pressing the ACTV>SET softkey
• Discrete input Channel Configurations
The list of discrete input channels allows the following operations:
• Select a discrete input channel's set data type
• Select a discrete input channel's set inversion status (true or false) (if its data type is
defined)
• Modify a discrete input channel's set active debounce time (if its data type is defined)
• Modify a discrete input channel's set inactive debounce time (if its data type is defined)

GSD Status Page

Data
The GSD Status Configuration page displays the following data reported from GSD 1 or GSD 2:
MAIN STATUS

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 • FPGA 1 status
• FPGA 2 status
• RAM status
• ROM status
• Over temperature alert status
• Under temperature alert status
• System failure status
• All status flags valid status
• Supercap failure count
• Active mode
Hardware Statistics
• Maximum system temperature
• Minimum system temperature
• Number of unit power ups
• Total unit on time (hours)
Voltage Range Monitor
• Valid system voltages flag status • +1.2V CH 1 power range status
• +28V power range status • +1.2V CH 2 power range status
• +12V power range status • -5V power range status
• +5V power range status • -12V power range status
• +3.3V power range status • Aircraft power range A status
• +2.5V CH 1 power range status • Aircraft power range B status
• +2.5V CH 2 power range status • Supercap voltage monitor status
• +1.3V power range status
Analog
• Aircraft power A
• Aircraft power B
• Temperature
Discrete
• System ID Program 1
• System ID Program 2

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Fuel
• System Fuel Type
Operations
The GSD Status Configuration page allows the following operations:
• Select a GSD unit

4.6.5.5 GEA Page Group

GIA Engine Configuration Page

Data
• Consult with Garmin Field Service Engineering regarding the applicability of each data
field to the Learjet 70/75 platform.

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GEA Status Page

There are nine page modes for the GEA Status page. Each mode is accessible via softkeys and
displayed data is described below:
Main Mode
The GEA Status Configuration page displays the following data for GEA 1, GEA 2, or GEA 3:
• Calibration valid • Main board internal temperature
• Configuration valid • Main board external temperature
• Internal voltage exceeded flag • Main board +2.5 reference voltage
• Main EEPROM failure status • Main board +5 external voltage
• EEPROM A failure status • Main board +10 external voltage
• EEPROM B failure status • Main board +12 external voltage
• RAM failure status • Main board -2.1 internal voltage
• ROM failure status • Main board +2.5 internal voltage
• XILINX failure status • Main board +3.3 internal voltage
• RS-485 (1 and 2) failure status • Main board +5 internal voltage
• COM channel over utilized status • Main board +5.75 transformer
voltage
• Main board aircraft power #1
• Main board +13.8 transformer
• Main board aircraft power #2
voltage

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 • Main board +30 transformer • Input / Output B board +3.3 internal
voltage voltage
• Input / Output A board +2.5 • Input / Output B board +5 internal
reference voltage voltage
• Input / Output A board -2.1 internal • Input / Output B board -5.75
voltage transformer voltage
• Input / Output A board +3.3 • Input / Output B board internal
internal voltage temperature
• Input / Output A board +5 internal • Input / Output B board external
voltage temperature
• Input / Output B board +2.5 • Input / Output B board backshell
reference voltage temperature
• Input / Output B board -2.1 internal
voltage
Data Viewing Modes
The following input viewing modes is available via softkey:
• Analog/Current
• Analog Input
• Current Monitor
• Engine Temperature
• Backshell Thermocouple
• Annunciator
• Digital Input
• Discrete Input
• For each input viewing mode, the following data is viewable:
• List of each input/output channel for the selected GEA
• Configured data type for each input/output channel
• Data validity of each input/output channel
• Data value of each input/output channel
Operations
In addition to the softkey operations, the GEA Status Configuration page allows the following
operation:
• Select which GEA to display data for

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GEA Configuration Page

Page Security
The GEA Configuration page allows modification after entering the key sequence: (softkey 1,
softkey 2, softkey 3, softkey 4) and is reserved for Garmin Field Service Engineering
troubleshooting.

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4.6.5.6 GTX Page Group
Transponder Airframe Configuration Page

Data
The Transponder Configuration page displays the following set data and active data for each
configured transponder:
• Address type • VFR code
• Address • Enhanced surveillance status
• Flight ID type • ADS-B transmit mode
• Flight ID • Aircraft width
• Aircraft weight • Aircraft length
• Maximum airspeed • Surveillance integrity type
Operations
The Transponder Configuration page allows the following operations:
• Select transponder unit
• Select address type

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 • Modify address
• Select flight ID type
• Modify flight ID
• Select aircraft weight
• Select maximum airspeed
• Modify VFR code
• Modify enhanced surveillance status
• Modify ADS-B transmit mode
• Modify aircraft width
• Modify aircraft length
• Modify surveillance integrity type
• Copying set data to active data by pressing the SET>ACTV softkey
• Copying active data to set data by pressing the ACTV>SET softkey (when only one
transponder is configured)
• Copying transponder #1 active data to set data and transponder #2 active data by
pressing the ACT1>SET softkey (when two transponders are configured)
• Copying transponder #2 active data to set data and transponder #1 active data by
pressing the ACT2>SET softkey (when two transponders are configured)

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Transponder Wiring Configuration Page

• Consult with Garmin Field Service Engineering regarding the applicability of this page in
regards to the Learjet 70/75.

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4.6.5.7 GRS Page Group
AHRS/Air Data Input Configuration Page

Data
The AHRS / Air Data Input Configuration page displays the following data:
• AHRS true heading angle (AHRS 1, 2, Standby)
• AHRS roll and pitch angles (AHRS 1, 2, Standby)
• AHRS X, Y, and Z accelerations (AHRS 1, 2, Standby)
• Air data static air temperatures (ADC 1, 2)
• Air data true and indicated airspeeds (ADC 1, 2, Standby)
• Air data vertical speed (ADC 1, 2)
• Air data barometric(ADC 1, 2), density (ADC 1, 2), and pressure altitudes (ADC 1, 2,
Standby)
• Air Data Static Pressure (ADC 1, 2, Standby)
• Air Data Differential Pressure (ADC 1, 2)
• Air Data Mach (ADC 1, 2, Standby)
• Low Speed Awareness Ratio (ADC 1, 2)
• Green Circle Ratio (ADC 1, 2)
• Yellow Band Ratio (ADC 1, 2)

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 • Yellow Band Offset (ADC 1, 2)
Operations
• No operations exist for the AHRS / Air Data Input Configuration page.
• No menu options exist for the AHRS / Air Data Input Configuration page.
• No softkey options exist for the AHRS / Air Data Input Configuration page.

GRS/GMU Calibration Page

Page Security
The GRS/GMU Calibration page allows modification after entering the key sequence: (softkey 9,
softkey 10, softkey 11, softkey 12)
Data
The GRS / GMU Calibration Configuration page displays the following data:

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 • Current GRS unit selected
• Current procedure selected
• GPS communication status
• Air data communication status
• Magnetometer communication status
• Pre-calibration checklist
• Calibration instructions
• Angle and tolerance level which aircraft must turn to right (during magnetometer
calibration)
• Angle and tolerance level to which aircraft must turn (during heading offset calibration)
• Number of seconds to hold aircraft's current position (during magnetometer and
heading offset calibrations)
• Calibration checklist (during pitch / roll offset calibration)
• Calibration status (displayed at appropriate times during each calibration)
• Engine run-up test results (displayed at end of engine run-up test)
• Magnetometer interference test results (displayed at end of magnetometer interference
test)
• Primary engine instrumentation window with the thumbnail disabled (see the airframe
specific
• requirements document; all supported airframe requirements documents are listed in
GDU-SsSWR)
Operations
The GRS / GMU Calibration Configuration page allows the following operations for each field on
the page:
• Select a GRS unit from the GRS drop-down list
• Select procedure (pitch/roll offset, magnetometer, heading offset, engine run-up test,
magnetometer interference test) from the procedure drop-down list
• Confirm each item in pre-calibration checklist by highlighting the row and pressing ENT,
which toggles the status box for that row from black to green
• Confirm user is ready to start the procedure by pressing ENT on each verification step,
then selecting the CONFIRM field, then pressing ENT
• Confirm user is at instructed heading (during heading offset calibration)
• Confirm each item in calibration checklist (during pitch / roll calibration)
• Confirm aircraft is level (during pitch / roll offset calibration)

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 • Confirm user is aware of calibration status (upon error or success of each calibration) by
requiring ENT press before continuing
• Confirm user is aware of engine run-up test results (upon success or failure) by requiring
ENT press before continuing
• Confirm user is aware of magnetometer interference test results (upon success or
failure) by requiring ENT press before continuing the units, the GMU44 has failed or a
GRS 7800 communication port failure.

4.6.5.8 ADC Page Group

ADC Configuration Page

Page Security
GDU airspeed filter time constants, GDU airspeed filter transition points, GDU vertical speed
filter time constant, GDU airspeed anticipation gain and maximum, and altitude and airspeed
error correction alert statuses are only displayed and editable with an unlock card.
Data
The ADC Configuration page displays the following data:
• Status of the altitude 1 error correction alert
• Status of the altitude 2 error correction alert
• Status of the airspeed 1 error correction alert
• Status of the airspeed 2 error correction alert
• GDU airspeed filter time constants (low, high)
• GDU airspeed filter time constant airspeed transition points (to low, to high)
• GDU vertical speed filter time constant
• GDU airspeed anticipation gain

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 • GDU airspeed anticipation maximum
Operations
The ADC Configuration page allows the following operations:
• Enable or disable the altitude 1 error correction alert
• Enable or disable the altitude 2 error correction alert
• Enable or disable the airspeed 1 error correction alert
• Enable or disable the airspeed 2 error correction alert
• Edit GDU airspeed filter time constants
• Edit GDU airspeed filter time constant airspeed transition points (to low, to high)
• Edit GDU vertical speed filter time constant
• Edit GDU airspeed anticipation gain
• Edit GDU airspeed anticipation maximum

4.6.5.9 GFC Page Group

GFC Configuration Page

Data
The GFC Configuration page displays the following data:
• Selected GIA unit (1 or 2)
• Settable and active AP disconnect removed flight director setting (yes, no)
• Settable and active pitch servo (none, GSA80, GSA81, GTA82, EMB500 TRIM, GSA80
HIGH SPEED, EMB505 TRIM, GSA9000)
• Settable and active roll servo (none, GSA80, GSA81, GTA82, EMB500 TRIM, GSA80 HIGH
SPEED, EMB505 TRIM, GSA9000)
• Settable and active yaw servo (none, GSA80, GSA81, GTA82, EMB500 TRIM, GSA80 HIGH
SPEED, EMB505 TRIM, GSA9000)

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 • Settable and active pitch trim servo (none, GSA80, GSA81, GTA82, EMB500 TRIM, GSA80
HIGH SPEED, EMB505 TRIM, GSA9000)
• Configured roll trim servo axis type (ROLL TRIM, YAW SAS)
• Settable and active roll trim or yaw SAS servo (none, GSA80, GSA81, GTA82, EMB500
TRIM, GSA80 HIGH SPEED, EMB505 TRIM, GSA9000)
• Settable and active yaw trim servo (none, GSA80, GSA81, GTA82, EMB500 TRIM, GSA80
HIGH SPEED, EMB505 TRIM, GSA9000)
Operations
The GFC Configuration page allows the following operations:
• Activating settable settings by pressing the SET>ACTV softkey
• Selecting GIA unit (1 or 2) from the GIA unit drop-down list
• Setting AP disconnect removes flight director setting (yes, no)
• Setting pitch servo (none, GSA80, GSA81, GTA82, EMB500 TRIM, GSA80 HIGH SPEED,
EMB505 TRIM, GSA9000)
• Setting roll servo (none, GSA80, GSA81, GTA82, EMB500 TRIM, GSA80 HIGH SPEED,
EMB505 TRIM, GSA9000)
• Setting yaw servo (none, GSA80, GSA81, GTA82, EMB500 TRIM, GSA80 HIGH SPEED,
EMB505 TRIM, GSA9000)
• Setting pitch trim servo (none, GSA80, GSA81, GTA82, EMB500 TRIM, GSA80 HIGH
SPEED, EMB505 TRIM, GSA9000)
• Setting the roll trim servo axis type (ROLL TRIM, YAW SAS)
• Setting roll trim or yaw SAS servo (none, GSA80, GSA81, GTA82, EMB500 TRIM, GSA80
HIGH SPEED, EMB505 TRIM, GSA9000)
• Setting yaw trim servo (none, GSA80, GSA81, GTA82, EMB500 TRIM, GSA80 HIGH SPEED,
EMB505 TRIM, GSA9000)

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GFC Status Page

Data
The following data is displayed on the GFC Status page:
• For each GIA and configured GSA or GTA, the GFC Status page displays the state of the
LRU's AP DISC input.
For each configured GSA or GTA, the GFC Status page is capable of the following:
• Display the state of the program lines for each processor
• Display the PFT state for each processor
• Display a test status message during execution of a servo slip-clutch or yaw SAS test.
For each configured GSA, the GFC Status page is capable of the following:
• Display the state of the following Boolean inputs: clutch engagement status, high
resolution load cell calibration, and high range load cell calibration
• Display the servo motor's speed (in RPM), voltage, and current as reported by the
control processor.
• Display the servo's torque (in in-lb) as reported by the monitor processor.
• Display numeric results of slip-clutch test (in in-lb).
For each configured GTA, the GFC Status page is capable of the following:
• Display the state of the SERVO ENABLE input
• Display the command voltage and current of the GTA.

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Operations
The following operations are available on the GFC Status page:
For each GIA and configured GSA or GTA, the GFC Status page provides an interface for restoring
the part number of the certification gains to its default value.
For each configured GSA, the GFC Status page is capable of the following:
• Provide an interface for engaging/disengaging the clutch
• Provide an interface for driving the servo at a specified RPM or stopping the servo
• Provide an interface for initiating a servo slip-clutch test on a specific axis.
• Provide an interface for initiating a servo slip-clutch test on all axes.
• For each configured GTA, the GFC Status page provides an interface for driving the GTA
at a specified voltage or stopping the GTA command
• If the yaw SAS servo is configured on GIA 1 and the PFT state for each processor is
passed, then the GFC Status page provides an interface for initiating a yaw SAS servo
test on this servo.
• If a servo slip-clutch test or a yaw SAS servo test is in progress, the GFC status page
provides an interface for canceling the diagnostic test
Related Functionality
For each configured GSA or GTA, the GFC Status page is capable of the following:
• Output the currently selected servo axis on HSDB.
• If the state of AP DISC input into any of the configured LRUs becomes inactive, the GFC
Status page resets all engagement/driving commands

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4.6.5.10 GMA Page Group
GMA Status Page

Data
• Selected GMA unit
Status
• Unit Type
• Power Cycles
• Power Hours
• CPU1 Fault Status (green check equals no fault)
• CPU2 Fault Status (green check equals no fault)
• CPU1 RAM Fault Status (green check equals no fault)
• CPU2 RAM Fault Status (green check equals no fault)
• CPU1 NonVol Fault Status (green check equals no fault)
• CPU2 NonVol Fault Status (green check equals no fault)
• CPU1 Electrical Fault Status (green check equals no fault)
• CPU2 Electrical Fault Status (green check equals no fault)
• FPGA Fault Status (green check equals no fault)

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 • Key Fault Status (green check equals no fault)
• Audio Fault Status (green check equals no fault)
• Routing Fault Status (green check equals no fault)
• Clip Fault Status (green check equals no fault)
Discrete In
• CPU1 GMA2 Strap Value (Low = GMA1, High = GMA2)
• CPU2 GMA2 Strap Value (Low = GMA1, High = GMA2)
• Pilot Push-To-Command Value
• Copilot Push-To-Command Value
• Passenger Push-To-Command Value
• Pilot Stereo Headset Short Status - Left and Right side (green check equals no short)
• Copilot Stereo Headset Short Status - Left and Right side (green check equals no
short)
• Passenger Stereo Headset Short Status - Left and Right side (green check equals no
short)
• Pilot Push-To-Talk Value
• Copilot Push-To-Talk Value
• Generic Inputs 1-10 Values
Discrete Out
• Exit Fail Safe Status (green check equals unit is out of fail safe mode)
• Middle Marker Sensitivity Value
• Digital Onside Push-To-Talk 1 Value
• Digital Onside Push-To-Talk 2 Value
• Digital Cross side Push-To-Talk 1 Value
• Digital Cross side Push-To-Talk 2 Value
• COM1 Microphone Key Value
• COM2 Microphone Key Value
• Generic Outputs A-G Values
• Generic Lamps A-C Values
Voltage
GMA36 Voltages
• Aircraft1 Supply Voltage Value
• Aircraft2 Supply Voltage Value

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 • 12 Volt Supply Monitor Value
• +12 Volt Supply Monitor Value
• -12 Volt Supply Monitor Value
Temperature
• Current Temperature (in Celsius)
• Minimum Temperature (in Celsius)
• Maximum Temperature (in Celsius)

GMA Volume Configuration Page

Data
• Selected GMA Unit
• Selected Volume Configuration Type
• Selected Output Range To Be Displayed
Volume Configuration
A lookup table representing the adjustable volume configuration setting for any specified
input/output pair. The actual setting is equivalent to the value in the top row (the output) + the
value in the leftmost column (the input) + the intersection point. Each of these settings are
individually displayed in the following manner:
• The value in the top row (output). This value will affect all inputs for that output.
• The value in the left column (input). This value will affect all outputs for that input.

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 • The value at an intersection. This value will only affect that individual input/output
pairing.
Operations
The Digital GMA Volume Configuration page allows the following operations:
• Select GMA unit
• Select Volume Configuration Type (Minimum or Maximum)
• Select Output Range to be Displayed (1-24 or 25-48)
A lookup table representing the adjustable volume configuration setting for any specified
input/output pair. The actual setting is equivalent to the value in the top row (the output) + the
value in the leftmost column (the input) + the intersection point. Each of these settings can be
individually modified in the following manner:
• Modifying the value in the top row (output) will affect all inputs for that output.
• Modifying the value in the left column (input) will affect all outputs for that input.
• Modifying the value at an intersection will only affect that individual input/output
pairing.
• Copy set information to the active information by pressing the SET>ACTV softkey

GMA Squelch Configuration Page

Data
SELECTED GMA UNIT

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AUDIO CONFIGURATION
• Set and active squelch threshold for all 95 inputs
NOTE: This value represents the volume the input must receive to break squelch.
• Set and active squelch persistence for all 95 inputs
NOTE: This value represents the length of time the input volume must be below the squelch
threshold to close squelch once it has been broken.
Operations
The Digital GMA Squelch Configuration page allows the following operations:
• Select GMA unit
• Modify the set configuration for the squelch threshold for any of the 95 inputs (Decibels)
NOTE: This value represents the volume the input must receive to break squelch.
• Modify the set configuration for the squelch persistence for any of the 95 inputs
(milliseconds)
NOTE: This value represents the length of time the input volume must be below the squelch
threshold to close squelch once it has been broken.

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GMA Options Configuration Page

Data
The Digital GMA Options Configuration page displays the following data:
Selected GMA Unit
Audio Configuration
• Text string for any of the 256 generic audio configuration options
• Set and active configuration setting for any of the 256 generic audio configuration
options
Operations
The Digital GMA Options Configuration page allows the following operations:
• Select GMA unit
• Modify the set configuration setting for any of the 256 generic audio configuration
options (User, On, or Off)
• Copy set information to the active information by pressing the SET>ACTV softkey
• Copy active information to the set information by pressing the ACTV>SET softkey
• Selected GMA unit
• Set and active setting for the disablement of the high sensitivity discrete
• Set and active audio offset threshold
• Set and active audio off debounce
• Set and active HI sensitivity offset

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 • Set and active LO sensitivity offset
GMA Marker Beacon Configuration Page

Data
The Digital GMA Marker Beacon Configuration page displays the following data:
Selected GMA Unit
Marker Beacon
• Set and active setting for the disablement of the high sensitivity discrete
• Set and active audio offset threshold
• Set and active audio off debounce
• Set and active HI sensitivity offset
• Set and active LO sensitivity offset
Operations
The Digital GMA Marker Beacon Configuration page allows the following operations:
• Select GMA unit
• Modify the set configuration for the disablement of the high sensitivity discrete
• Modify the set configuration for the audio offset threshold (Decibels)
NOTE: This value represents how soon the pilot will hear the marker beacon tone before the
marker beacon light illuminates.
• Modify the set configuration for the audio off debounce (milliseconds)
NOTE: The value represents how long the modulated marker beacon signal can drop below the
audio offset threshold value before the marker beacon tone will stop (very similar to squelch
persistence).
• Modify the set configuration for the HI sensitivity offset value (unit less)
• Modify the set configuration for the LO sensitivity offset value (unit less)
• Copy set information to the active information by pressing the SET>ACTV softkey

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4.6.5.11 GDL Page Group
GDL 69 Configuration Page

Configuration
• SELECT GDL ANTENNA―selects the GDL antenna.
• ANTENNA GAIN (LOWER dB)―sets the antenna gain value.
• CABLE LOSS INCLUDING INLINE ATTENUATIONS IF USED (NOMINAL dB)―Sets the inline
cable loss attenuation value.
• GDL CONFIGURABLE ATTENUATION (dB)―sets the desired GDL attenuation value.
• ETHERNET PORT 2, 3, 4―enables and/or disables the desired Ethernet port.
Data
• ID―displays the identification number for the GDL 69.
• ACTIVE―displays the active status for the GDL 69.
• SIGNAL―displays the signal level for the GDL 69:
0 – no signal
1 – weak signal
2 – adequate signal
3 – good signal

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 Levels 2 and 3 should allow for proper operation of all GDL 69 weather options.
Levels 0 and 1 are likely indications of problems with availability. A “204”
message in the signal field indicates that signal information has not initialized.
Diagnostics (For XM use only, not useful for troubleshooting)
• QUALITY OF SERVICE―displays the quality of service for the GDL 69.
• TERRESTRIAL ERROR STATUS―displays the terrestrial error status for the GDL 69.
• SATELLITE 1 ERROR―displays the error status for satellite 1.
• SATELLITE 2 ERROR―displays the error status for satellite 2.

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GDL 59 Status Page

Hardware Statistics
The GDL59 hardware statistics are displayed, including:
• The current system temperature in Celsius
• The maximum overall system temperature in Celsius
• The minimum overall system temperature in Celsius
• The unit power up count
• The unit power on time in hours
• The hardware version of the main GDL59 board
• The hardware version of the memory board on the GDL59
Discrete
The GDL59 discrete data is displayed, including:
• System ID pin status
• Attached GSR56 #1 or #2's heat OK status
• POTS phone on hook status
Hardware Failures
The GDL59 hardware failures is displayed, including:
• If the system temperature reading is invalid
• If the system temperature is too high
• If the system temperature is too low
• If the system NAND (flash memory) has failed
• If the memory board NAND (flash memory) has failed

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 • If the Wi-Fi module has failed
• If the system hardware statistics detection has failed
Voltage Range Monitor
The voltage monitor readings and failure statuses is displayed for all voltage monitors, which
include:
• +24V (in millivolts)
• +12V (in millivolts)
• +5V (in millivolts)
• +3.3V (in millivolts)
• +3.2V (in millivolts)
• +2.5V (in millivolts)
• +1.8V (in millivolts)
• +1.3V (in millivolts)
• -5V (in millivolts)
• -12V (in millivolts)
• Aircraft power A (in millivolts)
• Aircraft power B (in millivolts)
• Fan (in milliamperes)
• POTS battery (in millivolts)

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GDL 59 Configuration Page

Enabled Functionality
The GDL59 functionality that is enabled by configuration is displayed, including:
• Data logging/report functionality
• Voice communication
• Wi-Fi communication
Phone Settings
• The set and active setting for if the GDL59's audio system 1 phone is connected is
displayed
• The set and active setting for if the GDL59's POTS phone is connected is displayed
Volume Settings
The set and active volume in and volume out in percentage for all GDL59 phones is displayed,
including:
• AUD 1 for the internal cockpit phone
• IRIDIUM 1 for the external GSR56 #1 phone
• TONE for the playback of tones (volume out only)
• FLIGHT VOICE LOG for the FVL (flight voice logger) microphone (volume in only)
The audio system 1 (cockpit phone) status is displayed, including:
• IDLE if the phone not busy

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 • RINGING if a call is incoming
• DIAL TONE if there is a dial tone
• WAITING if a phone dialed is busy
• DIALING when calling another phone
• CONNECTED when talking with another phone
• FAILED if the phone has failed
• UNKNOWN if an unspecified phone status was provided or if there is no communication
about the phone status
If the audio system 1 (cockpit phone) status is CONNECTED, the phone that audio system 1 is
connected to is displayed, including:
• POTS for the internal phone in the cabin
• IRIDIUM 1 for the external GSR56 #1 phone
• IRIDIUM 2 for the external GSR56 #2 phone
• UNKNOWN if no connected phone(s) was specified or if connected to unspecified
phones
Operations
The following operations are available on the GDL59 Configuration Page:
• Whether or not the GDL59's audio system 1 is connected is selectable
• Whether or not the GDL59's audio system 1 is connected is only be selectable if voice
functionality is enabled for the GDL59
• Whether or not the GDL59's POTS is connected is selectable
• Whether or not the GDL59's POTS is connected is only selectable if voice functionality is
enabled for the GDL59
The volume in and volume out percentages for all GDL59 phones is modifiable, including:
• POTS for the internal phone in the cabin
• AUD 1 for the internal cockpit phone
• IRIDIUM 1 for the external GSR56 #1 phone
• IRIDIUM 2 for the external GSR56 #2 phone
• TONE for the playback of tones (volume out only)
• FLIGHT VOICE LOG for the FVL (flight voice logger) microphone (volume in only)
• Modification of set volume in and volume out percentages for all GDL59 phones is
disabled if voice functionality is disabled for the GDL59
• The cockpit phone is able to be commanded to dial by pressing the DIAL softkey
• The phone number pop-up page is used to collect the number to dial

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The DIAL softkey is enabled for the cockpit phone when all of the following are true:
• The phone status is IDLE or DIAL TONE
• There is another phone configured as available besides the cockpit phone
• The cockpit phone is able to commanded to end calls by pressing the HANGUP softkey
The HANGUP softkey is enabled for the cockpit phone when any of the following are true:
• The phone status is RINGING
• The phone status is WAITING
• The phone status is DIALING
• The phone status is CONNECTED
• The phone status is FAILED
• The phone status is DIAL TONE
• The GDL59 is able to be commanded to play or stop a tone on all GDL59 phones for
volume adjustment by toggling the TONE softkey
• The TONE softkey is disabled if there is no communication about the cockpit phone
status
• Set information is able to be copied to the active information by pressing the SET>ACTV
softkey
• A confirmation page is displayed asking if a user is sure they want to activate parameter
settings when the copy set information to active information operation is initially
triggered
• Active information is able to be copied to the set information by pressing the ACTV>SET
softkey
• A confirmation page is displayed asking if a user is sure they want to copy active settings
when the copy active information to set information operation is initially triggered
Related Functionality
Each cockpit phone command sent to the GDL59 is verified, displaying a message when the
following errors occur:
• A generic error occurred while processing the dial phone command
• A generic error occurred while processing the hang-up phone command
• The phone command timed out
Each tone command sent to the GDL59 is verified, displaying a message when the following
errors occur:
• A generic error occurred while processing the tone command
• The tone command timed out

