Garmin | G5 Electronic Flight Instrument for Experimental/LSA Aircraft | Garmin G5 Electronic Flight Instrument for Experimental/LSA Aircraft G5 Installation Manual for Non-Certified Aircraft

Garmin G5 Electronic Flight Instrument for Experimental/LSA Aircraft G5 Installation Manual for Non-Certified Aircraft
G5 Electronic Flight Display
Installation Manual for
Non-Certified Aircraft
190-02072-01
July, 2019
Revision 5
© 2019
Garmin Ltd. or its subsidiaries
All Rights Reserved
Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted,
disseminated, downloaded or stored in any storage medium, for any purpose without the express prior
written consent of Garmin. Garmin hereby grants permission to download a single copy of this manual and
of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to
print one copy of this manual or of any revision hereto, provided that such electronic or printed copy of this
manual or revision must contain the complete text of this copyright notice and provided further that any
unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited.
Garmin International, Inc.
1200 E. 151st Street
Olathe, KS 66062 USA
Garmin (Europe) Ltd.
Liberty House, Hounsdown Business Park
Southampton, Hampshire SO40 9LR U.K.
AVIATION LIMITED WARRANTY
G5 warranty information is available at https://www.garmin.com/en-US/legal/aviation-limited-warranty.
RECORD OF REVISIONS
Revision
Revision
Date
1
11/01/17
Initial Release
2
03/08/18
Added GMC 507 info
3
07/16/18
Added GPS Configuration Page info
4
11/08/18
Updated interconnect drawings
5
07/30/19
Updated Section 7 and added GAD 13 info
190-02072-01
Rev. 5
Description
G5 Installation Manual
Page A
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.
CURRENT REVISION DESCRIPTION
Page
Number
Section
Number
1-3
1.5.3
Added GAD 13 to optional LRU list
2-5
2.2.5
Added GAD 13 to CAN bus info
2-6
2.2.6
Added GAD 13 to CAN bus info
7-6, 7-9–7-11,
7-13, 7-14,
7-17–7-19
7
8-66, 8-67
8.4.13.6
A-1–A-8
Appendix A
Revision
5
190-02072-01
Rev. 5
Description of Change
Updated Figure 7-10 and Figure 7-13. Added Figure 7-6,
Figure 7-9, Figure 7-11, Figure 7-13, Figure 7-17,
Figure 7-18, and Figure 7-19
Updated A429 output label info in Table 8-19
Added appendix for GAD 13 info
G5 Installation Manual
Page i
DEFINITIONS OF WARNINGS, CAUTIONS, AND NOTES
WARNING
If these guidelines are not followed, the lithium-ion battery may experience a shortened life
span or may present a risk of damage to the device, fire, chemical burn, electrolyte leak,
and/or injury.
• Do not leave the battery exposed to a heat source or in a high temperature environment. To help
prevent damage, store the battery out of direct sunlight.
• For maximum battery longevity, store within a temperature range of -4˚ to 68˚F (from -20˚ to
20˚C).
• Do not use a sharp object to remove the battery.
• Do not disassemble, puncture, damage, or incinerate the device or battery.
• Keep the battery away from children.
• Only replace the battery with the approved replacement from Garmin. Using another battery
presents a risk of fire or explosion. To purchase a replacement battery, see you Garmin dealer or
the Garmin website.
• Contact your local waste disposal department to dispose of the device and battery in accordance
with applicable local laws and regulations.
WARNING
To reduce the risk of unsafe operation, carefully review and understand all aspects of the
G5 Install Manual & Pilot's Guide documentation and the Pilot’s Operating Handbook of
the aircraft. Thoroughly practice basic operation prior to actual use. During flight
operations, carefully compare indications from the G5 to all available flight displays. For
safety purposes, always resolve any discrepancies.
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 Proposition 65. If you have any questions or would
like additional information, please refer to our website at www.garmin.com/prop65
190-02072-01
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G5 Installation Manual
Page ii
CAUTION
The display uses a lens with a special coating that may be sensitive to certain oils, waxes,
and abrasive cleaners. CLEANERS CONTAINING AMMONIA WILL HARM THE ANTIREFLECTIVE COATING. It is very important to clean the lens using a clean, lint-free
cloth and a cleaner that is specified as safe for anti-reflective coatings. Avoid any
chemical cleaners or solvents that can damage plastic components.
CAUTION
The G5 does not contain any user-serviceable parts. Repairs should only be made by an
authorized Garmin service center. Unauthorized repairs or modifications could result in
permanent damage to the equipment and void both the warranty and the authority to
operate this device under FAA, FCC, and other applicable regulations.
NOTE
The G5 may only be installed in type-certificated aircraft in accordance with Garmin STC
SA01818WI.
NOTE
The term LRU, as used throughout this manual is an abbreviation for Line Replaceable
Unit. LRU is used generically in aviation for a product (such as a GSA 28 or GMC 307)
that can be readily "swapped out" (usually as a single component) for troubleshooting/
repair.
NOTE
References to the GMC Mode Controller throughout this manual apply equally to the
GMC 305, GMC 307, and GMC 507 except where specifically noted.
190-02072-01
Rev. 5
G5 Installation Manual
Page iii
SOFTWARE LICENSE AGREEMENT FOR GARMIN AVIATION PRODUCTS
BY USING THE DEVICE, COMPONENT OR SYSTEM MANUFACTURED OR SOLD BY GARMIN
(“THE GARMIN PRODUCT”), YOU AGREE TO BE BOUND BY THE TERMS AND CONDITIONS
OF THE FOLLOWING SOFTWARE LICENSE AGREEMENT. PLEASE READ THIS AGREEMENT
CAREFULLY. Garmin Ltd. and its subsidiaries (“Garmin”) grants you a limited license to use the
software embedded in the Garmin Product (the “Software”) in binary executable form in the normal
operation of the Garmin Product. Title, ownership rights, and intellectual property rights in and to the
Software remain with Garmin and/or its third-party providers. You acknowledge that the Software is the
property of Garmin and/or its third-party providers and is protected under the United States of America
copyright laws and international copyright treaties. You further acknowledge that the structure,
organization, and code of the Software are valuable trade secrets of Garmin and/or its third-party providers
and that the Software in source code form remains a valuable trade secret of Garmin and/or its third-party
providers. You agree not to reproduce, decompile, disassemble, modify, reverse assemble, reverse
engineer, or reduce to human readable form the Software or any part thereof or create any derivative works
based on the Software. You agree not to export or re-export the Software to any country in violation of the
export control laws of the United States of America.
190-02072-01
Rev. 5
G5 Installation Manual
Page iv
TABLE OF CONTENTS
PARAGRAPH
PAGE
1 Installation Information ..................................................................................1-1
1.1 Introduction ..................................................................................................................... 1-1
1.2 G5 Overview.................................................................................................................... 1-1
1.3 Inventory of Materials ..................................................................................................... 1-2
1.4 Unpacking the Unit.......................................................................................................... 1-2
1.5 Garmin Equipment .......................................................................................................... 1-3
1.6 Non-Garmin Equipment .................................................................................................. 1-4
1.7 Garmin Software and Documents.................................................................................... 1-4
2 Installation Preparation...................................................................................2-1
2.1 Electrical Considerations ................................................................................................. 2-1
2.2 Wiring/Cabling Considerations ....................................................................................... 2-2
2.3 Mechanical Considerations............................................................................................ 2-10
3 G5 Installation ..................................................................................................3-1
3.1 Primary Functions............................................................................................................ 3-1
3.2 General Specifications ..................................................................................................... 3-1
3.3 Installation Information ................................................................................................... 3-1
3.4 Unit Installation ............................................................................................................... 3-2
3.5 Antennas .......................................................................................................................... 3-4
3.6 Mounting Instructions...................................................................................................... 3-5
3.7 Outline and Installation Drawings ................................................................................... 3-9
4 GPS Antenna Installation ................................................................................4-1
4.1 Non-Garmin Antennas..................................................................................................... 4-1
4.2 Garmin Antennas ............................................................................................................. 4-1
5 G5 Pinout ..........................................................................................................5-1
5.1 J51 Connector .................................................................................................................. 5-1
6 Connector Installation Instructions................................................................6-1
6.1 Shield Block Installation Parts ........................................................................................ 6-1
6.2 Shield Termination Technique – Method A.1 (Standard) ............................................... 6-3
6.3 Shield Termination Technique – Method A.2 (Daisy Chain) ......................................... 6-7
6.4 Shield Termination Technique – Method B.1 (Quick Term) .......................................... 6-8
6.5 Shield Termination Technique – Method B.2 (Daisy Chain-Quick Term) ................... 6-11
6.6 Daisy Chain between Methods A.1 and B.1.................................................................. 6-12
6.7 Unit ID (Strapping)........................................................................................................ 6-13
6.8 Splicing Signal Wires .................................................................................................... 6-14
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Page v
PARAGRAPH
PAGE
7 Interconnect Drawings.....................................................................................7-1
8 G5 Configuration and Post Installation Checkout........................................8-1
8.1 Recommended Test Equipment....................................................................................... 8-1
8.2 Configuration Mode ........................................................................................................ 8-2
8.3 Software Loading Procedure ........................................................................................... 8-2
8.4 Configuration Pages ........................................................................................................ 8-3
9 Troubleshooting................................................................................................9-1
9.1 General Troubleshooting ................................................................................................. 9-1
9.2 SD Card Slot .................................................................................................................... 9-2
9.3 Unit Communication Error .............................................................................................. 9-2
9.4 Air Data Troubleshooting ................................................................................................ 9-2
9.5 Attitude Failure Troubleshooting .................................................................................... 9-2
9.6 Heading Failure Troubleshooting (with GMU 11).......................................................... 9-3
9.7 G5 Data Logging ............................................................................................................. 9-3
9.8 Sending Troubleshooting Data to Garmin....................................................................... 9-3
10 Maintenance..................................................................................................10-1
10.1 G5 Air Data Periodic Maintenance ............................................................................. 10-1
10.2 G5 Battery Periodic Maintenance................................................................................ 10-1
10.3 Return to Service Information ..................................................................................... 10-1
11 Performance Specifications/Licensing/Compliance ..................................11-1
11.1 GPS Specifications ...................................................................................................... 11-1
11.2 G5 Environmental Specifications ............................................................................... 11-1
11.3 G5 Performance Specifications ................................................................................... 11-2
11.4 RS-232 Text Output Format ........................................................................................ 11-3
Appendix A GAD 13 OAT Probe Interface Module Installation ...................A-1
A.1 Equipment Description .................................................................................................. A-1
A.2 General Specifications ................................................................................................... A-2
A.3 Mounting and Wiring Requirements ............................................................................. A-3
A.4 J131 Connector .............................................................................................................. A-5
A.5 Outline and Installation Drawings ................................................................................. A-7
Appendix B GMC 507 (AFCS Mode Controller) Installation ........................B-1
B.1 Equipment Description ...................................................................................................B-1
B.2 General Specifications ....................................................................................................B-2
B.3 Mounting and Wiring Requirements ..............................................................................B-2
B.4 J7001 Connector .............................................................................................................B-4
B.5 Outline and Installation Drawings ..................................................................................B-7
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Page vi
1 INSTALLATION INFORMATION
1.1 Introduction
This manual is intended to provide mechanical and electrical information for use in the planning and
design of an installation of the Garmin G5 into an aircraft. This manual is not a substitute for an approved
airframe-specific maintenance manual, installation design drawing, or complete installation data package.
Attempting to install equipment by reference to this manual alone and without first planning or designing
an installation specific to your aircraft may compromise your safety and is not recommended. The content
of this manual assumes use by competent and qualified avionics engineering personnel and/or avionics
installation specialists using standard aviation maintenance practices in accordance with Title 14 of the
Code of Federal Regulations and other relevant accepted practices. This manual is not intended for use by
individuals who do not possess the competencies and abilities set forth above.
NOTE
Garmin recommends installation of the G5 by a Garmin-authorized installer. To the extent
allowable by law, Garmin will not be liable for damages resulting from improper or
negligent installation of the G5. For questions, please contact Garmin Product Support at
1-888-606-5482.
1.2 G5 Overview
The G5 is an electronic instrument display capable of operating as a standalone flight display or a
fully integrated backup instrument for G3X systems. It features a bright, sunlight readable, 3.5-inch
color display which is sized to fit in a standard 3-1/8-inch instrument cutout. With integrated attitude/
air data sensors and GPS, the G5 replaces traditional electromechanical standby instruments by
combining essential information into one easy-to-read display. The G5 seamlessly integrates with
other G5 units in the same aircraft and with G3X systems via the CAN network. When installed as
part of a G3X system, the G5 provides a redundant source of attitude and air data to the G3X displays,
and additionally provides backup autopilot control allowing coupled GPS approaches to be flown or
continued in the event that the primary flight display is unavailable. When installed as a standalone
system, the G5 can also perform the autopilot function. In the case of aircraft power loss, the optional
battery backup sustains the G5 flight display with up to 4 hours of emergency power.
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Page 1-1
Power/ Ambient microSD™
Backlight Light
Card Slot
Sensor
Knob
Figure 1-1 G5 Bezel Overview
1.3 Inventory of Materials
This manual provides (and provides references to) mechanical and electrical information required for the
installation of the G5. This manual is intended to be a step-by-step guide to the installation, therefore it is
important that the steps in all sections be performed in order. All materials that are required/optional for
the installation of the G5 are listed in this section (as such, some of the information in this section is
repeated in following sections).
Before beginning the G5 installation, it is recommended that the installer perform a complete inventory of
all materials listed in this section (some materials are optional and may not be applicable to the
installation). Section 1 should be used to verify that all components ordered from Garmin have been
delivered correctly, and to identify any required materials that are not provided by Garmin.
1.4 Unpacking the Unit
Carefully unpack the equipment and make a visual inspection of all contents for evidence of damage
incurred during shipment. If any component of the G5 is damaged, notify the carrier and file a claim. To
justify a claim, save the original shipping container and all packing materials. Do not return any
equipment to Garmin until the carrier has authorized the claim.
Retain the original shipping containers for storage. If the original containers are not available, a separate
cardboard container should be prepared that is large enough to accommodate sufficient packing material to
prevent movement.
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Page 1-2
1.5 Garmin Equipment
1.5.1
G5 Installation Equipment
Table 1-1 G5 Installation Equipment
LRU
Assembly Part Number
Unit Only Part Number
G5, Unit Only
010-01485-00
011-03809-00
Installation Kit, G5
010-12493-10
011-03892-00
Battery Pack, G5
010-12493-00
011-03893-00
1.5.2
Optional GPS Antenna
The G5 includes a built-in GPS receiver with an internal antenna that can be used in many installations. A
Garmin or non-Garmin GPS antenna is optional for G5 installations when not using the G5's internal GPS
antenna. See Section 4 for supported antennas and antenna requirements.
1.5.2.1
Antenna Brackets/Doubler Plates
See the G3X/G3X Touch Installation Manual (190-01115-01) for detailed information.
1.5.3
Optional Garmin LRUs
The G5 can be installed in a standalone configuration or as part of the G3X system. Optional Garmin
LRUs (Line Replaceable Units) that can be installed with the G5 in the standalone configuration are listed
below. If any of these LRUs are to be used in this installation, verify that all required installation materials
such as connector kits have been acquired. Refer to the G3X/G3X Touch Installation Manual
(190-01115-01) available at https://support.garmin.com/support/manuals for additional installation
information for these LRUs and for the G3X system.
Optional Garmin LRUs:
•
•
•
•
•
•
•
GAD 13 OAT Probe Interface Module
GAD 29 ARINC 429 Adapter (required for connection to IFR Navigator)
GMC 305 Mode Controller
GMC 307 Mode Controller
GMC 507 Mode Controller
GMU 11 Magnetometer
GSA 28 Autopilot Servo
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Page 1-3
1.6 Non-Garmin Equipment
1.6.1
Wiring/Cabling Considerations
The installer will provide all wiring and cabling unless otherwise noted.
1.6.2
Contact and Crimp Tools
Recommended crimp tools used to build the wiring harnesses for the G5 are listed in Table 1-2. Equivalent
crimp tools may also be used.
Table 1-2 Pin Contact and Crimp Tools Part Numbers
Contact Type
Socket, Size 20,
20-24 AWG
Garmin Contact
Part Number
Recommended
Positioner
Recommended
Insertion/
Extraction Tool
Recommended
Hand Crimping
Tool
336-00022-02
M22520/2-08,
Daniels K13-1
M81969/1-04 for
size 22D pins and
M81969/1-02 for
size 20 pins
M22520/2-01,
Daniels AFM8
NOTE
Non-Garmin part numbers shown are not maintained by Garmin and consequently are subject
to change without notice.
1.6.3
BNC Connectors
BNC connectors may be required to terminate the GPS antenna cable, depending upon which antenna is
used. Check the GPS antenna installation instructions for detailed information.
1.6.4
Hex Driver
A 3/32” hex drive tool is required to secure the G5 to the panel as described in Section 3, G5 Installation.
1.6.5
SD Card
A microSD™ card can be used with the G5 for software updates and data logging. Garmin recommends
SanDisk® brand SD cards up to 32 GB.
1.6.6
Pneumatic Hoses and Connectors
Air hoses and fittings are required to connect pitot and static air to the G5. The G5 has a female 1/8-27
ANPT fitting for each pitot and static port. Use appropriate aircraft fittings to connect to pitot and static
system lines.
1.6.7
Silicone Fusion Tape
Use Garmin Part Number 249-00114-00 or similar to wrap the wiring/cable bundles.
1.7 Garmin Software and Documents
The G5 unit software and a panel cut-out DXF file are available for free download from
http://www8.garmin.com/support/collection.jsp?product=010-01485-00.
190-02072-01
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G5 Installation Manual
Page 1-4
2 INSTALLATION PREPARATION
This section provides electrical and mechanical information needed for planning the physical layout of the
G5 installation. Use the information in Section 2 to become familiar with all aspects of the installation
before actually beginning the physical installation of any equipment into the aircraft. Garmin recommends
that the installer become familiar with all sections of this document before beginning the installation. In
general terms, the below steps are recommended to be followed in order.
1.
2.
3.
4.
5.
6.
Inventory of all needed parts
Planning/layout of the installation
Installation of LRUs, antennas, and sensors
Construction of wiring harness, cables, and connectors
Software installation/configuration
Post-installation checkout procedure and calibration
2.1 Electrical Considerations
This section presents information required for planning the electrical layout of the G5 installation.
CAUTION
To avoid damage to the G5 and other LRUs, take precautions to prevent Electro-Static
Discharge (ESD) when handling connectors and associated wiring. ESD damage can be
prevented by touching an object that is of the same electrical potential as the LRU before
handling the LRU itself.
2.1.1
Power Specifications
The G5 is capable of operating at either 14 or 28 VDC. Table 2-1 lists the supply voltage and current draw
information for the G5. Use this information when determining power supply requirements. All installed
electrical appliances must be considered when determining total power requirements.
The specified current draw listed in Table 2-1 is measured with the display backlight set to 100%.
Table 2-1 G5 Power Requirements
Configuration
14 V (Maximum)
14 V (Typical)
28 V (Maximum)
28 V (Typical)
G5 Only
3.5 W,
0.250 Amp
2.8 W,
0.200 Amp
3.5 W,
0.125 Amp
2.8 W,
0.100 Amp
G5 w/Battery
10.7 W,
0.760 Amp
2.8 W,
0.200 Amp
10.7 W,
0.380 Amp
2.8 W,
0.100 Amp
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Page 2-1
2.2 Wiring/Cabling Considerations
Section 5 lists the pin information for the G5 and Section 7 contains interconnect drawings. It is
recommended that all LRUs be installed prior to constructing the wiring harnesses and cables.
Use MIL-W-22759/16 (or other approved wire) AWG #22 or larger wire for all non-shielded connections
unless otherwise specified. Use MIL-C-27500 (or other approved wire) AWG #22 or larger wire for all
shielded connections unless otherwise specified. The supplied standard pin contacts are compatible with
up to AWG #20 wire. In cases where some installations have more than one LRU sharing a common
circuit breaker, sizing and wire gauge is based on aircraft circuit breaker layout, length of wiring, current
draw on units, and internal unit protection characteristics.
RG400 or RG142 coaxial cable with 50 Ω nominal impedance and meeting applicable aviation regulations
should be used when installing an optional external GPS antenna.
2.2.1
Wiring Harness Installation
Use cable meeting the applicable aviation regulation for the interconnect wiring. Any cable meeting
specifications is acceptable for the installation. When routing cables, observe the following precautions:
•
•
•
•
•
•
All cable routing should be kept as short and as direct as possible.
Check that there is ample space for the cabling and mating connectors.
Avoid sharp bends in cabling.
Avoid routing near aircraft control cables.
Avoid routing cables near heat sources, RF sources, EMI interference sources, power sources (e.g.
400 Hz generators, trim motors, etc.) or near power for fluorescent lighting.
Route the GPS antenna cable as far as possible away from all COM transceivers and other antenna
cables.
The installer shall supply and fabricate all of the cables. Electrical connections are made through the D
subminiature connector. Section 5 defines the electrical characteristics of all input and output signals.
Required connectors and associated hardware are supplied with the connector kit.
Contacts for the connectors must be crimped onto the individual wires of the aircraft wiring harness.
Table 1-2 lists contact part numbers (for reference) and recommended crimp tools.
CAUTION
Check wiring connections for errors before connecting any wiring harnesses. Incorrect
wiring could cause internal component damage.
2.2.2
CAN Bus Considerations
The primary digital interface used to exchange data between the G5 and other LRUs is the Controller Area
Network, also known as the CAN bus. CAN was developed by Bosch GmbH in the 1980s, and its
specifications are currently governed by ISO 11898-2. CAN is widely used in aviation, automotive, and
industrial applications due to its simplicity and reliability.
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Page 2-2
2.2.3
CAN Bus Architecture
The electrical architecture of the CAN bus takes the form of a linear “backbone” consisting of a single
twisted wire pair with an LRU connected (terminated) at each end (Figure 2-1). The overall length of the
CAN bus from end to end should be 66 feet (20 meters) or less. At each of the two extreme ends of the
CAN bus, a 120 Ω resistor is installed to “terminate” the bus. Termination resistors are provided either
within the LRUs themselves, or via termination adapters that plug into an LRUs CAN connection (see
Section 2.2.5).
TERM
LRU
TERM
CAN BUS BACKBONE: CONSISTS OF TWISTED, SHIELDED PAIR
WIRING CONNECTED TO CAN-H AND CAN-L OF EACH LRU, AND
PROPERLY TERMINATED LRUs ON BOTH ENDS OF BUS.
LRU
TERMINATION CONNECTIONS
Figure 2-1 CAN Bus Backbone
Multiple LRU's may be connected in a daisy chain manner along the backbone of the CAN bus
(Figure 2-2).
LRU
Max. node length
1 foot (0.3 meter)
TERM
LRU
TERM
LRU
LRU
LRU
Figure 2-2 CAN Bus Node Connections
Daisy-chained LRUs (LRUs not at the extreme ends of the CAN bus) connect to the CAN backbone
through short “stub” or “node” connections (Figure 2-3). The length of each node connection should be
kept as short as possible, and should not exceed 1 foot (0.3 meter). The best way to connect devices
between the ends of the CAN bus while maintaining short stub node lengths is to splice the connections as
close to the device as practical. Unshielded wire sections should be kept as short as practical.
Multiple devices must not connect to the CAN bus backbone at the same point. Rather than splicing two or
more stub node connections together, the CAN bus should instead be daisy-chained from one device to the
next (Figure 2-3).
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G5 Installation Manual
Page 2-3
TERM
LRU
LRU
TERM
LRU
LRU
LRU
LINEAR CAN BACKBONE, DAISY-CHAINED CONNECTIONS WITH SHORT STUB
NODE LENGTHS. MULTIPLE LRUs ARE NOT CONNECTED TO THE BACKBONE
AT THE SAME LOCATION.
Figure 2-3 Correct CAN Wiring Example
LRU
LRU
LRU
LRU
HUB
DEVICE
LRU
LRU
LRU
AVOID “T” OR “Y” SHAPE
LRU
LRU
AVOID STAR SHAPE
LRU
LRU
DO NOT USE THIRD-PARTY
HUB DEVICES
Figure 2-4 Incorrect CAN Wiring Example
2.2.4
CAN Bus Wiring
Wiring used for the CAN bus should be shielded twisted-pair cable, MIL-C-27500 or equivalent. 22 AWG
or larger wire is recommended for physical robustness and ease of installation. The shields for each CAN
bus wire segment should be interconnected, forming a continuously connected shield from one end of the
CAN bus to the other (Figure 2-5). At a minimum, the CAN bus shield should always be grounded to the
device connector backshells at the two extreme ends of the bus, but it is recommended to also ground the
shield at all other devices on the CAN bus.