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GSR 56 (Iridium) Configuration Page

Configuration
The set and active values for whether or not the GSR56 is configured to be available is displayed
by displaying what the GSR56 is connected through, including:
• GIA1 (N/A for active data)
• GIA2 (N/A for active data)
• GDL59
• NONE
• UNKNOWN (for active data only)
Permission Level
The set and active permission level of the GSR56 is displayed, including:
• NONE if the GSR56 has no permissions
• VOICE if the GSR56 can perform voice communication
• DATA if the GSR56 can perform data communication
• UNKNOWN (for active data only)
Enabled Functionality
The set and active GSR56 functionality that is enabled is displayed, including:
• Whether or not voice communication is prioritized over data communication
• The set default international code shall be displayed
Operations
Operations available on the GSR56 Configuration Page are as follows:
• The default international code is modifiable.
• Default international code's can only be composed of the following characters:
o Digits "0" through "9"

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 o The pound key "#"
o The star key "*"

4.6.5.12 RMT Group

Remote Controller Status Page

Data
The Remote Controller Status page displays the following data:
• Current Remote Controller unit selected (GCU/GMC)
• The type of GCU or GMC configured
Selected Remote Controller's serial port #1 status:
• Configured GDU on Remote Controller serial port
• Online status of GDU configured on Remote Controller serial port (online or offline)
• GDU serial channel configured for Remote Controller interface
• Status of link from GDU to Remote Controller serial port (okay, fail, inactive)
Selected Remote Controller's serial port #2 status:
• Configured GDU on Remote Controller serial port
• Online status of GDU configured on Remote Controller serial port (online or offline)
• GDU serial channel configured for Remote Controller interface
• Status of link from GDU to Remote Controller serial port (okay, fail, inactive)

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Product data for the selected Remote Controller:
• Part Number
• Version
• Product String
• Description
• Copyright
• Serial Number
• Model Number
• Functions Present
Alert status for the selected Remote Controller:
• Configuration mismatch status (active or inactive)
• Unit failure - inoperative status (active or inactive)
• Stuck key status (active or inactive)
• Stuck key alert message text
Operations
The Remote Controller Status page allows the following operations:
• Select Remote Controller unit using the FMS knob
• Acknowledge the current Remote Controller alerts by pressing the AK ALRTS softkey
• Enable annunciator test mode by pressing the ANN TEST softkey

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4.6.5.13 GWX Page Group
GWX Configuration Page

Data
The GWX Configuration page displays the following data:
• GWX attitude data source (NONE, HSDB, A429, or ANALOG GYRO)
• GWX attitude pitch (degrees with 0.01 degree precision)
• GWX attitude roll (degrees with 0.01 degree precision)
GWX fault status boxes (green check for OK, red x for FAIL):
• Electrical
• AFC
• Config
• 400Hz
• Temp
• EEPROM
• Attitude
• RX TX

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 • RAM
• High Volt
• CAL
• FPGA
• Settable and active radar internal pitch trim (within +/- 4 degrees with 0.05 degree
precision)
• Settable and active radar internal roll trim (within +/- 4 degrees with 0.05 degree
precision)
• Non-modifiable return bins (only modifiable via configuration upload)
• Settable and active extended scan for GWX7x only (enable or disable)
• Settable and active antenna size for GWX7x only (10-INCH, 12-INCH, or 18-INCH)
• Settable and active average cruise speed for GWX7x only (0 to 999 knots)
• GDU-calculated configuration CRC
• GWX-calculated configuration CRC
Operations
The GWX Configuration page allows the following operations:
• Copy the set information to the active information by any of the following:
o Pressing the SET>ACTV softkey
o Pressing ENT while a settable configuration field is highlighted
• Copy the active information to the set information by pressing the ACTV>SET softkey
• Modify the set radar internal pitch trim using the FMS knob
• Modify the set radar internal roll trim using the FMS knob
• Modify the set extended scan for GWX7x only (enable or disable)
• Modify the set antenna size for GWX7x only (10-INCH, 12-INCH, or 18-INCH)
• Modify the set average cruise speed for GWX7x only (0 to 999 knots)

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4.6.5.14 GTS Page Group

GTS Configuration Page

Data
The GTS Configuration page displays the following data:
GTS fault flags (a positive indicator showing no fault, a negative indicator showing fault, an
unknown indicator showing unknown fault status)
• Calibration
• Configuration
• FPGA
• ROM
• Execution
• Electrical
• Whisper Shout
• Transmit Power
• 1030 MHz

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 • 1090 MHz
• PA/LNA
• Receiver
• Transmitter
• Baro Altitude
• Temperature
• TCAS Equip Timeout
• Radio Altitude
GTS Status
• A text field showing selected GTS unit type
• A text field showing temperature (Celsius degrees with 0.1 Celsius degree precision)
• A text field showing radio altitude availability
• A button for the GTS audio test
• A button for the GTS self-test
• A text field labeled "DATA LOG ENABLED" if the GTS data log is enabled
Configuration
• Set and active top antenna
• Set and active top antennal cable loss (decibels with 0.1 decibel precision)
• Set and active bottom antenna
• Set and active bottom antenna cable loss (decibels with 0.1 decibel precision)
• Set and active mode s address
• Set and active volume (decibels with 0.5 decibel precision)
• Set and active voice
• Set and active ADS-B TX
• Set and active landing gear
Operations
The GTS Configuration page allows the following operations:
• Copy set information to active information by pressing the Enter key or SET>ACTV
softkey.
• Copy active information to set information by pressing the ACTV>SET softkey.
• Modify top antenna by choosing one of the following antenna types using the FMS knob:
o Garmin GA58
o Sensor systems

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 o Modify top antenna cable loss using FMS knob.
o Modify bottom antenna by choosing one of the following antenna types using
the FMS knob:
• None
• Monopole
• Garmin GA58
• Sensor systems
Modify bottom antenna cable loss using FMS knob
Modify volume using FMS knob
Modify voice by choosing one of the following options using FMS knob:
• Male
• Female
Modify ADS-B TX by choosing one of the following options using FMS knob:
• Installed
• Not Installed
Modify landing gear by choosing one of the following gear types using FMS knob:
• Fixed
• Retractable
• Test GTS audio system by pressing "Audio Test" button.
• Test GTS TCAS test mode by pressing "Run Self-Test" button.

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4.6.5.15 GDR Page Group
GDR Status Page

Data
The GDR Status page displays the following data reported from the COM and AUX processors:
COM Faults
 RAM status
 ROM status
 Electrical hardware monitor status
 Voltage monitor status
 Temperature monitor status
 Low Temperature fault status
 High Temperature fault status
 Software revision fault status
 Software CRC fault status
 Invalid part number fault status
 Receiver fault status

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  Transmitter fault status
 AM transceiver fault status
 VDL transceiver fault status
 Antenna VSWR fault status (as indicated by transmitter reflected power)
 Push-To-Talk switch stuck failure status
 Transmitter Needs Service status
 Transmitter Current Limited status (may indicated poor antenna performance or low
input voltage)
AUX Faults
 RAM status
 ROM status
 Electrical hardware monitor status
 Voltage monitor status
 Temperature monitor status
 Low Temperature fault status
 High Temperature fault status
 Software revision fault status
 Software CRC fault status
 Invalid part number fault status
COM Board Power
 +6V power voltage
 Power-Amplifier power supply current
 Power-Amplifier power supply voltage
AUX Board Power
 Summed aircraft power voltage
 +12V power voltage
 +6V power voltage
 +5V power voltage
 +3.3V power voltage
 +1.8V power voltage
 -5V power voltage
 -12V power voltage

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COM Board Temperature Sensors
 Heater temperature
 Modulator temperature
 Power-Amplifier temperature
AUX Board Temperature Sensors
 Unit temperature
GDR Status
 Tuned Channel frequency
 Transmitter Power status (20W, 10W or 5W based on input voltage and over-
temperature conditions)
 Operational Mode (AM, VDL, ACARS)
 Emergency Mode status
Operations
The GDR Status page allows the following operations:
 None

GDR Configuration Page

Data
The Setup Configuration page displays the following data:
• COM receiver audio output gain
• COM transmitter sidetone audio gain
• COM transmitter microphone gain
• Squelch hysteresis

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• Squelch thresholds for 25 kHz and 8.33 kHz operational modes
• Remote transfer (tune to emergency frequency) configuration time in milliseconds
Operations
The Setup Configuration page allows the following operations:
• Select audio gains
• Select squelch performance (Note: positive offsets require a higher signal-to-noise ratio
to break squelch)
• Select remote transfer time (Note: a configuration of zero is permissible)
GDR 66/CPDLC TROUBLESHOOTING

Refer to the following sections in the Learjet AMM for GDR 66 maintenance/troubleshooting
information.
• Controller Pilot Datalink Communication System—Description And Operation- Section
23-25-00.
• Controller Pilot Data Link Communications (CPDLC) System— Maintenance Practices-
Adjustment/Test-Section 23-25-00.
• VHF Datalink Radio Unit— Maintenance Practices-Section 23-25-01.

4.6.5.16 Cal Page Group

Angle of Attack Calibration Page

The AOA calibration page allows the AOA Vane Offset to be entered. The Vane Offset procedure
is described in the AOA Calibration Procedure in Section 27-31-00 of the Learjet 106
Maintenance Manual MM-106 and MM-107.

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 4.6.6 GWX 70 Weather Radar Troubleshooting
In addition to the information given in this section, the Technician should refer to Sections 34-
42-00, and 34-42-03, and any other pertinent sections in the Learjet Maintenance Manual for
GWX 70 Weather Radar System maintenance/troubleshooting information.
4.6.6.1 GWX 70 Troubleshooting Table

The table below lists the various GWX fault indication descriptions and corrective actions.
The fault indications are reset if PFD1 is transitioned from normal mode to configuration mode.
It will return if the fault is persistent. It may not return if the fault is intermittent. The fault
indications also reset with a power cycle to the unit. Note: transitioning the MFD to
configuration mode will not reset the fault indications.
STATUS FAULT FAULT INDICATION CORRECTIVE ACTION
INDICATOR BOX INDICATION DESCRIPTION
ELECTRICAL Voltages within the unit are  Cycle unit twice to confirm
out of range. problem.
 Replace the GWX 70 if
condition remains.
400Hz Attitude input is not valid if  N/A for G5000s, this box
using the 400hz input. A valid should always be checked
400Hz attitude signal must be green.
received then lost to set this  If problem persists, replace the
box to red in the current GWX.
power cycle.
HIGH VOLT Monitoring for >33V at the  Check voltage at input of unit
power input to the GWX. (should be <33V). If over 33V,
Transitions unit to standby troubleshoot aircraft power
mode if over 33V. system.
 Check if condition occurred
due to aircraft system power
spike due to other non-G5000
electrical equipment loads.
 Correct issues that cause
aircraft electrical system
power spikes.
 If problem persists, replace the
GWX
 Cycle power on unit only to
see if fault remains, if it does,
replace the GWX.
AFC Automatic frequency control If problem persists, replace the
within the unit has a fault, will GWX.
make unit enter Standby
mode.

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 STATUS FAULT FAULT INDICATION CORRECTIVE ACTION
INDICATOR INDICATION DESCRIPTION
BOX
TEMP Unit temp >85C.  If condition occurred during
flight, replace the GWX 70.
 If condition occurs on the
ground due to excessive
heat inside the radome,
turn unit off and allow it to
cool before further use.
 If the condition occurs on
the ground and the
temperature is normal in
the radome, replace the
GWX 70.
RX TX Fault within the unit, will  Ensure latest GWX software
make unit enter standby version is installed.
mode.  If problem persists, replace
the GWX.

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 STATUS FAULT FAULT INDICATION CORRECTIVE ACTION
INDICATOR INDICATION DESCRIPTION
BOX
CAL Bad factory calibration data. Replace the GWX 70.
CONFIG Troubleshoot per GWX config
GWX and GDU configuration
message in the Advisory Message
do not match.
table.
EEPROM Internal EEPROM
Replace the GWX 70.
component failed.
RAM Internal RAM component
Replace the GWX 70.
failed.
FPGA Internal FPGA component
Replace the GWX 70.
failed.
ATTITUDE  Check the AHRS source for
The unit does not have a proper operation (refer to
valid attitude source via AHRS section or
A429 databus or 400Hz manufacturer’s manual).
input.  If problem persists, replace
the GWX.

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4.6.6.2 Miscellaneous Radar Faults
Problem Possible Cause Resolution
Radar audibly noisy during Excessive gear train noise or Remove radome.
ground operation. radome interference 1. Inspect interior surfaces of
the radome for contact
with the radar dish.
Correct interference by
adjusting or replacing
radome.
2. If no radome interference
is found, perform the
following:
3. Turn on the G5000.
4. Select the radar page on
the MFD.
5. Press the following
softkeys in the following
order: 7, 9, 9, 7.
6. Press the MODE softkey
7. Press the TEST softkey.
The radar dish will begin
scanning, but it will not be
transmitting.
8. Test the horizontal and
vertical modes to exercise
the gear train and
evaluate for noise.
9. Replace the GWX 70 if the
gears are excessively
noisy.
Radar fails to make a full Radome Interference or GWX 1. Remove the radome and
vertical or horizontal sweep 70 failure inspect interior surfaces
on the screen. for contact with the radar
dish. Correct interference
by adjusting or replacing
the radome.
2. If problem persists,
replace the GWX.

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4.7 COMMON G5000 ISSUES AND CORRECTIVE ACTIONS
This section lists some common issues and suggested corrective actions.
4.7.1 GDU 1400W
NOTE: In addition to the information in this section, refer to the following sections in the Learjet
AMM for GDU 1400W maintenance information:
Display Unit - Maintenance Practices
• Removal/Installation—Section 31-60-01
• Removal of the Display Unit (DU)— Section 31-60-01
• Installation of the Display Unit (DU)— Section 31-60-01
• Inspection/Check—Section 31-60-01
• Operational Check of the Display Unit—Section 31-60-01
• Cleaning —Section 31-60-01
• Cleaning the Display Unit—Section 31-60-01
Display/Keyboard Will Not Track Dimmer Bus
1. If you suspect the settings were manually changed by an operator, reload PFD1/2,
MFD, GCU and GMC Configuration files including optional equipment configuration
files that list PFD1/2 and MFD on the System Upload page.
2. Reload GDU configuration files.
3. If display is a PFD, swap PFD1 and PFD2 to see if problem remains with display.
Replace display if condition remains with the same unit.
4. If condition remains in original position after swapping displays, check display
dimmer input to verify voltage is present (disconnect the unit and check pin 59 in
the wire harness connector for a voltage.)
5. If display is the MFD, check dimmer input to verify voltage is present.
6. Replace MFD if dimmer voltage is present.
Display is Blank, Resets, Or Flickers
1. Cycle power. If GDU recovers, observe display for yellow text containing error
information at the top of the screen. If message indicates software need to be
reloaded, then reload software. Otherwise, replace the GDU.
2. Use a bright light to verify LCD is active.
3. Adjust avionics dimmer control full clockwise.
4. Manually turn up backlight on PFD1 and load configuration files to the GDU.
5. Ensure slide lock is fully engaged with the locking tabs on the back of the unit. If
slide lock is not fully engaged, remove connector and verify the locking tabs on the
GDU are perpendicular to the connector. If necessary, straighten them before
reseating connector.

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 6. Ensure GDU is receiving power and ground. If a circuit breaker is tripped, determine
source of short before resetting breaker.
7. Ensure circuit breakers have not failed and power wire connections are secure.
Swap PFD1 and PFD2. If problem follows unit, replace the display. Note the position
it failed in (PFD1/2). If problem does not follow unit, troubleshoot aircraft wiring for
fault.
SD Card is Stuck In GDU
1. DO NOT insert a screwdriver of any length into the card slot.
2. DO NOT pry against the overlay.
3. DO NOT force the SD Card out.
4. Use a small screwdriver in the groove on the side of the exposed end of the card to
help pull out the card.
5. You may need to push the card in further to release the card locking mechanism.
6. If the card can be removed, check the SD card for more than one label. Two or more
labels on the card will cause sticking.
7. Remove all but one label.
8. Ensure the SD card is from SanDisk. Use of other SD Cards is not approved.
9. If card was inserted with the label facing to the right, do not attempt to remove.
Return the unit to Garmin for repair.
A Button/Knob/Joystick Does Not Appear to Function
1. Go to the GDU TEST page in configuration mode and verify button, knob, or joystick
operates correctly by observing a change in color from red to green in the
button/knob/joystick icon when the button/knob/joystick is pressed. If a button is
stuck, the button icon will be green without pressing the button as soon as you turn
to the GDU TEST page.
2. If problem is verified, replace GDU.
Terrain/Obstacle/SafeTaxi Does Not Display
1. Check for any Database Error Messages. Correct any before proceeding.
2. Ensure supplemental data cards are inserted correctly in the lower slots of all three
GDU’s.
3. Allow the system to verify the data on the cards for after power-up. (Note: this may
take up to one hour.)
4. If a database does not activate, reload the problem database onto the SD Card or
replace the card. You may need to replace all data cards as a set to keep the
database cycles the same and prevent database mismatch errors.

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4.7.2 GIA 63W
NOTE: In addition to the information in this section, refer to the following sections in the Learjet
AMM for GIA 63W maintenance information:
INTEGRATED AVIONICS UNIT - MAINTENANCE PRACTICES
• Removal/Installation—Section 31-41-01
• Removal of the Integrated Avionics Unit Number 1 and Number— Section 31-41-01
• Installation of the Integrated Avionics Unit Number 1 and Number— Section 31-41-01
• Adjustment/Test—Section 31-41-01
• Operational Check of the Integrated Avionics Unit—Section 31-41-01
Weak COM Transmit Power
1. Swap GIA1 and GIA2, reconfigure both GIA’s to their new locations to verify if the
unit or aircraft wiring is the problem.
2. If problem follows unit, replace GIA.
3. If problem does not follow unit, check COM antenna and cabling for faults.
Weak COM Receiver
1. Swap GIA1 and GIA2, reconfigure both GIA’s to their new locations to verify if the
unit or aircraft wiring is the problem.
2. If problem follows unit, replace GIA.
3. If problem does not follow unit, check COM antenna and cabling for faults.
No COM Sidetone
1. Swap GIA1 and GIA2, reconfigure both GIA’s to their new locations to verify if the
unit or aircraft wiring is the problem.
2. If problem follows unit, replace GIA.
3. If problem persists, replace GMA #1 with a known good unit.
4. If problem persists, reinstall original GMA #1 and replace GMA #2.

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4.7.2.1 WAAS GPS

Background Information/GPS Receiver Operation

Each GIA 63W Integrated Avionics Unit (IAU) contains a GPS receiver. Information collected by
the specified receiver (GPS 1 for the #1 IAU or GPS 2 for the #2 IAU) may be viewed on the GPS 1
or GPS 2 Status Pane and the GPS Status Screen on the Touchscreen Controller (refer to Figure 4-
7).
These GPS sensor annunciations are most often seen after system power-up when one GPS
receiver has acquired satellites before the other, or one of the GPS receivers has not yet
acquired an SBAS (Satellite Based Augmentation System) signal. While the aircraft is on the
ground, the SBAS signal may be blocked by obstructions causing one GPS receiver to have
difficulty acquiring a good signal. Also, while airborne, turning the aircraft may result in one of
the GPS receivers temporarily losing the SBAS signal. If the sensor annunciation persists, check
for a system failure message by touching the MSG Button on Touchscreen Controller. If no
failure message exists, check the GPS Status Screen and compare the information for GPS 1 and
GPS 2. Discrepancies may indicate a problem.

Figure 4-7. GPS Receiver Information

Selecting the GPS receiver:

1. From the Home, touch Utilities > GPS Status.

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 2. Touch the GPS1 button to select the #1 GPS receiver. The button annunciator is green
when enabled, gray when disabled. The system displays the GPS1 STATUS Pane.
3. Touch the GPS 2 button to select the #2 GPS receiver. The button annunciator will be
green when selected on.
4. The system displays the GPS2 STATUS Pane.
Satellite Constellation Diagram
Satellites currently in view are shown at their respective positions on a sky view diagram. The
sky view is always in a north-up orientation, with the outer circle representing the horizon, the
inner circle representing 45° above the horizon, and the center point showing the position
directly overhead.
Each satellite is represented by an oval containing the Pseudo-random noise (PRN) number (i.e.,
satellite identification number). Satellites whose signals are currently being used are
represented by solid ovals.
Satellite Signal Status
The accuracy of the aircraft’s GPS fix is calculated using Estimated Position Uncertainty (EPU),
Dilution of Precision (DOP), and horizontal and vertical figures of merit (HFOM and VFOM). EPU
is the radius of a circle centered on an estimated horizontal position in which actual position has
95% probability of laying. EPU is a statistical error indication and not an actual error
measurement.
DOP measures satellite geometry quality (i.e., number of satellites received and where they are
relative to each other) on a range from 0.0 to 9.9, with lower numbers denoting better accuracy.
HFOM and VFOM, measures of horizontal and vertical position uncertainty, are the current 95%
confidence horizontal and vertical accuracy values reported by the GPS receiver.
The current calculated GPS position, time, altitude, ground speed, and track for the aircraft are
displayed below the satellite signal accuracy measurements.
GPS Receiver Status
The GPS solution type (ACQUIRING, 2D NAV, 2D DIFF NAV, 3D NAV, 3D DIFF NAV) for the active
GPS receiver (GPS 1 or GPS 2) is shown in the lower right of the GPS 1 and GPS 2 Status Pane.
When the receiver is in the process of acquiring enough satellite signals for navigation, the
receiver uses satellite orbital data (collected continuously from the satellites) and last known
position to determine the satellites that should be in view. ACQUIRING is indicated as the
solution until a sufficient number of satellites have been acquired for computing a solution.
When the receiver is in the process of acquiring a 3D navigational GPS solution, 3D NAV is
indicated as the solution until the 3D differential fix has finished acquisition. SBAS (Satellite-
Based Augmentation System) indicates INACTIVE. When acquisition is complete, the solution
status indicates 3D DIFF NAV and SBAS indicates ACTIVE.

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GPS Satellite Signal Strengths
The GPS 1 and GPS 2 Status Panes can be helpful in troubleshooting weak (or missing) signal
levels due to poor satellite coverage or installation problems. As the GPS receiver locks onto
satellites, a signal strength bar is displayed for each satellite in view, with the appropriate
satellite PRN number (01-32 or 120-138 for WAAS) below each bar. The progress of satellite
acquisition is shown in three stages, as indicated by signal bar appearance:
- No bar—Receiver is looking for the indicated satellite
- Hollow bar—Receiver has found the satellite and is collecting data
- Light blue bar—Receiver has collected the necessary data and the satellite signal can be used
- Green bar—Satellite is being used for the GPS solution
- Checkered bar—Receiver has excluded the satellite (Fault Detection and Exclusion)
- “D” indication—Denotes the satellite is being used as part of the differential computations
Each satellite has a 30-second data transmission that must be collected (signal strength bar is
hollow) before the satellite may be used for navigation (signal strength bar becomes solid).
Possible Solutions:
1. Check for possible external interference to the GPS receivers by selecting GPS status
page on the GTC and check the GPS strength bars on both GPS receivers. If the
signal strength level is erratic, or they disappear and reappear rapidly, or switch
between a solid and hollow bar frequently there is an external device interfering
with the GPS receivers. Turn off any devices that radiate a signal in the local area or
move the aircraft to another location to remove the interference.
2. Check date and time on Date/Time Setup Page. If date and time are incorrect, enter
the correct date and time.

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 3. Swap GIA1 and GIA2, to verify location of problem. If problem follows unit, clear the
GPS almanac by performing the following steps:
• Select the GIA RS-232/ARNIC 429 Config Page. At the top of the screen, select
the GIA that cannot acquire satellites (GIA1 or GIA2) and press the ENT key.
• Press the “CLR NV” softkey at the bottom of the screen.
• Select “OK” in the “Clear GIA nonvolatile memory?” pop-up window.
• Reload GIA Audio and Config files. Be sure to reload the config files for any
optional equipment installed on the aircraft that require the GIA config to be
updated.
• Cycle power on the system and allow it to restart in normal mode. Place the
aircraft outside and allow 15-30 minutes for the GPS to acquire a position and
download a new almanac.

4. If clearing nonvolatile memory is unsuccessful and the GPS still cannot acquire a
position, replace the GIA.
5. If problem does not follow unit, replace the GIA.
6. Check GPS antenna and cabling.

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4.7.2.2 NAV
Weak NAV Receiver
1. Set up a NAV/COM Ramp Test Set to radiate a test signal.
2. Swap GIA1 and GIA2 to verify location of problem.
3. If problem follows unit, replace GIA.
4. If problem does not follow unit, check NAV antenna, coupler, and cabling for faults.
Weak G/S Receiver
1. Set up a NAV/COM Ramp Test Set to radiate a test signal.
2. Swap GIA1 and GIA2 to verify location of problem.
3. If problem follows unit, replace GIA.
4. If problem does not follow unit, check NAV antenna, coupler, and cabling for faults.
4.7.3 GDC 7400 Air Data Computer
NOTE: In addition to the information in this section, refer to the following sections in the Learjet
AMM for GDC 7400 maintenance information:
AIR DATA SYSTEM - MAINTENANCE PRACTICES
• Adjustment/Test Section 34-17-00.
• Functional Test of the Air Data System Section 34-17-00.
• Operational Check of the Total Air Temperature (TAT) Probe Heater. (Refer to 34-17-02
in MM-105.) Section 34-17-00.
AIR DATA COMPUTERS - MAINTENANCE PRACTICES
• Adjustment/Test Section- 34-17-01.
• Functional Test of the Air Data System Section- 34-17-01.
TOTAL AIR TEMPERATURE PROBE - MAINTENANCE PRACTICES
• Inspection/Check -Section 34-17-02.
• Operational Check of the Total Air Temperature (TAT) Probe Heater-Section 34-17-02.

Altitude is Different Than Standby Altimeter

1. Perform a pitot/static check. Allow the GDC to warm up for fifteen minutes before
checking accuracy.
2. Determine which instrument is outside limits and recalibrate or replace. Note: Both
units may individually be in spec but show a difference in altitude. Do not return a
GDC to Garmin for service if not outside limits.
3. If GDC is outside limits, recalibration may be performed.
4. If GDC 7400 Config file does not load, replace GDC 7400 config module.
5. If problem persists, replace GDC 7400 config module wire harness.