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Rev. 5
G5 Installation Manual
Page 2-4
SHIELD GROUNDED AT EACH
DAISY-CHAINED LRU, RECOMMENDED
DAISY-CHAINED
LRU ON CAN BUS
CAN-H
CAN-L
SHIELD GROUND
CAN BUS TERMINATION
CAN BUS TERMINATION
CAN-H
CAN-L
CAN-H
CAN-L
SHIELD GROUND
SHIELD GROUND
SHIELD GROUNDED AT EACH END OF CAN BUS REQUIRED
CAN-H AND CAN-L WIRING SHOWN IS TWISTED SHIELDED PAIR
Figure 2-5 CAN Bus Shield Grounding
For proper CAN bus operation, it is important for all devices on the CAN bus to share a common power
ground reference. Connect all LRU power ground pins to a single common ground point - do not use local
ground points or use the aircraft structure as a ground return path.
2.2.5
CAN Bus Termination
At each of the two extreme ends of the CAN bus backbone, a 120 Ω resistor is installed to terminate the
bus. Separate resistors are not required, termination resistors are provided either within the LRUs
themselves, or via termination adapters that plug into an LRU’s CAN connection.
•
•
The GAD 13, GAD 29, GMU 11, GPS 20A, and G5 installation kits each provide a 9-pin
termination adapter that provides CAN bus termination when attached between the LRU and the
cable assembly. The termination adapter contains a 120 Ω resistor that is connected between pins
1 and 2 (Figure 2-6).
The GMC 507 and GSA 28 contain a 120 Ω resistor inside the unit that provides termination when
the two CAN-TERM pins are connected together (Figure 2-7).
GARMIN CAN TERMINATOR
Figure 2-6 CAN Bus Termination (011-02887-00) for the G5, GAD 13, GAD 29, GMU 11, and
GPS 20A
190-02072-01
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G5 Installation Manual
Page 2-5
GSA 28 SERVO
CAN_TERM_1
CAN_TERM_2
3
4
Figure 2-7 CAN Bus Termination for the GSA 28
Both ends of the CAN bus should be terminated (Figure 2-8) and devices that are not at the ends of the
CAN bus should not be terminated (Figure 2-9).
TERM
LRU
LRU
TERM
LRU
LRU
LRU
CORRECT - CAN BUS TERMINATED AT EACH END OF THE BACKBONE
Figure 2-8 Correct CAN Bus Termination Example
LRU
LRU
TERM
TERM
LRU
LRU
LRU
INCORRECT - ONE OF THE TERMINATIONS IS NOT AT THE END OF THE BACKBONE
LRU
LRU
TERM
LRU
LRU
LRU
INCORRECT - ONLY ONE END OF THE BACKBONE IS TERMINATED
Figure 2-9 Incorrect CAN Bus Termination Example
190-02072-01
Rev. 5
G5 Installation Manual
Page 2-6
2.2.6
CAN Bus LRU Removal Guidelines
The following should be considered when removing an LRU from the ends of the CAN bus.
•
•
•
2.2.7
GAD 13, GAD 29, GMU 11, GPS 20A, G5, or other devices that use the 9-pin CAN termination
adapter: The CAN bus will remain terminated as long as the CAN termination adapter is left
connected to the cable assembly.
GMC 507: The CAN Bus will be unusable until the LRU is reconnected or the bus is properly
terminated at both ends of the CAN backbone.
GSA 28: A removal adapter (part number 011-03158-00) is provided with each GSA 28 connector
kit. This adapter can be used when a GSA 28 is removed from the aircraft. The removal adapter
keeps the node on the CAN bus in the same state as when the servo was installed (either terminated
or un-terminated). The removal adapter also allows trim signals to pass through when no servo is
installed.
CAN Bus Installation Guidelines
For maximum reliability of the CAN bus, the following guidelines should be followed:
•
•
•
•
•
•
•
2.2.8
The CAN bus backbone must be a single linear path with exactly two distinct ends. CAN bus
connections should be daisy-chained from device to device. Avoid “T”, “Y”, and "star" topologies,
and do not use a hub device (Figure 2-4).
The overall length of the bus should not exceed 66 feet (20 meters).
Keep all stub node connections as short as practical. The maximum length of any stub node
connection is 1 foot (0.3 meter).
Avoid connecting more than one device to the CAN bus backbone at the same point. Instead, daisy
chain the CAN bus backbone from one device to the next.
Observe proper wiring, shielding, and grounding requirements described in Section 2.2.2.
Terminate the CAN bus at the two extreme ends of the bus, as described in Section 2.2.3.
When adding a new device to the CAN bus, evaluate proposed modifications to the CAN bus
wiring connections to ensure compliance with all of the preceding requirements.
CAN Bus Troubleshooting
The CAN bus is very simple, and a properly installed CAN bus is very reliable. If problems are occurring,
the following steps can help to identify the issue.
1. Review the status LED of devices on the CAN bus such as the GSA 28 servos. The status LED
indications are listed in Section 2-2.
Table 2-2 Status LED Indications
LED Indication
Description
No Light
No power
Steady Green
On but not communicating via CAN bus
Flashing Green
On and communicating via CAN bus
Red
Hardware fault
Alternating Red/Green
CAN bus network error (two identical LRUs are configured with
the same unit ID)
2. Make sure that the CAN bus is daisy-chained between CAN devices around the system, and that
CAN devices are not connected via a single point (star topology) or routed through a hub device.
190-02072-01
Rev. 5
G5 Installation Manual
Page 2-7
This can cause unwanted signal reflections and “orphan” some devices on the bus and prevent
their communication.
3. Make sure the CAN bus is terminated in only two locations, and only at the extreme ends of the
CAN bus.
4. With power removed, remove the CAN bus connector from one of the devices that is not located at
either of the extreme ends of the CAN bus.
a) Using an ohm meter, verify that the resistance between the CAN-H and CAN-L pins on the
connector is 60 Ω. This will verify that the CAN backbone is properly terminated at each
end (two 120 Ω terminating resistors in parallel).
b) A resistance of 120 Ω indicates that one of the two required CAN terminations is missing.
c) A resistance of 40 Ω or less indicates that too many terminations are installed.
5. Verify that the CAN-H and CAN-L signals are not swapped, shorted together, or open-circuited at
any LRU connector.
6. Verify that the CAN-H and CAN-L signals are not shorted to ground (this can happen when
shielded wire is installed incorrectly).
7. Highlight each device on the configuration mode Device Information page and verify that the
value displayed for Network Error Rate is a steady 0%.
Figure 2-10 Network Error Rate
8. Power up only the #1 G5 unit and one other CAN device at a time, and verify the connection
quality for each device. Sometimes a device will communicate only when it is the only powered
device on the CAN bus, if one or more of the above issues is present. Evaluating each CAN
device in turn can help narrow down a problem.
9. It is very important for each device on the CAN bus to share a common power/signal ground.
Ground potential differences between devices on the CAN bus can cause communication errors.
Ground devices to a common ground bus, not to the airframe or to multiple grounding buses.
190-02072-01
Rev. 5
G5 Installation Manual
Page 2-8
10. Advanced CAN diagnostics are available by selecting Device Information, Diagnostics, CAN
Network. Any increase of these parameters above zero is an indication of a CAN bus issue.
Figure 2-11 CAN Diagnostic Page
2.2.9
Cable Connector Installation
A coaxial cable connection is required for the optional external GPS antenna.
1. Route the coaxial cable to the unit location. Secure the cable in accordance with good aviation
practices.
2. Trim the coaxial cable to the desired length and install the BNC connector. If provided, follow the
connector manufacturer’s instructions for cable preparation.
190-02072-01
Rev. 5
G5 Installation Manual
Page 2-9
2.3 Mechanical Considerations
This section presents all information required for planning the physical layout of the G5 installation.
2.3.1
Physical Specifications
Use Table 2-3 to determine panel requirements. All width, height, and depth measurements are taken with
unit mounting ring and connectors (if applicable).
Table 2-3 G5 Physical Specifications
Width
Height
Depth*
Unit Weight
Weight of Unit and
Connector**
G5
3.42 in
3.60 in
2.61 in
0.55 lb
0.70 lb
G5 with Battery
3.42 in
3.60 in
3.03 in
0.83 lb
0.98 lb
Configuration
*Depth behind aircraft panel
**Weight includes mounting ring
2.3.2
Cooling Requirements
While no forced cooling air is required for the G5, it is highly recommended that the air behind the panel
be kept moving (by ventilation or a fan). Units tightly packed in the avionics stack heat each other through
radiation, convection, and sometimes by direct conduction. Even a single unit operates at a much higher
temperature in still air than in moving air. Fans or some other means of moving the air around electronic
equipment are usually a worthwhile investment.
NOTE
Avoid installing LRUs near heat sources. If this is not possible, ensure that additional cooling
is provided. Allow adequate space for installation of cables and connectors. The installer will
supply and fabricate all of the cables. All wiring should be in accordance with FAA
AC 43.13-1B and AC 43.13-2B.
2.3.3
Compass Safe Distance
After reconfiguring the avionics in the cockpit panel, if the unit is mounted less than 12 inches from the
compass, recalibrate the compass and make the necessary changes for noting correction data.
190-02072-01
Rev. 5
G5 Installation Manual
Page 2-10
3 G5 INSTALLATION
The G5 can be installed as a standalone flight display or a fully integrated backup instrument in the G3X
system. This section contains general information as well as installation information for the G5.
3.1 Primary Functions
•
•
•
•
•
•
•
•
•
Attitude (roll, pitch, and yaw)
Air data (altitude and airspeed)
Slip/skid and turn coordinator
GPS (ground speed and ground track)
Autopilot control (when installed with optional equipment)
Optional battery backup with up to 4 hours of emergency power
RS-232 and CAN communication interfaces
Course and navigation display (when installed with optional equipment)
Magnetic heading (when installed with optional equipment)
3.2 General Specifications
See Section 2.1.1 for power/current specifications, and Section 2.3.1 for dimension/weight specifications.
3.3 Installation Information
3.3.1
Required Equipment
One installation kit (Section 3-1) is required to install each G5 unit. The G5 Mounting Ring is included in
the installation kit to mount the G5 to the aircraft panel and to reinforce the panel cutout in thin panel
installations. The installation kit is not included with the G5.
Table 3-1 Contents of the G5 Installation Kit (011-03892-00)
Item
Garmin P/N
Quantity
Connector Kit, 9 Pin, w/CAN Term
011-03002-00
1
Mounting Ring, G5
115-02251-03
1
Screw, 6-32, 0.500"
211-60207-12
3
Table 3-2 Contents of the Connector Kit (011-03002-00)
Item
Garmin P/N
Quantity
Sub-Assy, Bkshl w/Hdw, Jackscrew, 9 pin
011-01855-00
1
Sub Assy, CAN Termination Kit
011-02887-00
1
Conn, Rcpt, D-Sub, Crimp Socket, 9 Ckt
330-00625-09
1
Contact, Sckt, D-Sub, Crimp, Size 20, 20-24 AWG
336-00022-02
9
190-02072-01
Rev. 5
G5 Installation Manual
Page 3-1
3.3.2
Additional Equipment Required
A 3/32” hex drive tool is required to secure the G5 to the panel as described in Section 3.6.3 and shown in
Figure 3-4.
Air hoses and fittings are required to connect pitot air and static air to the G5. The G5 uses a female 1/8-27
ANPT fitting for each of these ports. Use appropriate aircraft fittings to connect to pitot and static system
lines.
3.4 Unit Installation
Fabrication of a wiring harness is required. Sound mechanical and electrical methods and practices are
recommended for installation of the G5. Refer to Section 2.2 for wiring considerations, and to Section 5
for pinouts.
Connector kits include backshell assemblies. Garmin’s backshell connectors give the installer the ability
to quickly and easily terminate shield grounds at the backshell housing. Instructions needed to install the
Jackscrew Backshell and Shield Block Ground can be found in Section 6.
3.4.1
Mounting Requirements
The G5 includes an extremely sensitive inertial measurement unit. Consider the following when selecting
a mounting location:
•
•
•
•
•
•
•
•
3.4.2
Mount the G5 with the connector aligned to within 15.0° of the longitudinal axis of the aircraft
(display bezel parallel to the wing spar). Configuration allows for direct manual entry of the
present yaw offset when the instrument panel to which the G5 is mounted is not perpendicular to
the aircraft centerline.
The G5 should be rigidly mounted to the aircraft panel. To avoid degraded accuracy, the aircraft
panel should be rigid and panel flexing should be minimized.
The G5 should be mounted to the aircraft panel with the connector facing toward the front of the
aircraft.
The G5 should be mounted within 13 feet (4 meters) longitudinally of the aircraft CG (center of
gravity). In cases where the longitudinal distance from the CG is planned to be greater than 6.5
feet (2 meters), it is preferable to mount the G5 forward of the aircraft CG, if possible, to improve
autopilot performance.
To prevent degraded accuracy, avoid placing the G5 near areas that are prone to severe vibration.
The G5 must be leveled to within 30.0° of the flight level cruise attitude. An aircraft leveling and
offset calibration procedure must additionally be carried out prior to flight.
The mounting location for the G5 should be protected from rapid thermal transients, in particular
large heat loads from nearby high-power equipment.
Avoid placing the G5 within 1 inch of magnetically mounted antennas, speaker magnets, or other
strongly magnetic items.
Unit Mounting
For final installation and assembly, refer to the outline and installation drawings in Section 3.7.
1. Mount the G5 in a suitable location using the installation kit (Table 3-1) per the requirements in
Section 3.4.1.
2. Assemble the wiring harness and backshell connector.
3. Assemble the pneumatic hoses and connector.
4. Connect the CAN terminator if required (see Section 2.2.5).
5. Connect the backshell connector and hoses.
190-02072-01
Rev. 5
G5 Installation Manual
Page 3-2
3.4.3
Pneumatic Plumbing
The G5 has two ports that are connected to the aircraft’s pitot and static pressure sources. The ports are
labeled on the unit using the abbreviations “P” and “S” respectively (Figure 3-1). The pressure ports have
1/8-27 ANPT female threads. The mating fitting must have 1/8-27 ANPT male threads.
NOTE
The temporary port plugs attached to the pressure ports on a new G5 are not suitable for flight
and must be removed prior to the installation of G5 into the aircraft.
NOTE
In an installation with dual G5 units, pitot/static plumbing must be connected to both units.
Figure 3-1 G5 Air Hose Fitting Locations
Use appropriate air hoses and fittings to connect the pitot and static lines to the unit. Avoid sharp bends in
the tubing and attempt to route hoses away from aircraft control cables. The G5 should not be at the low
point of the pneumatic plumbing lines to avoid moisture or debris collecting at or near the unit. Ensure that
no deformations of the airframe surface have been made that would affect the relationship between static
air pressure and true ambient static air pressure for any flight condition. Refer to CFR Part 43, Appendix E
for approved practices while installing hoses and connections.
NOTE
A G5 installed as a standalone unit may optionally be configured to disable its internal air
data sensors. In this case, no connection to the aircraft's pitot/static system is required. If not
connected, the pitot/static fittings on the G5 should be covered with dust caps. A G5 with air
data disabled does not support autopilot functionality.
190-02072-01
Rev. 5
G5 Installation Manual
Page 3-3
3.4.4
Pneumatic Connections
The following steps should be used to aid in the fabrication of pneumatic hose connections and in attaching
the aircraft pitot pressure source and aircraft static pressure sources to the G5.
NOTE
Whenever the aircraft is connected to a pitot-static tester, such as during Part 43 Appendix E
altimeter tests, the pitot port must be covered by a pitot adapter that is controlled by the pitotstatic tester. Failure to do so will result in overpressuring and damaging the internal airspeed
sensor.
NOTE
Use of different colored tubing is recommended for static and pitot plumbing to avoid
plumbing connection errors. Incorrect plumbing connections will result in erroneous air data
information calculated by the G5.
Observe the following cautions when connecting pneumatic lines:
1. Make sure the aircraft static pressure port is plumbed directly to the unit static pressure input port
and the aircraft pitot pressure port is plumbed directly to the unit pitot pressure input port.
2. Seal the threads of pneumatic fittings at the connector ports. Use caution to ensure there are no
pneumatic leaks.
3. Use care to avoid getting fluids or particles anywhere within the pneumatic lines connected to the
G5.
3.5 Antennas
Refer to Section 4 for antenna installation information.
190-02072-01
Rev. 5
G5 Installation Manual
Page 3-4
3.6 Mounting Instructions
Refer to Section 3.7 for outline and installation drawings.
NOTE
In addition to the mounting requirements listed in Section 3.4.1, it is critical that the G5 be
installed with its display bezel perpendicular to the aircraft's longitudinal axis (display
bezel parallel to the wing spar) and as close to level in the roll axis as possible. Small roll
offsets, and pitch offsets up to 30 , can be corrected for during calibration.
3.6.1
Panel Cutout Template
The G5 Mounting Ring (115-02251-03) or Figure 3-9 can be used as a template when marking the panel
for cutout. See Figure 3-8 for complete cutout dimensions (the dimensions on Figure 3-8 are to verify the
accuracy of the printout only).
3.6.2
Mounting Ring Installation
Secure the mounting ring to the aircraft panel using the supplied #6-32 pan head Phillips mounting screws.
Evenly torque the mounting screws to 10-12 in-lb.
MOUNTING SCREW,
#6-32 PHP x 0.50[12.7]
211-60207-12
3 PLACES
G5 MOUNTING RING
115-02251-03
AIRCRAFT PANEL
Figure 3-2 G5 Mounting Ring
190-02072-01
Rev. 5
G5 Installation Manual
Page 3-5
3.6.3
Unit Installation
The G5 is installed by inserting the alignment pin located at the top of the unit into the mating hole in the
mounting ring, pushing the unit flush with the instrument panel, and fastening the captive 3/32” hex socket
head screw to the mounting ring as shown in Figure 3-3. To fasten the captive screw to the mounting ring,
insert a 3/32” hex drive tool through the access hole in the front cover of the G5 as shown in Figure 3-4.
Torque the captive mounting screw to 10-12 in-lb.
ALIGNMENT PIN
CAPTIVE 3/32 HEX
SOCKET HEAD SCREW
Figure 3-3 G5 Alignment Pin
190-02072-01
Rev. 5
G5 Installation Manual
Page 3-6
3/32 HEX DRIVER
Figure 3-4 G5 Hex Driver Insertion
190-02072-01
Rev. 5
G5 Installation Manual
Page 3-7
3.6.4
Captive Mounting Screw Replacement
The captive 3/32” hex socket head screw can be used for panel thicknesses up to 0.150 inch. For
installations with a panel thickness greater than 0.150 inch, the captive mounting screw can be replaced
with a standard #6-32 hex socket head screw. To replace the screw, remove the two #4-40 flat head
Phillips mount plate screws, the G5 screw mount plate, and the captive screw as shown in Figure 3-5.
Reverse this process to install the longer #6-32 hex socket head screw. Ensure correct orientation of the
screw mount plate before applying 6-8 in-lb of torque to the #4-40 mount plate screws.
NOTE
Standard #6-32 hex socket head screws use a 7/64” hex drive feature. The access hole in the
G5 bezel is large enough to accommodate this increase in hex tool size.
CAPTIVE 3/32 HEX
SOCKET HEAD SCREW
MOUNTING SCREW,
#4-40 FLHP x 0.25[6.4]
2 PLACES
G5 SCREW
MOUNT PLATE
Figure 3-5 G5 Mounting Screw Replacement
190-02072-01
Rev. 5
G5 Installation Manual
Page 3-8
3.03 76.9
BATTERY PACK
2.61 66.2
D-SUB
1.32 33.6
UNIT BODY
0
.67 17.1
1.30 32.9
3.7 Outline and Installation Drawings
.5 13 WITH BATTERY
0 WITHOUT BATTERY
CENTER OF GRAVITY
3.42 86.9
1.71 43.4
1.6 41
CENTER OF
GRAVITY
PITOT
R1.52 38.6
TYP.
P51
1.71 43.4
.34 8.7
STATIC
1.80 45.7
1.8 46
CENTER OF GRAVITY
3.60 91.4
GPS
NOTES:
1-1. DIMENSIONS: INCHES[mm]. METRIC VALUES ARE FOR REFERENCE ONLY.
1-2. DIMENSIONS ARE NOMINAL AND TOLERANCES
Figure 3-6 G5 Outline Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page 3-9
G5 INSTALLATION KIT
011-03892-00
CONNECTOR KIT, 9 PIN,
w/CAN TERM
011-03002-00
(OPTIONAL)
CAN TERMINATOR
011-02887-00
SEE NOTE 2-1
9 PIN D-SUB CONNECTOR
330-00625-09
9 PIN BACKSHELL
011-01855-00
MOUNTING SCREW,
#6-32 PHP x 0.50[12.7]
211-60207-12
3 PLACES
G5 MOUNTING RACK
115-02251-03
G5 UNIT
011-03809-00
SEE NOTE 2-2
G5 BATTERY PACK
011-03893-00
AIRCRAFT PANEL
NOTES:
2-1. DEPENDING ON HOW THE SYSTEM IS PHYSICALLY WIRED, THIS TERMINATOR MAY OR MAY NOT BE
NEEDED IN THE INSTALLATION. THE CAN BUS MUST BE TERMINATED AT ONLY THE TWO MOST EXTREME
POINTS ON THE CAN BACKBONE. IF USED WITH THE G3X SYSTEM REFER TO THE G3X INSTALL MANUAL
FOR SPECIFIC GUIDANCE ON CAN BUS WIRING.
2-2. ALL RED PLUGS MUST BE REMOVED AND DISCARDED. THEY ARE NOT TO BE USED FOR CAPPING AND
SEALING UNUSED PORTS.
Figure 3-7 G5 Installation Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page 3-10
1.237±.005 31.4±0.13
.150±.003 3.81±0.08
0
2X 1.237±.005 31.4±0.13
3X
2X 1.237±.005 31.4±0.13
0
1.237±.005 31.4±0.13
Cut out panel
to inside line
3.155 80.14
3.125 79.38
Figure 3-8 G5 Panel Cutout Measurements (Not to Scale)
190-02072-01
Rev. 5
G5 Installation Manual
Page 3-11
Cut out panel
to inside line
IMPORTANT!
Ensure the Page Scaling setting
is set to NONE when printing
this page. Verify dimensions
of printed template are
accurate before cutting panel.
For mounting holes, drill out with
#25 drill bit and use Garmin
mounting rack P/N 115-02251-03.
For panel cutout, drill out with a
3.125" diameter bimetal hole saw.
The outline in this drawing is identical
to the outline of the actual bezel.
Figure 3-9 G5 Panel Cutout Drawing (Template)
190-02072-01
Rev. 5
G5 Installation Manual
Page 3-12
4 GPS ANTENNA INSTALLATION
This section contains general information as well as installation information for GPS antennas. Garmin
recommends the antennas shown in Table 4-2. However, any equivalent antenna that meets the
specifications listed in Table 4-3 will work with the G5.
The G5 can receive GPS position information using the unit's internal antenna or by connecting an external
antenna. It is recommended to verify the ability of the G5 to receive GPS information via the unit's
internal antenna as GPS reception quality is dependent upon the installation (see Section 8.4.13.1 GPS
Reception). The G5 will share GPS information with any connected GDU 37X/4XX.
The G5 can additionally receive GPS position information from a GPS 20A or GDU 37X/4XX. A
minimum of one GPS antenna is required for G5 installations receiving GPS information from another
LRU. Additional GPS antennas may be used for redundancy, but are not required.
A GPS 20A (and connected GPS/WAAS antenna) can be used as the sole GPS source for a G5 system,
however it is recommended to also install a GPS antenna on a G5 or GDU 37X/4XX for redundancy. If
the G5's GPS receiver is not used in a particular installation, it may be disabled in configuration mode (see
Section 8.4.13).
4.1 Non-Garmin Antennas
Table 4-1 lists non-Garmin antennas currently supported by the G5. For non-Garmin antennas, follow the
manufacturer’s installation instructions. It is the installer’s responsibility to ensure that their choice of
antenna meets FAA standards according to the specific installation.
Table 4-1 Supported Non-Garmin Antennas
Model
Comant
2480-201
VHF/GPS*
Mount Style
Screw Mount,
Teardrop Footprint
Conn Type
Antenna
Type
Mfr
Antenna
Part
Number
BNC/TNC*
VHF COM/
GPS
Comant
CI 2480-201
Garmin
Order
Number
N/A
*The GPS antenna connector is TNC type. The VHF COM antenna connector is BNC type.
4.2 Garmin Antennas
NOTE
See the G3X/G3X Touch Installation Manual (190-01115-01) for detailed GPS antenna
installation information. All antenna mounting and unit installation recommendations
applicable to the GDU37X/4XX also apply to the G5.
NOTE
It is the installer’s responsibility to ensure that their choice of antenna meets FAA standards
according to the specific installation.