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4.7.3 GRS 7800 AHRS
NOTE: In addition to the information in this section, refer to the following sections in the Learjet
AMM for GRS 7800 maintenance information:
ATTITUDE HEADING REFERENCE SYSTEM (AHRS) - DESCRIPTION AND OPERATION
• Description-Section 34-26-00
• Operation-Section 34-26-00
ATTITUDE HEADING REFERENCE SYSTEM - MAINTENANCE PRACTICES
• Adjustment/Test-Section 34-26-00
• Functional Test of the Attitude Heading Reference System (AHRS)-Section 34-26-00

4.7.3.1 Common AHRS Issues and Possible Solutions

AHRS Does Not Complete Initialization

1. Ensure GPS has acquired at least four satellites, has a 3D navigation solution, and a
DOP of less than 5.0. This is particularly important if this issue appears during
ground operation only.
2. If the message ‘Calibrate AHRS/Mag’ is present, perform the GRS/GMU Calibration.
3. Check GRS 7800 configuration module wiring for damage.
4. Check GRS 7800 connector for bent pins. If no damage can be found, replace GRS
7800 configuration module.
5. If problem persists, replace the GRS 7800.
Attitude Appears Unstable
1. Ensure the four GRS 7800 mounting screws are tight. Finger tight is not sufficient, a
screwdriver must be used to verify.
2. Ensure mounting rack and airframe shelf are secure and all hardware and brackets
are present (CAUTION - do not loosen the mounting rack hardware to the airframe
shelf or the aircraft will need to be re-leveled and the PITCH/ROLL OFFSET procedure
performed).
3. Ensure GRS 7800 connector is securely fastened and proper strain relief is provided.
4. Remove GRS 7800 connector and verify there are no bent pins.
5. Replace the GRS 7800.
6. Contact Garmin for further troubleshooting if required.

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GRS 7800 Calibration Message

Figure 4-8. Calibrate AHRS/MAG Message

“The external installation configuration parameters are not considered calibrated”
These parameters are categorized into two sets: AHRS installation, and magnetic installation
parameters. If any one of the two is “NOT CALIBRATED”, the GRS 7800 heading, pitch, and roll
may all be flagged as invalid or a message displayed (as shown). Perform the required post-
installation calibration procedures. If the calibration is unsuccessful, the GRS configuration
module may require replacement as it stores the calibration information.
4.7.3.2 GRS 7800 Operational Modes

The GRS 7800 is capable of initializing and outputting valid data without any external inputs as
long as there is sufficient straight and level flight. Heading requires a valid input from a
magnetometer unless the unit is in DG mode, in which case the heading is set manually by the
pilot. The table below describes the pitch and roll limits for the GRS 7800 to initialize. One
condition not described in the table, is that the aircraft must fly straight and level to initialize in
Classical, No-Magnetometer and DG modes if air-data isn’t available. Also it takes 3 to 5 minutes
for the DG mode to initialize.

Attitude- Sensor Inputs Available & Reliable AHRS Outputs Valid

Solution Mode
Inertials1 Mag Air Data GPS Hdg Pitch Roll Ang Accels
Rates
Primary YES YES Not Used YES YES YES YES YES YES
Classical YES YES Used, Not NO YES YES YES YES YES
Required2
No- YES NO Used, Not Used, Not NO YES YES YES YES
Magnetometer Required2 Required3
DG Heading YES NO Used, Not Used, Not YES4 YES YES YES YES
mode (Pilot Required2 Required3
selectable)
Notes:
1. “Inertial” sensors means all three axes of angular rate sensors, and three axes of
accelerometers.

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 2. Air data information is not required in Classical or No-Magnetometer modes, however if
it is available it will be used during periods of extended acceleration/deceleration or
extended turning maneuvers. The performance may be degraded if air-data isn’t
available.
3. GPS information is not required in No-Magnetometer and DG Heading modes, but if it is
available it will be used to determine if in a low-acceleration state.
4. During DG mode operation, heading output is based on periodic pilot input of heading
information.
GRS 7800 Bank and Pitch Limits For In-Flight Initialization
Attitude-Solution Mode Bank Pitch
Entered Following Limit Limit
Initialization (deg) (deg)

Primary Mode ±20.0 ±5.0

Other Modes ±10.0 ±5.0

4.7.3.3 GRS 7800 Troubleshooting Questions

If possible, ask the operator the following questions to help the technician gather the
information to accurately troubleshoot the GRS 7800 operation.
1. What specifically was the nature of the failure? Was it a red-X of only heading, only
pitch/roll, or both?
2. If there was a red-X of pitch or roll information, did the PFD display the "AHRS Align:
Keep Wings Level" message which is indicative of an AHRS reset?

Figure 4-9. Attitude Fail Indication

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 Figure 4-10. AHRS Align Message
3. What exactly was the aircraft doing in the two minutes that preceded the failure (taxing
on the ground, flying straight-and-level flight, turning, climbing, etc)? If the problem
occurred on the ground, was in within 100 feet of a hanger using GPS repeaters?
4. How long did the failure last? Was it brief or sustained? Was it repetitive in nature? If it
was repetitive, about how many times did it happen? Did it happen on more than one
day?
5. Was the problem correlated with a specific maneuver or a specific geographic area?
6. Can the problem be repeated reliably?
7. Were any of system messages relating to AHRS observed within an hour of the
occurrence of the problem?
8. Did the onset of the problem occur shortly after a software upload to one or more
G5000 LRU, or shortly after a repeat of the magnetometer calibration procedure?
9. Were there any GPS messages or loss of position lock?

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4.7.3.4 GRS Aircraft Troubleshooting
1. Review the airframe logbook. See if any G5000, other avionics or electrical maintenance
had been performed recently.
2. Check power wire connections at the circuit breakers and check for intermittent circuit
breakers.
3. Have ground power put on the aircraft.
4. Turn on G5000 and record the system software level. This will be needed if assistance
from Garmin Product Support is required.
5. After the G5000 system has initialized (about one minute from power on), note any red-
x’s on the displays or system messages.
6. Try to verify the issue still exists before proceeding to the physical inspection below:
• Turn off G5000 and gain access to the GRS 7800.
• Inspect the physical installation of the GRS.
• Is the connector tight and locking slider engaged to the locking tabs on each side of
the GRS connector?
• Is the wire harness loose and able to move around during flight? This condition may
cause the wire to pull on or vibrate the connector making intermittent connections.
• Is the GRS mounted tight to the rack? If any doubt exists, use a screwdriver to check
the tightness of the four mounting screws.
• Look around the GRS for any heavy objects that may not be fastened tight to the
structure that could induce GRS vibration.
• Look for evidence of water or fluid contamination in the area around the GRS.
• Unplug the GRS connector and check for bent pins.
• Inspect the wire harness clamp on the rear of the connector to verify it’s not too
tight and damaging wires. Also check for some sort of protective wire wrap
between the wires and the clamp. If the wire clamp is installed upside down, it has
sharp edges that can cut into the wires.
• Verify the locking slider spring is strong enough to keep the slider in the locked
position by cycling the slider.
• Ensure metal objects (tool boxes, power carts, etc.) are not interfering with the
magnetometer and aircraft is not in hangar, near other buildings, parked over metal
drainage culverts or on hard surfaces that may contain steel reinforcements
• Check for software or failed data path error messages. Correct any errors before
proceeding.
• Ensure GRS 7800 unit connecter is secure and proper wire harness strain relief is
provided.

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 • Ensure the GRS 7800 is fastened down tightly in its mounting rack and that the
mounting rack is not loose (CAUTION - do not loosen the mounting rack hardware to
the airframe shelf or the aircraft will need to be re-leveled and the PITCH/ROLL
OFFSET procedure performed).
• Cycle GRS 7800 power to restart initialization.
• Ensure GPS has acquired at least four satellites, has a 3D navigation solution, and a
DOP of less than 5.0. This is particularly important for an ATTITUDE FAIL that
appears during ground operation only.
• Perform an Engine Run-Up Test to check if engine vibration is causing the GRS 7800
to invalidate outputs or reset.
• Perform the Magnetic Interference Test to determine if there is significant magnetic
interference from some device on the aircraft.
• Replace the GRS 7800.
• If problem persists, replace the GRS 7800 configuration module.
• If the condition is not resolved by following these instructions, contact Garmin
Product Support for additional assistance. In rare cases, a Garmin Field Service
Engineer may need to visit your facility to retrieve the fault logs stored in the GRS to
determine if the fault is in the GRS or the aircraft.

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4.7.4 GMA 36 Remote Audio Controller

NOTE: In addition to the information in this section, refer to the following sections in the Learjet
AMM for GMA 36 maintenance information:
Audio Processing Units 1 And 2 - Maintenance Practices
• Adjustment/Test-Section 23-50-01
• Operational Check of the Audio Processor Unit-Section 23-50-01
Noise in Audio
1. Most often the cause of the noise is external to the GMA 36. Try the following to
locate the source of the noise before replacing the GMA 36.
2. Try a different pair of headsets. Noise cancelling headsets may pick up and/or
generate more noise than standard headsets from their own circuitry.
3. Check for noise with engines turned off.
4. If the noise is present only when the engines are running, check the generator
and/or ignition system as possible sources of noise (see Learjet maintenance
manual).
5. Check for noise as all electrical equipment is turned on and off (strobes, other
radios, etc.).
6. If the noise is identified from one electrical system or component refer to the
Learjet maintenance manual.
7. Ensure the NAV/COM squelch is not open.
8. Ensure the ADF and DME audio is not active.
9. Ensure the marker beacon audio is not active.
10. Ensure the ICS squelch is not open. Master squelch level can be adjusted on the
GMA 36 CONFIGURATION page for higher noise environments.
11. Replace unit only after all possible external sources of noise are eliminated.
Buttons Do Not Work
1. Some buttons are disabled in the GMA CONFIGURATION setup by default. This is to
remove potential sources of audio noise for inputs that are not used. If in doubt as
to which buttons should be disabled, reload GMA config files and other config files
for optional equipment installed in the aircraft (i.e. ADF, HF, etc.).

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Speaker Cuts Out
1. Reduce volume level of the item that caused the speaker to cut out when turned up.
A speaker protection circuit disables the speaker output if the volume is too high. If
the volume is not sufficient, replace aircraft cabin speaker, reference the Learjet
Maintenance Manual.
2. Mic Audio Heard in Speaker
3. Reduce ICS Volume.

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4.7.5 XM Weather Receiver
NOTE: In addition to the information in this section, refer to the following sections in the Learjet
AMM for XM Weather Receiver Unit maintenance information:
XM Weather Receiver Unit - Maintenance Practices
• Removal/Installation-Section 46-20-01
• Removal of the XM Weather Receiver Unit-Section 46-20-01
• Installation of the XM Weather Receiver Unit-Section 46-20-01
• Adjustment/Test-Section 46-20-01
• Operational Check of the Flight Deck Information System-Section 46-20-01
No XM Weather Data Is Present
• Go to the SETUP – AVIONICS STATUS page on the GTC and ensure unit is online as
indicated by green .
• If a red X is present, verify the unit is receiving power at the rack connector.
• Ensure there are no GDL alerts in the messages window on the GTC. If there is an Alert
for software or configuration error or mismatch, reload the file noted in the Alert.
• Select SETTINGS and XM INFORMATION on GTC and verify the following:
• Unit is active. If unit is not active, perform the procedures in Appendix A.
• Signal strength indicated as STRONG. If strength is WEAK or NO SIGNAL, verify
connection with GDL 69 antenna and unit.
• Verify there is a good ground connection through the aircraft between the system rack
and the GDL69 unit. Reference the Aircraft Maintenance Manual for instructions on
how to check bonding and ground points.
• If problem(s) persists, replace the GDL 69.

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4.8 AUTOMATIC FLIGHT CONTROL SYSTEM (AFCS) TROUBLESHOOTING
The G5000 AFCS is a digital Automatic Flight Control System (AFCS), fully integrated within the
System avionics architecture. G5000 AFCS functionality in the Learjet 70/75 aircraft is distributed
across the following LRUs:
• GDU 1400W Primary Flight Displays (2) (PFD)
• GIA 63W Integrated Avionics Units (2)
• GMC 7250 AFCS Control Unit
• GSA 9000 AFCS Servos (3)
• GTA 82 Pitch Trim Adapters (2)
• GSM 9100 Servo Mounts (2)
The technician should refer to the following sections in the Learjet Maintenance Manual for
AFCS maintenance/troubleshooting information in addition to the information in this section:
AUTOPILOT - DESCRIPTION AND OPERATION
• Description-Section 22-10-00
• Flight Director (FD)-Section 22-10-00
• Autopilot-Section 22-10-00
• Controls-Section 22-10-00
• Indications-Section 22-10-00
• Operation-Section 22-10-00
AUTOPILOT SYSTEM - MAINTENANCE PRACTICES
• Adjustment/Test-Section 22-10-00
• Functional Test of the Autopilot System-Section 22-10-00
• Functional Test of Autopilot Autotrim Function and Mistrim Annunciation-Section 22-
10-00
AUTOPILOT MODE CONTROLLER - MAINTENANCE PRACTICES
• Operational Check of the Autopilot Mode Controller-Section 22-10-01
AUTOPILOT PITCH SERVO ACTUATOR - MAINTENANCE PRACTICES
• Inspection/Check-Section 22-10-02
• Operational Check of the Autopilot Pitch Servo-Section 22-10-02
AUTOPILOT PITCH SERVO GEARBOX - MAINTENANCE PRACTICES
• Adjustment/Test Section 22-10-03
• Adjustment of the Pitch Servo Cable Tension Section 22-10-03

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AUTOPILOT ROLL SERVO - MAINTENANCE PRACTICES
• Inspection/Check-Section 22-10-04
• Operational Check of the Autopilot Roll Servo-Section 22-10-04
AUTOPILOT ROLL SERVO GEARBOX - MAINTENANCE PRACTICES
• Adjustment/Test-Section 22-10-05
• Adjustment of the Roll Servo Cable Tension-Section 22-10-05
AUTOPILOT YAW SERVO - MAINTENANCE PRACTICES
• Operational Check of the Autopilot Yaw Servo-Section 22-10-06
AUTOPILOT YAW SERVO GEARBOX - MAINTENANCE PRACTICES
• Adjustment/Test-Section 22-10-07
• Adjustment of the Yaw Servo Cable Tension-Section 22-10-07
AUTOPILOT PRIMARY AND SECONDARY TRIM ADAPTER - MAINTENANCE PRACTICES
• Inspection/Check-Section 22-10-08
• Operational Check of the Pitch Trim Adapter-Section 22-10-08

4.9 DOWNLOADING GIA AND GSA MAINTENANCE LOGS

If additional assistance is needed troubleshooting autopilot faults, the maintenance logs can be
downloaded to an SD card as a text file (.txt) and e-mailed to Garmin Aviation Support at
avionics@garmin.com. Please notify Garmin Aviation Support before you send a maintenance
log to notify them you are sending it to prevent a delay in response. You may download multiple
GIA and GSA Maintenance Logs to the same file, however in your e-mail to Garmin you must
furnish the order in which they were downloaded (i.e. GIA1, then GIA2, then SRVO PTCH MON,
then SRVO PTCH CTL, etc.).

1. Insert a FAT 32 formatted SD card into the top slot of the PFD before turning on the
displays.
2. Power up PFD1/2 and MFD in the configuration mode.
3. On PFD1 in the System page group, use the small FMS knob to scroll to the following
Diagnostics Terminal page (next page):

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 4. Press the LG2CRD softkey at the bottom of the PFD1. Verify that the softkey text grays
out. This indicates the recording function is active and all text that is displayed in the
OUTPUT window will be saved to the card.
5. Enable the cursor by pressing the FMS knob, select “GIA1” in the LRU drop down menu
and then press the ENT key to select it.
6. Skip the SERVO box and move the cursor to the COMMAND box and select “View
Maintenance Log” in the drop down menu then press the ENT key. The error log data
will be displayed in the OUTPUT box. If you see the “more…press any key to continue”
text at the bottom of the screen, you may need to reselect “View Maintenance Log” to
allow GIA data to continue scrolling down the screen (note: pressing any of the keys will
not allow you to continue to scroll, disregard the text instructing you to do so). Continue
to scroll through all the OUTPUT data until you see the text, “End of Fault Log”.
7. Move the cursor back to the LRU box, select “GIA2” in the LRU drop down menu and
then press the ENT key to select it.
8. Skip the SERVO box and move the cursor to the COMMAND box and select “View
Maintenance Log” in the drop down menu then press the ENT key. The error log data
will be displayed in the OUTPUT box. If you see the “more…press any key to continue”
text at the bottom of the screen, you may need to reselect “View Maintenance Log” to
allow GIA data to continue scrolling down the screen (note: pressing any of the keys will
not allow you to continue to scroll, disregard the text instructing you to do so). Continue
to scroll through all the OUTPUT data until you see the text, “End of Fault Log”.
9. If you need to download Servo fault logs (usually done at the request of Garmin Product
Support), perform the following steps. Otherwise skip to step 10.
A. In the LRU box, you may select either “GIA1” or “GIA2”.

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 B. In the SERVO box, choose a servo. Each servo contains two logs, one in the
Monitor (MON) processor and one in the Control (CTL) processor. You must
download both for each servo separately.
C. In the COMMAND box, select “View Maintenance Log” and press the ENT key.
D. The log will appear in the OUTPUT box. It will scroll to the end automatically.
When it is complete, repeat steps A-C for the other servos in the aircraft. Be
sure to note the order the servos were downloaded in including the Monitor or
Control logs to e-mail to Garmin Aviation Support. Without knowing the order in
which the logs were downloaded, Garmin will be unable to process them and
will ask for another full download.
10. Press the LG2CRD softkey to turn off the recording function.
11. Wait 1 minute for the system to save the data from the download to the SD card.
12. While you are waiting for the data to be saved to the SD card, record the order of the
LRU's and/or Servos were downloaded so that you can provide that information to
Learjet or Garmin to help decipher the order of the error data.
13. Power down the G5000 and remove the SD card.
14. Insert the SD card in the card reader of a laptop or desktop computer and open the
“diag_buf_log.txt” file from the SD card using the Word Pad program. Verify that all of
the fault logs were downloaded by checking for the “End of Fault Log” message at the
end of the GIA data, and that the last servo log entry has the current date. Note: If the
GIA logs are full, they start overwriting the old ones and you will never get to the “End
of Fault Log”. They will just start recording the old logs again.
15. Insert the fault log as an attachment to an e-mail and include the LRU order how the
data was downloaded and send to Garmin Aviation Support at avionics@Garmin.com.

4.10 LRU EXTERNAL CONNECTOR INFORMATION

External connector information for each LRU such as pin numbers, pin names and descriptions is
contained in Appendix A. This maintenance manual contains no system interconnection pin
information.

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 Blank Page

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SECTION 5—LRU REPLACEMENT PROCEDURES

NOTE
All references in this section made to the GDL 69 also include the GDL 69 SXM.
This section contains basic procedures for removing and installing G5000 LRUs. Garmin LRU
installation manual part numbers are given in each section for technician reference. This section
is not a substitute for the approved Learjet maintenance manual, installation design drawing,
or complete installation data package. Supporting Garmin and Learjet publications are listed
for reference for each LRU.

NOTE
Once an LRU is replaced, software loading and testing is required. See Section 6
for the software loading and testing procedures for a replacement LRU.
Always ensure that aircraft power is off when removing and/or replacing an LRU. Unplug any
auxiliary power supplies. Before performing maintenance, the technician needs to verify that
LRU software part numbers and version numbers match the software configuration listed in the
general arrangement drawing. The Avionics Status Page on the GTC 570 can also be used to
check part numbers and versions (Figure 5-1).

Figure 5-1. LRU Information

The LRU Info Tab on the Avionics Status screen displays the status, serial numbers, and software
version numbers for all detected system LRUs. The system displays a green checked box for
each active LRUs. A yellow ‘X’ box indicates a failed LRU.
Viewing LRU information:
1. From Home, touch Utilities > Setup > Avionics Status.
2. If necessary, touch the LRU Info tab.
3. Scroll as needed and touch a LRU button to display a pop-up window with additional
information for the selected LRU.
4. When finished, touch the pop-up window (if displayed), or touch Back or Home.

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5.1 GCU 275 (REMOTE) PFD CONTROLLER

NOTE
In addition to the information in this section, refer to the Garmin GCU 275
Installation Manual (Part Number 190-00303-75) and the following section in
the Learjet AMM: Remote Controllers Removal/Installation—31-60-03.
The GCU 275 uses captive screws and does not have alignment marks.
Removal:
1. Turn each of the four locking sockets ¼ turn counter-clockwise using a 3/32” hex drive
tool and remove the controller from the instrument panel.
Installation:
1. Hold the unit flush with the instrument panel.
2. Orient the locking studs with the alignment marks in the vertical position.
3. Turn each of the four locking sockets ¼ turn clockwise using a 3/32” hex drive tool until
tight (20 ±2 in-lbs). The alignment marks are in the horizontal position when locked.

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5.2 GDC 7400 AIR DATA COMPUTER

NOTE
In addition to the information in this section, refer to the Garmin GDC 7400
Installation Manual (Part Number 190-01100-00) and the following section in
the Learjet AMM: Attitude Heading Reference Unit Removal/Installation—34-
26-01.

Figure 5-2. GDC 7400 Installation

Removal:
1. Pull back on the lockdown mechanism and simultaneously turn counterclockwise until
free.
2. Disengage the lockdown mechanism collar from the GDC 7400 hook and slide the GDC
7400 forward to remove from the mounting rack.
Installation:
1. Place the unit on the mounting rack, ensuring the GDC 7400 rear feet are aligned in the
mounting rack slots.
2. Slide the GDC 7400 back until the feet are fully engaged with the mounting rack.
3. Lift the lockdown mechanism collar in place on the GDC 7400 hook and hand turn
lockdown mechanism knob clockwise until the GDC 7400 is secure.

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5.3 GDL 59 WI-FI DATALINK AND FLIGHT PARAMETER RECORDER

NOTE
In addition to the information in this section, refer to the Garmin GDL 59
Installation Manual (Part Number 190-00837-00) and the following section in
the Learjet AMM: Recorder And Wireless Datalink Unit Removal/Installation—
45-45-02.

Removal:
1. Unlock the GDL 59 using the lever-locking handle.
2. Remove the GDL 59 from the rack.
Installation:
1. Insert the GDL 59 into the rack, noting proper orientation. Do not use excessive force
when inserting the GDL 59 into the rack. This may cause damage to occur to the
connectors, unit, and/or unit rack. If heavy resistance is felt during installation, stop!
Remove the GDL 59 and identify the source of resistance. The rear plate is designed to
float in the unit rack. Check to ensure the rear plate is not bound by the connector
harness.

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 2. Fasten the handle to the GDL 59 body using the provided Phillips screw. Start the handle
screw into the hole carefully to avoid cross-threading. Do not apply torque in excess of
14 in-lbs to the handle screw. The application of torque exceeding 14 in-lbs to this
screw will damage the LRU case and/or retaining hardware.
3. Lock the GDL 59 in place using the lever-locking handle.

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5.4 GDL 69/GDL 69 SXM DATALINK RECEIVER

NOTE
In addition to the information in this section, refer to the Garmin GDL 69
Installation Manual (Part Number 190-00355-02) and the following section in
the Learjet AMM: XM Weather Receiver Removal/Installation—46-20-01.

Figure 5-3. GDL 69/GDL 69 SXM Installation

Removal:
1. Loosen the Locking Lever Handle Securing Screw (4).
2. Raise the Locking Lever Handle (1).
3. Slide the unit out of the Mount Rack.

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Installation:
The following steps are for the remote mounting rack which is illustrated in Figure 5-3. The
steps are identical for the modular rack.
1. Loosen and remove the Locking Lever Handle Securing Screw (4). Then, lift up on the
end of the Locking Lever Handle (1).
2. Slide the GDL 69 unit into the Mount Rack carefully fitting the Locking Lever Handle Cam
Head (2) into the slot of the Locking Plate (3) of the Mount Rack.
3. After fully inserting the unit into the mount rack, visually note that the Cam Head (2)
remains seated in the slot of the Locking Plate (3).
4. When inserting the GDL 69 into the Remote Mount Rack, it may be possible for the Pivot
Pin (2) to fit between the unit and the mount rack without going into the slot of the
Locking Plate (3). If the Cam Head (2) does not seat in the slot of the Locking Plate (3),
the unit will not firmly engage with the mount rack and the unit could come loose from
the rack.
5. With the unit firmly engaged with the mount rack, lower the Locking Lever Handle (1).
Then, insert and tighten the Locking Lever Handle Securing Screw (4) to mechanically
secure the unit to the Mount Rack.

5.5 GDU 1400W DISPLAY UNIT

NOTE
In addition to the information in this section, refer to the Garmin GDU 1400W
Installation Manual (Part Number 190-00303-28) and the following section in
the Learjet AMM: Display Unit Removal/Installation—31-60-01.

Removal:
1. Turn each of the four fasteners counter-clockwise using a 3/32” hex drive tool.
2. Remove the display from the instrument panel.
Installation:
1. The GDU 1400W is installed by holding the unit flush with the instrument panel.
2. The pawl-latches should be fully retracted, in the horizontal position, so as to not
interfere with the panel opening.
3. A 3/32” hex drive tool is then used to turn each of the four fasteners clockwise until
tightened to the proper torque (20 in-lbs).
4. When tightened, the pawl-latches are in the vertical position.

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5.6 GEA 71 ENGINE AND AIRFRAME INTERFACE UNIT

NOTE
In addition to the information in this section, refer to the Garmin GEA 71
Installation Manual (Part Number 190-00303-40) and the following section in
the Learjet AMM: Engine And Airframe Interface Unit Removal/Installation—31-
41-02.
Removal:
1. Unlock the GEA 71 using the lever-locking handle.
2. Remove the unit from the rack.
Installation:

CAUTION
Do not use excessive force when inserting the GEA 71 into the rack. This may
cause damage to occur to the connectors, unit, and/or unit rack. If heavy
resistance is felt during installation, stop! Remove the GEA 71 and identify the
source of resistance. The rear plate is designed to float in the unit rack. Check
to ensure the rear plate is not bound by the connector harness.

1. Insert the GEA 71 into the rack, noting proper orientation.

CAUTION
Start the handle screw into the hole carefully, to avoid cross-threading. Do not
apply torque in excess of 14 in-lbs to the handle screw. The application of
torque exceeding 14 in-lbs to this screw will damage the LRU case and/or
retaining hardware.

2. Lock the GEA 71 in place using the lever-locking handle. Fasten the handle to the GEA
71 body using the provided Phillips screw.

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5.7 GIA 63W INTEGRATED AVIONICS UNIT

NOTE
In addition to the information in this section, refer to the Garmin GIA 63W
Installation Manual (Part Number 190-00303-05) and the following section in
the Learjet AMM: Integrated Avionics Unit Removal/Installation—31-41-01.

Removal:
1. Loosen the Phillips screw (or pull on the D-Ring and twist counter-clockwise 90°, for
units with a D-Ring).
2. Unlock the handle and remove the unit from the rack.
Installation:
1. Carefully slide the GIA 63W into the rack. Ensure that the orientation of the unit allows
for the engagement of the locking stud in the channel on the rack. The unit can only be
installed in one direction.
2. Push the GIA 63W lever down towards the bottom of the unit. This engages the locking
stud with the dogleg slot and locks unit into the rack. If there is excessive resistance, do
not force the unit.

CAUTION
Do not use excessive force when inserting the GIA 63(W) into the rack. This may
cause damage to the connectors, unit and/or unit rack. If excessive resistance is
felt during installation, stop! Remove the GIA 63(W) and identify the source of
resistance. The rear plates are designed to float in the unit rack. Check to
ensure the rear plates are not bound by the connectors or spring clip.

NOTE: The install screw is designed with a ratcheting socket that resists turning
counterclockwise, unless pushed in. This ensures that the engagement screw
cannot loosen under vibration.
3. Lock the handle into the GIA 63W body and tighten the Phillips screw (or push in the D-
Ring and twist clockwise 90°, for units with a D-Ring).