190-02072-01
Rev. 5
G5 Installation Manual
Page 4-1
Table 4-2 Supported Garmin Antennas
Mounting
Configuration
Model
Part Number
Install Manual
GA 26C (GPS)
011-00149-04
190-00082-00
Flange, Magnetic, or
Suction Cup Mounts
(in-cabin)
GA 35 (GPS/WAAS)
013-00235-0X
190-00848-00
Thru-Mount (tear drop
form factor)
GA 36 (GPS/WAAS)
013-00244-0X
190-00848-00
Thru-Mount (ARINC
743 form factor)
GA 56 (GPS)
011-00134-00
190-00094-00
Stud Mount (tear drop
form factor)
GA 57X (GPS/XM)
011-01032-10
190-00522-02
Thru-Mount (ARINC
743 form factor)
Table 4-3 GPS Antenna Minimum Requirements
Characteristic
Frequency Range
Gain
Noise Figure
Nominal Output Impedance
Specification
1565 to 1585 MHz
16 to 25 dB typical, 40 dB max
Less than 4.00 dB
50 Ω
Supply Voltage
4.5 to 6.5 VDC
Supply Current
up to 60 mA
190-02072-01
Rev. 5
G5 Installation Manual
Page 4-2
5 G5 PINOUT
Use the information in this section (along with other applicable sections in this document) to construct the
wiring required for the G5 installation.
Connector references used throughout this document use the prefixes "J" (Jack) and "P" (Plug). "J" refers
to the the connector on the LRU, and "P" refers to the connector on the wiring harness. "J" and "P"
designate the connector only, regardless of the contact type (pin or socket).
5.1 J51 Connector
1
5
6
9
Figure 5-1 J51 Connector on the G5
Table 5-1 J51 Pin Descriptions
Pin
5.1.1
Pin Name
I/O
1
CAN-H
I/O
2
CAN-L
I/O
3
UNIT ID
In
4
RS-232 RX 1
In
5
RS-232 TX 1
Out
6
SIGNAL GROUND
--
7
AIRCRAFT POWER 1
In
8
AIRCRAFT POWER 2
In
9
POWER GROUND
--
Aircraft Power
The G5 can operate using power from one or both inputs (AIRCRAFT POWER 1 and AIRCRAFT
POWER 2). The pins are internally connected using diodes to prevent current from flowing between the
two power inputs. AIRCRAFT POWER 2 is for connecting to an alternate power source, such as on
aircraft with two electrical buses.
190-02072-01
Rev. 5
G5 Installation Manual
Page 5-1
5.1.2
RS-232
The G5 has one RS-232 channel that may be used to output and/or receive data from another device. Refer
to Section 8.4.13.5 for detailed information.
5.1.3
CAN Bus
The G5 CAN bus conforms to the BOSCH standard for Controller Area Network 2.0-B and ISO 11898.
See Section 2.2.2 for details. The CAN bus connection on the G5 can be used for the following:
•
•
•
•
•
5.1.4
Connection to the G3X system
G5/G5 interconnect (non-G3X system)
G5/GSA 28 interconnect (non-G3X system)
G5/GAD 29 interconnect (non-G3X system)
G5/GMU 11 interconnect (non-G3X system)
Unit ID
The G5 detects its assigned unit type at startup by checking the UNIT ID pin. This pin can be strapped into
the following configurations. A maximum of two G5 units may be used in a single installation.
Table 5-2 Unit ID Configurations
190-02072-01
Rev. 5
Unit ID
Comment
G5 #1
Leave pin 3 unconnected
G5 #2
Ground pin 3 to pin 6 or pin 9
G5 Installation Manual
Page 5-2
6 CONNECTOR INSTALLATION INSTRUCTIONS
6.1 Shield Block Installation Parts
Table 6-1 and Table 6-2 list the parts needed to install a Shield Block. The item numbers in these tables
correspond to the example drawing in Figure 6-1. The parts listed in Table 6-1 are supplied in the G5
installation kit. The parts listed in Table 6-2 are to be provided by the installer as required.
Table 6-1 Garmin Supplied Shield Block Installation Parts for the G5
Item #
Description
GPN or MIL Spec
1
Backshell, Jackscrew, 9 pin
125-00171-00
6
Contact, Sckt, D-Sub, Crimp, Size 20, 20-24 AWG
336-00022-02
12
Clamp, Backshell, Jackscrew, 9 pin
115-01078-00
13
Screw, 4-40, 0.375”
211-60234-10
14
Cover, Backshell, Jackscrew, 9 pin
115-01079-00
15
Screw, 4-40, 0.187”
211-63234-06
Table 6-2 Installer Supplied Shield Block Installation Parts for the G5
Item #
Description
2
Multiple Conductor Shielded Cable
3
Drain Wire Shield Termination (optional)
4
Braid, Flat, 19-20 AWG Equivalent, Tin-plated Copper Strands,
36 AWG, Circular Mil Area 1000-1300
5
Floating Shield Termination (optional)
7
8
9
GPN or MIL Spec
Parts used depend on
method chosen
Ring terminal, #8, insulated, 18-22 AWG
MS25036-149
Ring terminal, #8, insulated, 14-16 AWG
MS25036-153
Ring terminal, #8, insulated, 10-12 AWG
MS25036-156
Screw, 8-32, 0.312", PHP, Stainless
MS51957-42
Screw, 8-32, 0.312", PHP, Cad-plated Steel
MS35206-242
Split Washer, #8, 0.045" Compressed Thickness, Stainless
MS35338-137
Split Washer, #8, 0.045" Compressed Thickness, Cad-plated
Steel
MS35338-42
Flat Washer, Stainless, #8, 0.032" Thick, 0.174" ID, 0.375" OD
NAS1149CN832R
10
Flat washer, Cad-plated Steel, #8, 0.032" Thick, 0.174" ID,
0.375" OD
NAS1149FN832P
11
Silicone Fusion Tape
190-02072-01
Rev. 5
249-00114-00
G5 Installation Manual
Page 6-1
NOTE
In Figure 6-1, “AR” denotes quantity “As Required” for the particular installation.
Figure 6-1 Example Shield Install onto a Jackscrew Backshell
190-02072-01
Rev. 5
G5 Installation Manual
Page 6-2
6.2 Shield Termination Technique – Method A.1 (Standard)
Figure 6-2 Shield Termination Technique Method A.1
Table 6-3 Shielded Cable Preparations for Garmin Connectors
Backshell
Size
Number
of Pins
Std/HD
Float
Min
(inches)
Float
Max
(inches)
Ideal
Float
(inches)
Window
Min
(inches)
Window
Max
(inches)
Ideal
Window
(inches)
1
9/15
1.25
2.25
1.75
2.75
5.25
4.25
2
15/26
1.5
2.5
2.0
3.0
5.5
4.5
3
25/44
1.5
2.5
2.0
3.0
5.5
4.5
4
37/62
1.5
2.5
2.0
3.0
5.5
4.5
5
50/78
1.5
2.5
2.0
3.0
5.5
4.5
1. At one end of a shielded cable (item 2, Figure 6-1) measure a distance between Window Min and
Window Max (Table 6-3) and cut a window (with a max size of 0.35 inch) in the jacket to expose
the shield. Use caution when cutting the jacket to avoid damaging the individual braids of the
shield. When dealing with a densely populated connector with many cables, it may prove beneficial to stagger the windows throughout the Window Min to Window Max range. If staggering is
not needed, the Ideal Window length is recommended. The following tools are recommended to
make the window cut:
• Coaxial Cable Stripper
• Thermal Stripper
• Sharp Razor Blade
2. Connect a flat braid (item 4, Figure 6-2) to the shield exposed through the window of the prepared
cable assembly from the preceding step. The flat braid should exit the front of the termination and
towards the connector. The flat braid should not exit the rear of the termination and loop back
towards the connector. Make the connection between the flat braid and the prepared cable
assembly using an approved shield termination technique.
NOTE
FAA AC 43.13-1B Chapter 11, Section 8 (Wiring Installation Inspection Requirements) may be
a helpful reference for termination techniques.
190-02072-01
Rev. 5
G5 Installation Manual
Page 6-3
Preferred Method:
Slide a solder sleeve (item 3, Figure 6-2) onto the prepared cable assembly and connect the flat
braid to the shield using a heat gun approved for use with solder sleeves. Using a solder sleeve
with a pre-installed flat braid may ease the assembly. The chosen size of solder sleeve must
accommodate both the number of conductors present in the cable and the flat braid.
Solder sleeves with pre-installed flat braid
The preferred solder sleeve is the Raychem S03 Series with a thermochromic temperature
indicator (S03-02-R-9035-100, S03-03-R-9035-100, S03-04-R-9035-100). These solder
sleeves come with a pre-installed braid and effectively take the place of items 3 and 4 in
Figure 6-2. Reference the Raychem installation procedure, RCPS 100-70, for detailed
instructions. Raychem recommends the following heating tools:
•
•
•
•
•
HL1802E
AA-400 Super Heater
CV-1981
MiniRay
IR-1759
Individual solder sleeves and flat braid
Solder Sleeves:
Reference the following MIL-SPECs for solder sleeves:
•
•
•
•
•
M83519/1-1
M83519/1-2
M83519/1-3
M83519/1-4
M83519/1-5
Flat Braid:
Flat braids should conform to the ASTMB33 standard for tin-plated copper wire and be made
up of 36 AWG strands to form an approximately 19-20 AWG equivalent flat braid. A circular
mil area range of 1000 to 1300 is required. The number of individual strands in each braid
bundle is not specified. Reference MIL-SPEC flat braid QQB575F36T062.
NOTE
Flat braid, as opposed to insulated wire, is specified in order to allow for a visual inspection of
the conductor as required for continued airworthiness.
Secondary Method:
Solder a flat braid to the shield exposed through the window of the prepared cable assembly.
Ensure a solid electrical connection through the use of acceptable soldering practices. Use care to
avoid applying excessive heat that burns through the insulation of the center conductor(s) and
shorts the shield to the signal wire(s). Slide a minimum of 0.75 inch of Teflon heat shrink tubing
(item 3, Figure 6-2) onto the prepared wire assembly and shrink using a heat gun. The chosen size
of heat shrink tubing must accommodate both the number of conductors present in the cable and
the flat braid.
190-02072-01
Rev. 5
G5 Installation Manual
Page 6-4
Teflon heat shrink tubing
Reference MIL-SPEC Teflon heat shrink tubing M23053/5-X-Y.
3. At the same end of the shielded cable and ahead of the previous shield termination, strip back the
jacket and shield from the end of the shielded cable to a distance between Float Min and Float Max
(Table 6-3) to expose the insulated center conductor(s). If possible, the Ideal Float length is
recommended.
Preferred Method:
Cut the jacket and the shield off at the same point so that no shield is exposed. Slide a minimum of
0.75 inch of Teflon heat shrink tubing (item 5, Figure 6-2) onto the cable and use a heat gun to
shrink the tubing. The chosen size of heat shrink tubing must accommodate the number of
conductors present in the cable.
Secondary Method:
Leave a maximum 0.35 inch of shield extending past the jacket. Fold this section of shield back
over the jacket. Slide a solder sleeve (item 5, Figure 6-2) over the end of the cable and use a heat
gun approved for solder sleeves to secure the connection. The chosen size of solder sleeve must
accommodate the number of conductors present in the cable.
4. Strip back approximately 0.17 inch of insulation from each wire of the shielded cable (item 2,
Figure 6-3) and crimp a contact (item 6, Figure 6-3) to each conductor. It is the responsibility of
the installer to determine the proper length of insulation to be removed. The wire must be visible
in the inspection hole after crimping and the insulation must be 1/64 – 1/32 of an inch from the end
of the contact as shown in Figure 6-3.
6
2
Figure 6-3 Insulation/Contact Clearance
190-02072-01
Rev. 5
G5 Installation Manual
Page 6-5
5. Insert the newly crimped pins and wires into the appropriate connector housing location as
specified by the installation wiring diagrams.
6. Cut the flat braid to a length that, with the addition of a ring terminal, will reach one of the tapped
holes of the Jackscrew Backshell (item 1, Figure 6-1). An appropriate amount of excess length
without looping should be given to the flat braid to allow it to freely move with the wire bundle.
NOTE
The window splice should be positioned such that the flat braid is no longer than 4 inches.
7. Guidelines for terminating the flat braid with an insulated ring terminal:
• Each tapped hole on the Jackscrew Backshell may accommodate a maximum of two
ring terminals.
• Each ring terminal may accommodate a maximum of three flat braids. However, it is
recommended to terminate a maximum of two flat braids per ring terminal.
• A #8, insulated, 18-22 AWG ring terminal is recommended for terminating a single
flat braid (reference MIL-SPEC MS25036-149).
• A #8, insulated, 14-16 AWG ring terminal is recommended for terminating two flat
braids (reference MIL-SPEC MS25036-153).
• A #8, insulated, 10-12 AWG ring terminal is recommended for terminating three flat
braids (reference MIL-SPEC MS25036-156).
8. Repeat the preceding steps as necessary for the remaining shielded cables.
9. Terminate the ring terminal to the Jackscrew Backshell by placing the following items on the
screw (item 8, Figure 6-1) in order: split washer (item 9, Figure 6-1), flat washer (item 10,
Figure 6-1), ring terminal (item 7, Figure 6-1). This assembly can then be screwed into the tapped
holes on the Jackscrew Backshell.
10. It is recommended to wrap the cable bundle with silicone fusion tape (item 11, Figure 6-1) at the
point where the backshell clamp (item 12, Figure 6-1) and backshell housing will contact the cable
bundle.
NOTE
Use of silicone fusion tape is at the discretion of the installer.
11. Place the smooth side of the backshell clamp across the cable bundle and secure using the provided
screws (item 13, Figure 6-1).
WARNING
Placing the grooved side of the backshell clamp across the cable bundle may cause damage
to the wires.
12. Attach the backshell cover (item 14, Figure 6-1) to the backshell using the provided screws
(item 15, Figure 6-1).
190-02072-01
Rev. 5
G5 Installation Manual
Page 6-6
6.3 Shield Termination Technique – Method A.2 (Daisy Chain)
In rare situations where more flat braids need to be terminated for a connector than three per ring terminal
it is allowable to daisy chain a maximum of two shields together before terminating to the ring terminal
(Figure 6-4). All other restrictions and instructions for the shield termination set forth in Method A.1 are
still applicable.
NOTE
The maximum length of the combined braids should be 4 inches.
Figure 6-4 Shield Termination Technique Method A.2
190-02072-01
Rev. 5
G5 Installation Manual
Page 6-7
6.4 Shield Termination Technique – Method B.1 (Quick Term)
If desired, the drain wire termination (item 3, Figure 6-1) and the floating shield termination (item 5,
Figure 6-1) can be effectively combined into a “Quick Term”. This method eliminates the float in the
cable insulation and moves the placement of the window described in Method A.1. This technique is
depicted in Figure 6-5.
NOTE
The original purpose for separating the shield drain termination from the float termination in
Method A.1 was to allow for a variety of lengths for the drain wires such that the shield drain
terminations would not all bunch up in the harness and to eliminate loops in the drain wires.
If Method B.1 is used, care must be taken to ensure that all drain shield terminations can still
be inspected. Garmin recommends using Method A.1 on connectors which require a large
number of shield drain terminations, as this will allow these terminations to be dispersed
across a larger area.
Figure 6-5 Shield Termination Technique Method B.1
1. At one end of a shielded cable (item 2, Figure 6-1) measure a distance between Window Min and
Window Max (Table 6-4) and cut a window (with a max size of 0.35 inch) in the jacket to expose
the shield. Use caution when cutting the jacket to avoid damaging the individual braids of the
shield. When dealing with a densely populated connector with many cables, it may prove beneficial to stagger the windows throughout the Window Min to Window Max range. If staggering is
not needed, the Ideal Window length is recommended. The following tools are recommended to
make the window cut:
• Coaxial Cable Stripper
• Thermal Stripper
• Sharp Razor Blade
190-02072-01
Rev. 5
G5 Installation Manual
Page 6-8
Table 6-4 Shielded Cable Preparations – (Quick Term)
Backshell Size
Number of Pins
Std/HD
Quick Term Min
(inches)
Quick Term Max
(inches)
Quick Term Float
(inches)
1
9/15
1.25
2.25
1.75
2
15/26
1.5
2.5
2.0
3
25/44
1.5
2.5
2.0
4
37/62
1.5
2.5
2.0
5
50/78
1.5
2.5
2.0
2. Strip back the jacket from the end of the shielded cable to a distance between Quick Term Min and
Quick Term Max (Table 6-3) to expose the shield. Next trim the shield so that a maximum of 0.35
inch of shield extends beyond the jacket. Fold this section of shield back over the jacket.
3. Connect a flat braid (item 4, Figure 6-5) to the folded back shield of the prepared cable assembly.
The flat braid should exit the front of the termination and towards the connector. The flat braid
should not exit the rear of the termination and loop back towards the connector. Make the
connection between the flat braid and the prepared cable assembly using an approved shield
termination technique.
NOTE
FAA AC 43.13-1B Chapter 11, Section 8 (Wiring Installation Inspection Requirements) may be
a helpful reference for termination techniques.
Preferred Method:
Slide a solder sleeve (item 3, Figure 6-5) onto the prepared cable assembly and connect the flat
braid to the shield using a heat gun approved for use with solder sleeves. Using a solder sleeve
with a pre-installed flat braid may ease the assembly. The chosen size of solder sleeve must
accommodate both the number of conductors present in the cable and the flat braid.
Secondary Method:
Solder a flat braid to the folded back shield of the prepared cable assembly. Ensure a solid
electrical connection through the use of acceptable soldering practices. Use care to avoid applying
excessive heat that burns through the insulation of the center conductor(s) and shorts the shield to
the signal wire(s). Slide a minimum of 0.75 inch of Teflon heat shrink tubing (item 3, Figure 6-5)
onto the prepared wire assembly and shrink using a heat gun. The chosen size of heat shrink
tubing must accommodate both the number of conductors present in the cable and the flat braid.
Teflon heat shrink tubing
Reference MIL-SPEC Teflon heat shrink tubing M23053/5-X-Y.
4. Insert the newly crimped pins and wires into the appropriate connector housing location as
specified by the installation wiring diagrams.
190-02072-01
Rev. 5
G5 Installation Manual
Page 6-9
5. Cut the flat braid to a length that, with the addition of a ring terminal, will reach one of the tapped
holes of the Jackscrew Backshell (item 1, Figure 6-1). An appropriate amount of excess length
without looping should be given to the flat braid to allow it to freely move with the wire bundle.
NOTE
The window splice should be positioned such that the flat braid is no longer than 4 inches.
6. Guidelines for terminating the flat braid with an insulated ring terminal:
• Each tapped hole on the Jackscrew Backshell may accommodate a maximum of two
ring terminals.
• Each ring terminal may accommodate a maximum of three flat braids. However, it is
recommended to terminate a maximum of two flat braids per ring terminal.
• A #8, insulated, 18-22 AWG ring terminal is recommended for terminating a single
flat braid (reference MIL-SPEC MS25036-149).
• A #8, insulated, 14-16 AWG ring terminal is recommended for terminating two flat
braids (reference MIL-SPEC MS25036-153).
• A #8, insulated, 10-12 AWG ring terminal is recommended for terminating three flat
braids (reference MIL-SPEC MS25036-156).
7. Repeat the preceding steps as necessary for the remaining shielded cables.
8. Terminate the ring terminal to the Jackscrew Backshell by placing the following items on the
screw (item 8, Figure 6-1) in order: split washer (item 9, Figure 6-1), flat washer (item 10,
Figure 6-1), ring terminal (item 7, Figure 6-1). This assembly can then be screwed into the tapped
holes on the Jackscrew Backshell.
9. It is recommended to wrap the cable bundle with silicone fusion tape (item 11, Figure 6-1) at the
point where the backshell clamp (item 12, Figure 6-1) and backshell housing will contact the cable
bundle.
NOTE
Use of silicone fusion tape is at the discretion of the installer.
10. Place the smooth side of the backshell clamp across the cable bundle and secure using the provided
screws (item 13, Figure 6-1).
WARNING
Warning: Placing the grooved side of the backshell clamp across the cable bundle may
cause damage to the wires.
11. Attach the backshell cover (item 14, Figure 6-1) to the backshell using the provided screws
(item 15, Figure 6-1).
190-02072-01
Rev. 5
G5 Installation Manual
Page 6-10
6.5 Shield Termination Technique – Method B.2 (Daisy Chain-Quick Term)
In rare situations where more flat braids need to be terminated for a connector than three per ring terminal
it is allowable to daisy chain a maximum of two shields together before terminating to the ring terminal
(Figure 6-6). All other restrictions and instructions for the shield termination set forth in Method B.1 are
still applicable.
NOTE
The maximum length of the combined braids should be 4 inches.
Figure 6-6 Shield Termination Technique Method B.2
190-02072-01
Rev. 5
G5 Installation Manual
Page 6-11
6.6 Daisy Chain between Methods A.1 and B.1
In rare situations where more flat braids need to be terminated for a connector than three per ring terminal
and a mixture of Methods A.1 and B.1 have been used, it is allowable to daisy chain a maximum of two
shields together between a Method A.1 and B.1 termination before terminating to the ring terminal
(Figure 6-7). All other restrictions and instructions for the shield termination set forth in Method A.1 and
B.1 are still applicable.
NOTE
The maximum length of the combined braids should be 4 inches.
Figure 6-7 Shield Termination Technique Methods A.1 and B.1
190-02072-01
Rev. 5
G5 Installation Manual
Page 6-12
6.7 Unit ID (Strapping)
The Unit ID Program Pin on the G5 provides a ground reference used by the hardware as a means of
configuring the unit for system identification. When installing two G5 units, the second unit must have its
UNIT ID pin (J51 pin 3) connected to ground. For the first G5, this pin should be left unconnected. The
following instructions illustrate how this ground strapping should be accomplished with the Jackscrew
Backshell.
1. Cut a 4-inch length of 22 AWG insulated wire.
WARNING
Flat braid is not permitted for this purpose. Use only insulated wire to avoid inadvertent
ground issues that can occur when using exposed conductors.
2. Strip back approximately 0.17 inch of insulation and crimp a contact to the 4-inch length of wire.
It is the responsibility of the installer to determine the proper length of insulation to be removed.
The wire must be visible in the inspection hole after crimping and the insulation must be 1/64 –
1/32 of an inch from the end of the contact as shown in Figure 6-3.
3. Insert the crimped pin and wire into the appropriate connector housing location as specified by the
installation wiring diagrams.
4. At the opposite end of the wire, strip back 0.2 inch of insulation.
5. Terminate this end of the wire in conjunction with the flat braids of the shield terminations. If this
ground strap is the only termination, use a #8, insulated, 18-22 AWG ring terminal for the
termination (reference MIL-SPEC MS25036-149).
190-02072-01
Rev. 5
G5 Installation Manual
Page 6-13
6.8 Splicing Signal Wires
Figure 6-8 shows an example two wire splice. Note that the splice must be made within 3 inches of the
Shield Block. A signal wire should be spliced into a maximum of three wires. This wire splicing
technique can be used with all the shield termination methods outlined in the previous sections. The
following wire splice parts are recommended:
•
•
Raychem D-436-36/37/38
MIL-SPEC MIL-S-81824/1
WARNING
eep the splice out of the backshell for pin extraction, and outside of the strain relief to
avoid preloading.
Figure 6-8 D-Sub Spliced Signal Wire Example
190-02072-01
Rev. 5
G5 Installation Manual
Page 6-14
7 INTERCONNECT DRAWINGS
NOTES:
1. UNLESS OTHERWISE NOTED, ALL STRANDED WIRE MUST CONFORM TO MIL-W-22759/16 OR EQUIVALENT.
2. UNLESS OTHERWISE NOTED, ALL SHIELDED WIRE MUST CONFORM TO MIL-C-27500 OR EQUIVALENT.
3. UNLESS OTHERWISE NOTED, ALL WIRES ARE 22 GAUGE MINIMUM.
4. SYMBOL DESIGNATIONS
TWISTED SHIELDED 3 CONDUCTOR
SHIELD TERMINATED TO GROUND
S
TWISTED SHIELDED PAIR
SHIELD TERMINATED TO GROUND
GARMIN SHIELD BLOCK GROUND
AIRCRAFT GROUND
COAXIAL CABLE
WIRE SPLICE CONNECTION
5. UNLESS OTHERWISE NOTED, ALL SHIELD GROUNDS MUST BE MADE TO THE RESPECTIVE UNIT BACKSHELLS.
ALL OTHER GROUNDS SHOULD BE TERMINATED TO AIRCRAFT GROUND AS CLOSE TO THE RESPECTIVE UNIT
AS POSSIBLE.
6. REFER TO THE G3X INSTALLATION MANUAL (190-01115-01) FOR INSTALLATION AND WIRING GUIDANCE
FOR ALL DEVICES EXCEPT THE G5 AND THE GNC/GNS/GTN UNITS.
7. A GAD 29 A429 INTERFACE CONNECTED TO THE CAN BUS IS REQUIRED WHEN A GNS 4XX(W)/5XX(W)
(INCLUDING GNS 480) OR A GTN 6XX/7XX NAVIGATOR IS USED.
Figure 7-1 G5 Interconnect Notes
190-02072-01
Rev. 5
G5 Installation Manual
Page 7-1
G5 FLIGHT INSTRUMENT
CAN-H
CAN-L
NOTE 1
P51
1
2
S
UNIT ID
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
GND TO IDENTIFY SECOND G5 UNIT
WHEN 2 ARE INSTALLED
3
5
4
6
REFER TO SERIAL PORT
CONFIGURATION OPTIONS
S
S
G5
POWER 1
POWER 2
POWER GROUND
7
8
9
#22
5
14/28 Vdc
OPTIONAL
GPS ANTENNA
PITOT
PNEUMATIC
CONNECTIONS
STATIC
NOTES:
1. CAN BUS IS USED WHEN INSTALLED IN A G3X SYSTEM OR WHEN
INSTALLED WITH GSA 28 SERVOS AND/OR GAD 29 A429 INTERFACE
CONFIGURATION GUIDANCE
1. G3X
A. NO CONFIGURATION REQUIRED
2. G5 (WHEN NOT USED WITH THE G3X SYSTEM)
A. ON THE G5 CONFIG MODE DEVICE INFORMATION
CONFIGURATION PAGE:
SET THE INSTALLATION TYPE TO "STANDALONE
INSTRUMENT"
Figure 7-2 G5 Standalone Interconnect Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page 7-2
G5 FLIGHT INSTRUMENT
P51
P3251
RS-232 RX 1
RS-232 TX 1
SIGNAL GROUND
4
5
6
ALTITUDE ENCODER
ALT FMT 3 25FT
S
31
52
S
OR
P3271
RS-232 RX 1
RS-232 TX 1
SIGNAL GROUND
4
5
6
ALTITUDE ENCODER
S
ICARUS ALT
19
25
S
GTX 345
ALTITUDE ENCODER
EXAMPLE
RS-232 RX 1
SIGNAL GROUND
ANY AVAILABLE RS-232
GTX 327
ALTITUDE ENCODER
EXAMPLE
RS-232 RX 1
SIGNAL GROUND
ANY AVAILABLE RS-232
Figure 7-3 G5 Used as an Altitude Encoder Interconnect Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page 7-3
GSA28 ROLL SERVO
RS-232 TX 1
RS-232 RX 1
P281
J30X1
7
8
2
1
S
CAN-H
CAN-L
CAN-TERMINATE
CAN-TERMINATE
G5 FLIGHT INSTRUMENT
CAN-H
CAN-L
GMC 305/307
AUTOPILOT CONTROL
PANEL
RS-232 RX 1
RS-232 TX 1
S
1
2
S
3
4
P51
1
2
S
GAD 29 A429 INTERFACE
(OPTIONAL)
CAN-H
CAN-L
P291
1
2
S
GSA28 PITCH SERVO
(OPTIONAL)
CAN-H
CAN-L
P281
1
2
CAN-TERMINATE
CAN-TERMINATE
3
4
PITCH STRAP
PITCH STRAP
5
8
GSA28 YAW SERVO
(OPTIONAL)
NC
NC
S
P281
CAN-H
CAN-L
1
2
S
CAN-TERMINATE
CAN-TERMINATE
3
4
YAW STRAP
YAW STRAP
6
7
NOTE: TERMINATION REQUIRED AT EACH
END OF THE CAN BUS
Figure 7-4 G5 CAN Bus Interconnect Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page 7-4
G5 FLIGHT INSTRUMENT
P51
GNC 255
NAV/COM
P2001
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
5
4
6
GARMIN VHF NAV RADIO
GARMIN VHF NAV RADIO
NOTE 1
NMEA
GARMIN VHF NAV RADIO
GARMIN VHF NAV RADIO
NOTE 2
NMEA
16
1
31
RS-232 IN
RS-232 OUT
SIGNAL GROUND
S
OR
SL 30
NAV/COM
37 PIN
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
5
4
6
4
5
3
RS-232 IN
RS-232 OUT
SIGNAL GROUND
S
OR
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
GNS 4XX(W)/5XX(W)
GPS/NAV/COM
P4001/5001
5
4
6
MAPMX
NOTE 3
MAPMX
56
S
RS-232 OUT 1
SIGNAL GROUND
ANY AVAILABLE RS-232
OR
GTN 6XX/7XX
GPS/NAV/COM
P1001
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
5
4
6
MAPMX
MAPMX FORMAT 2 OR MAPMX
6
44
S
S
RS-232 OUT 3
RS-232 GND 3/4
ANY AVAILABLE RS-232
OR
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
AERA 660/795/796
PORTABLE GPS
5
4
6
NMEA
S
NMEA
BLU
BLK
AERA 660 BARE WIRE CABLE (010-12373-01)
AERA 79X BARE WIRE CABLE (010-11756-01)
RS-232 TX 1
POWER GROUND
OR
ORN
BLK
RS-232 TX 2
POWER GROUND
NOTES
1. G5 TX CONFIGURED FOR NMEA (GNC255) WHEN MECHANICAL CDI IS IN USE
2. G5 TX NOT USED FOR SL30 WHEN MECHANICAL CDI IS IN USE
3. USE "MAPMX" FOR GNS WAAS UNITS AND "AVIATION" FOR NON-WAAS UNITS ON
BOTH GNS AND G5
CONFIGURATION GUIDANCE
SL30 OR GNC255 WITHOUT MECHANICAL CDI INSTRUMENT
(RS-232 CONNECTION TO G5 IS BI-DIRECTIONAL. OBS COURSE SELECTION IS MADE ON
THE G5)
A. G5 CONFIGURATION
SET RS-232 INPUT AND OUTPUT FORMAT TO "GARMIN VHF NAV RADIO"
B. NAV RADIO CONFIGURATION
SET GNC255 RS-232 FORMAT TO "NMEA" (NO SETTING FOR SL 30)
SET SL30/GNC255 INDICATOR TYPE TO "SERIAL"
SL30 OR GNC255 WITH MECHANICAL CDI INSTRUMENT
(OBS COURSE SELECTION IS MADE USING OBS KNOB ON MECHANICAL CDI)
A. G5 CONFIGURATION
SET RS-232 INPUT FORMAT TO "GARMIN VHF NAV RADIO"
SET RS-232 OUTPUT FORMAT TO "NMEA" (OPTIONAL FOR GNC255, NO SETTING
FOR SL30)
B. NAV RADIO CONFIGURATION
SET GNC 255 RS-232 FORMAT TO "NMEA" (NO SETTING FOR SL30)
SET SL30/GNC255 INDICATOR TYPE TO "RESOLVER"
Figure 7-5 G5 to Serial Navigator Interconnect Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page 7-5
G5 FLIGHT INSTRUMENT
HSI
P51
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
SL30 GNC255
37 PIN P2001
GARMIN VHF NAV RADIO
GARMIN VHF NAV RADIO
5
4
6
NMEA
16
1
31
4
5
3
SL 30/GNC 255
NAV/COM
RS-232 IN
RS-232 OUT
SIGNAL GROUND
S
G5 FLIGHT INSTRUMENT
PFD
P51
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
NONE OR OTHER FUNCTION
GARMIN VHF NAV RADIO
5
4
6
S
CONFIGURATION GUIDANCE
A. G5 CONFIGURATION
HSI: SET RS-232 INPUT AND OUTPUT FORMAT TO "GARMIN VHF NAV RADIO"
PFD: SET RS-232 INPUT FORMAT TO "GARMIN VHF NAV RADIO"
B. NAV RADIO CONFIGURATION
SET GNC255 RS-232 FORMAT TO "NMEA" (NO SETTING FOR SL 30)
SET SL30/GNC255 INDICATOR TYPE TO "SERIAL"
Figure 7-6 Dual G5 to GNC 255/SL30 Interconnect Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page 7-6
G5 FLIGHT INSTRUMENT
CAN-L
CAN-H
NOTE: INSTALL 011-02887-00 CAN TERMINATION
WHEN G5 INSTALLED AT END OF CAN BUS
P51
2
1
CAN BUS
S
UNIT ID
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
NOTE: GND TO IDENTIFY SECOND G5 UNIT
WHEN 2 ARE INSTALLED
3
5
4
6
NOTE: REFER TO SERIAL PORT
CONFIGURATION OPTIONS
S
S
NOTE: FOR A DUAL G5 INSTALLATION, WIRE THE SECOND G5 THE SAME AS
SHOWN FOR THE FIRST G5 AND GROUND PIN 3 TO IDENTIFY THE
SECOND UNIT AS #2.
G5
POWER 1
POWER 2
POWER GROUND
7
8
9
#22
14/28 Vdc
OPTIONAL
5
NAVIGATION DATA PROVIDED TO THE FIRST G5 SHOULD ALSO BE
PROVIDED TO THE SECOND G5.
GPS ANTENNA
PITOT
PNEUMATIC
CONNECTIONS
GSA28 ROLL SERVO
CAN-H
CAN-L
CAN-TERMINATE
CAN-TERMINATE
STATIC
CAN BUS
P281
1
2
S
3
4
NOTE: JUMPER ONLY REQUIRED WHEN LOCATED
AT END OF CAN BUS
CWS/DISCONNECT
15
TO CWS/DISC BUTTON
TRIM IN 1
TRIM IN 2
11
12
TO ROLL TRIM SWITCH
TO ROLL TRIM SWITCH
TRIM OUT 1
TRIM OUT 2
13
14
TO ROLL TRIM MOTOR
TO ROLL TRIM MOTOR
S
RS-232 TX 1
RS-232 RX 1
S
S
AUTOPILOT
SERVO POWER
SERVO POWER GND
GSA28 PITCH SERVO
SERVO POWER
SERVO POWER GND
CAN-H
CAN-L
10
9
14/28 Vdc
5
P281
10
9
#22
3
4
5
8
TO PITCH TRIM SWITCH
TO PITCH TRIM SWITCH
TO PITCH TRIM MOTOR
TO PITCH TRIM MOTOR
S
CAN BUS
1
2
S
NOTE: JUMPER ONLY REQUIRED WHEN LOCATED
AT END OF CAN BUS
6
7
15
TO CWS/DISC BUTTON
(OPTIONAL FOR YAW SERVO)
TRIM IN 1
TRIM IN 2
11
12
TO YAW TRIM SWITCH
TO YAW TRIM SWITCH
TRIM OUT 1
TRIM OUT 2
13
14
TO YAW TRIM MOTOR
TO YAW TRIM MOTOR
S
WIRE WHEN USING AUTO-TRIM
YAW SERVO
P111
CAN-H
CAN-L
1
2
UNIT ID
SIGNAL GROUND
3
6
POWER 1
POWER 2
POWER GROUND
7
8
9
7
5
9
15
AIRCRAFT POWER 1
POWER GROUND
AIRCRAFT POWER 2
POWER GROUND
CONNECT TO ALL SERVOS
(OPTIONAL FOR YAW SERVO)
CONFIGURATION GUIDANCE
1.
3
4
CWS/DISCONNECT
GMU11 MAGNETOMETER
LIGHTING BUS HI
LIGHTING BUS LO
WIRE WHEN USING AUTO-TRIM
P281
10
9
SEE PIN 6 NOTE
11
12
CWS/DISC BUTTON
N.O. PUSH TO GROUND
TO CWS/DISC BUTTON
15
13
14
SERVO POWER
SERVO POWER GND
RS-232 RX 2
RS-232 TX 2
6
S
11
12
YAW STRAP
YAW STRAP
4
3
NOTE: JUMPER ONLY REQUIRED WHEN LOCATED
AT END OF CAN BUS
TRIM IN 1
TRIM IN 2
CAN-TERMINATE
CAN-TERMINATE
RS-232 RX 1
RS-232 TX 1
PIN 6 NOTE: INSTALL AN EMPTY PIN 6 IN THE CABLE
CONNECTOR TO KEY THIS CONNECTOR AND PREVENT
IT FROM BEING INSTALLED UPSIDE DOWN
TRIM OUT 1
TRIM OUT 2
CAN-H
CAN-L
22
22
22
22
2
1
CAN BUS
1
2
PITCH STRAP
PITCH STRAP
GSA28 YAW SERVO
#
#
#
#
BACKUP PWR
CAN-TERMINATE
CAN-TERMINATE
CWS/DISCONNECT
#22
GMC305/307
J30X1
WIRE WHEN USING AUTO-TRIM
7
8
#22
3
14/28 Vdc
G5
A. ON THE G5 CONFIG MODE RS-232 CONFIGURATION PAGE:
SET THE INPUT AND OUTPUT FORMATS DEPENDING
ON DEVICE(S) CONNECTED TO RS-232 PORT
B. ON THE G5 CONFIG MODE FLIGHT CONTROLS CONFIGURATION
PAGE:
SET THE AUTOPILOT SERVO(S) TO ONE OF THE FOLLOWING:
- "ROLL ONLY"
- "PITCH + ROLL"
SET THE YAW DAMPER TO ONE OF THE FOLLOWING:
- "DISABLED"
- "ENABLED"
NOTE: INSTALL 011-02887-00 CAN TERMINATION
WHEN GMU11 INSTALLED AT END OF CAN BUS
S
NOTE: INSTALL JUMPER TO IDENTIFY SECOND
GMU11 WHEN 2 ARE INSTALLED
GMU11
#22
2
14/28 Vdc
OPTIONAL
Figure 7-7 G5 Autopilot System with GMC 305/307 Interconnect Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page 7-7
G5 FLIGHT INSTRUMENT
CAN-H
CAN-L
NOTE: INSTALL 011-02887-00 CAN TERMINATION
WHEN G5 INSTALLED AT END OF CAN BUS
P51
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
3
4
CAN-H
CAN-L
INSTALL JUMPER WHEN AT END OF CAN BUS
8
6
CAN BUS TERM 1
CAN BUS TERM 2
N/C
1
2
RESERVED
RESERVED
S
CAN BUS
S
UNIT ID
NOTE: GND TO IDENTIFY SECOND G5 UNIT
WHEN 2 ARE INSTALLED
3
5
4
6
NOTE: REFER TO SERIAL PORT
CONFIGURATION OPTIONS
S
OPTIONAL TO/GA SWITCH (ACTIVE LOW)
10
12
TO/GA IN
AP DISCONNECT OUT
7
9
15
AIRCRAFT POWER 1
AIRCRAFT POWER 2
POWER GROUND
OPTIONAL DC REFERENCE LIGHTING BUS
11
LIGHTING BUS HI
TO AUDIO PANEL ALERT INPUT
13
14
AUDIO OUT HI
AUDIO OUT LO
REQUIRED FOR CERTIFIED INSTALLATIONS ONLY
# 22
# 22
# 22
S
OPTIONAL BACKUP POWER
G5
POWER 1
POWER 2
POWER GROUND
7
8
9
GMC 507
J50X1
1
2
#22
14/28 Vdc
OPTIONAL
5
SONALERT
14/28 Vdc
GPS ANTENNA
5
5
SONALERT ACTIVE LOW
SONALERT ONLY USED WHEN THERE IS NO AUDIO PANEL
PITOT
PNEUMATIC
CONNECTIONS
GSA28 ROLL SERVO
CAN-H
CAN-L
CAN-TERMINATE
CAN-TERMINATE
PIN 6 NOTE: INSTALL AN EMPTY PIN 6 IN THE CABLE CONNECTOR
TO KEY THIS CONNECTOR AND PREVENT IT FROM BEING INSTALLED
UPSIDE DOWN IF PIN 6 IS NOT OTHERWISE USED
STATIC
CAN BUS
P281
NAVIGATION DATA PROVIDED TO THE FIRST G5 SHOULD ALSO BE
PROVIDED TO THE SECOND G5.
S
3
4
NOTE: JUMPER ONLY REQUIRED WHEN LOCATED
AT END OF CAN BUS
CWS/DISCONNECT
15
TO CWS/DISC BUTTON
TRIM IN 1
TRIM IN 2
11
12
TO ROLL TRIM SWITCH
TO ROLL TRIM SWITCH
TRIM OUT 1
TRIM OUT 2
13
14
CWS/DISC BUTTON
N.O. PUSH TO GROUND
CONNECT TO ALL SERVOS
TO ROLL TRIM MOTOR
TO ROLL TRIM MOTOR
S
RS-232 TX 1
RS-232 RX 1
NOTE: FOR A DUAL G5 INSTALLATION, WIRE THE SECOND G5 THE SAME AS
SHOWN FOR THE FIRST G5 AND GROUND PIN 3 TO IDENTIFY THE
SECOND UNIT AS #2.
1
2
(OPTIONAL FOR YAW SERVO)
WIRE WHEN USING AUTO-TRIM
N/C
N/C
7
8
AUTOPILOT
SERVO POWER
SERVO POWER GND
GSA28 PITCH SERVO
SERVO POWER
SERVO POWER GND
CAN-H
CAN-L
10
9
#22
14/28 Vdc
5
P281
10
9
#22
CAN BUS
1
2
CAN-TERMINATE
CAN-TERMINATE
3
4
PITCH STRAP
PITCH STRAP
5
8
S
NOTE: JUMPER ONLY REQUIRED WHEN LOCATED
AT END OF CAN BUS
CWS/DISCONNECT
15
TRIM IN 1
TRIM IN 2
11
12
TO CWS/DISC BUTTON
TO PITCH TRIM SWITCH
TO PITCH TRIM SWITCH
TRIM OUT 1
TRIM OUT 2
13
14
TO PITCH TRIM MOTOR
TO PITCH TRIM MOTOR
S
GSA28 YAW SERVO
WIRE WHEN USING AUTO-TRIM
CAN BUS
P281
CAN-H
CAN-L
1
2
CAN-TERMINATE
CAN-TERMINATE
3
4
YAW STRAP
YAW STRAP
6
7
CWS/DISCONNECT
TO CWS/DISC BUTTON
(OPTIONAL FOR YAW SERVO)
15
TRIM IN 1
TRIM IN 2
11
12
TO YAW TRIM SWITCH
TO YAW TRIM SWITCH
13
14
TO YAW TRIM MOTOR
TO YAW TRIM MOTOR
S
WIRE WHEN USING AUTO-TRIM
YAW SERVO
GMU11 MAGNETOMETER
10
9
P111
CAN-H
CAN-L
1
2
UNIT ID
SIGNAL GROUND
3
6
POWER 1
POWER 2
POWER GROUND
7
8
9
1.
G5
A. ON THE G5 CONFIG MODE RS-232 CONFIGURATION PAGE:
SET THE INPUT AND OUTPUT FORMATS DEPENDING
ON DEVICE(S) CONNECTED TO RS-232 PORT
S
NOTE: JUMPER ONLY REQUIRED WHEN LOCATED
AT END OF CAN BUS
TRIM OUT 1
TRIM OUT 2
SERVO POWER
SERVO POWER GND
CONFIGURATION GUIDANCE
#22
3
B. ON THE G5 CONFIG MODE FLIGHT CONTROLS CONFIGURATION
PAGE:
SET THE AUTOPILOT SERVO(S) TO ONE OF THE FOLLOWING:
- "ROLL ONLY"
- "PITCH + ROLL"
SET THE YAW DAMPER TO ONE OF THE FOLLOWING:
- "DISABLED"
- "ENABLED"
14/28 Vdc
NOTE: INSTALL 011-02887-00 CAN TERMINATION
WHEN GMU11 INSTALLED AT END OF CAN BUS
S
NOTE: INSTALL JUMPER TO IDENTIFY SECOND
GMU11 WHEN 2 ARE INSTALLED
GMU11
#22
2
14/28 Vdc
OPTIONAL
Figure 7-8 G5 Autopilot System with GMC 507 Interconnect Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page 7-8
G5 FLIGHT INSTRUMENT
CAN-L
CAN-H
NOTE: INSTALL 011-02887-00 CAN TERMINATION
WHEN G5 INSTALLED AT END OF CAN BUS
P51
2
1
CAN BUS
S
UNIT ID
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
NOTE: GND TO IDENTIFY SECOND G5 UNIT
WHEN 2 ARE INSTALLED
3
5
4
6
NOTE: REFER TO SERIAL PORT
CONFIGURATION OPTIONS
S
S
G5
POWER 1
POWER 2
POWER GROUND
7
8
9
#22
14/28 Vdc
OPTIONAL
5
GPS ANTENNA
PITOT
PNEUMATIC
CONNECTIONS
GAD 13 OAT PROBE
INTERFACE MODULE
CAN-H
CAN-L
STATIC
CAN BUS
P131
1
2
GTP 59
RTD OAT PROBE
S
GTP 59 POWER OUT
GTP 59 IN HI
GTP 59 IN LO
8
3
6
WHT
BLU
ORN
POWER
SENSE
LOW
S
OR
OAT PROBE OUT
OAT PROBE IN
1uA/°K CURRENT OUTPUT
OAT PROBE
VOLTAGE IN
CURRENT OUT
5
4
EXAMPLE PROBES ARE
EDMO 655 AND
DAVTRON C307PS
S
GAD 13
POWER
POWER GROUND
GMU11 MAGNETOMETER
7
9
P111
CAN-H
CAN-L
1
2
UNIT ID
SIGNAL GROUND
3
6
POWER 1
POWER 2
POWER GROUND
7
8
9
#22
5
14/28 Vdc
GAD 13 MAY OPTIONALLY BE CONNECTED
TO GAD 29 CIRCUIT BREAKER
NOTE: INSTALL 011-02887-00 CAN TERMINATION
WHEN GMU11 INSTALLED AT END OF CAN BUS
S
NOTE: INSTALL JUMPER TO IDENTIFY SECOND
GMU11 WHEN 2 ARE INSTALLED
#22
CONNECT TO G5 CIRCUIT BREAKER
OPTIONAL
CONFIGURATION GUIDANCE
1.
G5
A. ON THE G5 CONFIG MODE MAGNETOMETER PAGE:
SET THE MAGNETOMETER TO "ENABLED" WHEN A
GMU 11 MAGNETOMETER IS INSTALLED
B. ON THE G5 CONFIG MODE AIR DATA PAGE:
SET THE OUTSIDE AIR TEMP SENSOR TO "ENABLED" WHEN
A GAD 13 OAT PROBE MODULE IS INSTALLED
Figure 7-9 G5/GAD 13 to GMU 11 Interconnect Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page 7-9
G5 FLIGHT INSTRUMENT
CAN-H
CAN-L
NOTE: INSTALL 011-02887-00 CAN TERMINATION
WHEN G5 OR GAD 29 ARE INSTALLED
AT END OF CAN BUS
P51
1
2
CAN BUS
S
UNIT ID
NOTE: GND TO IDENTIFY SECOND G5 UNIT
WHEN 2 ARE INSTALLED
3
AERA 660 BARE WIRE CABLE (010-12373-01)
AERA 79X BARE WIRE CABLE (010-02600-10)
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
AERA 660/79X
5
4
6
NMEA OUT, 4800 OR 9600 BAUD
NMEA, 4800 OR 9600 BAUD
S
BLUE
YELLOW
RS-232 TX 1
RS-232 RX 1
ORANGE
PURPLE
RS-232 TX 2
RS-232 RX 2
BROWN
WHITE
GREEN
ALERT AUDIO LEFT
ALERT AUDIO RIGHT
ALERT AUDIO COMMON
S
FOR DUAL G5 INSTALLATIONS
ALSO CONNECT TO 2ND G5
G5
POWER 1
POWER 2
POWER GROUND
7
8
9
#22
14/28 Vdc
OPTIONAL
5
AERA
14/28 VDC
3
GPS ANTENNA
RED
BLACK
POWER
GROUND
PITOT
PNEUMATIC
CONNECTIONS
GAD 29
STATIC
P291
CAN-H
CAN-L
CAN BUS
1
2
S
POWER 1
POWER 2
POWER GROUND
GAD 29
#22
7
8
9
5
14/28 Vdc
OPTIONAL
P292
P2002
VOR/ILS (SDI 2)
ARINC 429 RX 2A (NAV)
ARINC 429 RX 2B (NAV)
VOR/ILS 2, LO SPEED
22
10
24
23
S
#2 GNC 255
NAV/COM
ARINC 429 OUT A
ARINC 429 OUT B
S
CONFIGURATION GUIDANCE
1. AERA 660/795/796
A. ON THE RS-232 INTERFACE SETUP PAGE:
CONFIGURE SERIAL PORT 1 TO "NMEA OUT" AND MAKE SURE
BAUD RATE ON G5 AND PORTABLE AGREE
2. G5
A. ON THE G5 CONFIG MODE ARINC 429 CONFIGURATION PAGE:
B. CONFIGURE ALL ARINC 429 PORTS AS SHOWN ABOVE
C. ON THE G5 CONFIG MODE RS-232 CONFIGURATION PAGE:
SET INPUT FORMAT TO "NMEA" AND SET BAUD RATE TO 4800 OR 9600
TO MATCH PORTABLE CONFIGURATION
3. GNC 255
A. SET ARINC 429 PORT CONFIGURATION TO "VOR/ILS 2" AND "LO SPEED"
B. SET CDI INDICATOR TYPE TO "CONVERTER" ON NAV CONFIGURATION PAGE
NOTE:
THIS INSTALLATION REQUIRES G5 V6.00 OR NEWER.