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5.8 GMA 36 AUDIO PROCESSOR AND MARKER BEACON RECEIVER

NOTE
In addition to the information in this section, refer to the Garmin GMA 36
Installation Manual (Part Number 190-00858-01) and the following section in
the Learjet AMM: Audio Processor Unit Removal/Installation—23-50-01.

Removal:
1. Loosen the Phillips screw and unlock the GMA 36.
2. Remove the GMA 36 from the rack.
Installation:

CAUTION
Do not use excessive force when inserting the GMA 36 into the rack. This may
damage the connectors, unit, and/or unit rack. If heavy resistance is felt during
installation, stop! Remove the GMA 36 and identify the source of resistance.
1. Insert the GMA 36 into the rack, noting proper orientation.
2. Lock the GMA 36 and tighten the Phillips screw.

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5.9 GMC 7250 AUTOPILOT MODE CONTROLLER

NOTE
In addition to the information in this section, refer to the Garmin GMC 7250
Installation Manual (Part Number 190-00303-70) and the following section in
the Learjet AMM: Autopilot Mode Controller Removal/Installation—22-10-01.

Removal:
1. Turn each of the four locking sockets ¼ turn counter-clockwise using a 3/32" hex drive
tool.
2. Remove the unit from the instrument panel.
Installation:
1. Hold the unit flush with the instrument panel. The locking studs should be orientated
with the alignment marks in the vertical position.
2. Turn each of the four locking sockets ¼ turn clockwise using a 3/32" hex drive tool. The
alignment marks are in the horizontal position when locked.

5.10 GRS 7800 AHRS AND GMU 44 MAGNETOMETER

NOTE
In addition to the information in this section, refer to the Garmin GRA/GMU
Installation Manual (Part Number 190-01091-00) and the following sections in
the Learjet AMM: Attitude Heading Reference Unit Removal/Installation—34-
26-01 and Magnetometer Removal/Installation 34-26-02.

NOTE
When mounting the GRS 7800 rack to the airframe, and the unit to the rack, it is
important to ensure that lockdown mechanisms are tight for proper unit
operation.
To install the GRS 7800 (refer to Figure 5-4):
1. Place the unit on the mounting rack. Slide the GRS 7800 back until the feet are fully
engaged with the mounting rack.
2. Lift the lockdown mechanism collars in place on the GRS 7800 hooks and hand turn
lockdown mechanism knobs clockwise until the GRS 7800 is secure.

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To disengage the GRS 7800 (refer to Figure 5-4):
1. Pull back on the lockdown mechanisms and simultaneously turn counterclockwise until
free.
2. Disengage the lockdown mechanism collars from the GRS 7800 hooks and slide the GRS
7800 forward to remove from the mounting rack.

Figure 5-4. GRS 7800 Mounting

Mounting the GMU 44
Mount the GMU 44 to its mounting plate, taking care to tighten the mounting screws firmly. The
metal components in the GMU 44s connector may slightly affect the magnetic field sensed by
the GMU 44.
Place the connector at least 2 inches from the body of the GMU 44 to minimize this effect. After
attaching the GMU 44s connector to its mate in the aircraft wiring, secure the connector in
place using good installation practices. This will ensure that any remaining magnetic effect can
be compensated for.
If the GMU 44 is ever removed, the anti-rotation properties of the mounting screws must be
restored. This may be done by replacing the screws with new Garmin P/N 211-60037-08. If
original screws must be re-used, coat screw threads with Loctite 242 (blue) thread-locking
compound, Garmin P/N 291-00023-02, or equivalent. Important: Mounting screws must be
brass.

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 NOTE
The GMU 44 must be mounted such that the pitch offset relative to the GRS
7800 mounting is less than 6.0 degrees. Likewise, the roll offset of the GMU 44
mounting relative to the GRS 7800 mounting should also be less than 6.0
degrees. Failure to meet these specifications may result in a failed
magnetometer calibration.

5.11 GSA 9000 SERVO ACTUATOR/GSM 9100 SERVO GEARBOX

NOTE
In addition to the information in this section, refer to the GSA 9000 Garmin
Installation Manual (Part Number 190-00303-85) and the following sections in
the Learjet AMM listed below:
Autopilot Pitch Servo Actuator - Maintenance Practices
• Removal/Installation —22-10-02
Autopilot Pitch Servo Gearbox - Maintenance Practices
• Removal/Installation—22-10-03
Autopilot Roll Servo - Maintenance Practices
• Removal/Installation —22-10-04
Autopilot Roll Servo Gearbox - Maintenance Practices
• Removal/Installation —22-10-05
Autopilot Yaw Servo - Maintenance Practices
• Removal/Installation—22-10-06
Autopilot Yaw Servo Gearbox - Maintenance Practices
• Removal/Installation—22-10-07

Removal:
To remove the GSA 9000/GSM 9100 reverse the installation steps.
Installation:
1. Fasten the GSM 9100 to the structural bracket per the aircraft manufacturer
specifications. Mounting hardware to be provided by the installing agency.
2. Attach the aircraft control surface cabling/chains to the output pulley or sprocket
following guidance provided in aircraft manufacturer specifications.
3. On some capstans, the center ball may snap into place. Always ensure the ball is fully
seated in the capstan.

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 4. Assemble the cable guards. Refer to aircraft-specific installation documentation for the
proper location of the cable guards. Use the recommended screws and washers to
install the cable guards.
5. Carefully mate the GSA 9000 with the GSM 9100. Fasten the GSA 9000 to the GSM 9100
per the aircraft manufacturer specifications. Mounting hardware to be provided by the
installing agency.
6. Connect the GSA 9000 connector to the aircraft harness. Make sure that the harness is
properly secured to the airframe.

5.12 GTA 82 TRIM ADAPTOR (H-STAB)

NOTE
In addition to the information in this section, refer to the Garmin GTA 82
Installation Manual (Part Number 190-00303-74) and the following section in
the Learjet AMM: Autopilot Primary And Secondary Trim Adapter
Removal/Installation—34-26-01.

Removal:
1. Mount the GTA 82 to the airframe using at least 6 or 10 screws.
2. Use cable ties to secure the cable assemblies to provide strain relief.
3. After the cable assemblies are made and wiring installed to the unit, route the wiring
bundle as appropriate.
Installation:
1. Use typical #8 mounting hardware to fasten the GTA 82 to the airframe. The installer
may attach typical #8 blind nuts to the airframe to facilitate installation and removal or
assemble the unit to the airframe using #8 flat washers and #8-32 locknuts. The
installer must provide any additional remote mounting equipment. Ensure that the GTA
82 chassis has a ground path to the airframe by having at least one mounting screw in
contact with the airframe.
2. After the cable assemblies are made and wiring installed to the unit, route the wiring
bundle as appropriate. Use cable ties to secure the cable assemblies to provide strain
relief.
3. The GTA 82 must be mounted using at least 6 screws, but may also be mounted using 10
screws.

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5.13 GSC 46 ENGINE SIGNAL CONDITIONER

NOTE
In addition to the information in this section, refer to the Sandia Corp.
Installation Manual Part Number 305952-00-IM and the following section in the
Learjet AMM: Engine Signal Conditioner Removal/Installation—77-41-04.

Removal:
1. Disconnect power and data cable from the unit.
2. Remove four machine screws attaching unit to mounting tray.
3. Remove the unit.
Installation:
1. Attach unit to mounting tray using four machine screws.
2. Connect power and data cable from the unit.

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5.14 GSD 41 DATA CONCENTRATOR

NOTE
In addition to the information in this section, refer to the Garmin GSD 41
Installation Manual (Part Number 190-00303-26) and the following section in
the Learjet AMM: Serial Data Concentrator Unit Removal/Installation—31-41-
03.

Removal:
• Unlock the GSD 41 using the lever-locking handle.
Remove the unit from the rack.
Installation:
1. Insert the GSD 41 into the rack, noting proper orientation.

CAUTION
Do not use excessive force when inserting the GSD 41 into the rack. This may
cause damage to occur to the connectors, unit, and/or unit rack. If heavy
resistance is felt during installation, stop! Remove the GSD 41 and identify the
source of resistance. The rear plate is designed to float in the unit rack. Check
to ensure the rear plate is not bound by the connector harness.

CAUTION
Start the handle screw into the hole carefully, to avoid cross-threading. Do not
apply torque in excess of 14 in-lbs to the handle screw. The application of
torque exceeding 14 in-lbs to this screw will damage the LRU case and/or
retaining hardware.

2. Lock the GSD 41 in place using the lever-locking handle. Carefully start the handle screw
into the hole to avoid cross threading.

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5.15 GSR 56 IRIDIUM SATELLITE TRANSCEIVER

NOTE
In addition to the information in this section, refer to the Garmin GSR 56
Installation Manual (Part Number 190-00836-00) and the following section in
the Learjet AMM: Iridium Satcom Transceiver Removal/Installation—23-13-01.

Removal:
1. Unlock the GSR 56 using the ratcheting latch mechanism.
2. Remove the unit from the rack.
Installation:

CAUTION
Do not use excessive force when inserting the GSR 56 into the rack. This may
cause damage to occur to the connectors, unit, and/or unit rack. If heavy
resistance is felt during installation, stop! Remove the GSR 56 and identify the
source of resistance.
1. Insert the GSR 56 into the rack, noting proper orientation
2. Lock the GSR 56 in place using the ratcheting latch mechanism.

5.16 GTC 570 TOUCH SCREEN CONTROLLER

NOTE
In addition to the information in this section, refer to the Garmin GTC 570
Installation Manual (Part Number 190-00987-00) and the following section in
the Learjet AMM: Touch Controller Removal/Installation—31-60-02.

Removal:
1. Remove the four captive screws using a 3/32” hex drive tool.
2. Remove the GTC 570 from the instrument panel.
Installation:
1. The GTC 570 is installed by holding the unit flush with the instrument panel.
2. A 3/32” hex drive tool is then used to turn each of the four captive screws clockwise
until tight (20 +/-2 in-lbs).

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5.16.1 GTC 570 Touch Screen Controller Fans

GTC 570 cooling fan may become inoperative, indicated by a “GTC FAN FAIL – GTC internal fan
failure. Unit needs service.” system message.
1. Remove the GTC 570 from the aircraft panel by following all instructions for removal as
described in the applicable airframe specific maintenance manual.
2. Remove the cooling fan assembly from the GTC 570 chassis, by removing (and
discarding) the three screws that connect the cooling fan assembly to the GTC 570
chassis, as shown in the following figure.

3. Disconnect both fan connectors (see following figure).

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 4. Using a pair of tweezers or needle-nose pliers, carefully connect the replacement fan
assembly fan connectors, noting orientation and ensuring both connectors are fully
engaged (see following figure).

CAUTION
Before proceeding to Step 5, ensure fan wires will not become pinched while
positioning the fan assembly over the chassis.

5. Secure the replacement fan assembly to the GTC 570 chassis using the three provided
screws. Torque each screw to 9 ± 1 in-lbs.
6. Verify that both cooling fans operate properly by performing a visual inspection, or by
using the GTC Status page. Follow one of the procedures listed below.

Visually Verifying the Cooling Fan Operation

1. Power the GTC 570 on in a heated hangar (15°C or greater) for 5-10 minutes, until the
internal temperature reaches approximately 30°C or greater (times may vary depending
on temperature).
2. Visually verify that cooling fans turn on and no fan system messages appear.
3. Indicate this service bulletin has been complied with by marking MOD 1 (011-01924-50)
or MOD 3 (011-01924-10) with a black permanent marker on the GTC 570 serial number
tag.
4. Secure the GTC 570 to the aircraft panel by following the instructions in the Learjet
maintenance manual (loading software is not required).

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Verifying the Cooling Fan Operation Using the GTC Status Page
1. Connect the GTC 570 wiring harness.
2. Place the GTC 570 in its mount without securing to the aircraft panel.
3. While in a heated hangar (15°C or greater), hold down the dual concentric knob while
applying power to the GTC 570 to enter Configuration mode.
4. Press the Status menu button on the GTC to navigate to the GTC Status page (see the
following figure).

5. Wait 5-10 minutes (times may vary depending on temperature), until the “Main Temp”
reaches approximately 30°C or greater.
6. Within one minute of “Main Temp” reaching 30°C or greater, verify both fan status
boxes turn green.
7. Indicate this service bulletin has been complied with by marking MOD 1 (011-01924-50)
or MOD 3 (011-01924-10) with a black permanent marker on the GTC 570 serial number
tag.
8. Secure the GTC 570 to the aircraft panel by following the instructions in the Learjet
maintenance manual (loading software is not required).

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5.17 GTS 8000 TCAS II PROCESSOR

NOTE
In addition to the information in this section, refer to the Garmin GTS 8000
Installation Manual (Part Number 190-00587-50) and the following section in
the Learjet AMM: TCAS II Processor Removal/Installation—34-43-01.

CAUTION
After any maintenance or modification is made to the GTS 8000 cables such as
replacing a connector or entire cable, be sure to adhere to all of the
specifications and limitations such as minimum and maximum cable
attenuation, attenuation balance between cables, phase matching etc.
Removal:
1. Disconnect the eight coax "quick-lock" connectors.
2. Disconnect the three electrical connectors.
3. Unlock the unit from the rack by loosening the ratcheting latch mechanism.
4. Remove the unit from the rack.
Installation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair
any damage.
2. Insert the unit into the installation rack.
3. Lock the unit into the rack by using the ratcheting latch mechanism.
4. Reconnect the eight coax "quick-lock" connectors and the three electrical connectors.

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5.18 GTX 3000 TRANSPONDER

NOTE
In addition to the information in this section, refer to the Garmin GTX 3000
Installation Manual (Part Number 190-00926-01) and the following section in
the Learjet AMM: ATC Transponder Removal/Installation—34-56-01.
Removal:
1. Unlock the GTX 3000 handle by loosening the Phillips screw on the handle.
2. Pull the handle upward to unlock the unit. Gently remove the unit from the rack.
Installation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair
any damage.
2. Gently insert the GTX 3000 into its rack. The handle should engage the dogleg track.
3. Press down on the GTX 3000 handle to lock the unit into the rack.
4. Lock the handle to the unit body using the Philips screw.

5.19 GWX 70 AIRBORNE WEATHER RADAR

NOTE
In addition to the information in this section, refer to the Garmin GWX 70
Installation Manual (Part Number 190-00829-01) and the following section in
the Learjet AMM: Weather Radar Receiver/Transmitter/Antenna (RTA)
Removal/Installation—34-42-03.
NOTE
Take care to avoid any contact between tools that can become magnetized and
the magnetron. Even momentary contact of a potentially magnetic object with
the magnetron case will cause serious weakening of the magnetic field. Use of
non-magnetic tools (typically beryllium copper or titanium) is recommended
when installing or servicing the GWX 70.
Removal:
1. Remove the connector from the unit by pushing on the slide lock tab on the side of the
connector which releases it and pull the connector away from the unit.
2. Remove the mounting bolts. Note and save the shims or washers behind each mounting
bolt location. They will need to be reinstalled in the same locations.

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Installation:
1. Place the same shims or washers in the same location where they were removed and
install the four mounting bolts. Torque the bolts to the specifications given in the OEM
maintenance manual.
2. Attach the connector to the unit by first pressing the slide lock tab on the side of the
connector, then align and mate the unit and wire harness connectors together, and then
release the slide lock tab. The locking tabs must be engaged on both ends of the
connector.
3. Verify that the wiring harness has been routed and secured in such a way that it cannot
be struck by or interfere with unit movement throughout the full range of sweep and
tilt.
4. Install the radome according to Learjet instructions.

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5.20 CONFIGURATION MODULE REMOVAL AND REPLACEMENT
Five configuration modules (Item 1 shown below) are located in the following LRU harness
connector backshells (Item 6): GDU 1400W PFD, and the GEA 71 Engine/Airframe Unit (4).

Figure 5-5. Configuration Module Assembly

Removal:
1. Disconnect connector from LRU.
2. Remove 2 screws (8) from cover (7) and remove cover.
3. Unplug connector from configuration module (1).
4. Remove configuration module.
Installation:
1. Inspect connector for damaged pins (4).
2. Place configuration module (1) in position.
3. Insert connector into configuration module (1).

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5.21 GEA 71 BACKSHELL THERMOCOUPLE REMOVAL and REPLACEMENT
The GEA 71 has a K-Type thermocouple (Item 1 shown below) installed in its backshell, in
addition to the configuration module. The thermocouple is used in conjunction with the
configuration module temperature sensor to compensate for temperature probe errors
resulting from the dissimilar metals at the pin contacts.

Figure 5-6. GEA Backshell Thermocouple

Removal:
1. Remove GEA 71.
2. Remove GEA connector backplate.
3. Remove connector assembly J711 from the backplate.
4. Remove screws, item 7, and cover, item 6, from the backshell, item 5.
5. Unscrew thermocouple from boss on backshell. Extract the thermocouple pins from the
connector.
Replacement:
1. Crimp pins, item 2, onto each of the thermocouple wires, item 1. Ensure that pre-
stripped wire length is 1/8" prior to crimping.
2. Insert newly crimped pins and wires into the appropriate connector housing location,
item 4, as specified by the Learjet Wiring Diagram.

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 3. Place thermocouple body, item 1, onto the backshell boss, item 5. Place the
thermocouple as shown in Figure 5-5 so that the wires exit towards the bottom of the
backshell.
4. Fasten thermocouple tightly to backshell using the provided screw, item 3.
5. Fasten cover, item 6, to backshell using screws, item 7.

5.22 GDR 66 VHF DATALINK RADIO UNIT

NOTE
In addition to the information in this section, refer to the Garmin GDR 66
Installation Manual (Part Number 190-00303-24) and the following section in
the Learjet AMM : VHF Datalink Radio Unit Removal/Installation—23-25-01.

Removal:
1. Disconnect electrical power from the aircraft.
2. Open the tailcone equipment access door.
3. Disconnect the electrical connectors and coaxial connector from the datalink radio unit.
4. Loosen the hold-down knob that holds the datalink radio unit in the mounting tray.
5. Remove the datalink radio unit from the tray.
Installation of the VHF Datalink Radio Unit
1. Get the necessary tools and equipment
2. Put the datalink radio unit in the mounting tray.
CAUTION: do not use tools to tighten hold-down knobs. Damage to the hold-down
knobs can occur.
3. Tighten the hold-down knob finger tight.
4. Measure the electrical resistance between the unit and the aircraft structure. The
resistance must not be more than the specified value. (Refer to Chapter 20 of the Wiring
Manual for specified resistance values and resistance measurement procedures.)
CAUTION: examine the electrical connectors for damaged, tarnished, bent, or loose
pins and sockets before installation.
5. Connect the electrical connectors and coaxial connector to the datalink radio unit.
6. Perform the Functional Test of the Controller Pilot Data Link Communication (CPDLC)
System.
7. Perform the Operational Check of the VHF Datalink Radio Unit.
8. Install the tailcone equipment access door.

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5.23 FLIGHT DATA RECORDER UNIT

NOTE
In addition to the information in this section, refer to the following section in the
Learjet AMM: Flight Data Recorder Unit Removal/Installation—31-30-01.
Removal:
1. Get the necessary tools and equipment.
CAUTION: pull straight out when you remove the flight data recorder unit. A sideways
or an up-and-down motion can cause damage to the connector pins.
2. Disconnect electrical power from the aircraft.
3. Loosen the hold-down knob that attaches the flight data recorder unit in the tray.
4. Remove the flight data recorder unit from the aircraft.
Installation:
CAUTION: pull straight out when you remove the flight data recorder unit. A sideways
or an up-and-down motion can cause damage to the connector pins. Do not use tools to
tighten hold-down knobs. Damage to the hold-down knobs can occur.
1. Install the recorder unit in the mounting tray and tighten the hold-down knob finger
tight.
2. Measure the electrical resistance between the recorder unit and the aircraft structure.
The resistance must not be more than the specified value. (Refer to Chapter 20 of the
Wiring Manual for specified resistance values and resistance measurement procedures.)
3. Connect electrical power to the aircraft.
4. Perform the Functional Test of the Flight Data Recorder System.

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 Blank Page

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SECTION 6—LRU SOFTWARE LOADING

NOTE
All references in this section made to the GDL 69 also include the GDL 69 SXM.
This section describes how to load software and configuration to an individual G5000 LRU for
the following situations:
• Reinstalling an Original LRU (same serial number)
• Installing a LRU in Opposite Locations for Troubleshooting Purposes. If the unit itself is
suspect as the source of the problem, and there is a second unit of the same P/N in the
aircraft that is known to be good, that swapping unit positions is allowed for
troubleshooting to confirm if the unit is bad or not before ordering a replacement unit.
• Installing a New, Repaired, or Exchanged LRU
The section also contains, where applicable, testing procedures to ensure proper operation after
an LRU has been removed and reinstalled. This section describes the minimum tests that should
be performed after maintenance. The technician must also perform any additional return to
service tests required by the Learjet Aircraft Maintenance Manual to verify correct installation in
the aircraft.

NOTES
DO NOT REMOVE POWER FROM THE G5000 WHEN LOADING SOFTWARE. Power
loss during a software load may cause an LRU to stop working. Replacing an LRU
caused by corrupted software due to power loss is not covered under warranty.
Do not rely on only the aircraft batteries when loading software. Connect a
ground power unit to the aircraft.
All screens in this section are only intended for visual reference only. All
information depicted, including software version and part numbers is subject to
change and may not be current. Refer to the Learjet Aircraft Maintenance
Manual for approved software versions and part numbers.
DO NOT PRESS THE CANCEL SOFTKEY AT THE BOTTOM OF THE SCREEN DURING
THE SOFTWARE LOAD. If there is a software loading problem, allow the software
to automatically stop the load. Pressing the CANCEL softkey may result in an
unresponsive LRU requiring replacement.
Use only SanDisk SD™ cards for loading software and configuration files. The use
of other cards is not approved.

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6.1 SUPPORTING PUBLICATIONS

Of particular importance to the technician loading and configuring G5000 software are the
following Learjet documents:
• Learjet AMM-Secure Digital Cards-Description and Operation-31-40-01.
• Learjet AMM-Software and Configuration Load-Maintenance Practices-31-40-02.
• Learjet AMM-Configuration Load- Maintenance Practices -31-40-03.
• Learjet AMM-Secure Digital Card Crew Profile System- Maintenance Practices-31-40-04.
• Learjet AMM-Database Management System-Maintenance Practices-31-40-05.
• Learjet AMM-Current Aircraft Configuration Check-Maintenance Practices-31-40-06.
• Learjet AMM-Software Target Load-Maintenance Practices-31-40-07.
6.2 SECURE DIGITAL CARDS
Information regarding SD Cards are contained in Section 31-40-01 of the LJ AMM.
6.3 SOFTWARE LOADING PROCEDURES
6.3.1 GCU 275 PFD Controller
Reinstalling an Original GCU 275
No software or configuration loading is required if an original GCU 275 is reinstalled. This does
not include units which were repaired since their software and configuration files were deleted
at that time.
Installing a GCU 275 in Opposite Locations for Troubleshooting Purposes
No software or configuration loading is required if the original GCU #1 and GCU #2 are installed
in opposite locations for troubleshooting purposes.
Installing a New, Repaired, or Exchanged CGU 275
Load software and configuration to the GCU 275 according to Section 31-60-03 in the Learjet
AMM.
GCU 275 Operational Check
Perform an operational check of the Flight Deck Information System according to Section 31-60-
00 in the Learjet AMM.

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6.3.2 GDC 7400 AIR DATA COMPUTER
Reinstalling an Original GDC 7400
No software or configuration loading is required if an original GDC 7400 is reinstalled. This does
not include units which were repaired since their software and configuration files were deleted
at that time.
Installing a GDC 7400 in Opposite Locations for Troubleshooting Purposes
Load GDC 7400 software and configuration according to Section 31-40-07 in the Learjet AMM.
Installing a New, Repaired, or Exchanged GDC 7400
Load GDC 7400 software and configuration according to Section 34-26-01 in the Learjet AMM.
New GDC 7400 Configuration Module Installed
Load the configuration files if a GDC 7400 configuration module has been replaced.
GDC 7400 Operational Check
Perform a functional test of the Air Data Computer according to Section 34-17-01 in the Learjet
AMM.

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6.3.3 GDL 59 WI-FI DATALINK AND FLIGHT PARAMETER RECORDER
Reinstalling an Original GDL 59
No software or configuration loading is required if an original GDL 59 is reinstalled. This does
not include units which were repaired since their software and configuration files were deleted
at that time.
Installing a New, Repaired, or Exchanged GDL 59
Load GDL 59 software and configuration according to Section 45-45-02 in the Learjet AMM.
Loading Optional Configuration Files
If the GDL 59 is replaced, and the GSR 56 #1 option is installed, perform GDL 59 configuration
loading according to Section 45-45-02 in the Learjet AMM.
GDL 59 Operational Check
Perform a functional test of the Maintenance Information System according to Section 45-45-00
in the Learjet AMM.
NOTE: The GSR 56 does not require software or configuration loading if it is replaced. Contact
Garmin and/or Iridium to establish service.

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6.3.4 GDL 69 SXM Weather Data Link (Option)
Reinstalling an Original GDL 69 SXM
No software or configuration loading is required if an original GDL is reinstalled. This does not
include units which were repaired since their software and configuration files were deleted at
that time.
Installing a New, Repaired, or Exchanged GDL 69 SXM
Perform the GDL 69 SXM (configuration only) loading procedure according to Section 46-20-01
in the Learjet AMM.
GDL 69 SXM Operational Check
Perform an operational check of the Flight Deck Information System according to Section 46-20-
01 in the Learjet AMM.

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6.3.5 GDU 1400W DISPLAY UNIT

Reinstalling an Original GDU 1400W

No software or configuration loading is required if the removed display(s) are reinstalled in their
original locations. This does not include units that were returned for repair, since their software
and configuration files were deleted at that time.
Installing a GDU 1400W in Opposite Locations for Troubleshooting Purposes
No software or configuration loading is required. The displays do not need to be returned to
their original locations after swapping.
Installing a New, Repaired, or Exchanged GDU 1400W
Load software to the GDU 1400W according to Section 31-60-01 in the Learjet AMM.
GDU Operational Check
Perform an operational check of the display according to Section 31-60-01 in the Learjet AMM.

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6.3.6 GEA 71 Engine and Airframe Interface Unit
Reinstalling an Original GEA 71
No software or configuration loading is required if an original GEA 71 is reinstalled. This does
not include units which were repaired since their software and configuration files were deleted
at that time.
Installing a GEA 71 in Opposite Locations for Troubleshooting Purposes
No software or configuration loading is required if the GEA units which were removed are
installed in opposite locations (GEA 1 and GEA 2 in opposite unit racks). Proceed with a GEA 71
operational check.
NOTE: the procedure above is for swapping 1 and 2 or 3 and 4. If you swap 1 and 3, or 2 and 3,
or 2 and 4 you will need to load configuration according to Section 31-40-07 in the Learjet AMM.
Installing a New, Repaired, or Exchanged GEA 71
Load GEA 71 software according to Section 31-41-02 in the Learjet AMM.
GEA 71 Operational Check
Perform an operational check of the GEA 71 according to Section 31-41-02 in the Learjet AMM.