Figure 7-10 G5/GAD 29 to aera/GNC 255 Dual Nav Interconnect Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page 7-10
G5 FLIGHT INSTRUMENT
CAN-H
CAN-L
NOTE: INSTALL 011-02887-00 CAN TERMINATION
WHEN G5 OR GAD 29 ARE INSTALLED
AT END OF CAN BUS
P51
1
2
CAN BUS
S
UNIT ID
NOTE: GND TO IDENTIFY SECOND G5 UNIT
WHEN 2 ARE INSTALLED
3
AERA 660 BARE WIRE CABLE (010-12373-01)
AERA 79X BARE WIRE CABLE (010-02600-10)
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
AERA 660/79X
5
4
6
NMEA OUT, 4800 OR 9600 BAUD
NMEA, 4800 OR 9600 BAUD
S
BLUE
YELLOW
RS-232 TX 1
RS-232 RX 1
ORANGE
PURPLE
RS-232 TX 2
RS-232 RX 2
BROWN
WHITE
GREEN
ALERT AUDIO LEFT
ALERT AUDIO RIGHT
ALERT AUDIO COMMON
S
FOR DUAL G5 INSTALLATIONS
ALSO CONNECT TO 2ND G5
G5
POWER 1
POWER 2
POWER GROUND
7
8
9
#22
14/28 Vdc
OPTIONAL
5
AERA
14/28 VDC
RED
BLACK
3
GPS ANTENNA
POWER
GROUND
PITOT
PNEUMATIC
CONNECTIONS
GAD 29
STATIC
P291
CAN-H
CAN-L
CAN BUS
1
2
S
POWER 1
POWER 2
POWER GROUND
GAD 29
#22
7
8
9
5
14/28 Vdc
OPTIONAL
P292
P3751
EFIS/AIRDATA 1 (SDI 2)
A429 TX 1A (AIR DATA)
A429 TX 1B (AIR DATA)
#2 GNX 375 GPS
EFIS/AIRDATA, LO SPEED
24
12
48
67
S
ARINC 429 IN 1A
ARINC 429 IN 1B
S
P3752
GPS (SDI 2)
ARINC 429 RX 1A (GPS)
ARINC 429 RX 1B (GPS)
GAMA FORMAT 1, LNAV 2, LO SPEED
10
29
23
11
S
ARINC 429 OUT 1A
ARINC 429 OUT 1B
S
CONFIGURATION GUIDANCE
1. GNX 375
A. ON THE CONFIG MODE ARINC 429 CONFIGURATION PAGE:
SET IN 1 SPEED TO "LOW"
SET IN 1 DATA TO "EFIS/AIRDATA"
SET OUT 1 SPEED TO "LOW"
SET OUT 1 DATA TO "GAMA FORMAT 1"
SET OUT 1 SDI TO "LNAV 2"
2. AERA 660/795/796
B. ON THE RS-232 INTERFACE SETUP PAGE:
CONFIGURE SERIAL PORT 1 TO "NMEA OUT" AND MAKE SURE
BAUD RATE ON G5 AND PORTABLE AGREE
CONFIGURE SERIAL PORT 2 RECEIVE TO "MAPMX"
3. G5
B. ON THE G5 CONFIG MODE ARINC 429 CONFIGURATION PAGE:
SET OUTPUT 1 TO "EFIS/AIRDATA 1 (SDI 1)"
SET INPUT 1 TO "GARMIN GPS (SDI 2)"
SET INPUT 2 TO "GARMIN VOR/ILS (SDI 2)"
B. ON THE G5 CONFIG MODE RS-232 CONFIGURATION PAGE:
SET INPUT FORMAT TO "NMEA" AND MAKE SURE BAUD RATE ON G5 AND PORTABLE
MATCH
Figure 7-11 G5/GAD 29 to aera/GNX 375 Dual Nav Interconnect Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page 7-11
G5 FLIGHT INSTRUMENT
CAN-H
CAN-L
NOTE: INSTALL 011-02887-00 CAN TERMINATION
WHEN G5 OR GAD 29 ARE INSTALLED
AT END OF CAN BUS
P51
1
2
CAN BUS
S
UNIT ID
NOTE: GND TO IDENTIFY SECOND G5 UNIT
WHEN 2 ARE INSTALLED
3
AERA 660 BARE WIRE CABLE (010-12373-01)
AERA 79X BARE WIRE CABLE (010-02600-10)
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
AERA 660/79X
5
4
6
NMEA OUT, 4800 OR 9600 BAUD
NMEA, 4800 OR 9600 BAUD
S
BLUE
YELLOW
RS-232 TX 1
RS-232 RX 1
ORANGE
PURPLE
RS-232 TX 2
RS-232 RX 2
BROWN
WHITE
GREEN
ALERT AUDIO LEFT
ALERT AUDIO RIGHT
ALERT AUDIO COMMON
S
FOR DUAL G5 INSTALLATIONS
ALSO CONNECT TO 2ND G5
G5
POWER 1
POWER 2
POWER GROUND
7
8
9
#22
14/28 Vdc
OPTIONAL
5
AERA
14/28 VDC
RED
BLACK
3
GPS ANTENNA
POWER
GROUND
PITOT
PNEUMATIC
CONNECTIONS
GAD 29
STATIC
P291
CAN-H
CAN-L
CAN BUS
1
2
S
POWER 1
POWER 2
POWER GROUND
GAD 29
#22
7
8
9
5
14/28 Vdc
OPTIONAL
P292
#2 GTN 6XX/7XX
GPS/NAV/COM
P1004
VOR/ILS (SDI 2)
ARINC 429 RX 2A (NAV)
ARINC 429 RX 2B (NAV)
VOR/ILS 2, LO SPEED
24
23
22
10
S
ARINC 429 OUT A
ARINC 429 OUT B
S
P1001
GPS (SDI 2)
ARINC 429 RX 1A (GPS)
ARINC 429 RX 1B (GPS)
GARMIN 429, LNAV 2, LO SPEED
23
11
S
EFIS/AIRDATA 1 (SDI 2)
A429 TX 1A (AIR DATA)
A429 TX 1B (AIR DATA)
10
29
ARINC 429 OUT 1A
ARINC 429 OUT 1B
48
67
ARINC 429 IN 1A
ARINC 429 IN 1B
S
EFIS FORMAT 2, LO SPEED
24
12
S
S
CONFIGURATION GUIDANCE
1. GTN 6XX/7XX
A. ON THE CONFIG MODE ARINC 429 CONFIGURATION PAGE:
SET IN 1 SPEED TO "LOW"
SET IN 1 DATA TO "EFIS FORMAT 2"
SET OUT 1 SPEED TO "LOW"
SET OUT 1 DATA TO "GARMIN 429"
SET OUT 1 SDI TO "LNAV 2"
B. ON THE CONFIG MODE MAIN INDICATOR (ANALOG) CONFIGURATION PAGE:
SET SELECTED COURSE FOR VLOC TO "IGNORED"
C. ON THE CONFIG MODE VOR/LOC/GS CONFIGURATION PAGE:
SET NAV RADIO TO "ENABLED"
SET TX SPEED TO "LOW"
SET SDI TO "VOR/ILS 2"
2. AERA 660/795/796
A. ON THE RS-232 INTERFACE SETUP PAGE:
CONFIGURE SERIAL PORT 1 TO "NMEA OUT" AND MAKE SURE
BAUD RATE ON G5 AND PORTABLE AGREE
3. G5
B. ON THE G5 CONFIG MODE ARINC 429 CONFIGURATION PAGE:
SET OUTPUT 1 TO "EFIS/AIRDATA 1 (SDI 1)"
SET INPUT 1 TO "GARMIN GPS (SDI 2)"
SET INPUT 2 TO "GARMIN VOR/ILS (SDI 2)"
B. ON THE G5 CONFIG MODE RS-232 CONFIGURATION PAGE:
SET INPUT FORMAT TO "NMEA" AND MAKE SURE BAUD RATE ON G5 AND
PORTABLE MATCH
Figure 7-12 G5/GAD 29 to aera/GTN 6XX/7XX Dual Nav Interconnect Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page 7-12
G5 FLIGHT INSTRUMENT
CAN-H
CAN-L
NOTE: INSTALL 011-02887-00 CAN TERMINATION
WHEN G5 OR GAD 29 ARE INSTALLED
AT END OF CAN BUS
P51
1
2
CAN BUS
S
UNIT ID
NOTE: GND TO IDENTIFY SECOND G5 UNIT
WHEN 2 ARE INSTALLED
3
#1 GTN 6XX/7XX
GPS/NAV/COM
P1001
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
5
4
6
MAPMX
MAPMX FORMAT 2 OR MAPMX
6
44
S
S
RS-232 OUT 3
RS-232 GND 3/4
ANY AVAILABLE RS-232
G5
POWER 1
POWER 2
POWER GROUND
7
8
9
#22
14/28 Vdc
OPTIONAL
5
GPS ANTENNA
PITOT
PNEUMATIC
CONNECTIONS
GAD 29
STATIC
P291
CAN-H
CAN-L
CAN BUS
1
2
S
POWER 1
POWER 2
POWER GROUND
GAD 29
#22
7
8
9
5
14/28 Vdc
OPTIONAL
P292
#1 GTN 6XX/7XX
GPS/NAV/COM
P1004
VOR/ILS (SDI 1)
ARINC 429 RX 2A (NAV)
ARINC 429 RX 2B (NAV)
VOR/ILS 1, LO SPEED
22
10
24
23
S
ARINC 429 OUT A
ARINC 429 OUT B
S
P1001
GPS (SDI 1)
ARINC 429 RX 1A (GPS)
ARINC 429 RX 1B (GPS)
23
11
A429 TX 1A (AIR DATA)
A429 TX 1B (AIR DATA)
24
12
GARMIN 429, LNAV 1, LO SPEED
S
10
29
ARINC 429 OUT 1A
ARINC 429 OUT 1B
48
67
ARINC 429 IN 1A
ARINC 429 IN 1B
S
EFIS/AIR DATA 1 (SDI 1)
EFIS FORMAT 2, LO SPEED
S
S
#2 GNC 255
NAV/COM
P2002
VOR/ILS (SDI 2)
ARINC 429 RX 4A (NAV)
ARINC 429 RX 4B (NAV)
VOR/ILS 2, LO SPEED
16
4
24
23
S
ARINC 429 OUT A
ARINC 429 OUT B
S
CONFIGURATION GUIDANCE
1. GTN 6XX/7XX
A. ON THE CONFIG MODE ARINC 429 CONFIGURATION PAGE:
CONFIGURE ALL ARINC 429 PORTS AS SHOWN ABOVE
B. ON THE CONFIG MODE MAIN INDICATOR (ANALOG) CONFIGURATION PAGE:
SET SELECTED COURSE FOR VLOC TO "IGNORED"
C. ON THE CONFIG MODE VOR/LOC/GS CONFIGURATION PAGE:
SET NAV RADIO TO "ENABLED"
SET TX SPEED TO "LOW"
SET SDI TO "VOR/ILS 1"
D. ON THE RS-232 CONFIG PAGE
SET CHNL 3 INPUT TO "MAPMX FORMAT 2" WHEN THIS FORMAT IS AVAILABLE
SET CHNL 3 OUTPUT TO "MAPMX" WHEN "MAPMX FORMAT 2" INPUT NOT AVAILABLE
2. G5
A. ON THE G5 CONFIG MODE ARINC 429 CONFIGURATION PAGE:
CONFIGURE IN/OUT PORTS AS SHOWN ABOVE
B. ON THE G5 CONFIG MODE RS-232 CONFIGURATION PAGE:
SET INPUT FORMAT TO "MAPMX"
3. GNC 255
A. SET ARINC 429 PORT CONFIGURATION TO "VOR/ILS 2" AND "LO SPEED"
B. SET CDI INDICATOR TYPE TO "CONVERTER" ON NAV CONFIGURATION PAGE
Figure 7-13 G5/GAD 29 to GNC 255/GTN 6XX/7XX Dual Nav Interconnect Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page 7-13
G5 FLIGHT INSTRUMENT
CAN-H
CAN-L
NOTE: INSTALL 011-02887-00 CAN TERMINATION
WHEN G5 OR GAD 29 ARE INSTALLED
AT END OF CAN BUS
P51
1
2
CAN BUS
S
UNIT ID
NOTE: GND TO IDENTIFY SECOND G5 UNIT
WHEN 2 ARE INSTALLED
3
P1
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
5
4
6
AVIATION
AVIATION
24
GPS 155XL/GNC 300XL
GPS NAVIGATORS
RS-232 OUT 1
RS-232 GND
S
G5
POWER 1
POWER 2
POWER GROUND
7
8
9
#22
14/28 Vdc
OPTIONAL
5
GPS ANTENNA
PITOT
PNEUMATIC
CONNECTIONS
GAD 29
STATIC
P291
CAN-H
CAN-L
CAN BUS
1
2
S
POWER 1
POWER 2
POWER GROUND
GAD 29
#22
7
8
9
5
14/28 Vdc
OPTIONAL
P292
P1
GPS (SDI 1)
ARINC 429 RX 1A (GPS)
ARINC 429 RX 1B (GPS)
23
11
A429 TX 1A (AIR DATA)
A429 TX 1B (AIR DATA)
24
12
KING EFS 40/50
GPS 155XL/GNC 300XL
GPS NAVIGATORS
16
15
ARINC 429 OUT A
ARINC 429 OUT B
32
33
ARINC 429 IN A
ARINC 429 IN B
S
EFIS/AIR DATA (SDI 1)
COURSE/HEADING
S
CONFIGURATION GUIDANCE
1. GPS 155XL/GNC 300XL
A. ON THE CONFIG MODE ARINC 429 CONFIGURATION PAGE:
SET IN TO "COURSE/HEADING"
SET OUT TO "KING EFS 40/50"
B. ON THE I/0 CHANNEL1 CONFIG PAGE
SET IN TO "OFF"
SET OUT TO "AVIATION"
2. G5
A. ON THE G5 CONFIG MODE ARINC 429 CONFIGURATION PAGE:
SET OUTPUT 1 TO "EFIS/AIRDATA 1 (SDI 1)"
SET INPUT 1 TO "GARMIN GPS (SDI 1)"
B. ON THE G5 CONFIG MODE RS-232 CONFIGURATION PAGE:
SET INPUT FORMAT TO "AVIATION"
Figure 7-14 G5/GAD 29 to GNC 300XL/GPS 155XL Dual Nav Interconnect Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page 7-14
G5 FLIGHT INSTRUMENT
CAN-H
CAN-L
NOTE: INSTALL 011-02887-00 CAN TERMINATION
WHEN G5 OR GAD 29 ARE INSTALLED
AT END OF CAN BUS
P51
1
2
CAN BUS
S
UNIT ID
NOTE: GND TO IDENTIFY SECOND G5 UNIT
WHEN 2 ARE INSTALLED
3
P4001/5001
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
5
4
6
MAPMX
MAPMX
56
S
GNS 4XX(W)/5XX(W)
GPS/NAV/COM
RS-232 OUT 1
SIGNAL GROUND
ANY AVAILABLE RS-232
G5
POWER 1
POWER 2
POWER GROUND
7
8
9
#22
14/28 Vdc
OPTIONAL
5
GPS ANTENNA
PITOT
PNEUMATIC
CONNECTIONS
GAD 29
STATIC
P291
CAN-H
CAN-L
CAN BUS
1
2
S
POWER 1
POWER 2
POWER GROUND
GAD 29
#22
7
8
9
5
14/28 Vdc
OPTIONAL
P292
ARINC 429 RX 2A (NAV)
ARINC 429 RX 2B (NAV)
P4006/5006
ONLY USED FOR 430(W)/530(W)
22
10
24
23
GNS 4XX(W)/5XX(W)
GPS/NAV/COM
ARINC 429 OUT A
ARINC 429 OUT B
S
P4001/5001
ARINC 429 RX 1A (GPS)
ARINC 429 RX 1B (GPS)
23
11
46
47
ARINC 429 OUT A
ARINC 429 OUT B
48
49
ARINC 429 IN 1A
ARINC 429 IN 1B
S
A429 TX 1A (AIR DATA)
A429 TX 1B (AIR DATA)
24
12
S
CONFIGURATION GUIDANCE
1. GNS 4XX(W)/5XX(W)
A. ON THE CONFIG MODE MAIN ARINC 429 CONFIGURATION PAGE:
SET IN 1 SPEED TO "LOW"
SET IN 1 DATA TO "EFIS/AIRDATA"
SET OUT SPEED TO "LOW"
SET OUT DATA TO "GAMA 429"
SET SDI TO "LNAV 1"
B. ON THE CONFIG MODE MAIN CDI/OBS CONFIGURATION PAGE (GNS 430(W)/530(W) ONLY):
PRESS MENU AND THEN SELECT "IGNORE SEL CRS FOR VLOC?"
MENU WILL DISPLAY "ALLOW SEL COURSE FOR VLOC?" WHEN SET CORRECTLY
C. ON THE CONFIG MODE VOR/LOC/GS ARINC 429 CONFIGURATION PAGE (GNS 430(W)/530(W) ONLY):
SET RX AND TX SPEED TO "LOW"
SET SDI TO "VOR/ILS 1"
D. ON THE MAIN RS-232 CONFIG PAGE
SET CHNL 1 INPUT TO "OFF"
SET CHNL 1 OUTPUT TO "MAPMX" (WAAS UNITS) OR "AVIATION" (NON-WAAS UNITS)
2. G5
A. ON THE G5 CONFIG MODE ARINC 429 CONFIGURATION PAGE:
SET OUTPUT 1 TO "EFIS/AIRDATA 1 (SDI 1)"
SET INPUT 1 TO "GARMIN GPS (SDI 1)"
SET INPUT 2 TO "GARMIN VOR/ILS (SDI 1)"
B. ON THE G5 CONFIG MODE RS-232 CONFIGURATION PAGE:
SET INPUT FORMAT TO "MAPMX" (WAAS UNITS) OR "AVIATION" (NON-WAAS UNITS)
Figure 7-15 G5/GAD 29 to GNS 4XX/5XX Interconnect Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page 7-15
G5 FLIGHT INSTRUMENT
CAN-H
CAN-L
NOTE: INSTALL 011-02887-00 CAN TERMINATION
WHEN G5 OR GAD 29 ARE INSTALLED
AT END OF CAN BUS
P51
1
2
CAN BUS
S
UNIT ID
NOTE: GND TO IDENTIFY SECOND G5 UNIT
WHEN 2 ARE INSTALLED
3
P1
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
5
4
6
MAPMX
MAPMX
5
23
S
GNS 480
GPS/NAV/COM
RS-232 OUT 1
SERIAL GROUND 1
ANY AVAILABLE RS-232
G5
POWER 1
POWER 2
POWER GROUND
7
8
9
#22
14/28 Vdc
OPTIONAL
5
GPS ANTENNA
PITOT
PNEUMATIC
CONNECTIONS
GAD 29
STATIC
P291
CAN-H
CAN-L
CAN BUS
1
2
S
POWER 1
POWER 2
POWER GROUND
ARINC 429 RX 2A (NAV)
ARINC 429 RX 2B (NAV)
GAD 29
#22
7
8
9
5
14/28 Vdc
OPTIONAL
GNS 480
GPS/NAV/COM
P292
P5
22
10
5
25
ARINC 429 OUT 2A
ARINC 429 OUT 2B
4
24
ARINC 429 OUT 1A
ARINC 429 OUT 1B
8
28
ARINC 429 IN 2A
ARINC 429 IN 2B
S
ARINC 429 RX 1A (GPS)
ARINC 429 RX 1B (GPS)
23
11
S
A429 TX 1A (AIR DATA)
A429 TX 1B (AIR DATA)
24
12
S
CONFIGURATION GUIDANCE
1. GNS 480
A. ON THE GND MAINT MODE ARINC 429 SETUP PAGE:
SET CH_IN 2 SEL TO "EFIS"
SET CH_IN 2 SPEED TO "LOW"
SET CH_IN 2 SDI TO "SYS1"
SET CH_OUT 1 SEL TO "GAMA 429 NO FP"
SET CH_OUT 1 SPEED TO "LOW"
SET CH_OUT 1 SDI TO "SYS1"
SET CH_OUT 2 SEL TO "VOR/ILS"
SET CH_OUT 2 SPEED TO "LOW"
SET CH_OUT 2 SDI TO "SYS1"
B. ON THE GND MAINT MODE RESOLVER INTERFACE SETUP PAGE:
SET RESOLVER TO "NOT INSTALLED"
C. ON THE GND MAINT MODE MISCELLANEOUS SETUP PAGE:
SET CDI SELECT TO "USE"
D. ON THE GND MAINT MODE SERIAL SETUP PAGE:
SET CHNL 1 OUTPUT TO "MAPMX"
2. G5
A. ON THE G5 CONFIG MODE ARINC 429 CONFIGURATION PAGE:
SET OUTPUT 1 TO "EFIS/AIRDATA 1 (SDI 1)"
SET INPUT 1 TO "GARMIN GPS (SDI 1)"
SET INPUT 2 TO "GARMIN VOR/ILS (SDI 1)"
B. ON THE G5 CONFIG MODE RS-232 CONFIGURATION PAGE:
SET INPUT FORMAT TO "MAPMX"
Figure 7-16 G5/GAD 29 to GNS 480 Interconnect Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page 7-16
G5 FLIGHT INSTRUMENT
CAN-H
CAN-L
NOTE: INSTALL 011-02887-00 CAN TERMINATION
WHEN G5 OR GAD 29 ARE INSTALLED
AT END OF CAN BUS
P51
1
2
CAN BUS
S
UNIT ID
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
GNX 375
GPS/XPDR
NOTE: GND TO IDENTIFY SECOND G5 UNIT
WHEN 2 ARE INSTALLED
3
P3752
MAPMX
FORMAT 1
MAPMX
5
4
6
20
5
34
RS-232 IN 1
RS-232 OUT 1
SIGNAL GROUND
S
S
G5
POWER 1
POWER 2
POWER GROUND
#22
7
8
9
14/28 Vdc
OPTIONAL
5
GPS ANTENNA
OPTIONAL WHEN G5 USED
WITH GNX 375
PITOT
PNEUMATIC
CONNECTIONS
GAD 29
STATIC
P291
CAN-H
CAN-L
CAN BUS
1
2
P3751
S
POWER 1
POWER 2
POWER GROUND
GAD 29
#22
7
8
9
5
OPTIONAL INPUT
FOR EXTERNAL
ALTITUDE ENCODER
14/28 Vdc
OPTIONAL
9
31
52
RS-232 OUT 3
RS-232 IN 3
SIGNAL GROUND
27
28
ARINC 429 IN 1A
ARINC 429 IN 1B
P292
A429 TX 1A (AIR DATA)
A429 TX 1B (AIR DATA)
EFIS/AIRDATA FORMAT 1 (NAV 1, LOW SPEED)
24
12
EFIS/AIRDATA
S
S
P3752
ARINC 429 RX 1A (GPS)
ARINC 429 RX 1B (GPS)
GARMIN GPS (NAV 1, LOW SPEED)
23
11
GAMA FORMAT 1
S
OPTIONAL DISPLAY FOR
TRAFFIC/WEATHER
RS-232 IN 1
RS-232 OUT 1
SIGNAL GROUND
CONNEXT 57600 BAUD
YEL
BLU
BLK
1
2
ARINC 429 OUT 1A
ARINC 429 OUT 1B
S
CONNEXT INTERFACE
CONNEXT 57600
S
6
21
35
RS-232 OUT 2
RS-232 IN 2
SIGNAL GROUND
15
REMOTE GO AROUND
30
44
AIRCRAFT GROUND
AIRCRAFT POWER
S
AERA 660/79X EXAMPLE
OPTIONAL TO/GA BUTTON
N.O. PUSH TO GROUND
GMC 507
TO/GA INPUT 10
NOTE: EXAMPLE DPST SWITCH IS APEM 4743 SERIES
GNX
14/28 VDC
P3751
5
GROUND PIN 38 TO FORCE UNIT TO POWER ON
AUTOMATICALLY WHEN POWER IS APPLIED
OPTIONAL DISPLAY FOR
TRAFFIC/WEATHER
RS-232 IN 1
RS-232 OUT 1
SIGNAL GROUND
21
42
AIRCRAFT POWER
AIRCRAFT POWER
20
41
38
AIRCRAFT GROUND
AIRCRAFT GROUND
POWER CONTROL
8
30
51
RS-232 OUT 4
RS-232 IN 4
SIGNAL GROUND
7
29
50
RS-232 OUT 5
RS-232 IN 5
SIGNAL GROUND
43
23
22
1
CONFIG
CONFIG
CONFIG
CONFIG
P4X02
CONNEXT 57600 BAUD
47
48
27
CONNEXT INTERFACE
CONNEXT 57600
S
S
GDU 4XX EXAMPLE
OPTIONAL DISPLAY FOR
TRAFFIC/WEATHER
RS-232 IN 1
RS-232 OUT 1
SIGNAL GROUND
P4X02
CONNEXT 57600 BAUD
47
48
27
CONNEXT INTERFACE
S
CONNEXT 57600
S
GDU 4XX EXAMPLE
CONFIG MODULE
(CONNECTOR BACKSHELL)
OR
GAE ALTITUDE
ENCODER
011-03080-00
PWR
RED
GND
DATA
CLK
BLK
YEL
WHT
MODULE
MODULE
MODULE
MODULE
PWR
GND
DATA
CLK
NOTES:
1. PRESSURE ALTITUDE IS PROVIDED BY THE G5 TO THE GNX 375 OVER THE EFIS/AIRDATA
ARINC 429 LINK. USE OF AN EXTERNAL ALTITUDE ENCODER OR THE GAE MODULE IS
OPTIONAL AND GENERALLY UNNECESSARY.
2. CONFIGURE THE RS-232 AND ARINC 429 PORTS PER THE LABELING ON THE ABOVE WIRING
DIAGRAM.
3. ON THE GNX 375 MAIN INDICATOR (ANALOG) CONFIG MODE SETUP PAGE, SET THE SELECTED COURSE
FIELD TO "ALLOWED".
Figure 7-17 G5/GAD 29 to GNX 375 Interconnect Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page 7-17
G5 FLIGHT INSTRUMENT
CAN-H
CAN-L
NOTE: INSTALL 011-02887-00 CAN TERMINATION
WHEN G5 OR GAD 29 ARE INSTALLED
AT END OF CAN BUS
P51
1
2
CAN BUS
S
UNIT ID
GNC 355
GPS/COM
NOTE: GND TO IDENTIFY SECOND G5 UNIT
WHEN 2 ARE INSTALLED
3
P3551
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
MAPMX
5
4
6
MAPMX
S
31
9
52
RS-232 IN 1
RS-232 OUT 1
SIGNAL GROUND
27
28
ARINC 429 IN 1A
ARINC 429 IN 1B
S
G5
POWER 1
POWER 2
POWER GROUND
#22
7
8
9
14/28 Vdc
OPTIONAL
5
GPS ANTENNA
OPTIONAL WHEN G5 USED
WITH GPS 175
PITOT
PNEUMATIC
CONNECTIONS
GAD 29
STATIC
P291
CAN-H
CAN-L
CAN BUS
1
2
S
POWER 1
POWER 2
POWER GROUND
GAD 29
#22
7
8
9
5
14/28 Vdc
OPTIONAL
P292
A429 TX 1A (AIR DATA)
A429 TX 1B (AIR DATA)
EFIS/AIRDATA FORMAT 1 (NAV 1, LOW SPEED)
24
12
EFIS/AIRDATA
S
ARINC 429 RX 1A (GPS)
ARINC 429 RX 1B (GPS)
S
GARMIN GPS (NAV 1, LOW SPEED)
23
11
GAMA FORMAT 1
S
5
6
ARINC 429 OUT 1A
ARINC 429 OUT 1B
S
OPTIONAL TO/GA BUTTON
N.O. PUSH TO GROUND
36
REMOTE GO AROUND
43
23
22
1
CONFIG
CONFIG
CONFIG
CONFIG
21
42
20
41
AIRCRAFT
AIRCRAFT
AIRCRAFT
AIRCRAFT
GMC 507
TO/GA INPUT 10
NOTE: EXAMPLE DPST SWITCH IS APEM 4743 SERIES
CONFIG MODULE
(CONNECTOR BACKSHELL)
PWR
RED
GND
DATA
CLK
BLK
YEL
WHT
MODULE
MODULE
MODULE
MODULE
PWR
GND
DATA
CLK
GPS
14/28 VDC
GMA 240/245/245R
AUDIO PANEL
COM1 AUDIO IN HI
COM1 AUDIO LO
COM1 MIC AUDIO OUT HI
COM1 MIC KEY OUT
5
P2401
P3552
9
10
S
S
S
S
11
12
POWER 1
POWER 1
GROUND
GROUND
7
18
COM AUDIO HI
COM AUDIO LO
20
5
MIC AUDIO LO
MIC AUDIO IN HI
11
MIC TRANSMIT
NOTES:
1. CONFIGURE THE RS-232 AND ARINC 429 PORTS PER THE LABELING ON THE ABOVE WIRING
DIAGRAM.
2. ON THE GNC 355 MAIN INDICATOR (ANALOG) CONFIG MODE SETUP PAGE, SET THE
SELECTED COURSE FIELD TO "ALLOWED".
3. THE GNC 355 COM RADIO MAY BE CONNECTED AS COM1 OR COM2 ON THE AUDIO PANEL.
Figure 7-18 G5/GAD 29 to GNC 355 Interconnect Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page 7-18
G5 FLIGHT INSTRUMENT
CAN-H
CAN-L
NOTE: INSTALL 011-02887-00 CAN TERMINATION
WHEN G5 OR GAD 29 ARE INSTALLED
AT END OF CAN BUS
P51
1
2
CAN BUS
S
UNIT ID
GPS 175
NOTE: GND TO IDENTIFY SECOND G5 UNIT
WHEN 2 ARE INSTALLED
3
P1751
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
MAPMX
5
4
6
MAPMX
S
31
9
52
RS-232 IN 1
RS-232 OUT 1
SIGNAL GROUND
27
28
ARINC 429 IN 1A
ARINC 429 IN 1B
S
G5
POWER 1
POWER 2
POWER GROUND
#22
7
8
9
14/28 Vdc
OPTIONAL
5
GPS ANTENNA
OPTIONAL WHEN G5 USED
WITH GPS 175
PITOT
PNEUMATIC
CONNECTIONS
GAD 29
STATIC
P291
CAN-H
CAN-L
CAN BUS
1
2
S
POWER 1
POWER 2
POWER GROUND
GAD 29
#22
7
8
9
5
14/28 Vdc
OPTIONAL
P292
A429 TX 1A (AIR DATA)
A429 TX 1B (AIR DATA)
EFIS/AIRDATA FORMAT 1 (NAV 1, LOW SPEED)
24
12
EFIS/AIRDATA
S
ARINC 429 RX 1A (GPS)
ARINC 429 RX 1B (GPS)
S
GARMIN GPS (NAV 1, LOW SPEED)
23
11
GAMA FORMAT 1
S
5
6
ARINC 429 OUT 1A
ARINC 429 OUT 1B
S
OPTIONAL TO/GA BUTTON
N.O. PUSH TO GROUND
36
REMOTE GO AROUND
43
23
22
1
CONFIG
CONFIG
CONFIG
CONFIG
21
42
20
41
AIRCRAFT
AIRCRAFT
AIRCRAFT
AIRCRAFT
GMC 507
TO/GA INPUT 10
NOTE: EXAMPLE DPST SWITCH IS APEM 4743 SERIES
CONFIG MODULE
(CONNECTOR BACKSHELL)
PWR
RED
GND
DATA
CLK
BLK
YEL
WHT
MODULE
MODULE
MODULE
MODULE
PWR
GND
DATA
CLK
GPS
14/28 VDC
5
POWER 1
POWER 1
GROUND
GROUND
NOTES:
1. CONFIGURE THE RS-232 AND ARINC 429 PORTS PER THE LABELING ON THE ABOVE WIRING
DIAGRAM.
2. ON THE GPS 175 MAIN INDICATOR (ANALOG) CONFIG MODE SETUP PAGE, SET THE SELECTED COURSE
FIELD TO "ALLOWED".
Figure 7-19 G5/GAD 29 to GPS 175 Interconnect Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page 7-19
G5 FLIGHT INSTRUMENT
CAN-H
CAN-L
NOTE: INSTALL 011-02887-00 CAN TERMINATION
WHEN G5 OR GAD 29 ARE INSTALLED
AT END OF CAN BUS
P51
1
2
CAN BUS
S
UNIT ID
NOTE: GND TO IDENTIFY SECOND G5 UNIT
WHEN 2 ARE INSTALLED
3
P1001
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
5
4
6
MAPMX
MAPMX FORMAT 2 OR MAPMX
6
44
S
S
GTN 6XX/7XX
GPS/NAV/COM
RS-232 OUT 3
RS-232 GND 3/4
ANY AVAILABLE RS-232
G5
POWER 1
POWER 2
POWER GROUND
7
8
9
#22
14/28 Vdc
OPTIONAL
5
GPS ANTENNA
PITOT
PNEUMATIC
CONNECTIONS
GAD 29
STATIC
P291
CAN-H
CAN-L
CAN BUS
1
2
S
POWER 1
POWER 2
POWER GROUND
GAD 29
#22
7
8
9
5
14/28 Vdc
OPTIONAL
P292
ARINC 429 RX 2A (NAV)
ARINC 429 RX 2B (NAV)
P1004
22
10
24
23
S
GTN 6XX/7XX
GPS/NAV/COM
ARINC 429 OUT A
ARINC 429 OUT B
S
P1001
ARINC 429 RX 1A (GPS)
ARINC 429 RX 1B (GPS)
23
11
A429 TX 1A (AIR DATA)
A429 TX 1B (AIR DATA)
24
12
S
S
10
29
ARINC 429 OUT 1A
ARINC 429 OUT 1B
48
67
ARINC 429 IN 1A
ARINC 429 IN 1B
S
S
CONFIGURATION GUIDANCE
1. GTN 6XX/7XX
A. ON THE CONFIG MODE ARINC 429 CONFIGURATION PAGE:
SET IN 1 SPEED TO "LOW"
SET IN 1 DATA TO "EFIS FORMAT 2"
SET OUT 1 SPEED TO "LOW"
SET OUT 1 DATA TO "GARMIN 429" (GTN V6.50 AND LATER)
SET OUT 1 DATA TO "GAMA FORMAT 1" WHEN "GARMIN 429" NOT AVAILABLE
SET OUT 1 SDI TO "LNAV 1"
B. ON THE CONFIG MODE MAIN INDICATOR (ANALOG) CONFIGURATION PAGE:
SET SELECTED COURSE FOR VLOC TO "IGNORED"
C. ON THE CONFIG MODE VOR/LOC/GS CONFIGURATION PAGE:
SET NAV RADIO TO "ENABLED"
SET TX SPEED TO "LOW"
SET SDI TO "VOR/ILS 1"
D. ON THE RS-232 CONFIG PAGE
SET CHNL 3 INPUT TO "MAPMX FORMAT 2" WHEN THIS FORMAT IS AVAILABLE
SET CHNL 3 OUTPUT TO "MAPMX" WHEN "MAPMX FORMAT 2" INPUT NOT AVAILABLE
2. G5
A. ON THE G5 CONFIG MODE ARINC 429 CONFIGURATION PAGE:
SET OUTPUT 1 TO "EFIS/AIRDATA 1 (SDI 1)"
SET INPUT 1 TO "GARMIN GPS (SDI 1)"
SET INPUT 2 TO "GARMIN VOR/ILS (SDI 1)"
B. ON THE G5 CONFIG MODE RS-232 CONFIGURATION PAGE:
SET INPUT FORMAT TO "MAPMX"
Figure 7-20 G5/GAD 29 to GTN 6XX/7XX Interconnect Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page 7-20
G5 FLIGHT INSTRUMENT
CAN-H
CAN-L
NOTE: INSTALL 011-02887-00 CAN TERMINATION
WHEN G5 OR GAD 29 ARE INSTALLED
AT END OF CAN BUS
P51
1
2
CAN BUS
S
UNIT ID
NOTE: GND TO IDENTIFY SECOND G5 UNIT
WHEN 2 ARE INSTALLED
3
P1001
RS-232 TX 1
RS-232 RX 1
SIGNAL GROUND
5
4
6
MAPMX
MAPMX FORMAT 2 OR MAPMX
S
6
44
S
#1 GTN 6XX/7XX
GPS/NAV/COM
RS-232 OUT 3
RS-232 GND 3/4
ANY AVAILABLE RS-232
G5
POWER 1
POWER 2
POWER GROUND
7
8
9
#22
14/28 Vdc
OPTIONAL
5
GPS ANTENNA
PITOT
PNEUMATIC
CONNECTIONS
GAD 29
STATIC
P291
CAN-H
CAN-L
CAN BUS
1
2
S
POWER 1
POWER 2
POWER GROUND
GAD 29
#22
7
8
9
5
14/28 Vdc
OPTIONAL
P292
P1004
VOR/ILS (SDI 1)
ARINC 429 RX 2A (NAV)
ARINC 429 RX 2B (NAV)
VOR/ILS 1, LO SPEED
24
23
22
10
S
#1 GTN 6XX/7XX
GPS/NAV/COM
ARINC 429 OUT A
ARINC 429 OUT B
S
P1001
GPS (SDI 1)
ARINC 429 RX 1A (GPS)
ARINC 429 RX 1B (GPS)
GARMIN 429, LNAV 1, LO SPEED
23
11
S
EFIS/AIR DATA 1 (SDI 1)
A429 TX 1A (AIR DATA)
A429 TX 1B (AIR DATA)
10
29
ARINC 429 OUT 1A
ARINC 429 OUT 1B
48
67
ARINC 429 IN 1A
ARINC 429 IN 1B
S
EFIS FORMAT 2, LO SPEED
24
12
S
S
P1004
VOR/ILS (SDI 2)
ARINC 429 RX 4A (NAV)
ARINC 429 RX 4B (NAV)
VOR/ILS 2, LO SPEED
16
4
24
23
S
#2 GTN 6XX/7XX
GPS/NAV/COM
ARINC 429 OUT A
ARINC 429 OUT B
S
P1001
GPS (SDI 2)
ARINC 429 RX 3A (GPS)
ARINC 429 RX 3B (GPS)
GARMIN 429, LNAV 2, LO SPEED
17
5
S
EFIS/AIR DATA 1 (SDI 2)
A429 TX 2A (AIR DATA)
A429 TX 2B (AIR DATA)
10
29
ARINC 429 OUT 1A
ARINC 429 OUT 1B
48
67
ARINC 429 IN 1A
ARINC 429 IN 1B
S
EFIS FORMAT 2, LO SPEED
18
6
S
S
CONFIGURATION GUIDANCE
1. GTN 6XX/7XX
A. ON THE CONFIG MODE ARINC 429 CONFIGURATION PAGE:
CONFIGURE ALL ARINC 429 PORTS AS SHOWN ABOVE
B. ON THE CONFIG MODE MAIN INDICATOR (ANALOG) CONFIGURATION PAGE:
SET SELECTED COURSE FOR VLOC TO "IGNORED"
C. ON THE CONFIG MODE VOR/LOC/GS CONFIGURATION PAGE:
SET NAV RADIO TO "ENABLED"
SET TX SPEED TO "LOW"
SET SDI TO "VOR/ILS 1" FOR #1 GTN, "VOR/ILS 2" FOR #2 GTN
D. ON THE RS-232 CONFIG PAGE
SET CHNL 3 INPUT TO "MAPMX FORMAT 2" WHEN THIS FORMAT IS AVAILABLE
SET CHNL 3 OUTPUT TO "MAPMX" WHEN "MAPMX FORMAT 2" INPUT NOT AVAILABLE
2. G5
A. ON THE G5 CONFIG MODE ARINC 429 CONFIGURATION PAGE:
CONFIGURE IN/OUT PORTS AS SHOWN ABOVE
B. ON THE G5 CONFIG MODE RS-232 CONFIGURATION PAGE:
SET INPUT FORMAT TO "MAPMX"
Figure 7-21 G5/GAD 29 to GTN 6XX/7XX Dual Nav Interconnect Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page 7-21
8 G5 CONFIGURATION AND POST INSTALLATION CHECKOUT
The checkout procedures in this section are recommended to be performed after installing the G5. The
calibration procedures are required to be performed after installing the G5. It is assumed that the person
performing these checks is familiar with the aircraft, has a working knowledge of typical avionics systems,
and has experience using the test equipment defined in this section.
NOTE
See G5 Pilot's Guide for operational instructions.
NOTE
Some procedures in this section require that the GPS receiver is receiving sufficient satellite
signal to compute a present position. This requires outdoor line of sight to GPS satellite
signals or a GPS indoor repeater.
NOTE
As these procedures involve engine run-up and moving the aircraft, it is recommended that the
installer read this entire section before beginning the checkout procedure.
NOTE
All test equipment should have current calibration records.
CAUTION
Be sure to check all aircraft control movements before flight is attempted to ensure that the
wiring harness does not touch any moving part.
8.1 Recommended Test Equipment
The following test equipment is recommended to conduct and complete all post installation checkout
procedures in this section:
•
•
•
•
•
Digital Multi-Meter (DMM) for power troubleshooting and wiring connection check
Ground power unit capable of supplying 14/28 Vdc power to the aircraft systems and avionics
Outdoor line of sight to GPS satellite signals or GPS indoor repeater
Digital level or equivalent
Pitot/static ramp tester (only required if unit fails a periodic static system test)
190-02072-01
Rev. 5
G5 Installation Manual
Page 8-1
8.2 Configuration Mode
All of the configuration and calibration procedures in this section are performed in configuration mode.
To enter configuration mode, hold down the knob while powering on the G5.
Figure 8-1 Entering Configuration Mode
8.3 Software Loading Procedure
G5 software loading can be performed in either normal or configuration mode. Manually loading software
to the G5 is not required when the G5 is installed as part of a G3X system.
1. Power on the G5, then insert a properly formatted microSD™ card into the microSD™ card slot.
NOTE
It is also acceptable to insert the microSD
card before powering on the unit.
2. A software update message appears on the screen. Select OK to begin the update.
NOTE
The software update message will only be displayed if the version of software to be loaded is
newer than the version currently on the unit.
3. The unit will reboot to the software update screen and the software update will begin
automatically. This screen will show the progress of the software update.
4. Ensure power is not removed while the update is being performed.
5. The unit will reboot after the update is complete.
6. The new software version may be viewed while the unit powers on or in the configuration mode
menu.
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Rev. 5
G5 Installation Manual
Page 8-2
8.4 Configuration Pages
8.4.1
Device Information Page
NOTE
When a G5 is installed as part of a G3X system, some configuration pages are not available
because configuration settings are automatically transferred from the GDU 37X/4XX to the
G5.
The Device Information page displays LRU (device) specific information such as the software versions of
devices connected to the G5. The devices listed on this page are dependent upon the Installation Type
setting (G3X System Backup or Standalone Instrument). Faults are indicated by a red "X" next to the
affected LRU.
Figure 8-2 Device Information Page
The G5 can be configured as a Standalone Unit or (if connected to a G3X system) it will automatically be
configured as G3X Backup Unit. When connected to a G3X system, the G5 will not allow the Installation
Type setting to be changed (as long as the G5 is communicating with G3X LRUs). To select the
Installation Type:
1.
2.
3.
4.
Power on the unit in configuration mode.
Select Device Information.
Scroll to select Installation Type, and press the knob.
Select either G3X System Backup or Standalone Instrument.
Figure 8-3 Installation Type Page
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G5 Installation Manual
Page 8-3
8.4.2
Attitude Configuration Page
The Attitude Configuration page is used to configure user display preferences and to complete the postinstallation calibration procedures.
Table 8-1 Attitude Configuration Settings
Configuration
Setting
Description
Indicator Type
Select Normal to display a triangular aircraft reference symbol indicator on the
PFD (similar to single cue). Select Alternate to display a cross-pointer aircraft
reference symbol (similar to dual-cue).
This setting is only present when the Installation Type setting is configured as a
Standalone Unit and the installation does not have an autopilot configured.
Pitch Display
Adjusts the scale of the pitch ladder on the PFD. Compact spaces the pitch
markings closer together. Normal mimics the spacing of typical mechanical
attitude indicators. Expanded spaces the markings further apart.
190-02072-01
Rev. 5
G5 Installation Manual
Page 8-4
Table 8-1 Attitude Configuration Settings
The roll (bank angle) indication may be selected to be a Ground Pointer (default)
or a Sky Pointer configuration.
Roll Display
For the more common Ground Pointer configuration, both the roll arc and the pitch
ladder remain anchored to the horizon and the roll pointer beneath the roll arc
points to the present roll angle.
For the Sky Pointer configuration, the pitch ladder continues to roll with the
horizon, but the roll arc remains fixed and centered in the display. The roll pointer
beneath the roll arc moves with the horizon and in the opposite direction to aircraft
roll.
Vibration Test
190-02072-01
Rev. 5
Validates the vibration characteristics of the G5 installation. See Section 8.4.6.2
for more information.
G5 Installation Manual
Page 8-5
Table 8-1 Attitude Configuration Settings
Allows for direct manual entry of the present yaw offset when the instrument
panel to which the G5 is mounted is not perpendicular to the aircraft centerline.
The limit on this setting is +/- 15 degs. Positive is clockwise.
Calibrate Yaw
Offset
Calibrate Pitch/Roll
Calibrates the G5's pitch and roll measurements to a known level attitude. See
Section 8.4.6.1 for more information.
Pitch Calibration
Allows for direct manual entry or adjustment of the present pitch offset. The limit
on this setting is +/- 30 degs. Positive is pitch up. For example, an aircraft that is
continuously indicating a pitch attitude that is 2 degs high would need to reduce
this pitch offset value by 2 degs.
Roll Calibration
Allows for direct manual entry or adjustment of the present roll offset. The limit
on this setting is +/- 2 degs. Positive is roll right.
User Pitch Offset
If disabled, the pitch offset cannot be adjusted and will default to zero
(standalone installation only). Enables and disables the pitch offset in normal
mode.
This setting is only present when the Installation Type setting is configured as a
Standalone Unit.
Automatic Declutter
Enables and disables the automatic change from the HSI page to the PFD page
when the aircraft enters an unusual pitch/roll attitude.
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G5 Installation Manual
Page 8-6
Figure 8-4 Attitude Configuration Page
190-02072-01
Rev. 5
G5 Installation Manual
Page 8-7
8.4.3
Air Data Configuration Page
The Air Data Configuration page is used to configure user display preferences and to complete the postinstallation calibration procedures.
Table 8-2 Air Data Configuration Settings
Configuration
Setting
Description
Air Data Sensors
Select Disabled to disable the G5's internal air data sensors and hide airspeed,
altitude, and vertical speed information on the PFD. This option is intended for
single standalone G5 installations where the pitot/static inputs are not connected.
This setting is only present when the Installation Type setting is configured as a
Standalone Unit and the installation does not have an autopilot configured.
Vertical Speed
Indicator
Configures the G5's PFD vertical speed indicator to display ±1500 fpm,
±2000 fpm, or ±3000 fpm.
Calibrate Static
Pressure
Performs a field calibration of the G5's static pressure sensor. Only required
when the G5 has failed a periodic altimeter test. See Section 8.4.6.3 for more
information.
Figure 8-5 Air Data Configuration Page
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Rev. 5
G5 Installation Manual
Page 8-8
8.4.4
Airspeed Configuration Page
This page allows for configuration of the reference speeds. The aircraft Vspeeds can be entered using the
knob on the G5.
To clear a reference speed setting:
1. Highlight the desired reference speed setting.
2. Rotate the knob counterclockwise until a blank field is displayed.
Figure 8-6 Airspeed Configuration Page
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Rev. 5
G5 Installation Manual
Page 8-9
8.4.5
Magnetometer Configuration Page
The Magnetometer Configuration page is used to enable or disable the magnetometer function depending
on whether an optional GMU 11 Magnetometer is connected to the G5.
Table 8-3 Magnetometer Configuration Settings
Configuration
Setting
Description
Magnetometer
Select Disabled to disable the G5's optional magnetometer function. The
Enabled option is intended for single standalone G5 installations that are
connected to a GMU 11 Magnetometer.
Status
Indicates status of communication with GMU 11.
Orientation
Used to inform the G5 of the mounted orientation of a GMU 11 Magnetometer
(optional). See Section 8.4.6.4 for detailed instructions.
Interference Test
Used to verify that no magnetic interference exists near the GMU 11 installation.
See Section 8.4.6.5 for detailed instructions.
Calibrate
Magnetometer
Used to calibrate the magnetometer in the mounted location/orientation. See
Section 8.4.6.6 for detailed instructions.
Figure 8-7 Magnetometer Configuration Page
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Rev. 5
G5 Installation Manual
Page 8-10
8.4.6
G5 Post-Installation Calibration Procedures
After mechanical and electrical installation of the G5 has been completed, prior to operation, a set of postinstallation calibration procedures must be carried out. Table 8-4 describes the required and optional
calibration procedures.
Table 8-4 Post-Installation Calibration Procedure Summary
Calibration
Procedure
Procedure Name
Procedure
Description
Installations Requiring Procedure
A
Pitch/Roll Offset
Compensation
Level aircraft
Procedure A is required for all installations
B
Engine Run-Up
Vibration Test
Validate vibration
characteristics of
installation
Procedure B is required for all installations
C
Air Data Static
Pressure
Calibration
Altitude
re-calibration
Procedure C is only used when the G5 has
failed a periodic altimeter test
D
Magnetometer
Unit Orientation
Configure
magnetometer
installation
orientation
Procedure D is required for all GMU 11
installations
Validate no
magnetic
interference with
GMU 11
Magnetometer
Procedure E is required for initial
installation verification.
This test should also be repeated to verify
all subsequent electrical changes
associated with devices within 10 feet of
the magnetometer. Such changes include,
but are not limited to, wiring, shielding or
grounding changes to any light, strobe,
beacon or other electrical device located
near or in the same wing as the
magnetometer. Likewise, this test should
also be repeated to verify all subsequent
changes to materials within 10 feet of the
magnetometer. Such changes include,
but are not limited to, addition, removal or
modification of ferrous or electrically
conductive materials located near or in the
same wing as the magnetometer unit.