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6.3.7 GIA 63W INTEGRATED AVIONICS UNIT

Reinstalling an Original GIA 63W

No software or configuration loading is required if the GIA which was removed is reinstalled in
its original position (GIA #1 and GIA #2 in their original racks). This does not include units that
were returned for repair since their software and configuration files were deleted at that time.
Installing a GIA 63W in Opposite Locations for Troubleshooting Purposes
No software or configuration loading is required if the original GIA units are installed in opposite
locations for troubleshooting (GIA #1 and GIA #2 in opposite unit racks). The units however,
need to be reconfigured. Load GIA 63W configuration according to Section 31-40-07.
Installing a New, Repaired, or Exchanged GIA 63W
Load GIA 63W software and configuration according to Section 31-41-01 in the LJ AMM.
GIA Operational Check
Perform an operational check of the GIA 63W according to Section 31-41-01 in the Learjet AMM.

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6.3.8 GMA 36 AUDIO PROCESSOR AND MARKER BEACON RECEIVER

Reinstalling an Original GMA 36

No software or configuration loading is required if an original GMA 36 is reinstalled. This does
not include units which were repaired since their software and configuration files were deleted
at that time.
Installing a GMA 36 in Opposite Locations for Troubleshooting Purposes
Load GMA 36 software and configuration according to Section 31-40-07 in the Learjet AMM.
Installing a New, Repaired, or Exchanged GMA 36
Load GMA 36 software and configuration according to Section 23-50-01 in the Learjet AMM.
GMA Operational Check
Perform an audio processor unit adjustment/test according to Section 23-50-01 in the Learjet
AMM.

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6.3.9 GMC 7250 AUTOPILOT MODE CONTROLLER
Reinstalling an Original GMC 7250
No software or configuration loading is required if an original GMC 7250 is reinstalled. This does
not include units which were repaired since their software and configuration files were deleted
at that time.
Installing a New, Repaired, or Exchanged GMC 7250
Load GMC 7250 software and configuration according to Section 22-10-01 in the Learjet AMM.
GMC 7250 Operational Check
Perform an Autopilot Mode Controller operational check according to Section 22-10-01 in the
Learjet AMM.

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6.3.10 GRS 7800 AHRS
Reinstalling an Original GRS 7800
No software or configuration loading is required if an original GRS 7800 is reinstalled. This does
not include units which were repaired since their software and configuration files were deleted
at that time.
Installing a GRS 7800 in Opposite Locations for Troubleshooting Purposes
No software loading or configuration is required if the original GRS units are installed in opposite
locations for troubleshooting (GRS #1 and GRS #2 in opposite unit racks). However, if a GRS rack
is removed or loosened perform a functional test of the Attitude Heading Reference System
according to Section 34-26-00 in the Learjet AMM.
Installing a New, Repaired, or Exchanged GRS 7800
Load GRS 7800 software and configuration according to Section 34-26-01 in the Learjet AMM.
GRS 7800 Operational Check
Perform a functional test of the Attitude Heading Reference System according to Section 34-26-
00 the Learjet AMM.
NOTE: This procedure must be completed any time a GRS Configuration Module is replaced. This
procedure must be completed any time the shelf/structure the GRS is mounted to is disturbed
(removed).

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6.3.11 GMU 44
Reinstalling an Original GMU 44
No software or configuration loading is required if an original GMU 44 is reinstalled. This does
not include units which were repaired since their software and configuration files were deleted
at that time.
Installing a GMU 44 in Opposite Locations for Troubleshooting Purposes
Load GMU software and configuration according to Section 31-40-07 in the Learjet AMM.
Installing a New, Repaired, or Exchanged GMU 44
Load GMU 44 software and configuration according to Section 34-26-02 in the Learjet AMM.
GMU 44 Operational Check
Perform an operational check of the GMU 44 according to Section 34-24-00 the Learjet AMM.
NOTE: This procedure must be completed any time a GRS Configuration Module is replaced. This
procedure must be completed any time the shelf/structure the GRS is mounted to is disturbed
(removed).

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6.3.12 GSA 9000 SERVO ACTUATOR

Original Servo(s) Reinstalled

No software or configuration loading is required if an original GSA 9000 is reinstalled. This does
not include units which were repaired since their software and configuration files were deleted
at that time.
New or Repaired Servo Installed

Load GSA 9000 software according to the following sections in the Learjet AMM:
Autopilot Pitch Servo Actuator - 22-10-02
Autopilot Pitch Servo Gearbox - 22-10-03
Autopilot Roll Servo - 22-10-04
Autopilot Roll Servo Gearbox - 22-10-05
Autopilot Yaw Servo - 22-10-06
Autopilot Yaw Servo Gearbox - 22-10-07
GSA 9000 Operational Checks
 Perform an operational check of the Autopilot Pitch Servo according to Section 22-10-02
in the Learjet AMM.
 Perform an operational check for the Roll Servo according to Section 22-10-04 in the
Learjet AMM.
 Perform an operational check for the Yaw Servo according to Section 22-10-06 in the
Learjet AMM.

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6.3.13 GSC 46 SIGNAL CONDITIONER

Reinstalling an Original GSC 46

If the unit which was removed is reinstalled (same serial numbers) no software loading or
configuration is required.
New or Repaired GSC 46 Installed
If a new or repaired unit is installed, no software loading or configuration is required.
GSC 46 Operational Check
Perform an operational check of the Engine Signal Conditioner according to Section 77-41-04 in
the Learjet AMM.

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6.3.14 GSD 41 DATA CONCENTRATOR
Original GSD 41 Reinstalled
No software or configuration loading is required if an original GSD 41 is reinstalled. This does
not include units which were repaired since their software and configuration files were deleted
at that time.
Installing a GSD 41 in Opposite Locations for Troubleshooting Purposes
Load GSD 41 software and configuration according to Section 31-40-07 in the Learjet AMM.
New, Repaired or Exchanged GSD 41 Installed
Load GSD 41 software and configuration according to 31-41-03 in the Learjet AMM.
GSD 41 Operational Check
Perform an operational check of the Serial Data Concentrator Unit according to Section 31-41-03
in the Learjet AMM.

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6.3.15 GSM 9100 SERVO GEARBOX
Reinstalling an Original GSM 9100
No software or configuration files need to be loaded.
Installing a New, Repaired, or Exchanged GSM 9100
If a new, repaired, or exchanged GSM 9100 is installed, no software or configuration files need
to be loaded. Perform an operational check of the Autopilot Pitch, Roll, and Yaw Servos
according sections 22-10-02 (Pitch) -04 (Roll) and -06 (Yaw) in the Learjet AMM.

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6.3.16 GTA 82 TRIM ADAPTOR
Reinstalling an Original GTA 82
No software loading is required if an original GTA 82 is reinstalled. This does not include units
which were repaired since their software and configuration files were deleted at that time.
Installing a GTA 82 in Opposite Locations for Troubleshooting Purposes
No software loading is required if the original GTA #1 and GTA #2 are installed in opposite
locations for troubleshooting purposes.
Installing a New, Repaired, or Exchanged GTA 82
Load GTA 82 software according to Section 22-10-08 in the Learjet AMM.
GTA 82 Operational Check
Perform a functional test of Autopilot System according to Section 22-10-08 in the Learjet AMM.

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6.3.17 GTC 570 TOUCH SCREEN CONTROLLER
Reinstalling an Original GTC 570
No software loading is required if an original GTC 570 is reinstalled. This does not include units
which were repaired since their software and configuration files were deleted at that time.
Installing a GTC 570 in Opposite Locations for Troubleshooting Purposes
No software loading is required if the original GTC #1 and GTC #2 are installed in opposite
locations for troubleshooting purposes.
Installing a New, Repaired, or Exchanged GTC 570
Load GTC 570 software according to Section 31-60-02 in the Learjet AMM.
GTC 570 Operational Check
Perform an operational check of the Touchscreen Controllers according to Section 31-60-02 in
the Learjet AMM.

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6.3.18 GTS 8000 TCAS II SYSTEM

Reinstalling an Original GTS 8000

No software or configuration loading is required if an original GTS 8000 is reinstalled. This does
not include units which were repaired since their software and configuration files were deleted
at that time.
Installing a New, Repaired, or Exchanged GTS 8000
Load GTS 8000 software and configuration according to Section 34-43-01 in the Learjet AMM.
GTS 8000 Operational Check
Perform an operational check of the TCAS II system according to Section 34-43-01 in the Learjet
AMM.

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6.3.19 GTX 3000 TRANSPONDER
Reinstalling an Original GTX 3000
No software or configuration loading is required if an original GTX 3000 is reinstalled. This does
not include units which were repaired since their software and configuration files were deleted
at that time.
Installing a GTX 3000 in Opposite Locations for Troubleshooting Purposes
No software or configuration loading is required if the original GTX #1 and GTX #2 are installed
in opposite locations for troubleshooting purposes.
Installing a New, Repaired, or Exchanged GTX 3000
Load GTX 3000 software and configuration according to Section 34-56-01 in the Learjet AMM.
GTX 3000 Operational Check
Perform a functional test of the ATC Transponder System according to Section 34-56-00 in the
Learjet AMM.

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6.3.20 GWX 70 AIRBORNE WEATHER RADAR
Reinstalling an Original GWX 70
No software or configuration loading is required if an original GWX 70 is reinstalled. This does
not include units which were repaired since their software and configuration files were deleted
at that time.
Installing a New, Repaired, or Exchanged GWX 70
Load GWX 70 software and configuration according to Section 34-42-03 in the Learjet AMM.
GWX 70 Operational Check
Perform a functional test of Weather Radar System according to Section 34-42-00 in the Learjet
AMM.

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6.3.21 GDR 66 VHF Digital Radio
Reinstalling an Original GDR 66
No software installation is required if an original GDR 66 is reinstalled. This does not include
units which were repaired since their software and configuration files were deleted at that time.
Installing a New, Repaired, or Exchanged GDR 66
Load GDR 66 software and configuration according to Section 23-25-01 in the Learjet AMM.
GDR 66 Operational Check
Perform an operational check of the VHF Datalink Radio Unit according to Section 23-25-01 in
the Learjet AMM.

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SECTION 7—PERIODIC MAINTENANCE

NOTE
This section contains basic periodic maintenance procedures for the G5000. The
information in this section does not replace the time limits and maintenance
checks are contained in chapter 5 of the Supplemental Maintenance Manual
number M100544ICT-SMM-0200.

NOTE

All references in this section made to the GDL 69 also include the GDL 69 SXM.
7.1 PROCEDURES
7.1.1 Pitot/Static Leak Test
Perform a pitot/static leak test described in Title 14 CFR §§ 91.411 and Part 43 Appendix E.
Allow the GDC 7400 to operate at least 15 minutes before starting the test.
7.1.2 Altimeter (GDC 7400 and PFD)
According to 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 7400 are not subject to these errors.
7.1.3 Airspeed Function Test (GDC 7400 and PFD)
Check for correct indication.
7.1.4 Vertical Speed Indicator (GDC 7400 and PFD)
Check for correct indication.
7.1.5 GTX 3000 Transponder
Test according to Title 14 CFR §§ 91.411, 91.413 and Part 43 Appendix F.
7.1.6 GRS 7800 Earth Magnetic Field Updates
The GRS 7800 uses an earth magnetic field model which is updated once every five years. The
update is expected to be available from Garmin by July 1 of each of the following years: 2010,
2015, and every five years thereafter, as long as the GRS 7800 remains a Garmin supported
product. Otherwise maintenance of the GRS 7800 is on condition of failure only.
7.1.7 GA 37
Maintenance of the GA 37 antenna is “on-condition” only. Periodic maintenance is not required.

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7.1.8 GIA 63W
Maintenance of the GIA 63(X) is “on condition” for all units installed in airframes that require
power interrupt Category B (50mS). For airframes that require the GIA 63(X) to comply with
RTCA/DO-160D or RTCA/DO-160E (as specified in applicable Environmental Qualification Form)
power interrupt Category A (200mS), compliance with the applicable GIA 63(X) Mod Status
described in the following table must be accomplished.

Long Term Power Interrupt Category A (200 mS) Mod Status

7.1.9 GCU 275

Maintenance of the GCU 275 is “on condition” only. For regulatory periodic functional checks,
refer to approved aircraft maintenance manuals or manual supplements for actual aircraft
maintenance requirements.
7.1.10 GDC 7400
Per Part 43 Appendix E, paragraph (b)(2), Garmin specifies a test procedure equivalent to Part
43 Appendix E, paragraph (b)(1). The tests of sub-paragraphs (iv) (Friction) and (vi) (Barometric
Scale Error) are not applicable because the digital outputs of the GDC 7400 are not susceptible
to these types of errors. Other than periodic testing as required by 14CFR91.411 and in
accordance with the above information, maintenance of the GDC 7400 is ‘on condition’ only.
7.1.11 GDL 59
Maintenance of the GDL 59 is “on condition” only. For regulatory periodic functional checks,
refer to approved aircraft maintenance manuals or manual supplements for actual aircraft
maintenance requirements.
7.1.12 GDL 69
No schedule servicing tasks or internal manual adjustments are required on the GDL 69 Series. If
installation requires use of audio suppression inputs, each installed input must be verified for
proper operation on an annual basis.

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7.1.13 GDU 1400W
Maintenance of the GDU 1400W is “on condition” only. For regulatory periodic functional
checks, refer to approved aircraft maintenance manuals or manual supplements for actual
aircraft maintenance requirements.
7.1.14 GEA 71
Maintenance of the GEA 71 is “on condition” only. For regulatory periodic functional checks,
refer to approved aircraft maintenance manuals or manual supplements for actual aircraft
maintenance requirements.
7.1.15 GMA 36
Other than for regulatory periodic functional checks, maintenance of the GMA 36 is “on
condition” only.
7.1.16 GMC 7250
Maintenance of the GMC 7250 is “on condition” only. For regulatory periodic functional checks,
refer to approved aircraft maintenance manuals or manual supplements for actual aircraft
maintenance requirements.
7.1.17 GMU 44
After mechanical and electrical installation of the GRS 77 AHRS and GMU 44 magnetometer
have been completed, prior to operation, a set of post-installation calibration procedures must
be carried out.
7.1.18 GRS 7800
After mechanical and electrical installation of the GRS 7800 AHRS and GMU 44 magnetometer
have been completed, prior to operation, a set of post-installation calibration procedures must
be carried out.
7.1.19 GSA 9000/GSM 9100
Maintenance of the GSA 9000/GSM 9100 is “on condition” only.
7.1.20 GSD 41
Maintenance of the GSD 41 is “on condition” only. For regulatory periodic functional checks,
refer to approved aircraft maintenance manuals or manual supplements for actual aircraft
maintenance requirements.
7.1.21 GSR 56
Maintenance of the GSR 56 is “on condition” only. For regulatory periodic functional checks,
refer to approved aircraft maintenance manuals or manual supplements for actual aircraft
maintenance requirements.
7.1.22 GTA 82
Maintenance of the GTA 82 is “on condition” only. For regulatory periodic functional checks,
refer to approved aircraft maintenance manuals or manual supplements for actual aircraft
maintenance requirements.

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7.1.23 GTC 570
Maintenance of the GTC 570 is “on condition” only.
Screen Cleaning
Screen Cleaning mode temporarily deactivates touch input on the Touchscreen Controller glass
screen to facilitate cleaning. Garmin recommends using a microfiber or soft cotton cloth lightly
dampened with clean water to clean the glass surface of the Touchscreen Controller. Do not
use chemical cleaning agents, as these may damage the coating on the glass surface.
Cleaning the Touchscreen Controller screen:
1. From Home, touch Utilities > Screen Cleaning.
2. The Touchscreen Controller indicates the screen may be cleaned. Clean the screen as
needed.
3. Press or turn any knob to return to the Utilities Screen.
7.1.24 GTS 8000
Before returning the aircraft to service, the GTS 8XX Configuration and Checkout Log must be
completed and attached with the Instructions for Continued Airworthiness so that any aircraft
with the modifications detailed in this manual may be properly maintained.
7.1.25 GTX 3000
Test according to Title 14 CFR §§ 91.411 and 91.413 as well as Part 43 Appendix F. Other than
for regulatory checks, maintenance of the GTX 3000 is ‘on condition’ only.
7.1.26 GWX 70
Other than for regulatory checks, maintenance of the GWX 70 is ‘on condition’ only.

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SECTION 8—REINSTALLING SYSTEM SOFTWARE
System Software loading procedures for the Learjet 70/75 are covered in the Learjet AMM.
Reference section 31-41 and the specific LRU sub-sections.

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 Blank Page

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 APPENDIX A — LRU CONNECTOR PIN DESCRIPTIONS

This section contains pin names and descriptions for LRU connectors.

A.1 GDU 1400W Display Unit

P14001 Connector
View of J14001 connector from back of unit
21 20 19 18 17 16 15 14 13 12 11 10 9 8 7 6 5 4 3 2 1

42 41 40 39 38 37 36 35 34 33 32 31 30 29 28 27 26 25 24 23 22

62 61 60 59 58 57 56 55 54 53 52 51 50 49 48 47 46 44

Pin Pin Name I/O

1 CONFIG MODULE GROUND Out
2 ETHERNET OUT 1 A Out
3 ETHERNET OUT 1 B Out
4 ETHERNET IN 1 A In
5 ETHERNET IN 1 B In
6 ETHERNET OUT 2 A Out
7 ETHERNET OUT 2 B Out
8 ETHERNET IN 2 A In
9 ETHERNET IN 2 B In
10 ETHERNET OUT 3 A Out
11 ETHERNET OUT 3 B Out
12 ETHERNET IN 3 A In
13 ETHERNET IN 3 B In
14 SPARE DISCRETE IN* In
15 REVERSIONARY MODE SELECT 2 In
16 ARINC 429 IN 2 A In
17 ARINC 429 IN 2 B In
18 ARINC 429 IN 1 A In
19 ARINC 429 IN 1 B In
20 LIGHTING BUS 2 HI In
21 LIGHTING BUS 2 LO In
22 CONFIG MODULE DATA I/O
23 CONFIG MODULE POWER OUT Out
24 RESERVED --
25 RESERVED --
26 SIGNAL GROUND --
27 POWER GROUND --
28 EXT ENCODER IN* 3 In
29 POWER GROUND --
30 SIGNAL GROUND --
31 SIGNAL GROUND --
32 SIGNAL GROUND --
33 POWER GROUND --
34 SIGNAL GROUND --

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 Connector P14001, continued
Pin Pin Name I/O
35 AIRCRAFT POWER 1 In
36 SIGNAL GROUND --
37 AIRCRAFT POWER 1 In
38 SIGNAL GROUND --
39 AIRCRAFT POWER 2 In
40 SIGNAL GROUND --
41 AIRCRAFT POWER 2 In
42 SIGNAL GROUND --
43 CONFIG MODULE CLOCK Out
44 RS-232 OUT 1 Out
45 RS-232 IN 1 In
46 RS-232 OUT 2 Out
47 RS-232 IN 2 In
48 ETHERNET OUT 4A Out
49 ETHERNET OUT 4 B Out
50 ETHERNET IN 4 A In
51 ETHERNET IN 4 B In
52 EXT ENCODER IN* 1 Out
53 RESERVED --
54 DEMO MODE SELECT* In
55 CDU SYSTEM ID PROGRAM* 1 In
56 CDU SYSTEM ID PROGRAM* 2 In
57 CDU SYSTEM ID PROGRAM* 3 In
58 REVERSIONARY MODE SELECT 1 In
59 LIGHTING BUS HI In
60 LIGHTING BUS LO In
61 EXT ENCODER IN* 2 In
62 EXT ENCODER IN* 4 In
* Indicates Active Low

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J23010 Connector
View of J23010 from back of unit

Pin Pin Name I/O

1 COMPOSITE VIDEO IN 1 In

J23020 Connector
View of J23020 from back of unit

Pin Pin Name I/O

1 COMPOSITE VIDEO IN 2 In

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A.2 GTC 570 Touch Screen Controller

P5701 Connector
View of J5701 connector from back of unit
21 20 19 18 17 16 15 14 13 12 11 10 9 8 7 6 5 4 3 2 1

42 41 40 39 38 37 36 35 34 33 32 31 30 29 28 27 26 25 24 23 22

62 61 60 59 58 57 56 55 54 53 52 51 50 49 48 47 46 44

Pin Pin Name I/O

1 RESERVED --
2 ETHERNET OUT 1 A Out
3 ETHERNET OUT 1 B Out
4 ETHERNET IN 1 A In
5 ETHERNET IN 1 B In
6 ETHERNET OUT 2 A Out
7 ETHERNET OUT 2 B Out
8 ETHERNET IN 2 A In
9 ETHERNET IN 2 B In
10 ETHERNET OUT 3 A Out
11 ETHERNET OUT 3 B Out
12 ETHERNET IN 3 A In
13 ETHERNET IN 3 B In
14 RESERVED --
15 SPARE_1* In
16 ARINC 429 IN 2 A In
17 ARINC 429 IN 2 B In
18 ARINC 429 IN 1 A In
19 ARINC 429 IN 1 B In
20 RESERVED --
21 RESERVED --
22 RESERVED --
23 RESERVED --
24 RESERVED --
25 RESERVED --
26 SIGNAL GROUND --
27 POWER GROUND --
28 COMPOSITE VIDEO IN 1 HI In
29 POWER GROUND --
30 SIGNAL GROUND --
31 POWER GROUND --
32 SIGNAL GROUND --
33 POWER GROUND --
34 SIGNAL GROUND --
35 AIRCRAFT POWER 1 In
36 SIGNAL GROUND --
37 RESERVED --
38 SIGNAL GROUND --

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 Pin Pin Name I/O
39 AIRCRAFT POWER 2 In
40 SIGNAL GROUND --
41 RESERVED --
42 SIGNAL GROUND --
43 RESERVED --
44 RS-232 OUT 1 Out
45 RS-232 IN 1 In
46 RS-232 OUT 2 Out
47 RS-232 IN 2 In
48 RESERVED --
49 RESERVED --
50 RESERVED --
51 RESERVED --
52 RESERVED --
53 RESERVED --
54 DEMO MODE SELECT* In
55 GTC SYSTEM ID PROGRAM* 1 In
56 GTC SYSTEM ID PROGRAM* 2 In
57 GTC SYSTEM ID PROGRAM* 3 In
58 SPARE_2* In
59 LIGHTING BUS HI In
60 LIGHTING BUS LO In
61 RESERVED --
62 COMPOSITE VIDEO IN 2 HI In
* Indicates Active Low

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A.3 GIA 63W Integrated Avionics Unit

P601 (COM)
View of J601 connector from back of unit

Pin Pin Name I/O

1 RESERVED (UNSQUELCHED AUDIO TEST) --
2 RESERVED --
3 RESERVED --
4 COM MIC KEY* In
5 RESERVED --
6 RESERVED --
7 COM MIC AUDIO IN HI In
8 COM MIC AUDIO IN LO (GROUND) --
9 COM 500 AUDIO OUT HI Out
10 COM 500 AUDIO OUT LO Out
11 TRANSMIT INTERLOCK* In
12 COM REMOTE TRANSFER* In
13 COM DIGITAL AUDIO OUT Out
14 ON-SIDE COM MIC DIGITAL AUDIO IN In
15 SIGNAL GROUND --
16 COM REMOTE POWER OFF In
17 AIRCRAFT POWER 1 In
SPARE --
18 CROSS-SIDE COM MIC DIGITAL AUDIO IN (011-01105-20 AND In
011-01105-30 ONLY)
19 AIRCRAFT POWER 1 In
20 SPARE --
21 AIRCRAFT POWER 1 In
22 SPARE --
23 AIRCRAFT POWER 2 In
24 SPARE --
25 AIRCRAFT POWER 2 In
26 SPARE --
27 AIRCRAFT POWER 2 In
28 RESERVED --
29 RESERVED --
30 POWER GROUND --
31 POWER GROUND --
32 RESERVED --
33 RESERVED --
34 RESERVED --
* Indicates Active Low
† Pin not currently supported

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 Connector P601, continued
Pin Pin Name I/O
35 RESERVED --
36 RESERVED --
37 RESERVED --
38 RESERVED --
39 RESERVED --
40 RESERVED --
41 RESERVED --
42 RESERVED --
43 POWER GROUND --
44 POWER GROUND --
* Indicates Active Low
† Pin not currently supported

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P602 (VOR/ILS)
View of J602 connector from back of unit
21 20 19 18 17 16 15 14 13 12 11 10 9 8 7 6 5 4 3 2 1

42 41 40 39 38 37 36 35 34 33 32 31 30 29 28 27 26 25 24 23 22

62 61 60 59 58 57 56 55 54 53 52 51 50 49 48 47 46 44

Pin Pin Name I/O

1 VOR/LOC +TO Out
VOR/LOC +FROM (VOR/LOC COMMON) Out
2
VOR/LOC +FROM (NAV COMMON) (011-01105-20 AND 011-01105-30 ONLY) Out
3 VOR/LOC +FLAG Out
VOR/LOC -FLAG (VOR/LOC COMMON) Out
4
VOR/LOC -FLAG (NAV COMMON) (011-01105-20 AND 011-01105-30 ONLY) Out
5 VOR/LOC +LEFT Out
VOR/LOC +RIGHT (VOR/LOC COMMON) Out
6
VOR/LOC +RIGHT (NAV COMMON) (011-01105-20 AND 011-01105-30 ONLY) Out
7 RESERVED --
8 VOR/LOC COMPOSITE OUT Out
9 VOR OBS ROTOR C Out
10 VOR OBS ROTOR H (GROUND) --
VOR OBS STATOR E (VOR/LOC COMMON) Out
11
VOR OBS STATOR E (NAV COMMON) (011-01105-20 AND 011-01105-30 ONLY) Out
12 VOR OBS STATOR F In
13 VOR OBS STATOR D In
VOR OBS STATOR G (VOR/LOC COMMON) Out
14
VOR OBS STATOR G (NAV COMMON) (011-01105-20 AND 011-01105-30 ONLY) Out
15 VOR/LOC SUPERFLAG Out
16 VOR/LOC 500 AUDIO OUT HI Out
17 VOR/LOC 500 AUDIO OUT LO Out
18 KING SERIAL DME CLOCK (011-00781-0() AND 011-01105-0() ONLY) Out
19 KING SERIAL DME DATA (011-00781-0() AND 011-01105-0() ONLY) Out
20 KING SERIAL RNAV REQUEST (011-00781-0() AND 011-01105-0() ONLY) In
21 KING SERIAL RNAV* MODE (011-00781-0() AND 011-01105-0() ONLY) In
22 SIGNAL GROUND --
23 VOR/ILS ARINC 429 OUT B Out
24 VOR/ILS ARINC 429 OUT A Out
25 VOR OBI CLOCK Out
26 VOR OBI SYNC Out
27 VOR OBI DATA Out
28 VOR/ILS REMOTE TRANSFER* In
29 ILS ENERGIZE* Out
30 RESERVED --
31 RESERVED --
32 GLIDESLOPE +FLAG Out
33 PARALLEL DME 1 MHZ-D Out
34 GLIDESLOPE +UP Out
35 VOR/ILS ARINC 429 IN B In
36 VOR/ILS ARINC 429 IN A In
* Indicates Active Low-† Pin not currently supported