Garmin recommends this test be
performed at least once every 12 months.
Compass rose
taxi maneuver
Procedure F is required for all installations.
This calibration must be performed after
every Pitch/Roll Offset Compensation and
following a removal or replacement of the
GMU 11, or degaussing of the area near
the GMU 11 location.
E
F
190-02072-01
Rev. 5
Magnetometer
Interference Test
Magnetometer
Calibration
Procedure
G5 Installation Manual
Page 8-11
8.4.6.1
Calibration Procedure A: Pitch/Roll Offset Compensation
NOTE
This procedure requires orienting the aircraft to normal flight attitude. This can be done
by using jacks or placing wood blocks under the nose-wheel, for example. As another
example, if the number of degrees ‘nose high’ the aircraft flies in straight and level cruise
is known, a digital level can be used to orient the aircraft to normal flight attitude prior to
the calibration.
NOTE
The G5 must be installed to be level in pitch/roll within 30.0 of the aircraft in-flight level
cruise attitude. In-flight level cruise attitude is not necessarily the same as the level
reference provided by the manufacturer (such as fuselage longerons).
1. Select the Attitude Configuration page.
2. Select Calibrate Pitch/Roll.
3. Ensure that aircraft and the unit comply with all on-screen instructions, then select Start.
Figure 8-8 Calibration Page
4. A progress screen will then be displayed. There is a 30 second countdown timer for the procedure
that resets when the aircraft moves.
5. When the calibration is complete, a successful status message will be displayed along with the new
pitch and roll offsets.
NOTE
The pilot may adjust the displayed pitch attitude in normal mode. The maximum amount of
pitch display adjustment available in normal mode is ±5.0°. This feature should not be
used to compensate for a non-conforming installation that does not meet the requirements
of the pitch/roll offset compensation calibration procedure.
NOTE
In a G3X system, or a non-G3X system with multiple G5 units, if the pitch/roll offset procedure
is performed for one unit, it should be performed on all other G3X AHRS units or G5 units
before moving the aircraft.
190-02072-01
Rev. 5
G5 Installation Manual
Page 8-12
8.4.6.2
Calibration Procedure B: Engine Run-Up Vibration Test
NOTE
Calibration Procedure B is required for all installations to validate the vibration
characteristics of the installation.
Passing the Engine Run-Up Vibration test does not remove the requirement to rigidly mount the G5. The
Engine Run-Up Vibration Test is intended to help discover mounting issues but successful completion of
the test does not validate the mounting of the G5, and does not account for all possible vibration profiles
that may be encountered during normal aircraft operation
1. Select the Attitude Configuration page.
2. Select Vibration Test.
3. Ensure the aircraft complies with all on-screen instructions, then select Start.
Figure 8-9 Vibration Test Page
4. Gradually increase engine power from idle to full power and back over the course of 1-2 minutes.
A progress screen will be displayed showing the status of the test.
5. Select Done when the test has been completed. Passing results will be indicated by a green check
mark and failures will be indicated by a red "X". If failures are indicated, repeat the test. If
failures persist, the installation should be considered unreliable until the source of the vibration
problem is identified and remedied. Record the out of range limit values for future reference.
190-02072-01
Rev. 5
G5 Installation Manual
Page 8-13
The following are potential causes for failures of the engine run-up test:
a) Excessive flexing of the G5 mechanical mounting with respect to airframe (see Section 3.4.1
for applicable mounting requirements and instructions).
b) Vibration or motion of the G5 caused by neighboring equipment and/or supports.
c) Mounting of the G5 in a location that is subject to severe vibrations (e.g. close to an engine
mount).
d) Mounting screws and other hardware for G5 not firmly attached.
e) Absence of recommended mounting supports.
f) G5 connector not firmly attached to unit.
g) Cabling leading to the G5 not firmly secured to a supporting structure.
h) An engine/propeller combination that is significantly out of balance.
NOTE
In some aircraft, attempting the engine run-up test on a day with very strong and/or gusty
winds may cause the test to occasionally fail. However, windy conditions should not be taken
as evidence that the test would pass in calm conditions; an actual pass is required before the
installation can be considered adequate.
190-02072-01
Rev. 5
G5 Installation Manual
Page 8-14
8.4.6.3
Calibration Procedure C: Air Data Static Pressure Calibration
The Air Data Configuration page has a selection for static pressure calibration. This procedure is used to
perform an altimeter re-calibration. The altitude pressure sensor used in the G5 is very low drift and does
not typically require re-calibration.
NOTE
This calibration is only used when the G5 fails a periodic altimeter test and should only rarely,
if ever, be used.
The static pressure calibration requires the use of a pressure control system (test set) with an altitude
accuracy of at least ±5 feet at sea level and ±20 feet at 30,000 feet. It is necessary to re-calibrate to sea
level (0 feet), 10,000 feet, 20,000 feet, and optionally to 30,000 feet. The operator is allowed to finish the
calibration at the end of the 20,000-foot calibration if the 30,000-foot calibration is not desired.
CAUTION
To avoid damaging the G5 pressure sensors, both the pitot and static ports must be
connected to the test set.
1. Select the Air Data Configuration page.
2. Select Calibrate Static Pressure.
3. Ensure all on-screen instructions have been complied with, then select Start.
Figure 8-10 Static Pressure Calibration Page
4. At each calibration point the display will present a screen indicating the pressure altitude to set.
Once the altitude is set, select Ready to calibrate this pressure.
5. During the calibration at each pressure, the pressure must be held constant for 30 seconds for the
calibration step to be successful. The calibration may be cancelled at any point should the test
setup require adjustment before repeating. A progress screen will be displayed showing the status
of the test.
6. Select Done when the static pressure calibration is successfully completed.
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Rev. 5
G5 Installation Manual
Page 8-15
8.4.6.4
Calibration Procedure D: Magnetometer Unit Orientation
1. Select the Magnetometer Configuration page.
2. Ensure that the Status field displays Data Valid.
3. Select the Orientation of the GMU 11 in the installation using the on-screen instructions as a guide.
Figure 8-11 Select Magnetometer Orientation
4. Ensure that the correct orientation is now displayed on the Magnetometer Configuration page.
190-02072-01
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G5 Installation Manual
Page 8-16
8.4.6.5
Calibration Procedure E: Magnetometer Interference Test
NOTE
Calibration Procedure E is required for all installations that include a GMU 11 in order to
validate the magnetic characteristics of the installation.
1. Select the Magnetometer Configuration page.
2. Select Interference Test.
3. Ensure that the aircraft complies with all on-screen instructions, then select Next.
Figure 8-12 Magnetometer Interference Test
4. Ensure that the aircraft has been properly prepared per the on-screen instructions. See Table 8-5
for a sample test sequence. Select Start to begin the test.
Figure 8-13 Magnetometer Interference Test
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G5 Installation Manual
Page 8-17
5. The operator should carry out the actions called for in the prepared test sequence. During
calibration, a real-time value is displayed that represents the current magnetic field strength as a
percentage of the maximum limit.
Figure 8-14 Magnetometer Interference Test In Progress
NOTE
It is important that all actions are carried out in the order and at the precise elapsed time
as specified in the prepared test sequence.
6. After completing the prepared test sequence, select Done. The test status will indicate whether the
interference test passed or failed. The worst case magnetic deviation value will indicate the test
margins. Values less than or equal to 100% constitute a pass and greater than 100% constitute a
fail.
Figure 8-15 Magnetometer Interference Test Passed
190-02072-01
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G5 Installation Manual
Page 8-18
Table 8-5 Magnetometer Interference Test Sequence Example
Elapsed Time Since Start of Test (min:sec)
190-02072-01
Rev. 5
Action
0:00
Test begins
0:10
Aileron full right
0:20
Aileron full left
0:30
Aileron level
0:40
Elevator up
0:50
Elevator down
1:00
Elevator level
1:20
Rudder left
1:40
Rudder right
1:50
Rudder center
2:00
Flaps down
2:10
Flaps up
2:20
Autopilot on
2:30
Autopilot off
2:40
Landing gear up
2:50
Landing gear down
3:00
Speed brake up
3:10
Speed brake down
3:20
Navigation lights on
3:30
Navigation lights off
3:40
Landing lights on
3:50
Landing lights off
4:00
Taxi lights on
4:10
Taxi lights off
4:20
Landing and taxi lights on
4:30
Landing and taxi lights off
4:40
Strobes on
4:50
Strobes off
5:00
Recognition lights on
5:10
Recognition lights off
5:20
Turn on all wing-tip lights simultaneously (this will
typically include navigation lights, recognition lights,
and strobe)
5:30
Turn off all wing-tip lights simultaneously
5:40
Beacon on
5:50
Beacon off
6:00
Pitot heat on
6:10
Pitot heat off
6:20
End of test
G5 Installation Manual
Page 8-19
If the test fails, the installation should be considered unreliable until the source of magnetic interference is
identified and remedied. The magnetometer interference test must be repeated until passed. When the
magnetometer interference test fails, record the three greatest magnetic deviation values and their
corresponding timestamps. A maximum deviation value greater than 100% of the total limit indicates a
problem that must be resolved. Compare the corresponding timestamps with the prepared test sequence to
identify which action produced the problem. Contact Garmin for assistance in resolving the problem.
NOTE
Two common reasons for a failed magnetometer interference test are:
1) New equipment is installed in close proximity to the GMU 11 Magnetometer.
2) An existing or new electronic device has become grounded through the aircraft
structure instead of via the proper ground wire in a twisted shielded pair.
8.4.6.6
Calibration Procedure F: Magnetometer Calibration Procedure
NOTE
Calibration Procedures A, B, and C must be successfully completed prior to Calibration
Procedure F.
NOTE
Calibration Procedure F must be carried out at a location that is determined to be free of
magnetic disturbances, such as a compass rose. Attempting to carry out this maneuver on
a typical ramp area will not yield a successful calibration. The accuracy of the
magnetometer cannot be guaranteed if this calibration is not performed in a magnetically
clean location.
Taxi the aircraft to a site that has been determined to be free of magnetic disturbances. Ensure that there are
no nearby magnetic materials on or near the perimeter of the site. If unavoidable, maneuver the aircraft to
keep the magnetometer from passing within 20 feet (6.1 meters) of such objects. Additionally, ensure that
vehicles or other aircraft are an adequate distance (40 feet [12.2 meters]) away from the aircraft during the
calibration procedure.
At the site, align the aircraft to a heading of magnetic north (±5°). It is best to offset the aircraft position to
the west of the north/south axis to provide space for the aircraft to turn clockwise around the site during the
procedure as indicated in Figure 8-16.
Figure 8-16 Aircraft Alignment
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G5 Installation Manual
Page 8-20
With the aircraft stationary, initiate the magnetometer calibration procedure as follows:
1. Select the Magnetometer Configuration page.
2. Select Calibrate Magnetometer.
3. Ensure that all on-screen instructions have been complied with, then select Next.
Figure 8-17 Magnetometer Calibration Page
4. Ensure that all on-screen instructions have been complied with, then select Next.
Figure 8-18 Magnetometer Calibration Page
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G5 Installation Manual
Page 8-21
5. Ensure that all on-screen instructions have been complied with, then select Start.
Figure 8-19 Magnetometer Calibration Page
6. Follow the on-screen instructions by holding the current aircraft position. During this time the
magnetometer will be calibrating the magnetic environment of the installation. The dots at the end
of the text will be removed as this step of the test progress.
Figure 8-20 Magnetometer Calibration Page
7. After holding the starting position, continue following the on-screen instructions by slowly turning
the aircraft to the right. The dots at the end of the text will be removed as the aircraft rotates 30º.
8. Continue following the on-screen instructions until the calibration is completed. The turn and hold
procedure detailed above will repeat for a total of 12 cycles before the calibration is complete
(resulting in the aircraft completing a full circle of rotation).
9. If the calibration is successful, a passing status message will be displayed. The calibration will
abort if it cannot be successfully completed. Ensure all on-screen instruction are followed and
repeat the test (if necessary) to obtain a successful calibration.
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G5 Installation Manual
Page 8-22
8.4.7
Flight Controls Configuration Page
Figure 8-21 Flight Controls Configuration Page
8.4.7.1
General Autopilot Description
The GSA 28 based autopilot system is a fully integrated, high performance autopilot that can control up to
three axes of an aircraft (refer to the G3X Installation Manual for GSA 28 installation information). Each
GSA 28 servo is also capable of managing the trim control for its axis. The following four subsections
(roll, pitch, yaw, and trim) are provided to aid the pilot/installer in understanding/configuring the Garmin
GSA 28 autopilot system.
NOTE
A GMC Mode Controller is required to use the G5 autopilot controls.
Roll Servo
All GSA 28 autopilot systems require a servo to control the roll axis of an aircraft. A single axis GSA 28
installation that controls only the roll axis is sometimes referred to as a “wing-leveler”.
The roll servo follows roll steering commands from the G5 so the airplane will hold a desired roll angle,
follow a desired heading/track, or follow the lateral component of a flight plan.
During the flight test phase of the autopilot checkout, the roll servo aggressiveness will be adjusted to get
the desired in-fight performance. The roll servo gain setting is used to set the aggressiveness of the roll
servo. A larger number will cause the roll servo to more aggressively control the aircraft and a smaller
number will cause the roll servo to less aggressively control the aircraft.
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Figure 8-22 Roll Servo Configuration Page
Pitch Servo
Most GSA 28 autopilot systems consist of both a roll and pitch servo allowing for full 2-axis control of the
aircraft.
The pitch servo follows vertical guidance commands from the G5 so the airplane will hold a desired pitch
angle, vertical speed, airspeed, or altitude, or follow the vertical component of a flight plan.
Vertical control of the aircraft is all based on controlling the pitch angle with two additional sub-modes for
vertical speed and airspeed. What this means is that the basic pitch mode performance must be properly
adjusted before changing settings that adjust the vertical speed and airspeed based modes.
NOTE
Ensure pitch mode functionality is properly adjusted before attempting to adjust vertical speed
or airspeed mode performance.
During the flight test phase of the autopilot checkout, the pitch servo aggressiveness will be adjusted to get
the desired in-fight performance. The pitch servo gain setting is used to set the aggressiveness of the pitch
servo. A larger number will cause the pitch servo to more aggressively control the aircraft, and a smaller
number will cause the pitch servo to less aggressively control the aircraft.
Figure 8-23 Pitch Servo Configuration Page
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Yaw Damper
The GSA 28 autopilot system can be expanded to support a yaw damper. The yaw damper will control the
rudder to compensate or remove aircraft body yaw (tail wagging). The yaw damper will also try to null the
lateral acceleration (center the ball) over the long term. The ball centering portion of the yaw damper is
not a replacement for proper rudder trim.
NOTE
Yaw damper functionality requires a GMC Mode Controller with a YD button.
During the flight test phase, the yaw damper is configured and set up after the basic two axis pitch and roll
performance has been properly configured. This is done so the pilot can focus on properly adjusting the
performance of each individual component of the autopilot system without trying to tune them all at once.
NOTE
Ensure basic autopilot functionality is properly adjusted before using the yaw damper.
During the flight test phase of the autopilot checkout, the yaw servo aggressiveness will be adjusted to get
the desired in-fight performance. The yaw servo gain setting is used to set the aggressiveness of the yaw
servo. A larger number will cause the yaw servo to more aggressively control the aircraft, and a smaller
number will cause the yaw servo to less aggressively control the aircraft.
Figure 8-24 Yaw Damper Configuration Page
Trim Control
The GSA 28 autopilot servos can be used to control the trim system in an aircraft. When the autopilot is
disengaged, the servos can adjust the trim speed based on the current aircraft airspeed. This allows the trim
to run slower at high airspeeds and faster at low airspeeds. When the autopilot is engaged in the air, the
servos can adjust the trim control to minimize the force on the primary controls. This helps ensure the
aircraft will be properly trimmed when the autopilot is later disengaged.
During the flight test phase, the trim system is configured and set up after the primary autopilot
performance has been properly configured. This is done so the pilot can focus on properly adjusting the
performance of the primary autopilot system without having the autotrim functionality interfere.
NOTE
Ensure basic autopilot functionality is properly adjusted before enabling trim control for
any servo.
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8.4.7.2
On-Ground Initial Checkout
NOTE
The following post installation checkout must be followed after every completed installation.
These steps should be followed when using a Garmin mounting kit or non-Garmin mounting
parts to install the GSA 28.
After mounting the GSA 28, please complete the following steps prior to completing the first flight with
the GSA 28.
1. Verify that the flight controls can move from stop to stop without binding or interference. Check
that the GSA 28 output mechanism and added linkage do not come in contact with any part of the
airframe while traveling through its full range of motion.
2. Verify that the travel of the flight controls is being limited by the airplane’s primary stops and not
the secondary stops provided by the GSA 28 stop bracket.
3. Ensure the structural integrity of the mounting bracket is adequate for the application and well
secured to the airframe. Bracket deflection caused by normal servo loading and aircraft
acceleration/vibration should be minimal. Verify there are no cracks or sharp inside corners that
could lead to fatigue failures.
4. Verify the fasteners used to mount the servo to the airframe are installed and have been tightened.
5. Make sure the AP DISC wire is correctly wired and tested.
6. If powering the servo through a “pullable” circuit breaker (recommended), ensure the circuit
breaker is both accessible and easily identifiable to the pilot.
7. Repeat steps 1-6 for all GSA 28 servos in the aircraft.
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8.4.7.3
On-Ground Setup
Servo Wiring Checkout
The first phase of setting up the autopilot system is to verify the proper wiring of the GSA 28 servos while
on the ground.
1. If the installation is a 1-axis (roll only) autopilot, use the Flight Controls Configuration page to
configure the autopilot servos for roll only.
2. If the installation is a 2-axis (pitch and roll) autopilot, use the Flight Controls Configuration page
to configure the autopilot servos for pitch and roll.
3. If the installation is a 3-axis (pitch, roll, and yaw) autopilot, use the Flight Controls Configuration
page to configure the autopilot servos for pitch and roll and enable the yaw damper.
4. Ensure the pitch, roll, and yaw servos are properly communicating by checking the Device
Information page. Each device should have a green check mark next to it.
Figure 8-25 Device Information Page
5. Select the Autopilot Roll Servo Configuration page and verify the proper trim activity with the
servo connected to an auxiliary trim motor.
Figure 8-26 Autopilot Roll Servo Configuration Page
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a) Center the aileron trim switch to input no trim command. Verify the aileron trim switch is
not moving. Verify the roll servo is properly indicating no trim activity.
b) Use the aileron trim switch to input a roll right trim command. Verify the aileron trim
switch properly moves for roll right trim. Verify the roll servo is properly indicating roll
right trim activity.
c) Use the aileron trim switch to input a roll left trim command. Verify the aileron trim switch
properly moves for roll left trim. Verify the roll servo is properly indicating roll left trim
activity.
d) If the aileron trim response is reversed, select Reverse for the Trim Motor Direction, then
repeat all of step 5.
6. Select the Autopilot Pitch Servo Configuration page and verify the proper trim activity with the
servo connected to an auxiliary trim motor.
Figure 8-27 Autopilot Pitch Servo Configuration Page
a) Center the elevator trim switch to input no trim command. Verify the elevator trim switch is
not moving. Verify the pitch servo is properly indicating no trim activity.
b) Use the elevator trim switch to input a nose up trim command. Verify the elevator trim
switch properly moves for nose up trim. Verify the pitch servo is properly indicating nose
up trim activity.
c) Use the elevator trim switch to input a nose down trim command. Verify the elevator trim
switch properly moves for nose down trim. Verify the pitch servo is properly indicating
nose down trim activity.
d) If the elevator trim response is reversed, select Reverse for the Trim Motor Direction, then
repeat all of step 6.
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7. Select the Yaw Damper Configuration page and verify the proper trim activity with the servo
connected to an auxiliary trim motor.
Figure 8-28 Yaw Damper Configuration Page
a) Center the aircraft rudder trim switch to input no trim command. Verify the rudder trim
switch is not moving. Verify the yaw servo is properly indicating no trim activity.
b) Use the rudder trim switch to input a yaw right trim command. Verify the rudder trim
switch properly moves for yaw right trim. Verify the yaw servo is properly indicating yaw
right trim activity.
c) Use the rudder trim switch to input a yaw left trim command. Verify the rudder trim switch
properly moves for yaw left trim. Verify the yaw servo is properly indicating yaw left trim
activity.
d) If the rudder trim response is reversed, select Reverse for the Trim Motor Direction, then
repeat all of step 7.
8. Select the Autopilot Roll Servo Configuration page to configure the servo direction.
a) With the Servo Direction set to Normal, the servo arm should move clockwise to cause a
bank left aileron movement and the servo arm should move counterclockwise to cause a
bank right aileron movement.
b) With the Servo Direction set to Reverse, the servo arm should move clockwise to cause a
bank right aileron movement and the servo arm should move counterclockwise to cause a
bank left aileron movement.
9. Select the Autopilot Pitch Servo Configuration page to configure the servo direction.
a) With the Servo Direction set to Normal, the servo arm should move clockwise to cause a
nose down elevator movement and the servo arm should move counterclockwise to cause a
nose up elevator movement.
b) With the Servo Direction set to Reverse, the servo arm should move clockwise to cause a
nose up elevator movement and the servo arm should move counterclockwise to cause a
nose down elevator movement.
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10. Select the Yaw Damper Configuration page to configure the servo direction.
a) With the Servo Direction set to Normal, the servo arm should move clockwise to cause a
nose left rudder movement and servo arm should move counterclockwise to cause a nose
right rudder movement.
b) With the Servo Direction set to Reverse, the servo arm should move clockwise to cause a
nose right rudder movement and the servo arm should move counterclockwise to cause a
nose left rudder movement.
11. Set the Trim Motor Control to Disabled using the Autopilot Roll Servo, Autopilot Pitch Servo, and
Yaw Damper Configuration pages as applicable.
NOTE
Initial autopilot tuning is done with the trim control disabled to avoid the autotrim function
from interfering with the initial autopilot tuning.
a) By disabling the trim motor control, this will disable autotrim and airspeed scheduled trim,
but the pilot can still control trim in the aircraft using the normal manual electric trim inputs.
Autotrim and airspeed scheduled trim will be setup later in the autopilot setup procedure.
12. The proper minimum and maximum airspeed limits for the pitch servo can be set in the Autopilot
Pitch Servo Configuration page. The pitch servo will lower or raise the nose of the aircraft to keep
the aircraft within these airspeed limits.
a) The minimum airspeed limit should be set above the stall speed of the aircraft with some
margin.
b) The maximum airspeed limit should be set below the never exceed speed of the aircraft with
some margin.
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8.4.7.4
On-Ground Autopilot Setup
The next phase of setting up the Garmin autopilot system is to verify the proper functionality of the
autopilot system on the ground in normal mode. This phase of the checkout requires a valid ground track
and pitch output from the G5. This means the post installation procedures must have already been
completed on the G5 before performing the on-ground autopilot normal mode checkout.
NOTE
If the installation does not include a magnetometer, HDG mode will be replaced by TRK
mode. All other instructions are applicable to either type of installation.
1. Leave the autopilot disengaged and verify the controls can be manipulated smoothly with no
control system binding.
2. Engage the autopilot in HDG/PIT mode and command a nose down, left bank.
a) Press the AP button on the GMC Mode Controller.
b) Press the HDG button on the GMC Mode Controller.
c) Push the knob on the G5 to access the menu.
d) Select Track from the menu on the G5.
e) Push and hold the knob on the G5 to center the HDG bug.
f) Rotate the knob on the G5 counterclockwise to command a left turn.
g) Rotate the wheel on the GMC Mode Controller down to command a pitch downward.
3. Verify the stick properly moves toward the nose and toward the left wing smoothly with no control
system binding.
4. Engage the autopilot in HDG/PIT mode and command a nose down, right bank.
a) Press the AP button on the GMC Mode Controller.
b) Press the HDG button on the GMC Mode Controller.
c) Push the knob on the G5 to access the menu.
d) Select Track from the menu on the G5.
e) Push and hold the knob on the G5 to center the HDG bug.
f) Rotate the knob on the G5 clockwise to command a right turn.
g) Rotate the wheel on the GMC Mode Controller down to command a pitch downward.
5. Verify the stick properly moves toward the nose and toward the right wing smoothly with no
control system binding.
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6. Engage the autopilot in HDG/PIT mode and command a nose up, right bank.
a) Press the AP button on the GMC Mode Controller.
b) Press the HDG button on the GMC Mode Controller.
c) Push the knob on the G5 to access the menu.
d) Select Track from the menu on the G5.
e) Push and hold the knob on the G5 to center the HDG bug.
f) Rotate the knob on the G5 clockwise to command a right turn.
g) Rotate the wheel on the GMC Mode Controller up to command a pitch upwards.
7. Verify the stick properly moves toward the tail and toward the right wing smoothly with no control
system binding.