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 Connector P602, continued
Pin Pin Name I/O
37 PARALLEL DME 100 KHZ-A Out
38 GLIDESLOPE SUPERFLAG Out
39 PARALLEL DME 100 KHZ-B Out
40 PARALLEL DME 100 KHZ-C Out
41 DME COMMON In
42 PARALLEL DME 100 KHZ-D Out
43 PARALLEL DME 50 KHZ Out
44 RESERVED --
45 PARALLEL DME 1 MHZ-A Out
46 PARALLEL DME 1 MHZ-B Out
47 PARALLEL DME 1 MHZ-C Out
48 RESERVED --
49 SIGNAL GROUND --
50 RESERVED --
51 SPARE --
52 SPARE --
GLIDESLOPE –FLAG (GLIDESLOPE COMMON) Out
53
GLIDESLOPE –FLAG (NAV COMMON) (011-01105-20 AND 011-01105-30 ONLY) Out
54 PARALLEL DME 100KHZ-E Out
GLIDESLOPE +DOWN (GLIDESLOPE COMMON) Out
55
GLIDESLOPE +DOWN (NAV COMMON) (011-01105-20 AND 011-01105-30 ONLY) Out
56 PARALLEL DME 1MHZ-E Out
57 RESERVED --
SPARE --
58
GLIDESLOPE COMPOSITE OUT (011-01105-20 AND 011-01105-30 ONLY) Out
59 VOR/LOC DIGITAL AUDIO OUT Out
60 SIGNAL GROUND --
61 POWER GROUND --
62 POWER GROUND --
* Indicates Active Low
† Pin not currently supported

G5000 Line Maintenance Manual-Learjet 70/75 Page A-9

190-01386-00 Revision C
P603 (Main Serial)
View of J603 connector from back of unit

60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78

40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59

21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20

Pin Pin Name I/O

1 RESERVED --
2 ETHERNET OUT A Out
3 ETHERNET OUT B Out
4 RS-485 4 A I/O
5 RS-485 4 A I/O
6 RS-485 4 B I/O
7 RS-485 4 B I/O
8 MAIN ARINC 429 IN 3 A In
9 MAIN ARINC 429 IN 3 B In
10 MAIN ARINC 429 IN 4 A In
11 MAIN ARINC 429 IN 4 B In
12 MAIN ARINC 429 IN 5 A In
13 MAIN ARINC 429 IN 5 B In
14 MAIN ARINC 429 IN 6 A In
15 MAIN ARINC 429 IN 6 B In
16 MAIN ARINC 429 IN 7 A In
17 MAIN ARINC 429 IN 7 B In
18 MAIN ARINC 429 IN 8 A In
19 MAIN ARINC 429 IN 8 B In
20 CAN BUS 1 HI I/O
21 RESERVED --
22 CAN BUS 1 LO I/O
23 RS-485 1 A I/O
24 RS-485 1 B I/O
25 RS-485 2 A I/O
26 RS-485 2 B I/O
27 RS-485 3 A/RS-422 IN A I/O
28 RS-485 3 B/RS-422 IN B I/O
29 MAIN ARINC 429 IN 1 A In
30 CAN BUS 2 LO I/O
31 MAIN ARINC 429 IN 1 B In
32 CAN BUS 2 HI I/O
33 MAIN ARINC 429 IN 2 A In
34 CAN BUS 1 TERMINATION --
35 MAIN ARINC 429 IN 2 B In
36 RS-485 5 A/RS-422 OUT A I/O
* Indicates Active Low
† Pin not currently supported

Page A-10 G5000 Line Maintenance Manual-Learjet 70/75

Revision C 190-01386-00
 Connector P603, continued
Pin Pin Name I/O
37 RS-485 5 B/RS-422 OUT B I/O
38 RESERVED --
39 CAN BUS 2 TERMINATION --
40 RESERVED --
41 MAIN RS-232 IN 1 In
42 SIGNAL GROUND --
43 MAIN RS-232 OUT 1 Out
44 MAIN RS-232 IN 2 In
45 SIGNAL GROUND --
46 MAIN RS-232 OUT 2 Out
47 MAIN RS-232 IN 3 In
48 SIGNAL GROUND --
49 MAIN RS-232 OUT 3 Out
50 MAIN RS-232 IN 4 In
51 SIGNAL GROUND --
52 MAIN RS-232 OUT 4 Out
53 MAIN RS-232 IN 5 In
54 SIGNAL GROUND --
55 MAIN RS-232 OUT 5 Out
56 MAIN RS-232 IN 6 In
57 SIGNAL GROUND --
58 MAIN RS-232 OUT 6 Out
59 MAIN RS-232 IN 7 In
60 RESERVED --
61 SIGNAL GROUND --
62 MAIN RS-232 OUT 7 Out
63 MAIN RS-232 IN 8 In
64 SIGNAL GROUND --
65 MAIN RS-232 OUT 8 Out
66 RESERVED --
67 GPS PPS OUT Out
68 RESERVED --
69 VOICE ALERT DIGITAL AUDIO OUT Out
70 MAIN ARINC 429 OUT 1 B Out
71 MAIN ARINC 429 OUT 1 A Out
72 MAIN ARINC 429 OUT 2 B Out
73 MAIN ARINC 429 OUT 2 A Out
74 MAIN ARINC 429 OUT 3 B Out
75 MAIN ARINC 429 OUT 3 A Out
76 ETHERNET IN A In
77 ETHERNET IN B In
78 RESERVED --
* Indicates Active Low
† Pin not currently supported

G5000 Line Maintenance Manual-Learjet 70/75 Page A-11

190-01386-00 Revision C
P604 (Main Discrete)
View of J604 connector from back of unit

Pin Pin Name I/O

1 ANNUNCIATE* 22 Out
2 VOICE ALERT 500 AUDIO OUT HI Out
3 VOICE ALERT 500 AUDIO OUT LO Out
4 DISCRETE IN 13 In
5 DISCRETE IN 14 In
6 ANNUNCIATE* 1 Out
7 DISCRETE IN* 1 In
8 DISCRETE IN* 2 In
9 DISCRETE IN* 3 In
10 DISCRETE IN 15 In
11 AUTOPILOT DISCONNECT IN In
12 DISCRETE IN* 4 In
13 DISCRETE IN* 5 In
14 DISCRETE IN* 6 In
15 DISCRETE IN 16 In
16 DISCRETE IN 17 In
17 DISCRETE IN* 7 In
18 DISCRETE IN* 8 In
19 DISCRETE IN* 9 In
20 DISCRETE IN* 10 In
21 DISCRETE IN* 11 In
22 GIA SYSTEM ID PROGRAM* 1 In
23 GIA SYSTEM ID PROGRAM* 2 In
24 DISCRETE IN* 12 In
25 ANNUNCIATE* 2 Out
26 ANNUNCIATE* 3 Out
27 ANNUNCIATE* 4 Out
28 ANNUNCIATE* 5 Out
29 ANNUNCIATE* 6 Out
30 ANNUNCIATE* 7 Out
31 ANNUNCIATE* 8 Out
32 ANNUNCIATE* 9 Out
33 ANNUNCIATE* 10 Out
34 ANNUNCIATE* 11 Out
35 ANNUNCIATE* 12 Out
36 ANNUNCIATE* 13 Out
37 ANNUNCIATE* 14 Out
38 ANNUNCIATE* 15 Out
39 ANNUNCIATE* 16 Out
* Indicates Active Low
† Pin not currently supported

Page A-12 G5000 Line Maintenance Manual-Learjet 70/75

Revision C 190-01386-00
 Connector P604, continued
Pin Pin Name I/O
40 ANNUNCIATE* 17 Out
41 ANNUNCIATE* 18 Out
42 ANNUNCIATE* 19 Out
43 ANNUNCIATE* 20 Out
44 ANNUNCIATE* 21 Out
* Indicates Active Low
† Pin not currently supported

G5000 Line Maintenance Manual-Learjet 70/75 Page A-13

190-01386-00 Revision C
P605 (I/O 1)
View of J605 connector from back of unit

60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78

40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59

21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20

Pin Pin Name I/O

1 RADAR ALTIMETER DC HI† In
2 RADAR ALTIMETER DC LO† In
3 DISCRETE IN 18A In
4 SPARE --
5 SPARE --
6 SPARE --
7 SPARE --
8 FLIGHT DIRECTOR PITCH +UP In
9 FLIGHT DIRECTOR PITCH +DOWN In
10 FLIGHT DIRECTOR ROLL +RIGHT In
11 FLIGHT DIRECTOR ROLL +LEFT In
12 DISCRETE IN 19A In
13 POTENTIOMETER SIGNAL IN† In
14 POTENTIOMETER REF IN HI† In
15 POTENTIOMETER REF IN LO† In
16 DISCRETE IN 20A In
17 MAIN LATERAL DEVIATION +LEFT Out
18 MAIN LATERAL DEVIATION +RIGHT (MAIN COMMON) Out
19 MAIN LATERAL +FLAG Out
20 MAIN LATERAL –FLAG (MAIN COMMON) Out
21 SPARE --
22 SPARE --
23 MAIN VERTICAL DEVIATION +UP Out
24 MAIN VERTICAL DEVIATION +DOWN (MAIN COMMON) Out
25 MAIN VERTICAL +FLAG Out
26 MAIN VERTICAL –FLAG (MAIN COMMON) Out
27 SPARE --
28 SPARE --
29 AIRCRAFT POWER 1 In
30 POTENTIOMETER SIGNAL OUT† Out
31 AIRCRAFT POWER 1 In
32 POTENTIOMETER REF OUT HI† Out
33 AIRCRAFT POWER 2 In
34 POTENTIOMETER REF OUT LO (GROUND)† Out
35 AIRCRAFT POWER 2 In
36 GIA REMOTE POWER OFF In
* Indicates Active Low
† Pin not currently supported

Page A-14 G5000 Line Maintenance Manual-Learjet 70/75

Revision C 190-01386-00
 Connector P605, continued
Pin Pin Name I/O
37 DISCRETE IN* 1A In
38 DISCRETE IN* 2A In
39 DISCRETE IN* 3A In
40 DISCRETE IN* 4A In
41 DISCRETE IN* 5A In
42 DISCRETE IN* 6A In
43 DISCRETE IN* 7A In
44 DISCRETE IN* 8A In
45 DISCRETE IN* 9A In
46 DISCRETE IN* 10A In
47 DISCRETE OUT* 1A Out
48 SIGNAL GROUND --
49 DISCRETE IN* 11A In
50 DISCRETE IN 21A In
51 DISCRETE IN 22A In
52 DISCRETE IN* 12A In
53 DISCRETE IN* 13A In
54 DISCRETE IN* 14A In
55 DISCRETE IN* 15A In
56 OUTER MARKER LAMP IN In
57 MIDDLE MARKER LAMP IN In
58 AIRWAY/INNER MARKER LAMP IN In
59 DISCRETE IN* 16A In
60 DISCRETE IN 23A In
61 SIGNAL GROUND --
62 MAIN LATERAL SUPERFLAG Out
63 MAIN VERTICAL SUPERFLAG Out
64 SUPERFLAG 4A Out
65 SPARE --
66 SPARE --
67 SUPERFLAG 1A Out
68 DISCRETE OUT* 2A Out
69 DISCRETE OUT* 3A Out
70 DISCRETE OUT* 4A Out
71 ANNUNCIATE* 1A Out
72 ANNUNCIATE* 2A Out
73 DISCRETE IN* 17A In
74 DISCRETE IN 24A In
75 SUPERFLAG 2A Out
76 POWER GROUND --
77 SUPERFLAG 3A Out
78 POWER GROUND --
* Indicates Active Low
† Pin not currently supported

G5000 Line Maintenance Manual-Learjet 70/75 Page A-15

190-01386-00 Revision C
P606 (I/O 2)
View of J606 connector from back of unit

60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78

40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59

21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20

Pin Pin Name I/O

1 26 VAC VERTICAL GYRO REF HI† In
2 26 VAC VERTICAL GYRO REF LO† In
3 26 VAC ADF REF HI† In
4 26 VAC ADF REF LO† In
5 26 VAC AFCS REF HI† In
6 26 VAC AFCS REF LO† In
7 DIRECTIONAL GYRO MOTOR A† In
8 DIRECTIONAL GYRO MOTOR B† In
9 SIGNAL GROUND --
10 ADF X/COS In
11 ADF Y/SIN In
12 ADF Z (GROUND) In
13 SIGNAL GROUND --
14 HEADING X† In
15 HEADING Y† In
16 HEADING Z (GROUND)† In
17 SIGNAL GROUND --
18 PITCH ATTITUDE X† In
19 PITCH ATTITUDE Y† In
20 PITCH ATTITUDE Z (GROUND)† In
21 ROLL ATTITUDE X† In
22 ROLL ATTITUDE Y† In
23 ROLL ATTITUDE Z (GROUND)† In
24 SIGNAL GROUND --
25 SPARE --
26 SPARE --
27 SPARE --
28 SPARE --
29 RESERVED --
30 SIGNAL GROUND --
31 RESERVED --
32 ADF DC REF IN In
33 RESERVED --
34 ANALOG ROLL STEERING HI Out
35 RESERVED --
36 ANALOG ROLL STEERING LO (GROUND) Out
* Indicates Active Low
† Pin not currently supported

Page A-16 G5000 Line Maintenance Manual-Learjet 70/75

Revision C 190-01386-00
 Connector P606, continued
Pin Pin Name I/O
37 HEADING BOOTSTRAP OUT X† Out
38 HEADING BOOTSTRAP OUT Y† Out
39 HEADING BOOTSTRAP OUT Z (GROUND)† Out
40 AC ROLL ATTITUDE OUT HI† Out
41 AC ROLL ATTITUDE OUT LO (GROUND)† Out
42 AC PITCH ATTITUDE OUT HI† Out
43 AC PITCH ATTITUDE OUT LO (GROUND)† Out
44 YAW RATE +RIGHT† Out
45 YAW RATE +LEFT (GROUND)† Out
46 HEADING DATUM HI Out
47 HEADING DATUM LO (GROUND) Out
48 COURSE DATUM HI Out
49 COURSE DATUM LO (GROUND) Out
50 SIGNAL GROUND --
51 26 VAC DIRECTIONAL GYRO REF HI† In
52 26 VAC DIRECTIONAL GYRO REF LO† In
53 REMOTE ANNUNCIATE CLOCK In
54 REMOTE ANNUNCIATE DATA In
55 REMOTE ANNUNCIATE SYNC In
56 MAIN OBI CLOCK† Out
57 MAIN OBI DATA† Out
58 MAIN OBI SYNC† Out
59 MAIN KING SERIAL DME DATA I/O
60 MAIN KING SERIAL DME CLOCK I/O
61 MAIN KING SERIAL DME HOLD* OUT† Out
62 MAIN KING SERIAL DME REQUEST Out
63 MAIN KING SERIAL DME ON* OUT† Out
64 MAIN KING SERIAL RNAV REQUEST† In
65 RESERVED --
66 RESERVED --
67 DISCRETE OUT* 1B Out
68 DISCRETE OUT* 2B Out
69 DISCRETE OUT* 3B Out
70 DISCRETE OUT* 4B Out
71 DISCRETE OUT* 5B Out
72 DISCRETE OUT* 6B Out
73 DISCRETE OUT* 7B Out
74 DISCRETE OUT* 8B Out
75 DISCRETE OUT* 9B Out
76 RESERVED --
77 DISCRETE OUT* 10B Out
78 RESERVED --
* Indicates Active Low
† Pin not currently supported

G5000 Line Maintenance Manual-Learjet 70/75 Page A-17

190-01386-00 Revision C
 A.4 GDC 7400 Air Data Computer

J74001

Pin Pin Name I/O

1 OAT PROBE POWER OUT Out
2 OAT PROBE IN HI In
3 OAT PROBE IN LO In
4 RS-232 IN 1 In
5 RS-232 OUT 1 Out
6 SIGNAL GROUND --
7 SIGNAL GROUND --
8 RS-232 IN 2 In
9 RS-232 OUT 2 Out
10 ARINC 429 IN 1 A In
11 ARINC 429 IN 2 A In
12 ARINC 429 IN 3 A In
13 ARINC 429 IN 4 A In
14 ARINC 429 OUT 1 A Out
15 ARINC 429 OUT 2 A Out
16 ARINC 429 OUT 3 A Out
17 ARINC 429 IN 1 B In
18 ARINC 429 IN 2 B In
19 ARINC 429 IN 3 B In
20 ARINC 429 IN 4 B In
21 ARINC 429 OUT 1 B Out
22 ARINC 429 OUT 2 B Out
23 ARINC 429 OUT 3 B Out
24 ARINC 429 OUT 4 A Out

Page A-18 G5000 Line Maintenance Manual-Learjet 70/75

Revision C 190-01386-00
 GDC 7400, Connector P74001, continued
Pin Pin Name I/O
25 SIGNAL GROUND --
26 SIGNAL GROUND --
27 SIGNAL GROUND --
28 SIGNAL GROUND --
29 SIGNAL GROUND --
30 SIGNAL GROUND --
31 ARINC 429 OUT 4 B Out
32 DISCRETE IN* 1 In
33 DISCRETE IN* 2 In
34 DISCRETE IN* 3 In
35 DISCRETE IN* 4 In
36 DISCRETE IN* 5 In
37 DISCRETE IN* 6 In
38 DISCRETE IN 7 In
39 DISCRETE IN 8 In
40 RESERVED --
41 ADC SYSTEM ID PROGRAM* 1 In
42 ADC SYSTEM ID PROGRAM* 2 In
43 SIGNAL GROUND --
44 RESERVED --
45 RESERVED --
46 RESERVED --
47 RESERVED --
48 RESERVED --
49 POWER GROUND --
50 POWER GROUND --
51 RESERVED --
52 RESERVED --
53 RESERVED --
54 AIRCRAFT POWER 1 In
55 AIRCRAFT POWER 2 In

An asterisk (*) following a signal name denotes that the signal is an Active Low, requiring a
ground to activate.

G5000 Line Maintenance Manual-Learjet 70/75 Page A-19

190-01386-00 Revision C
A.5 GEA 71 Engine and Airframe Interface Unit

P701 Connector
View of P701 connector looking at rear of unit.

60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78

40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59

21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20

Pin Pin Name I/O

1 CONFIG MODULE GROUND --
2 DIGITAL IN* 1 In
3 DIGITAL IN* 2 In
4 SIGNAL GROUND --
5 RS 485 1 A I/O
6 RS 485 1 B I/O
7 RS 485 2 A I/O
8 RS 485 2 B I/O
9 GEA SYSTEM ID PROGRAM* 1 In
10 GEA SYSTEM ID PROGRAM* 2 In
11 TRANSDUCER POWER OUT LO (GROUND) --
12 TRANSDUCER POWER OUT LO (GROUND) --
13 TRANSDUCER POWER OUT LO (GROUND) --
14 +10 VDC TRANSDUCER POWER OUT Out
15 +5 VDC TRANSDUCER POWER OUT Out
16 +12 VDC TRANSDUCER POWER OUT Out
17 ENGINE TEMP ANALOG IN 6 HI In
18 ENGINE TEMP ANALOG IN 6 LO In
19 SIGNAL GROUND --
20 POWER GROUND --
21 CONFIG MODULE POWER Out
22 ANALOG IN 1 HI In
23 ANALOG IN 1 LO In
24 ANALOG IN 2 HI In
25 ANALOG IN 2 LO In
26 ENGINE TEMP ANALOG IN 1 HI In
27 ENGINE TEMP ANALOG IN 1 LO In
28 ENGINE TEMP ANALOG IN 2 HI In
29 ENGINE TEMP ANALOG IN 2 LO In
30 ENGINE TEMP ANALOG IN 3 HI In
31 ENGINE TEMP ANALOG IN 3 LO In
32 SIGNAL GROUND --
33 ENGINE TEMP ANALOG IN 4 HI In
34 ENGINE TEMP ANALOG IN 4 LO In
35 AIRCRAFT POWER 1 In
36 ENGINE TEMP ANALOG IN 5 HI In
37 AIRCRAFT POWER 2 In
38 ENGINE TEMP ANALOG IN 5 LO In

Page A-20 G5000 Line Maintenance Manual-Learjet 70/75

Revision C 190-01386-00
 Connector P701, continued

Pin Pin Name I/O

39 SIGNAL GROUND --
40 CONFIG MODULE DATA I/O
41 DIGITAL IN* 3 In
42 ANALOG IN 3 HI In
43 ANALOG IN 3 LO In
44 ANALOG IN 4 HI In
45 ANALOG IN 4 LO In
46 ANALOG IN 5 HI In
47 ANALOG IN 5 LO In
48 ENGINE TEMP ANALOG IN 7 HI In
49 ENGINE TEMP ANALOG IN 7 LO In
50 ENGINE TEMP ANALOG IN 8 HI In
51 ENGINE TEMP ANALOG IN 8 LO In
52 ENGINE TEMP ANALOG IN 9 HI In
53 ENGINE TEMP ANALOG IN 9 LO In
54 ENGINE TEMP ANALOG IN 10 HI In
55 ENGINE TEMP ANALOG IN 10 LO In
56 ENGINE TEMP ANALOG IN 11 HI In
57 ENGINE TEMP ANALOG IN 11 LO In
58 ENGINE TEMP ANALOG IN 12 HI In
59 ENGINE TEMP ANALOG IN 12 LO In
60 CONFIG MODULE CLOCK Out
61 DIGITAL IN* 4 In
62 ANALOG IN 6 HI In
63 ANALOG IN 6 LO In
64 ANALOG IN 7 HI In
65 ANALOG IN 7 LO In
66 ANALOG IN 8 HI In
67 ANALOG IN 8 LO In
68 THERMOCOUPLE REF IN HI In
69 THERMOCOUPLE REF IN LO In
70 DISCRETE IN* 1 In
71 DISCRETE IN* 2 In
72 ANALOG IN 9 HI In
73 ANALOG IN 9 LO In
74 ANALOG IN 10 HI In
75 ANALOG IN 10 LO In
76 DISCRETE IN* 3 In
77 GEA REMOTE POWER OFF In
78 POWER GROUND --

G5000 Line Maintenance Manual-Learjet 70/75 Page A-21

190-01386-00 Revision C
P702 Connector

View of P702 connector looking at rear of unit.

60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78

40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59

21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20

Pin Pin Name I/O

1 ANNUNCIATE* 1A Out
2 ANNUNCIATE* 2A Out
3 ANNUNCIATE* 3A Out
4 ANNUNCIATE* 4A Out
5 RESERVED --
6 RESERVED --
7 RESERVED --
8 RESERVED --
9 RESERVED --
10 RESERVED --
11 TRANSDUCER POWER OUT LO (GROUND) --
12 TRANSDUCER POWER OUT LO (GROUND) --
13 TRANSDUCER POWER OUT LO (GROUND) --
14 +10 VDC TRANSDUCER POWER OUT A Out
15 +5 VDC TRANSDUCER POWER OUT A Out
16 +12 VDC TRANSDUCER POWER OUT A Out
17 RESERVED --
18 RESERVED --
19 RESERVED --
20 RESERVED --
21 RESERVED --
22 RESERVED --
23 RESERVED --
24 RESERVED --
25 DISCRETE IN* 11A In
26 DISCRETE IN* 12A In
27 DISCRETE IN* 13A In
28 DISCRETE IN* 14A In
29 DISCRETE IN* 15A In
30 DISCRETE IN* 16A In
31 SIGNAL GROUND --
32 SIGNAL GROUND --
33 SIGNAL GROUND --
34 SIGNAL GROUND --
35 SIGNAL GROUND --
36 SIGNAL GROUND --
37 SIGNAL GROUND --
38 SIGNAL GROUND --
39 SIGNAL GROUND --

Page A-22 G5000 Line Maintenance Manual-Learjet 70/75

Revision C 190-01386-00
 Connector P702, continued
Pin Pin Name I/O
40 DISCRETE IN* 17A In
41 DISCRETE IN* 18A In
42 DISCRETE IN* 19A In
43 DISCRETE IN* 20A In
44 ANALOG/CURRENT MONITOR IN 1A HI In
45 ANALOG/CURRENT MONITOR IN 1A LO In
46 ANALOG/CURRENT MONITOR IN 2A HI In
47 ANALOG/CURRENT MONITOR IN 2A LO In
48 ANALOG/CURRENT MONITOR IN 3A HI In
49 ANALOG/CURRENT MONITOR IN 3A LO In
50 ANALOG/CURRENT MONITOR IN 4A HI In
51 ANALOG/CURRENT MONITOR IN 4A LO In
52 ANALOG IN 1A HI In
53 ANALOG IN 1A LO In
54 ANALOG IN 2A HI In
55 ANALOG IN 2A LO In
56 ANALOG IN 3A HI In
57 ANALOG IN 3A LO In
58 ANALOG IN 4A HI In
59 ANALOG IN 4A LO In
60 DISCRETE IN* 1A In
61 DISCRETE IN* 2A In
62 DISCRETE IN* 3A In
63 DISCRETE IN* 4A In
64 DISCRETE IN* 5A In
65 DISCRETE IN* 6A In
66 DISCRETE IN* 7A In
67 DIGITAL IN* 5A In
68 DIGITAL IN* 6A In
69 DIGITAL IN* 7A In
70 DIGITAL IN* 8A In
71 DISCRETE IN* 8A In
72 DISCRETE IN* 9A In
73 DISCRETE IN* 10A In
74 DIGITAL IN* 1A In
75 DIGITAL IN* 2A In
76 DIGITAL IN* 3A In
77 DIGITAL IN* 4A In
78 SIGNAL GROUND --

G5000 Line Maintenance Manual-Learjet 70/75 Page A-23

190-01386-00 Revision C
A.6 GRS 7800 AHRS

P78001 Connector

Pin Pin Name I/O

1 CONFIG MODULE CLOCK Out
2 CONFIG MODULE POWER OUT Out
3 SIGNAL GROUND --
4 SIGNAL GROUND --
5 CONFIG MODULE DATA I/O
6 CONFIG MODULE GROUND --
7 ARINC 429 OUT 1 A Out
8 GPS PPS IN 1 LO In
9 GPS PPS IN 2 HI In
10 ARINC 429 IN 1 A In
11 ARINC 429 IN 2 A In
12 SPARE --
13 ARINC 429 OUT 1 B Out
14 ARINC 429 OUT 2 A Out
15 GPS PPS IN 1 HI In
16 GPS PPS IN 2 LO In
17 ARINC 429 IN 1 B In
18 SIGNAL GROUND --
19 ARINC 429 IN 2 B In
20 SPARE --
21 PPS_SELECT In
22 ARINC 429 OUT 2 B Out
23 RS-232 IN 2 In
24 SIGNAL GROUND --
25 AHRS SYSTEM ID PROGRAM* 1 In
26 AHRS SYSTEM ID PROGRAM* 2 In
27 DISCRETE IN* 1 In
28 DISCRETE IN* 2 In
29 (CONNECTOR KEY—NO CONNECTION) --
30 SPARE --
31 RS-232 OUT 2 Out
32 RESERVED --
33 RESERVED --
34 AIR/GROUND* STATUS IN In
35 DISCRETE IN 3 In
36 DISCRETE IN 4 In
37 DISCRETE IN 5 In

Page A-24 G5000 Line Maintenance Manual-Learjet 70/75

Revision C 190-01386-00
 Pin Pin Name I/O
38 SPARE --
39 SPARE --
40 RS-232 IN 3 In
41 RESERVED --
42 RESERVED --
43 ARINC 429 IN 3 A In
44 SIGNAL GROUND --
45 ARINC 429 IN 4 A In
46 ARINC 429 OUT 3 A Out
47 SPARE --
48 ARINC 429 OUT 4 A Out
49 RS-232 OUT 3 Out
50 RESERVED --
51 ARINC 429 IN 3 B In
52 ARINC 429 IN 4 B In
53 SIGNAL GROUND --
54 ARINC 429 OUT 3 B Out
55 ARINC 429 OUT 4 B Out
56 SIGNAL GROUND --
57 RESERVED --
58 MAGNETOMETER RS-485 IN A In
59 MAGNETOMETER RS-485 IN B In
60 RS-232 OUT 1 Out
61 POWER GROUND --
62 POWER GROUND --
63 AIRCRAFT POWER 1 In
64 MAGNETOMETER POWER OUT Out
65 MAGNETOMETER GROUND --
66 AIRCRAFT POWER 2 In

G5000 Line Maintenance Manual-Learjet 70/75 Page A-25

190-01386-00 Revision C
A.7 GMU 44 Magnetometer
The GMU 44 has a single connector at the end of a 6” pigtail. This connects to the GRS 7X to
send it magnetic, tilt, and temperature information via RS-422 (This is sometimes called RS-485
in system interconnect drawings to simplify). The GMU 44 also receives messages (for testing
and code upload) via RS-232 and +12 V DC power through the pigtail.

Pin Pin Name I/O

1 SHIELD GROUND --
2 RS-485 OUT B Out

3 SHIELD GROUND --

4 RS-485 OUT A Out

5 SPARE --

6 POWER GROUND --

7 SPARE --

8 RS-232 IN In

9 +12 VDC POWER In

View of GMU 44 Connector Looking at Pigtail

Page A-26 G5000 Line Maintenance Manual-Learjet 70/75

Revision C 190-01386-00
A.8 GMA 36 Audio Processor and Marker Beacon Receiver

P3471 Connector
View of J3471 connector from back of unit

60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78

40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59

21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20

Pin Pin Name I/O

1 FAIL SAFE WARN AUDIO IN In
2 TRANSCEIVER 4 MIC KEY* OUT Out
3 ALERT 2 AUDIO IN HI In
4 ALERT 2 AUDIO IN LO In
5 RESERVED --
6 RECEIVER 1 AUDIO IN HI (DIFFERENTIAL) In
7 ON-SIDE COM AUDIO IN HI In
8 ON-SIDE COM AUDIO LO (GROUND) --
9 ON-SIDE CREW HEADSET AUDIO OUT LEFT Out
10 ON-SIDE CREW HEADSET AUDIO OUT RIGHT Out
11 ON-SIDE CREW HEADSET AUDIO OUT LO Out
12 TRANSCEIVER 2 AUDIO IN HI In
13 TRANSCEIVER 2 AUDIO LO (GROUND) --
14 RECEIVER 2 AUDIO IN HI (DIFFERENTIAL) In
15 RECEIVER 5 AUDIO IN HI (DIFFERENTIAL) In
16 RECEIVER 5 AUDIO IN LO (DIFFERENTIAL) In
17 MUSIC 1 AUDIO IN LEFT In
18 MUSIC 1 AUDIO IN RIGHT In
19 ALERT 4 AUDIO IN HI (DIFFERENTIAL) In
20 ALERT 5 AUDIO IN HI (DIFFERENTIAL) In
21 RESERVED --
22 RESERVED --
23 TRANSCEIVER 4 MIC AUDIO OUT HI (DIFFERENTIAL) Out
24 RESERVED --
25 RECEIVER 1 AUDIO IN LO (DIFFERENTIAL) In
26 ON-SIDE COM MIC AUDIO OUT HI Out
27 ON-SIDE COM MIC KEY* OUT Out
28 ON-SIDE CREW MIC AUDIO IN HI In
29 ON-SIDE CREW MIC KEY* IN In
30 ON-SIDE CREW MIC IN LO In
31 RECEIVER 4 AUDIO IN HI (DIFFERENTIAL) In
32 TRANSCEIVER 2 MIC AUDIO OUT HI Out
33 TRANSCEIVER 2 MIC KEY* OUT Out
34 RECEIVER 2 AUDIO IN LO (DIFFERENTIAL) In

G5000 Line Maintenance Manual-Learjet 70/75 Page A-27

190-01386-00 Revision C
 Connector P3471, continued
Pin Pin Name I/O
35 RECEIVER 3 AUDIO IN HI (DIFFERENTIAL) In
36 RECEIVER 3 AUDIO IN LO (DIFFERENTIAL) In
37 MUSIC 1 AUDIO IN LO In
38 ALERT 3 AUDIO IN HI (DIFFERENTIAL) In
39 ALERT 3,4,5 AUDIO IN LO (DIFFERENTIAL) In
40 CROSS-SIDE BUS OUT 1 B Out
41 CROSS-SIDE BUS OUT 1 A Out
42 TRANSCEIVER 4 AUDIO IN HI (DIFFERENTIAL) In
43 TRANSCEIVER 4 AUDIO IN LO (DIFFERENTIAL) In
44 PASS 3 MIC AUDIO IN HI In
45 PASS 3 MIC AUDIO IN LO (GROUND) --
46 PASS 1 MIC AUDIO IN HI In
47 PASS 1 MIC AUDIO IN LO (GROUND) --
48 PASS HEADSET AUDIO OUT LO Out
49 SECONDARY CREW MIC AUDIO IN HI In
50 SECONDARY CREW MIC KEY* IN In
51 SECONDARY CREW MIC IN LO In
52 RECEIVER 4 AUDIO IN LO (DIFFERENTIAL) In
53 SUMMED AUDIO OUT LO (GROUND) --
54 ALERT 1 AUDIO IN HI (DIFFERENTIAL) In
55 ALERT 1 AUDIO IN LO (DIFFERENTIAL) In
56 MUSIC 2 AUDIO IN LEFT In
57 MUSIC 2 AUDIO IN RIGHT In
58 TRANSCEIVER 3 AUDIO IN HI In
59 TRANSCEIVER 3 AUDIO LO (GROUND) --
60 CROSS-SIDE BUS IN 1 A In
61 CROSS-SIDE BUS IN 1 B In
62 TRANSCEIVER 4 MIC AUDIO OUT LO (DIFFERENTIAL) Out
63 PASS 4 MIC AUDIO IN HI In
64 PASS 4 MIC AUDIO IN LO (GROUND) --
65 PASS 2 MIC AUDIO IN HI In
66 PASS 2 MIC AUDIO IN LO (GROUND) --
67 PASS HEADSET AUDIO OUT LEFT Out
68 PASS HEADSET AUDIO OUT RIGHT Out
69 SECONDARY CREW HEADSET AUDIO OUT LEFT Out
70 SECONDARY CREW HEADSET AUDIO OUT RIGHT Out
71 SECONDARY CREW HEADSET AUDIO OUT LO Out
72 SUMMED AUDIO OUT HI Out
73 RESERVED --
74 RECEIVER 6 AUDIO IN HI (DIFFERENTIAL) In
75 RECEIVER 6 AUDIO IN LO (DIFFERENTIAL) In
76 MUSIC 2 AUDIO IN LO In
77 TRANSCEIVER 3 MIC AUDIO OUT HI Out
78 TRANSCEIVER 3 MIC KEY* OUT Out
* Indicates Active Low

Page A-28 G5000 Line Maintenance Manual-Learjet 70/75

Revision C 190-01386-00
P3472 Connector
View of J3472 connector from back of unit

60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78

40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59

21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20

Pin Pin Name I/O

1 RESERVED --
2 ETHERNET IN B In
3 ETHERNET OUT B Out
4 RESERVED --
5 RESERVED --
6 RS-232 OUT 1 Out
7 RS-232 IN 1 In
8 ON-SIDE COM MIC DIGITAL AUDIO OUT Out
9 ON-SIDE COM DIGITAL AUDIO IN In
10 OXYGEN MASK MIC SELECT* IN In
11 ON-SIDE CREW ICS KEY* IN In
12 SECONDARY CREW ICS KEY* IN In
13 FORCE FAILSAFE* In
14 POWER GROUND In
15 RESERVED --
16 POWER GROUND --
17 COM SWAP* IN In
18 PROGRAM GROUND --
19 RESERVED --
20 RESERVED --
21 RESERVED --
22 ETHERNET IN A In
23 ETHERNET OUT A Out
24 GMA SYSTEM ID PROGRAM* In
25 RESERVED --
26 RESERVED --
27 RESERVED --
28 ON-SIDE NAV DIGITAL AUDIO IN In
29 ON-SIDE VOICE ALERT DIGITAL AUDIO IN In
30 AIRCRAFT POWER 2 In
31 RESERVED --
32 AIRCRAFT POWER 2 In
33 RESERVED --
34 RESERVED --

G5000 Line Maintenance Manual-Learjet 70/75 Page A-29

190-01386-00 Revision C
 Connector P3472, continued
Pin Pin Name I/O
35 RESERVED --
36 RESERVED --
37 RESERVED --
38 RS-232 OUT 2 Out
39 RS-232 IN 2 In
40 RESERVED --
41 SPEAKER AUDIO OUT LO Out
42 SPEAKER AUDIO OUT HI Out
43 RESERVED --
44 PROGRAM GROUND Out
45 RESERVED --
46 PROGRAM GROUND Out
47 CROSS-SIDE COM MIC DIGITAL AUDIO OUT Out
48 CROSS-SIDE COM DIGITAL AUDIO IN In
49 RESERVED --
50 RESERVED --
51 RESERVED --
52 RESERVED --
53 AIRCRAFT POWER 1 In
54 RESERVED --
55 AIRCRAFT POWER 1 In
56 RESERVED --
57 RESERVED --
58 RESERVED --
59 MARKER ANTENNA LO In
60 RESERVED --
61 CROSS-SIDE VOICE ALERT DIGITAL AUDIO IN In
62 RESERVED --
63 RESERVED --
64 PA MUTE* OUT Out
65 RESERVED --
66 RESERVED --
67 PROGRAM GROUND --
68 CROSS-SIDE NAV DIGITAL AUDIO IN In
69 POWER GROUND --
70 RESERVED --
71 POWER GROUND --
72 RESERVED --
73 RESERVED --
74 RESERVED --
75 RESERVED --
76 RESERVED --
77 COCKPIT CALL SELECT* In
78 MARKER ANTENNA HI In
* Indicates Active Low

Page A-30 G5000 Line Maintenance Manual-Learjet 70/75

Revision C 190-01386-00
A.9 GDL 69/GDL 69 SXM Weather Data Link Receiver
View of P691 connector looking at rear of unit.
60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78

40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59

21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20

Pin # Name I/O Notes

1 Config Module Ground Out
2 RS-232 Out 2 Out
3 RS-232 Out 3 Out
4 Signal Ground --
5 RS-232 In 2 In
6 RS-232 In 3 In
7 RS-232 In 1 In SW Version 3.10 or
higher
8 RS-232 Out 1 Out SW Version 3.10 or
higher
9 Reserved --
10 Reserved --
11 Signal Ground --
12 Spare --
13 Signal Ground --
14 Spare --
15 Spare --
16 Spare --
17 Audio Out 1 Lo (Spare For GDL 69) Out GDL 69A/69AH Only
18 Audio Out 1 Right (Spare For GDL 69) Out GDL 69A/69AH Only
19 Audio Out 1 Left (Spare For GDL 69) Out GDL 69A/69AH Only
20 Power Ground --
21 Config Module Power Out Out
22 Ethernet In 1 B In
23 Ethernet In 1 A In
24 Ethernet Out 1 B Out
25 Ethernet Out 1 A Out
26 Ethernet In 2 B In
27 Ethernet In 2 A In
28 Ethernet Out 2 B Out
29 Ethernet Out 2 A Out
30 Ethernet In 3 B In
31 Ethernet In 3 A In
32 Ethernet Out 3 B Out
33 Ethernet Out 3 A Out
34 Spare --
35 Aircraft Power 1 In
36 Spare --
37 Aircraft Power 2 In

G5000 Line Maintenance Manual-Learjet 70/75 Page A-31

190-01386-00 Revision C
 Pin # Name I/O Notes
38 Spare --
39 Signal Ground --
40 Config Module Data I/O
41 Spare --
42 Spare --
43 Spare --
44 Spare --
45 Spare --
46 Spare --
47 Spare --
48 Spare --
49 Spare --
50 Spare --
51 Spare --
52 Out GDL 69A/69AH Only
Line Out Lo (Spare For GDL 69)
(Note 1)
53 Out GDL 69A/69AH Only
Line Out Right (Spare For GDL 69)
(Note 1)
54 Out GDL 69A/69AH Only
Line Out Left (Spare For GDL 69)
(Note 1)
55 Spare --
56 Ethernet In 4 B In
57 Ethernet In 4 A In
58 Ethernet Out 4 B Out
59 Ethernet Out 4 A Out
60 Config Module Clock Out
61 Audio Suppression Select 1 (Spare For GDL 69) In GDL 69A/69AH Only
62 Audio Suppression Select 2 (Spare For GDL 69) In GDL 69A/69AH Only
63 Audio Suppression Select 3 (Spare For GDL 69) In GDL 69A/69AH Only
64 Audio Suppression Select* 4 (Spare For GDL 69) In GDL 69A/69AH Only
65 Audio Suppression Select* 5 (Spare For GDL 69) In GDL 69A/69AH Only
66 Audio Suppression Select* 6 (Spare For GDL 69) In GDL 69A/69AH Only
67 Discrete In* 2 (Audio Channel Control) In GDL 69A/69AH Only
68 Reserved -- For Factory Use
Only
69 Reserved -- For Factory Use
Only
70 Audio Mute* In
71 Channel Increment* In
72 Channel Decrement* In
73 Volume Increment* In
74 Volume Decrement* In
75 Signal Ground --
76 Spare --
77 Data Link Remote Power Off In
78 Power Ground --

Page A-32 G5000 Line Maintenance Manual-Learjet 70/75

Revision C 190-01386-00
 A.10 GDL 59 Wi-Fi Datalink and Flight Parameter Recorder

P591 Connector
View of J591 connector looking at rear of unit.

60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78

40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59

21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20

Pin Pin Name I/O

1 USER ETHERNET OUT 5 A Out
2 USER ETHERNET IN 5 A In
3 AVIONICS ETHERNET OUT 2 A Out
4 AVIONICS ETHERNET IN 2 A In
5 USER ETHERNET OUT 3 A Out
6 USER ETHERNET IN 3 A In
7 USER ETHERNET OUT 4 A Out
8 USER ETHERNET IN 4 A In
9 AVIONICS ETHERNET OUT 1 A Out
10 AVIONICS ETHERNET IN 1 A In
11 SIGNAL GROUND --
12 SPARE --
13 IRIDIUM AUDIO IN 2 HI In
14 IRIDIUM AUDIO OUT 2 HI Out
15 IRIDIUM AUDIO IN 1 HI In
16 IRIDIUM AUDIO OUT 1 HI Out
17 AUDIO SYSTEM 2 AUDIO IN HI In
18 AUDIO SYSTEM 2 AUDIO OUT HI Out
19 AUDIO SYSTEM 1 AUDIO IN HI In
20 AUDIO SYSTEM 1 AUDIO OUT HI Out
21 USER ETHERNET OUT 5 B Out
22 USER ETHERNET IN 5 B In
23 AVIONICS ETHERNET OUT 2 B Out
24 AVIONICS ETHERNET IN 2 B In
25 USER ETHERNET OUT 3 B Out
26 USER ETHERNET IN 3 B In
27 USER ETHERNET OUT 4 B Out
28 USER ETHERNET IN 4 B In
29 AVIONICS ETHERNET OUT 1 B Out
30 AVIONICS ETHERNET IN 1 B In
31 SIGNAL GROUND --
32 IRIDIUM AUDIO IN 2 LO In
33 IRIDIUM AUDIO OUT 2 LO Out
34 IRIDIUM AUDIO IN 1 LO In
35 IRIDIUM AUDIO OUT 1 LO Out
36 AUDIO SYSTEM 2 AUDIO IN LO In
37 AUDIO SYSTEM 2 AUDIO OUT LO Out
38 AUDIO SYSTEM 1 AUDIO IN LO In

G5000 Line Maintenance Manual-Learjet 70/75 Page A-33

190-01386-00 Revision C
 Connector P591, continued
Pin Pin Name I/O
39 AUDIO SYSTEM 1 AUDIO OUT LO Out
40 RESERVED I/O
41 RESERVED --
42 RESERVED --
43 RESERVED --
44 SIGNAL GROUND --
45 SIGNAL GROUND --
46 SIGNAL GROUND --
47 RESERVED --
48 AIRCRAFT POWER 2 In
49 AIRCRAFT POWER 2 In
50 RESERVED --
51 SIGNAL GROUND --
52 POWER GROUND --
53 POWER GROUND --
54 POWER GROUND --
55 POWER GROUND --
56 IRIDIUM 1 STATUS DISCRETE 1* IN In
57 SPARE --
58 RESERVED --
59 POTS HANDSET RING I/O
60 RESERVED I/O
61 RESERVED In
62 RESERVED --
63 RS232 OUT 1 Out
64 RS232 IN 1 In
65 RS232 OUT 2 Out
66 RS232 IN 2 In
67 RESERVED --
68 RESERVED --
69 RESERVED --
70 RESERVED --
71 AIRCRAFT POWER 1 In
72 AIRCRAFT POWER 1 In
73 IRIDIUM 1 REMOTE POWER ON* Out
74 IRIDIUM 2 REMOTE POWER ON* Out
75 DATA LINK REMOTE POWER OFF In
76 IRIDIUM 2 STATUS DISCRETE* IN In
77 RESERVED --
78 POTS HANDSET TIP I/O

* Denotes Active Low (Ground to activate)

Page A-34 G5000 Line Maintenance Manual-Learjet 70/75

Revision C 190-01386-00
A.11 GSR 56 Iridium Satellite Transceiver

P561 Connector
View of J561 connector looking at unit

Pin Pin Name I/O

1 AUDIO OUT HI Out
2 AUDIO OUT LO Out
3 POWER GROUND --
4 AUDIO IN HI In
5 AUDIO IN LO In
6 POWER GROUND --
7 RESERVED --
8 RESERVED --
9 RESERVED --
10 RESERVED --
11 SIGNAL GROUND --
12 RS-232 OUT Out
13 RS-232 IN In
14 SIGNAL GROUND --
15 RESERVED --
16 IRIDIUM REMOTE POWER ON* In
17 POWER GROUND --
18 RESERVED --
19 POWER GROUND --
20 RESERVED --
21 HEATER POWER In
22 HEATER 1 HI --
23 POWER GROUND --
24 SPARE --
25 RESERVED --
26 RESERVED --
27 RESERVED --
28 RESERVED --
29 RESERVED --
30 RESERVED --
31 STATUS DISCRETE* OUT Out
32 AIRCRAFT POWER 1 In
33 AIRCRAFT POWER 1 In
34 AIRCRAFT POWER 2 In
*Denotes Active Low (Ground to activate)

G5000 Line Maintenance Manual-Learjet 70/75 Page A-35

190-01386-00 Revision C
 Connector P561, continued
Pin Pin Name I/O
35 AIRCRAFT POWER 2 In
36 HEATER POWER In
37 HEATER 2 HI --
38 HEATER 1 LO --
39 RESERVED --
40 RESERVED --
41 RESERVED --
42 RESERVED --
43 SIGNAL GROUND --
44 RESERVED --
*Denotes Active Low (Ground to activate)

A.12 GMC 7250 Autopilot Mode Controller

P7101
View of J7101 connector from back of unit

Pin Pin Name I/O

1 RS-232 OUT 1 Out
2 RS-232 IN 1 In
3 RS-232 OUT 2 Out
4 RS-232 IN 2 In
5 POWER GROUND --
6 SIGNAL GROUND --
7 AIRCRAFT POWER 1 In
8 SIGNAL GROUND --
9 AIRCRAFT POWER 2 In
CONTROL UNIT REMOTE POWER OFF (GMC 705/710/715 Only) In
10
RESERVED (GMC 720) --
11 LIGHTING BUS HI In
12 LIGHTING BUS LO In
13 RESERVED --
14 RESERVED --
15 POWER GROUND --

Page A-36 G5000 Line Maintenance Manual-Learjet 70/75

Revision C 190-01386-00
A.13 GWX 70 Airborne Weather Radar

View of J751 connector from back of unit

Pin Pin Name I/O
1 USB DATA HI I/O
2 USB DATA LO I/O
3 ETHERNET IN B In
4 ETHERNET IN A In
5 POWER GROUND --
6 26 VAC GYRO REF HI In
7 26 VAC GYRO REF LO In
8 POWER GROUND --
9 ARINC 429 IN 4 A In
10 ARINC 429 IN 4 B In
11 POWER GROUND --
12 ARINC 429 IN 1 B In
13 ARINC 429 IN 1 A In
14 POWER GROUND --
15 RESERVED --
16 RESERVED --
17 AIRCRAFT POWER 2 In
18 AIRCRAFT POWER 1 In
19 AIRCRAFT POWER 2 In
20 AIRCRAFT POWER 1 In
21 USB GROUND --
22 ETHERNET OUT B Out
23 ETHERNET OUT A Out
24 CONFIG MODULE POWER Out
25 ROLL ATTITUDE HI In
26 ROLL ATTITUDE LO In
27 SIGNAL GROUND --
28 ARINC 429 IN 3B In
29 ARINC 429 IN 3A In
30 ARINC 429 OUT A Out
31 ARINC 429 IN 2 B In
32 ARINC 429 IN 2 A In
33 RESERVED --
34 RESERVED --
35 RESERVED --
36 AIRCRAFT POWER 2 In
37 AIRCRAFT POWER 1 In
38 AIRCRAFT POWER 2 In
39 AIRCRAFT POWER 1 In
40 USB VBUS POWER Out
41 ARINC 429 IN 5 A In

G5000 Line Maintenance Manual-Learjet 70/75 Page A-37

190-01386-00 Revision C
 Pin Pin Name I/O
42 ARINC 429 IN 5 B In
43 CONFIG MODULE GROUND --
44 PITCH ATTITUDE HI In
45 PITCH ATTITUDE LO In
46 SIGNAL GROUND --
47 RESERVED --
48 RESERVED --
49 SIGNAL GROUND --
50 RESERVED --
51 RESERVED --
52 SIGNAL GROUND --
53 RESERVED --
54 ANTENNA SELECT* 1 In
55 ANTENNA SELECT* 0 In
56 RADAR REMOTE POWER OFF* In
57 SIGNAL GROUND --
58 RS-232 OUT 2 Out
59 RS-232 IN 2 In
60 CONFIG MODULE CLOCK Out
61 CONFIG MODULE DATA I/O
62 ARINC 453 OUT B Out
63 ARINC 453 OUT A Out
64 SIGNAL GROUND --
65 RESERVED --
66 RESERVED --
67 SIGNAL GROUND --
68 RESERVED --
69 RESERVED --
70 SIGNAL GROUND --
71 ARINC 429 IN 6 B In
72 ARINC 429 IN 6 A In
73 ARINC 429 OUT B Out
74 RS-232 IN 1 In
75 RS-232 OUT 1 Out
76 SIGNAL GROUND --
77 RS-232 IN 3 In
78 RS-232 OUT 3 Out

Page A-38 G5000 Line Maintenance Manual-Learjet 70/75

Revision C 190-01386-00
A.14 GSD 41 Data Concentrator

P411 Connector
View of J411 connector looking at rear of unit.

60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78

40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59

21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20

Pin Pin Name I/O

1 RESERVED --
2 ETHERNET IN 1 B In
3 ETHERNET IN 1 A In
4 ETHERNET OUT 1 B Out
5 ETHERNET OUT 1 A Out
6 ETHERNET IN 2 B In
7 ETHERNET IN 2 A In
8 ETHERNET OUT 2 B Out
9 ETHERNET OUT 2 A Out
10 ETHERNET IN 3 B In
11 ETHERNET IN 3 A In
12 ETHERNET OUT 3 B Out
13 ETHERNET OUT 3 A Out
14 ETHERNET IN 4 B In
15 ETHERNET IN 4 A In
16 ETHERNET OUT 4 B Out
17 ETHERNET OUT 4 A Out
18 DISCRETE IN* 1 In
19 DISCRETE IN* 2 In
20 DISCRETE IN* 3 In
21 RESERVED --
22 MAIN1 ARINC 429 IN 1 A In
23 MAIN1 ARINC 429 IN 1 B In
24 MAIN1 ARINC 429 IN 2 A In
25 MAIN1 ARINC 429 IN 2 B In
26 MAIN1 ARINC 429 IN 3 A In
27 MAIN1 ARINC 429 IN 3 B In
28 MAIN1 ARINC 429 IN 4 A In
29 MAIN1 ARINC 429 IN 4 B In
30 MAIN1 ARINC 429 IN 5 A In
31 MAIN1 ARINC 429 IN 5 B In
32 MAIN1 ARINC 429 IN 6 A In
33 MAIN1 ARINC 429 IN 6 B In
34 MAIN1 ARINC 429 IN 7 A In
35 MAIN1 ARINC 429 IN 7 B In
36 MAIN1 ARINC 429 IN 8 A In
37 MAIN1 ARINC 429 IN 8 B In
38 DISCRETE IN* 4 In

G5000 Line Maintenance Manual-Learjet 70/75 Page A-39

190-01386-00 Revision C
* Denotes Active Low (Ground to activate)

Connector P411, continued

Pin Pin Name I/O
39 DISCRETE IN* 5 In
40 RESERVED --
41 DISCRETE IN* 6 In
42 DISCRETE IN* 7 In
43 DISCRETE IN* 8 In
44 DISCRETE IN* 9 In
45 DISCRETE IN* 10 In
46 POWER GROUND --
47 POWER GROUND --
48 SIGNAL GROUND --
49 SIGNAL GROUND --
50 SIGNAL GROUND --
51 DISCRETE IN* 11 In
52 DISCRETE IN* 12 In
53 DISCRETE IN* 13 In
54 DISCRETE IN* 14 In
55 DISCRETE IN* 15 In
56 DISCRETE IN* 16 In
57 DISCRETE IN* 17 In
58 DISCRETE IN* 18 In
59 DISCRETE IN* 19 In
60 RESERVED --
61 DISCRETE IN* 20 In
62 DISCRETE IN* 21 In
63 DISCRETE IN* 22 In
64 DISCRETE IN* 23 In
65 DISCRETE IN* 24 In
66 MAIN1 ARINC 429 OUT 4 A Out
67 MAIN1 ARINC 429 OUT 4 B Out
68 AIRCRAFT POWER 1 In
69 GSD SYSTEM ID PROGRAM* 1 In
70 GSD SYSTEM ID PROGRAM* 2 In
71 AIRCRAFT POWER 2 In
72 MAIN1 ARINC 429 OUT 1 A Out
73 MAIN1 ARINC 429 OUT 1 B Out
74 MAIN1 ARINC 429 OUT 2 A Out
75 MAIN1 ARINC 429 OUT 2 B Out
76 MAIN1 ARINC 429 OUT 3 A Out
77 MAIN1 ARINC 429 OUT 3 B Out
78 GSD REMOTE POWER OFF In

* Denotes Active Low (Ground to activate)

Page A-40 G5000 Line Maintenance Manual-Learjet 70/75

Revision C 190-01386-00
P412 Connector

View of J412 connector looking at rear of unit.

60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78

40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59

21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20

Pin Pin Name I/O

1 MAIN2 RS-485/RS-422 1 A I/O
2 MAIN2 RS-485/RS-422 1 B I/O
3 MAIN2 RS-485/RS-422 2 A I/O
4 MAIN2 RS-485/RS-422 2 B I/O
5 MAIN2 RS-485/RS-422 3 A I/O
6 MAIN2 RS-485/RS-422 3 B I/O
7 MAIN2 RS-485/RS-422 4 A I/O
8 MAIN2 RS-485/RS-422 4 B I/O
9 MAIN2 RS-485/RS-422 5 A I/O
10 MAIN2 RS-485/RS-422 5 B I/O
11 MAIN2 RS-485/RS-422 6 A I/O
12 MAIN2 RS-485/RS-422 6 B I/O
13 MAIN2 RS-485/RS-422 7 A I/O
14 MAIN2 RS-485/RS-422 7 B I/O
15 MAIN2 RS-485/RS-422 8 A I/O
16 MAIN2 RS-485/RS-422 8 B I/O
17 MAIN2 RS-485/RS-422 9 A I/O
18 MAIN2 RS-485/RS-422 9 B I/O
19 MAIN2 RS-485/RS-422 10 A I/O
20 MAIN2 RS-485/RS-422 10 B I/O
21 MAIN2 RS-485/RS-422 11 A I/O
22 MAIN2 RS-485/RS-422 11 B I/O
23 MAIN2 RS-485/RS-422 12 A I/O
24 MAIN2 RS-485/RS-422 12 B I/O
25 MAIN2 RS-485/RS-422 13 A I/O
26 MAIN2 RS-485/RS-422 13 B I/O
27 MAIN2 RS-485/RS-422 14 A I/O
28 MAIN2 RS-485/RS-422 14 B I/O
29 MAIN2 ARINC 429 OUT 4 A Out
30 MAIN2 ARINC 429 OUT 4 B Out
31 DISCRETE IN* 20A In
32 DISCRETE IN* 21A In
33 DISCRETE IN* 1A In
34 DISCRETE IN* 2A In
35 DISCRETE IN* 3A In
36 DISCRETE IN* 4A In
37 DISCRETE IN* 5A In
38 DISCRETE IN* 6A In
39 DISCRETE IN* 7A In

G5000 Line Maintenance Manual-Learjet 70/75 Page A-41

190-01386-00 Revision C
 Connector P412, continued
Pin Pin Name I/O
40 DISCRETE IN 8A In
41 DISCRETE IN 9A In
42 DISCRETE IN 10A In
43 DISCRETE IN 11A In
44 DISCRETE IN 12A In
45 DISCRETE IN 13A In
46 DISCRETE IN 14A In
47 DISCRETE IN 15A In
48 SIGNAL GROUND --
49 SIGNAL GROUND --
50 SIGNAL GROUND --
51 MAIN2 ARINC 429 IN 1 A In
52 MAIN2 ARINC 429 IN 1 B In
53 MAIN2 ARINC 429 IN 2 A In
54 MAIN2 ARINC 429 IN 2 B In
55 MAIN2 ARINC 429 IN 3 A In
56 MAIN2 ARINC 429 IN 3 B In
57 MAIN2 ARINC 429 IN 4 A In
58 MAIN2 ARINC 429 IN 4 B In
59 DISCRETE IN 16A In
60 MAIN2 ARINC 429 IN 5 A In
61 MAIN2 ARINC 429 IN 5 B In
62 MAIN2 ARINC 429 IN 6 A In
63 MAIN2 ARINC 429 IN 6 B In
64 MAIN2 ARINC 429 IN 7 A In
65 MAIN2 ARINC 429 IN 7 B In
66 MAIN2 ARINC 429 OUT 1 A Out
67 MAIN2 ARINC 429 OUT 1 B Out
68 DISCRETE IN 17A In
69 MAIN2 ARINC 429 OUT 2 A Out
70 MAIN2 ARINC 429 OUT 2 B Out
71 DISCRETE IN 18A In
72 MAIN2 ARINC 429 OUT 3 A Out
73 MAIN2 ARINC 429 OUT 3 B Out
74 MAIN2 ARINC 717 IN 1 A In
75 MAIN2 ARINC 717 IN 1 B In
76 MAIN2 ARINC 717 OUT 1 A Out
77 MAIN2 ARINC 717 OUT 1 B Out
78 DISCRETE IN 19A In

* Denotes Active Low (Ground to activate)

Page A-42 G5000 Line Maintenance Manual-Learjet 70/75

Revision C 190-01386-00
A.15 GSA 9000 Servo Actuator
P90001

View of J90001 Connector, (Looking At Connector)

Pin Pin Name I/O
A AP DISCONNECT In
B RS-485 2 B I/O
C SERVO PROGRAM 4A (/DISCRETE IN* 1) In
D SERVO PROGRAM 3 In
E SERVO PROGRAM 2 In
F SERVO PROGRAM 1 In
G RS-485 1 A I/O
H RS-485 1 B I/O
J AIRCRAFT POWER 2 In
K RESERVED --
L RS-485 1 B I/O
M RS-485 1 A I/O
N RS-485 2 B I/O
P RS-485 2 A I/O
R RS-485 2 A I/O
S PROGRAM GROUND --
T PROGRAM GROUND --
U PROGRAM GROUND --
V SERVO PROGRAM 4B (/DISCRETE IN* 2) In
W AIRCRAFT POWER 1 In
X RESERVED --
Y POWER GROUND 2 --
Z POWER GROUND 1 --

G5000 Line Maintenance Manual-Learjet 70/75 Page A-43

190-01386-00 Revision C
A.16 GTA 82 Trim Adaptor

J821

Connector J821
Pin Pin Name I/O
1 MANUAL TRIM CW* In
2 AIRCRAFT POWER In
3 POWER GROUND --
4 SERVO ENABLE In
5 AP DISCONNECT In
6 SERVO PROGRAM 1 In
7 SERVO PROGRAM 2 In
8 SERVO PROGRAM 3 In
9 MOTOR CW Out
10 MANUAL TRIM ARM* In
11 MANUAL TRIM CCW* In
12 RESERVED --
13 RESERVED --
14 RESERVED --
15 RESERVED --
16 PROGRAM GROUND --
17 PROGRAM GROUND --
18 MOTOR COMMON Out
19 MANUAL TRIM ENABLE* In
20 RS-485 2 A I/O
21 RS-485 2 B I/O
22 RS-485 1 B I/O
23 RS-485 1 A I/O
24 RESERVED --
25 RESERVED --
26 MOTOR CCW Out

An asterisk (*) following a signal name denotes that the signal is an Active Low, requiring a ground to
activate

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A.17 GTS 8000 TCAS II System

P8001 (Digital)
View of J8001 connector from back of unit

60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78

40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59

21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20

Pin Pin Name I/O

1 CONFIG MODULE GROUND --
2 RS-232 OUT 1 Out
3 RS-232 IN 1 In
4 SIGNAL GROUND --
5 RS-232 OUT 2 Out
6 RS-232 IN 2 In
7 SIGNAL GROUND --
8 RS-232 OUT 3 Out
9 RS-232 IN 3 In
10 SIGNAL GROUND --
11 RS-232 OUT 4 Out
12 RS-232 IN 4 In
13 SIGNAL GROUND --
14 ARINC 429 OUT 1 A Out
15 ARINC 429 OUT 1 B Out
16 ARINC 429 IN 1 A In
17 ARINC 429 IN 1 B In
18 SIGNAL GROUND --
19 GPS PPS 1 IN In
20 SIGNAL GROUND --
21 CONFIG MODULE POWER OUT Out
22 SIGNAL GROUND --
23 ARINC 429 OUT 2 A Out
24 ARINC 429 OUT 2 B Out
25 ARINC 429 IN 2 A In
26 ARINC 429 IN 2 B In
27 SIGNAL GROUND --
28 ARINC 429 OUT 3 A Out
29 ARINC 429 OUT 3 B Out
30 ARINC 429 IN 3 A In
31 ARINC 429 IN 3 B In
32 SIGNAL GROUND --
33 ARINC 429 OUT 4 A Out
34 ARINC 429 OUT 4 B Out
35 ARINC 429 IN 4 A In
36 ARINC 429 IN 4 B In
37 RS-422 IN A In
38 RS-422 IN B In

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190-01386-00 Revision C
 Connector P8001 continued
Pin Pin Name I/O
39 SIGNAL GROUND --
40 CONFIG MODULE DATA I/O
41 SIGNAL GROUND --
42 ARINC 429 OUT 5 A Out
43 ARINC 429 OUT 5 B Out
44 ARINC 429 IN 5 A In
45 ARINC 429 IN 5 B In
46 SIGNAL GROUND --
47 ARINC 429 OUT 6 A Out
48 ARINC 429 OUT 6 B Out
49 ARINC 429 IN 6 A In
50 ARINC 429 IN 6 B In
51 SIGNAL GROUND --
52 ETHERNET OUT A Out
53 ETHERNET OUT B Out
54 ETHERNET IN A In
55 ETHERNET IN B In
56 SIGNAL GROUND --
57 RS-422 OUT A Out
58 RS-422 OUT B Out
59 SIGNAL GROUND --
60 CONFIG MODULE CLOCK Out
61 RESERVED --
62 RESERVED --
63 RESERVED --
64 RESERVED --
65 RESERVED --
66 RESERVED --
67 RESERVED --
68 RESERVED --
69 SPARE --
70 SPARE --
71 SPARE --
72 SPARE --
73 GPS PPS IN 2 HI In
74 GPS PPS IN 2 LO In
75 USB VBUS POWER In
76 USB DATA HI I/O
77 USB DATA LO I/O
78 USB GROUND --

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P8002 (Analog/Discrete)
View of J8002 connector from back of unit

60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78

40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59

21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20

Pin Pin Name Applicable Model** I/O

1 SIGNAL GROUND --
RA DISPLAY STATUS VALID* 1 GTS 8000 In
2
RESERVED GTS 855/GTS 825 --
RA DISPLAY STATUS VALID* 2 GTS 8000 In
3
RESERVED GTS 855/GTS 825 --
4 RESERVED --
5 SIGNAL GROUND --
6 AIR/GROUND* In
7 SPARE --
8 TRAFFIC DISPLAY 1 STATUS VALID* In
9 TRAFFIC DISPLAY 2 STATUS VALID* In
10 GEAR DOWN AND LOCKED* In
11 ADVISORY INHIBIT* 1 In
12 ADVISORY CANCEL* In
13 RESERVED --
14 SELF TEST INHIBIT PROGRAM* In
CLIMB INHIBIT* 1 GTS 8000 In
15
RESERVED GTS 855/GTS 825 --
CLIMB INHIBIT* 2 GTS 8000 In
16
RESERVED GTS 855/GTS 825 --
INCREASED CLIMB INHIBIT* 1 GTS 8000 In
17
RESERVED GTS 855/GTS 825 --
INCREASED CLIMB INHIBIT* 2 GTS 8000 In
18
RESERVED GTS 855/GTS 825 --
PERFORMANCE LIMIT* GTS 8000 In
19
RESERVED GTS 855/GTS 825 --
20 RESERVED --
21 SIGNAL GROUND --
22 RESERVED --
23 RESERVED --
24 RESERVED --
25 RESERVED --
26 RESERVED --
27 RESERVED --
28 RESERVED --
29 RESERVED --
30 RESERVED --
*Denotes that the signal is Active Low.
**Items in this column denote pin information specific to the listed model. Pin information applies to all
models (GTS 8000, GTS 855, and GTS 825) if blank.

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190-01386-00 Revision C
 Connector P8002, continued
Pin Pin Name Applicable Model** I/O
31 RESERVED --
32 RESERVED --
33 RESERVED --
34 RESERVED --
35 RESERVED --
36 RESERVED --
37 RESERVED --
38 RESERVED --
39 SIGNAL GROUND --
40 SIGNAL GROUND --
41 HEADING X HI In
42 HEADING X LO (GROUND) --
43 SIGNAL GROUND --
44 HEADING Y HI In
45 HEADING Y LO (GROUND) --
46 SIGNAL GROUND --
47 SPARE --
48 EXTERNAL SUPPRESSION I/O I/O
49 SIGNAL GROUND --
ANNUN* 1 (CORRECTIVE RA) GTS 8000 Out
50
ANNUN* 1 (TA DISPLAY ENABLE) GTS 855/GTS 825 Out
51 ANNUN* 2 (AURAL TA) Out
52 SPARE --
ANNUN* 3 (PREVENTIVE RA) GTS 8000 Out
53
ANNUN* 3 (VISUAL TA) GTS 855/GTS 825 Out
54 TRAFFIC SYSTEM STATUS VALID* Out
55 RESERVED --
ADVISORY INHIBIT* 2 GTS 8000 In
56
RESERVED GTS 855/GTS 825 --
57 SIGNAL GROUND --
58 ALERT AUDIO OUT HI Out
59 ALERT AUDIO OUT LO Out
60 HEADING Z HI (GROUND) In
61 HEADING Z LO (GROUND) --
62 SIGNAL GROUND --
63 26 VAC HEADING REF HI In
64 26 VAC HEADING REF LO In
65 SIGNAL GROUND --
66 SPARE --
67 SPARE --
68 HEADING VALID In
69 HEADING VALID* In
70 SIGNAL GROUND --
71 ANALOG RADAR ALTIMETER HI In
72 ANALOG RADAR ALTIMETER LO In
*Denotes that the signal is Active Low.

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Revision C 190-01386-00
**Items in this column specify pin information specific to the listed model. Pin information applies to all
models (GTS 8000, GTS 855, and GTS 825) if blank.

Pin Pin Name Applicable Model** I/O

73 SIGNAL GROUND --
74 SELF TEST INITIALIZE SELECT* In
75 TRAFFIC OPERATE/STANDBY* In
76 ANALOG RADAR ALTIMETER VALID In
77 SPARE --
78 SIGNAL GROUND --
*Denotes that the signal is Active Low.
**Items in this column specify pin information specific to the listed model. Pin information applies to all
models (GTS 8000, GTS 855, and GTS 825) if blank.

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190-01386-00 Revision C
P8003 (Power Supply)
View of J8003 connector from back of unit

Pin Pin Name I/O

1 POWER GROUND --
2 AIRCRAFT POWER 1 In
3 AIRCRAFT POWER 1 In
4 AIRCRAFT POWER 2 In
5 AIRCRAFT POWER 2 In
6 POWER GROUND --
7 RESERVED --
8 RESERVED --
9 RESERVED --
10 RESERVED --
11 POWER GROUND --
12 RESERVED --
13 RESERVED --
14 POWER GROUND --
15 RESERVED --
16 RESERVED --
17 POWER GROUND --
18 TRAFFIC SYSTEM REMOTE POWER ON* In
19 POWER GROUND --
20 POWER GROUND --
21 POWER GROUND --
22 POWER GROUND --
23 POWER GROUND --
24 POWER GROUND --
25 POWER GROUND --
26 POWER GROUND --
27 POWER GROUND --
28 POWER GROUND --
29 POWER GROUND --
30 POWER GROUND --
31 POWER GROUND --
32 POWER GROUND --
33 POWER GROUND --
34 POWER GROUND --
35 POWER GROUND --
36 TRAFFIC SYSTEM REMOTE POWER OFF In
37 POWER GROUND --
An asterisk (*) following a signal name denotes that the signal is Active Low.

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Revision C 190-01386-00
A.18 GCU 275 PFD Controller
P4751
View of J4751 connector from back of unit

Pin Pin Name I/O

1 RS-232 OUT 1 Out
2 RS-232 IN 1 In
3 RS-232 OUT 2 Out
4 RS-232 IN 2 In
5 POWER GROUND --
6 SIGNAL GROUND --
7 AIRCRAFT POWER 1 In
8 SIGNAL GROUND --
9 AIRCRAFT POWER 2 In
CONTROL UNIT REMOTE POWER OFF (GCU 475/476/477/478 Only) In
10
RESERVED (GCU 275) --
11 LIGHTING BUS HI In
12 LIGHTING BUS LO In
13 RESERVED (TEST MODE SELECT*) --
14 RESERVED --
15 POWER GROUND --

G5000 Line Maintenance Manual-Learjet 70/75 Page A-51

190-01386-00 Revision C
A.19 GDR 66 Data Link Transceiver
J661

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G5000 Line Maintenance Manual-Learjet 70/75 Page A-53
190-01386-00 Revision C
J662

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Revision C 190-01386-00
APPENDIX B — AFM/AFMS/POH CONSIDERATIONS
The following information may be published in the approved AFM, AFMS, and/or POH provided
the system is installed in accordance with AC 20-138A and is comprised of two TSO-C145a Class
3 approved Garmin GIA 63Ws, two/three TSO-C146a Class 3 approved Garmin GDU 1XXX Display
Units, Garmin GA36 and GA37 antennas, and GPS software version 3.2 or later approved
version:
NOTE
Text contained in brackets “[ ]” is meant to serve as an example and will need to
be modified in order to reflect the actual installation.
B.1 GARMIN GNSS (GPS/SBAS) NAVIGATION SYSTEM EQUIPMENT APPROVALS
The Garmin GNSS navigation system installed in this aircraft is a GPS system with a Satellite
Based Augmentation System (SBAS) comprised of [two TSO-C145a Class 3 approved Garmin GIA
63Ws, TSO-C146a Class 3 approved Garmin GDU 1XXX Display Units, Garmin GA36 and GA37
antennas, and GPS software version 3.2 or later approved version]. The Garmin GNSS
navigation system in this aircraft is installed in accordance with AC 20-138A.
The Garmin GNSS navigation system as installed in this aircraft complies with the requirements
of AC 20-138A and is approved for navigation using GPS and SBAS (within the coverage of a
Satellite Based Augmentation System complying with ICAO Annex 10) for IFR en route, terminal
area, and non-precision approach operations (including those approaches titled “GPS”, “or GPS”,
and “RNAV (GPS)” approaches). The Garmin GNSS navigation system installed in this aircraft is
approved for approach procedures with vertical guidance including “LPV” and “LNAV/VNAV”,
within the U.S. National Airspace System.
The Garmin GNSS navigation system as installed in this aircraft complies with the equipment
requirements of AC 90-105 and meets the equipment performance and functional requirements
to conduct RNP terminal departure and arrival procedures and RNP approach procedures
without RF (radius to fix) legs. Part 91 subpart K, 121, 125, 129, and 135 operators require
operational approval from the FAA.
The Garmin GNSS navigation system as installed in this aircraft complies with the equipment
requirements of AC 90-100A for RNAV 2 and RNAV 1 operations. In accordance with AC 90-
100A, Part 91 operators (except subpart K) following the aircraft and training guidance in AC 90-
100A are authorized to fly RNAV 2 and RNAV 1 procedures. Part 91 subpart K, 121, 125, 129,
and 135 operators require operational approval from the FAA.
The Garmin GNSS navigation system as installed in this aircraft has been found to comply with
the requirements for primary means of Class II navigation in oceanic and remote navigation
(RNP-10) without time limitations in accordance with AC 20-138A and FAA Order 8400.12A. The
Garmin GNSS navigation system can be used without reliance on other long-range navigation
systems. This does not constitute an operational approval.
The Garmin GNSS navigation system as installed in this aircraft has been found to comply with
the navigation requirements for primary means of Class II navigation in oceanic and remote
navigation (RNP-4) in accordance with AC 20-138A and FAA Order 8400.33. The Garmin GNSS
navigation system can be used without reliance on other long-range navigation systems.

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190-01386-00 Revision C
Additional equipment may be required to obtain operational approval to utilize RNP-4
performance. This does not constitute an operational approval.
The Garmin GNSS navigation system as installed in this aircraft complies with the accuracy,
integrity, and continuity of function, and contains the minimum system functions required for
PRNAV operations in accordance with JAA Administrative & Guidance Material Section One:
General Part 3: Temporary Guidance Leaflets, Leaflet No 10 (JAA TGL-10 Rev 1). The GNSS
navigation system has [two ETSO-145 / TSO-C145a Class 3 approved Garmin GIA 63Ws, and
ETSO-146 / TSO-C146a Class 3 approved Garmin GDU 1XXX Display Units]. The Garmin GNSS
navigation system as installed in this aircraft complies with the equipment requirements for
PRNAV and BRNAV operations in accordance with AC 90-96A and JAA TGL-10 Rev 1. This does
not constitute an operational approval.
Garmin International holds an FAA Type 2 Letter of Acceptance (LOA) in accordance with
AC 20-153 for database integrity, quality, and database management practices for the
Navigation database. Pilots and operators can view the LOA status at www.garmin.com >
Aviation Databases > Type 2 LOA Status.
Navigation information is referenced to WGS-84 reference system.
B.2 GARMIN GNSS (GPS/SBAS) NAVIGATION SYSTEM LIMITATIONS
The pilot must confirm at system initialization that the Navigation database is current.
Navigation database is expected to be current for the duration of the flight. If the AIRAC cycle
will change during flight, the pilot must ensure the accuracy of navigation data, including
suitability of navigation facilities used to define the routes and procedures for flight. If an
amended chart affecting navigation data is published for the procedure, the database must not
be used to conduct the procedure.
GPS/SBAS based IFR enroute, oceanic, and terminal navigation is prohibited unless the pilot
verifies and uses a valid, compatible, and current Navigation database or verifies each waypoint
for accuracy by reference to current approved data.
Discrepancies that invalidate a procedure must be reported to Garmin International. The
affected procedure is prohibited from being flown using data from the Navigation database until
a new Navigation database is installed in the aircraft and verified that the discrepancy has been
corrected. Contact information to report Navigation database discrepancies can be found at
www.garmin.com > Support > Contact Garmin Support > Aviation. Pilots and operators can view
navigation data base alerts at www.garmin.com > In the Air > NavData Alerts.
For flight planning purposes, in areas where SBAS coverage is not available, the pilot must check
RAIM availability. Within the United States, RAIM availability can be determined using the
Garmin WFDE Prediction program, [part number 006-A0154-01 (included in trainer software)
version 3.00 or later approved version with GARMIN GA36 and GA37 antennas selected], or the
FAA’s en route and terminal RAIM prediction website: www.raimprediction.net, or by contacting a
Flight Service Station.
Within Europe, RAIM availability can be determined using the Garmin WFDE Prediction program
or Europe’s AUGER GPS RAIM Prediction Tool at http://augur.ecacnav.com/augur/app/home. For
other areas, use the Garmin WFDE Prediction program. This requirement is not necessary if
SBAS coverage is confirmed to be available along the entire route of flight. The route planning
and WFDE prediction program may be downloaded from the Garmin website on the internet.

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Revision C 190-01386-00
For information on using the WFDE Prediction Program, refer to Garmin WAAS FDE Prediction
Program, part number 190-00643-01, ‘WFDE Prediction Program Instructions’.
For flight planning purposes, operations within the U.S. National Airspace System on RNP and
RNAV procedures when SBAS signals are not available, the availability of GPS integrity RAIM
shall be confirmed for the intended route of flight. In the event of a predicted continuous loss
of RAIM of more than five minutes for any part of the intended route of flight, the flight should
be delayed, canceled, or re-routed on a track where RAIM requirements can be met.
For flight planning purposes for operations within European B-RNAV and P-RNAV airspace, if
more than one satellite is scheduled to be out of service, then the availability of GPS integrity
RAIM shall be confirmed for the intended flight (route and time). In the event of a predicted
continuous loss of RAIM of more than five minutes for any part of the intended flight, the flight
should be delayed, canceled, or re-routed on a track where RAIM requirements can be met.
For flight planning purposes, operations where the route requires Class II navigation the
aircraft’s operator or pilot-in-command must use the Garmin WFDE Prediction program to
demonstrate that there are no outages on the specified route that would prevent the Garmin
GNSS navigation system to provide primary means of Class II navigation in oceanic and remote
areas of operation that requires (RNP-10 or RNP-4) capability. If the Garmin WFDE Prediction
program indicates fault exclusion (FDE) availability will exceed 34 minutes in accordance with
FAA Order 8400.12A for RNP-10 requirements, or 25 minutes in accordance with FAA Order
8400.33 for RNP-4 requirements, then the operation must be rescheduled when FDE is
available.
Both Garmin GPS navigation receivers must be operating and providing GPS navigation guidance
to their respective PFD for operations requiring RNP-4 performance.
North Atlantic (NAT) Minimum Navigational Performance Specifications (MNPS) Airspace
operations per AC 91-49 and AC 120-33 require both GPS/SBAS receivers to be operating and
receiving usable signals except for routes requiring only one Long Range Navigation sensor. Each
display computes an independent navigation solution based on the on-side GPS sensor.
However, either display will automatically revert to the cross-side sensor if the on-side sensor
fails or if the cross-side sensor is determined to be more accurate. [On G2000 installations a
“BOTH ON GPS1” or “BOTH ON GPS2” message does not necessarily mean that one GPS has
failed. Refer to the MFD AUX-GPS STATUS page to determine the state of the unused GPS].
Whenever possible, RNP and RNAV routes including Standard Instrument Departures (SIDs) and
Obstacle Departure Procedures (ODPs), Standard Terminal Arrival (STAR), and enroute RNAV
“Q” and RNAV “T” routes should be loaded into the flight plan from the database in their
entirety, rather than loading route waypoints from the database into the flight plan individually.
Selecting and inserting individual named fixes from the database is permitted, provided all fixes
along the published route to be flown are inserted. Manual entry of waypoints using
latitude/longitude or place/bearing is prohibited.
“GPS”, “or GPS”, and “RNAV (GPS)” instrument approaches using the Garmin navigation systems
are prohibited unless the pilot verifies and uses the current Navigation database. GPS based
instrument approaches must be flown in accordance with an approved instrument approach
procedure that is loaded from the Navigation database.

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190-01386-00 Revision C
Not all published Instrument Approach Procedures (IAP) are in the Navigation database. Pilots
planning on flying an RNAV instrument approach must ensure that the Navigation database
contains the planned RNAV Instrument Approach Procedure and that approach procedure must
be loaded from the Navigation database into the FMS flight plan by its name.
IFR non-precision approach approval using the GPS/SBAS sensor is limited to published
approaches within the U.S. National Airspace System. Approaches to airports in other airspace
are not approved unless authorized by the appropriate governing authority.
The navigation equipment required to join and fly an instrument approach procedure is
indicated by the title of the procedure and notes on the IAP chart. Use of the Garmin GPS/SBAS
receivers to provide navigation guidance during the final approach segment of an ILS, LOC, LOC-
BC, LDA, SDF, MLS or any other type of approach not approved for “or GPS” navigation is
prohibited. When using the Garmin VOR/LOC/GS receivers to fly the final approach segment,
VOR/LOC/GS navigation data must be selected and presented on the CDI of the pilot flying.
Navigation information is referenced to WGS-84 reference system, and should only be used
where the Aeronautical Information Publication (including electronic data and aeronautical
charts) conform to WGS-84 or equivalent.

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