8. Engage the autopilot in HDG/PIT mode and command a nose up, left bank.
a) Press the AP button on the GMC Mode Controller.
b) Press the HDG button on the GMC Mode Controller.
c) Push the knob on the G5 to access the menu.
d) Select Track from the menu on the G5.
e) Push and hold the knob on the G5 to center the HDG bug.
f) Rotate the knob on the G5 counterclockwise to command a left turn.
g) Rotate the wheel on the GMC Mode Controller up to command a pitch upwards.
9. Verify the stick properly moves toward the tail and toward the left wing smoothly with no control
system binding.
10. If the stick position does not move in the correct direction, correct the roll and pitch servo
directions documented in the Servo Wiring Checkout.
11. Engage the autopilot and verify it can be overpowered in both the pitch and roll axes. If the
autopilot cannot be overpowered, use the Autopilot Roll Servo and Autopilot Pitch Servo
Configuration pages to reduce the Maximum Torque setting for the associated servo.
12. Engage the autopilot and verify that it properly disconnects with a short press and release of the
CWS/DISCONNECT button.
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8.4.7.5
On-Ground Yaw Damper Setup
The next phase of setting up the Garmin autopilot system is to verify the proper functionality of the yaw
damper system on the ground in normal mode. This phase of the checkout requires a valid output from the
G5. This means the post installation procedures must have been completed on the G5 before performing
the on-ground autopilot normal mode checkout.
1. Leave the yaw damper disengaged and verify the rudder pedals can be manipulated smoothly with
no control system binding.
2. Engage the autopilot in YD mode by pressing the YD button on the GMC Mode Controller.
3. Verify the rudder properly moves to the correct direction by standing by the tail of the aircraft,
facing the vertical stabilizer, and pushing on the fuselage. The rudder should move AWAY from
you (the rudder should move in the same direction that the rear fuselage is moving):
a) If the rudder does not move the correct direction, correct the yaw servo direction documented in the Servo Wiring Checkout.
4. Engage the yaw damper and verify it can be overpowered in the yaw axis using rudder pedal
inputs. If the autopilot cannot be overpowered, use the Yaw Damper Configuration page to reduce
the Maximum Torque setting for the yaw damper servo.
5. The CWS/DISCONNECT input can optionally be connected to the Yaw Damper. If this
connection was made, engage the yaw damper and verify that it properly disconnects with a short
press and release of the CWS/DISCONNECT button.
8.4.7.6
In-Air Autopilot Setup
The next phase of setting up the Garmin autopilot system is to verify and tune the proper functionality of
the autopilot system while airborne. Refer to Section 8.4.7.1 for general autopilot use and functionality.
WARNING
This stage of the flight test involves allowing the GSA 28 autopilot servos to manipulate the
flight control surfaces of the aircraft. Extreme caution should be used during the initial
engagement of the autopilot system. The pilot should always have easy access to the autopilot
disconnect button to disconnect the autopilot and take control of the aircraft at anytime.
At a minimum, please follow the following safety guidelines before the initial autopilot engagement:
•
•
•
•
Quick access to autopilot disconnect
Safe altitude above and away from all terrain and obstacles
No air traffic in the area
Safe airspeed below maneuvering speed (VA)
NOTE
If desired, in the following procedures, the expert configurations can be accessed from the
Autopilot Roll Servo, Autopilot Pitch Servo, and Yaw Damper Configuration pages.
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Roll Servo
1. Use the Setup page in normal mode to adjust the roll servo gain setting.
a) Engage the autopilot in ROL/PIT mode with the aircraft approximately level.
i.
Press the AP button on the GMC Mode Controller to engage the AP.
ii. Press the YD button on the GMC Mode Controller to disengage the YD.
b) Press the knob of the G5 to access the menu.
c) Select Setup from the menu.
d) Select the Autopilot Roll Servo page.
e) Select the Servo Gain entry.
f) Adjust the servo gain so that the aircraft properly responds to the roll guidance from the
flight director.
i.
Overpower the autopilot to fly away from the current flight director commanded roll.
ii. Release the controls and monitor the autopilot response and closure back to the commanded roll.
iii. Set the servo gain higher to make the autopilot more aggressive.
iv. Set the servo gain lower to make the autopilot less aggressive.
2. The roll servo has additional expert configurations that can be adjusted to achieve the desired
lateral mode performance. These settings are detailed in Table 8-7 and should only be adjusted
after studying the descriptions to properly understand their effect on the roll servo.
Pitch Servo
1. Use the Setup page in normal mode to adjust the pitch servo gain setting. It is important to ensure
proper autopilot response in PIT mode before proceeding to adjust other autopilot pitch axis gains
and modes (including ALT and VS modes).
a) Engage the autopilot in ROL/PIT mode with the aircraft approximately level.
i.
Press the AP button on the GMC Mode Controller to engage the AP.
ii. Press the YD button on the GMC Mode Controller to disengage the YD.
b) Press the knob on the G5 to access the menu.
c) Select Setup from the menu.
d) Select the Autopilot Pitch Servo page.
e) Select the Servo Gain entry.
f) Adjust the servo gain so that the aircraft properly responds to the pitch guidance from the
flight director.
i.
Overpower the autopilot to fly away from the current flight director commanded pitch.
ii. Release the controls and monitor the autopilot response and closure back to the commanded pitch.
iii. Set the servo gain higher to make the autopilot more aggressive.
iv. Set the servo gain lower to make the autopilot less aggressive.
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2. The pitch servo has additional expert configurations that can be adjusted to achieve the desired
vertical mode performance. These settings are detailed in Table 8-8 and should only be adjusted
after studying the descriptions to properly understand their effect on the pitch servo.
Pitch Servo Gain
The pitch servo gain settings should be configured only after the pitch/roll servo max torque and servo
gains have been set per the preceding pages.
The minimum maximum airspeed limit entries set the limits of the autopilot vertical authority. The
autopilot will limit the pitch control to stay within these airspeed limits.
The vertical speed gain entry is one of the most important gains in the system since it controls the behavior
of the VNAV, ALT, and VS modes and also largely determines how well the plane flies approaches with
vertical guidance.
The vertical speed gain is adjusted in a very similar manner to the pitch servo gain. Engage the autopilot in
ROL/VS mode in level flight (vertical speed approximately zero).
Adjust the vertical speed gain so that the aircraft properly responds to the VS guidance from the flight
director.
1. Overpower the autopilot to fly away from the current flight director commanded vertical speed.
2. Release the controls and monitor the autopilot response and closure back to the commanded
vertical speed.
3. Set the vertical speed gain higher to make the autopilot more aggressive if it feels “lazy” or not as
responsive as desired.
4. Set the vertical speed gain lower to make the autopilot less aggressive if the control is too “harsh”
or more responsive than desired.
The vertical acceleration gain can often be left set at 1.00, but can be used to improve altitude captures
when climbing or descending in VS or VNAV mode.
1. Climb to an altitude target in VS mode and observe the altitude capture.
2. Set the vertical acceleration gain higher if the aircraft objectionably overshoots the altitude target
before leveling off at the correct altitude.
3. Set the vertical acceleration gain lower if the aircraft objectionably undershoots the altitude target
before leveling off at the correct altitude.
Similar to the vertical speed gain, the airspeed gain can be used to improve airspeed hold performance
when needed.
Pitch Gain has advanced and expert configurations that can be adjusted to achieve the desired
performance. These settings are detailed in Table 8-8 and should only be adjusted after studying the
descriptions to properly understand their effect on pitch gain.
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Yaw Damper Setup
The next phase of setting up the Garmin yaw damper system is to verify and tune the proper functionality
of the yaw damper system in the air.
WARNING
This stage of the flight test involves allowing the GSA 28 autopilot servos to manipulate the
flight control surfaces of the aircraft. Extreme caution should be used during the initial
engagement of the autopilot system. The pilot should always have easy access to the autopilot
disconnect button to disconnect the autopilot and take control of the aircraft at anytime.
At a minimum, please follow the following safety guidelines before the initial autopilot engagement:
•
•
•
•
1.
Quick access to autopilot disconnect
Safe altitude above and away from all terrain and obstacles
No air traffic in the area
Safe airspeed below maneuvering speed (VA)
Use the Setup page in normal mode to adjust the yaw damper gain setting.
a) Press the knob on the G5 to access the menu.
b) Select Setup from the menu.
c) Select the Yaw Damper page.
d) Select the Servo Gain entry.
e) Adjust the servo gain so that the aircraft properly responds to the yaw body rates (tail
wagging).
i.
Engage the autopilot in LVL mode with the aircraft approximately level.
ii. Press the LVL button on the GMC Mode Controller to engage the AP in LVL mode.
iii. Press the YD button on the GMC Mode Controller to disengage the YD.
iv. Fly a yaw doublet and engage the YD as the ball swings through the center.
1. Use the right foot rudder to swing the ball left.
2. Use the left foot rudder to swing ball back right.
3. Engage the yaw damper by pressing the YD button on the GMC Mode Controller
as the ball swings through the center.
4. Set the servo gain so the established yaw body rate from the yaw doublet is
properly dampened out.
a) Set the servo gain higher to make the yaw damper more aggressive (if
needed).
b) Set the servo gain lower to make the yaw damper less aggressive (if needed).
2. The yaw servo has additional expert configurations that can be adjusted to achieve the desired yaw
damping performance. These settings are detailed in Table 8-9 and should only be adjusted after
studying the descriptions to properly understand their effect on the yaw servo.
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8.4.7.7
On-Ground Trim System Setup
After setting up and testing the GSA 28 based autopilot and yaw damper systems, the pilot can configure
the trim system.
1. Set the Trim Motor Control to Enabled using the Autopilot Roll Servo, Autopilot Pitch Servo, and
Yaw Damper Configuration pages for all servos that are connected to auxiliary trim motors.
a) The recommended setting for the Fastest Trim Motor Speed is 100% (this value will be
adjusted during the in-air setup).
b) The recommended setting for the Slowest Trim Motor Speed is 25% (this value will be
adjusted during the in-air setup).
NOTE
The Maximum Trim Run Time entry allows optional configuration of a time limit for use with a
manual electric trim. When the manual trim input switch is pressed, the electric trim motor
will stop running after the time limit expires, and will not run again until the trim input switch
is released and pressed again. This can help prevent "trim runway" caused by a stuck trim
input switch. If the maximum trim motor run time is not set, the electric trim motor will run
indefinitely as long as the manual trim input switch is held. Trim run time has no effect on
auto trim.
2. Return to the Flight Controls Configuration page to set the airspeed thresholds for the fastest and
slowest trim movement.
a) The recommended setting for the Trim Low Airspeed Threshold is the airspeed typically
used for cruise flight.
b) The recommended setting for the Trim High Airspeed Threshold is the airspeed typically
used to fly the normal aircraft landing pattern.
3. Re-verify proper trim movement described in Section 8.4.7.3.
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8.4.7.8
In-air Trim System Setup
The next phase of setting up the GSA 28 based trim control system is to verify and set the proper
functionality of the trim system in the air. Refer to Section 8.4.7.1 for general autopilot use and
functionality.
WARNING
This stage of the flight test involves allowing the GSA 28 autopilot servos to manipulate the
flight control surfaces of the aircraft. Extreme caution should be used during this phase of
the flight test. The pilot should always have easy access to the autopilot disconnect button
to disconnect the autopilot and take control of the aircraft at anytime.
At a minimum, please follow the following safety guidelines before the initial autopilot engagement:
•
•
•
•
1.
Quick access to autopilot disconnect
Safe altitude above and away from all terrain and obstacles
No air traffic in the area
Safe airspeed below maneuvering speed (VA)
Use the Setup page in normal mode to adjust the trim motor speed to get the desired manual
electric trim response.
a) Press the knob on the G5 to access the menu.
b) Select Setup from the menu.
c) Note the low and high airspeed threshold settings on this page.
d) Select the Autopilot Roll Servo, Autopilot Pitch Servo, or Yaw Damper pages as applicable.
e) Adjust the trim motor speeds at the two airspeed thresholds to get a desirable trim response.
i.
Trim aircraft using manual electric trim inputs
ii. Trim response should not be overly slow
iii. Trim response should not be overly fast
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8.4.7.9
Autopilot Configuration Options
The installer needs to make the following autopilot configuration selections when setting up the GSA 28
based autopilot system.
Flight Controls Configuration Page
These selections are made in configuration mode using the Flight Controls page.
Figure 8-29 Automatic Flight Control Configuration Page
Table 8-6 Flight Control Configuration Settings
Configuration
Setting
Description
Trim Low Airspeed
Threshold
The GSA 28 servos are capable of airspeed scheduling the aircraft’s manual
electric trim.
The Trim Low Airspeed Threshold setting is the airspeed at which the trim motor
will be moved at its fastest setting. This should be the lower of the two airspeeds.
The recommended setting for the Trim Low Airspeed Threshold is the airspeed
typically used for cruise flight.
Trim High Airspeed
Threshold
The GSA 28 servos are capable of airspeed scheduling the aircraft’s manual
electric trim.
The Trim High Airspeed Threshold setting is the airspeed at which the trim motor
will be moved at its slowest setting. This should be the higher of the two
airspeeds. The recommended setting for the Trim High Airspeed Threshold is
the airspeed typically used to fly the normal aircraft landing pattern.
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Table 8-6 Flight Control Configuration Settings
Configuration
Setting
Description
Control Wheel
Steering
The CWS/DISCONNECT discrete input to the GSA 28 servos is connected to a
momentary push button which can function either as a dedicated Autopilot
Disconnect (AP DISC) button, or as a combined Autopilot Disconnect / Control
Wheel Steering (AP/CWS) button.
Regardless of configuration, a short press and release of the AP DISC or AP/
CWS button will disengage the autopilot if it is engaged.
If Control Wheel Steering is enabled, pressing and holding the AP/CWS button
places the autopilot into CWS mode. In CWS mode, the servos are temporarily
disengaged, allowing hand-flying of the aircraft to a new aircraft attitude while the
AP/CWS button is held. When the AP/CWS button is released, the autopilot
exits CWS mode and the flight director synchronizes to the current aircraft
attitude (if applicable for the current flight director mode).
If Control Wheel Steering is disabled, CWS is not supported and the AP button
serves as a dedicated AP DISC button only. The AP DISC button will disconnect
the autopilot any time it is pressed, regardless of how long it is held.
Engage AP Via
CWS Input
If Control Wheel Steering is enabled, the AP/CWS button can optionally be
configured to engage the autopilot when pressed and held.
If Engage AP Via CWS Input is enabled, the autopilot will automatically engage
when the AP/CWS button is pressed and held.
If Engage AP Via CWS Input is disabled, pressing the AP/CWS button while the
autopilot is not engaged has no effect. In this state, the autopilot can only be
engaged using the GMC Mode Controller AP button.
AFCS Setup Page
Controls access to the Automatic Flight Control System Setup page in normal
mode. Leave this item set to Enabled unless specifically required for the
installation.
190-02072-01
Rev. 5
G5 Installation Manual
Page 8-40
Roll Servo Configuration Page
The installer needs to make the following roll servo configuration selections when setting up the GSA 28
based autopilot system. All selections are available in configuration mode using the Autopilot Roll Servo
Configuration page. Selections available in the normal mode Setup menu are noted with an asterisk in
Table 8-7.
Figure 8-30 Automatic Roll Servo Configuration Page
Table 8-7 Autopilot Roll Servo Configuration Settings
Configuration
Setting
Description
Maximum Torque*
The GSA 28 roll servo has a configurable maximum torque setting. This
determines how much torque the servo will output before the electronic slip
clutch begins to slip.
The Maximum Torque setting should be set high enough to not slip during inflight air loading, but low enough for the pilot to override the autopilot if required.
The Maximum Torque setting can be adjusted from 15% to 100% in 5% steps.
Servo Gain*
The GSA 28 roll servo has a configurable servo gain setting. This determines
how aggressively the roll servo will move the aileron surfaces.
The Servo Gain should be set high enough to properly fly the desired roll,
heading, and track, but low enough to avoid being overly aggressive in the
aileron movements.
The servo gain setting can be adjusted from 0.00 to 10.00 in steps of 0.05.
*Available in normal mode
190-02072-01
Rev. 5
G5 Installation Manual
Page 8-41
Table 8-7 Autopilot Roll Servo Configuration Settings
Configuration
Setting
Description
Servo Direction
The GSA 28 roll servo has a configurable servo direction.
The Servo Direction should be set to Normal if a clockwise movement of the
servo arm causes a bank left aileron movement.
The Servo Direction should be set to Reverse if a counterclockwise movement of
the servo arm causes a bank left aileron movement.
After selecting the proper servo direction, the installer should engage the
autopilot system in normal mode and verify proper aileron response by using
HDG/TRK mode and rotating the track bug to the left and to the right of the
current track.
Clutch Monitor
The GSA 28 roll servo has the ability to monitor itself for a stuck clutch situation.
If the servo has a large amount of side loading (typically due to a capstan
installation), this can occasionally lead to invalid stuck clutch failures.
The Clutch Monitor should be enabled for all control arm installations.
The Clutch Monitor can be disabled for capstan installations with larger side
loads to prevent invalid stuck clutch failures.
Trim Motor Control
The GSA 28 roll servo has the ability to control an auxiliary roll trim motor.
The Trim Motor Control should be enabled if the GSA 28 roll servo is connected
to an auxiliary trim motor.
The Trim Motor Control should be disabled if the GSA 28 roll servo is not
connected to an auxiliary trim motor.
Trim Motor
Direction
The GSA 28 roll servo has a configurable trim motor direction. Select the Normal
or Reversed setting depending on which is required for the proper trim motor
movement when using the aircraft trim motor switches on the ground with the
autopilot disengaged (servos powered).
Trim Low Airspeed
Thresh
This setting specifies the airspeed below which the trim motor is always run at
the Fasted Trim Motor Speed specified below.
Trim High Airspeed
Thresh
This setting specifies the airspeed above which the trim motor is always run at
the Slowest Trim Motor Speed specified below.
Fastest Trim Motor
Speed
The GSA 28 roll servo will control the aileron trim on the aircraft.
The Fastest Trim Motor Speed is the speed at which the roll servo will run the
auxiliary trim motor when at or below the Trim Low Airspeed Thresh airspeed.
Expressed as a percentage of the maximum auxiliary trim motor speed. The
Fastest Trim Motor Speed can be adjusted from 5% to 100% in 5% steps.
Slowest Trim Motor
Speed
The GSA 28 roll servo will control the aileron trim on the aircraft.
The Slowest Trim Motor Speed is the speed at which the roll servo will run the
auxiliary trim motor when at or above the Trim High Airspeed Thresh airspeed.
Expressed as a percentage of the maximum auxiliary trim motor speed. The
Slowest Trim Motor Speed can be adjusted from 5% to 100% in 5% steps.
*Available in normal mode
190-02072-01
Rev. 5
G5 Installation Manual
Page 8-42
Table 8-7 Autopilot Roll Servo Configuration Settings
Configuration
Setting
Description
Slowest Auto Trim
Motor Speed
(expert
configuration)
The GSA 28 roll servo has the ability to drive the auxiliary trim motor at various
speeds.
The Slowest Auto Trim Motor Speed should be set so the auxiliary trim motor will
move as slowly as possible. The slowest possible movement will ensure that
there is no noticeable aircraft response when the auxiliary trim motor is run
during autotrim.
The Slowest Auto Trim Motor Speed can be adjusted from 5% to 100% in 5%
steps.
Maximum Trim Run
Time
The GSA 28 servos can limit the maximum continuous run time of the trim motor.
This can be used to help prevent the potential for a trim runaway situation.
The Maximum Trim Run Time Limit is the maximum amount of time the trim
servo will be run continuously when a manual electric trim input is detected. If
the maximum time is exceeded, the pilot will need to release the Manual Electric
Trim (MET) control and then reassert it to continue running trim.
Fine Adjust Amount
(expert
configuration)
The GSA 28 roll servo is capable of making very small adjustments to fine tune
the aileron position. The Fine Adjust Amount is the amount in which these
adjustments are made. Use the Fine Adjust Amount and Fine Adjust Time to
correct very small oscillations in the aircraft.
Fine Adjust Amount is an expert configuration setting, and should generally be
not be changed by the installer. The default value is 0.
Fine Adjust Time
(expert
configuration)
The GSA 28 roll servo is capable of making very small adjustments to fine tune
the aileron position. The Fine Adjust Time is the rate at which these adjustments
are made. Use the Fine Adjust Amount and Fine Adjust Time to correct very
small oscillations in the aircraft.
Fine Adjust Time is an expert configuration setting, and should generally be not
be changed by the installer. The default value is 0.20.
*Available in normal mode
190-02072-01
Rev. 5
G5 Installation Manual
Page 8-43
Pitch Servo Configuration Page
The installer needs to make the following pitch servo configuration selections when setting up the GSA 28
based autopilot system. All selections are available in configuration mode using the Autopilot Pitch Servo
page. Selections available in the normal mode Setup menu are noted with an asterisk in Table 8-8.
Figure 8-31 Automatic Pitch Servo Configuration Page
Table 8-8 Autopilot Pitch Servo Configuration Settings
Configuration
Setting
Description
Maximum Torque*
The GSA 28 pitch servo has a configurable maximum torque setting. This
determines how much torque the servo will output before the electronic slip
clutch begins to slip.
The Maximum Torque setting should be set high enough to not slip during inflight air loading, but low enough for the pilot to override the autopilot if required.
The Maximum Torque setting can be adjusted from 15% to 100% in 5% steps.
Servo Gain*
The GSA 28 pitch servo has a configurable servo gain setting. This determines
how aggressively the pitch servo will move the elevator surfaces.
The Servo Gain should be set high enough to properly fly the desired pitch,
vertical speed, and altitude, but low enough to avoid being overly aggressive in
the elevator movements.
The servo gain setting can be adjusted from 0.00 to 10.00 in steps of 0.05.
Servo Direction
The GSA 28 pitch servo has a configurable servo direction.
The Servo Direction should be set to Normal if a clockwise movement of the
servo arm causes a nose down elevator movement.
The Servo Direction should be set to Reverse if a counterclockwise movement of
the servo arm causes a nose down elevator movement.
After selecting the proper servo direction, the installer should engage the
autopilot system in normal mode and verify proper elevator response by rotating
the pitch reference up and down from the current pitch.
*Available in normal mode
190-02072-01
Rev. 5
G5 Installation Manual
Page 8-44
Table 8-8 Autopilot Pitch Servo Configuration Settings
Configuration
Setting
Description
Clutch Monitor
The GSA 28 pitch servo has the ability to monitor itself for a stuck clutch
situation.
If the servo has a large amount of side loading (typically due to a capstan
installation), this can occasionally lead to invalid stuck clutch failures.
The Clutch Monitor should be enabled for all control arm installations.
The Clutch Monitor can be disabled for capstan installations with larger side
loads to prevent invalid stuck clutch failures.
Trim Motor Control
The GSA 28 pitch servo has the ability to control an auxiliary pitch trim motor.
The Trim Motor Control should be enabled if the GSA 28 pitch servo is connected
to an elevator trim motor.
The Trim Motor Control should be disabled if the GSA 28 pitch servo is not
connected to an auxiliary trim motor.
Trim Motor
Direction
The GSA 28 pitch servo has a configurable trim motor direction. Select the
Normal or Reversed setting depending on which is required for the proper trim
motor movement when using the aircraft trim motor switches on the ground with
the autopilot disengaged (servos powered).
Fastest Trim Motor
Speed
The GSA 28 pitch servo will control the elevator trim on the aircraft.
The Fastest Trim Motor Speed is the speed at which the pitch servo will run the
auxiliary trim motor when at or below the corresponding airspeed.
Expressed as a percentage of the maximum auxiliary trim motor speed. The
Fastest Trim Motor Speed can be adjusted from 5% to 100% in 5% steps.
Slowest Trim Motor
Speed
The GSA 28 pitch servo will control the elevator trim on the aircraft.
The Slowest Trim Motor Speed is the speed at which the pitch servo will run the
auxiliary trim motor when at or above the corresponding airspeed.
Expressed as a percentage of the maximum auxiliary trim motor speed. The
Slowest Trim Motor Speed can be adjusted from 5% to 100% in 5% steps
Slowest Auto Trim
Motor Speed
(expert
configuration)
The GSA 28 pitch servo has the ability to drive the auxiliary trim motor at various
speeds.
The Slowest Auto Trim Motor Speed should be set so the auxiliary trim motor will
move as slowly as possible. The slowest possible movement will ensure that
there is no noticeable aircraft response when the auxiliary trim motor is run
during autotrim.
The Slowest Auto Trim Motor Speed can be adjusted from 5% to 100% in 5%
steps.
Maximum Trim Run
Time
The GSA 28 servos can limit the maximum continuous run time of the trim motor.
This can be used to help prevent the potential for a trim runaway situation.
The Maximum Trim Run Time Limit is the maximum amount of time the trim
servo will be run continuously when a manual electric trim input is detected. If
the maximum time is exceeded, the pilot will need to release the Manual Electric
Trim (MET) control and then reassert it to continue running trim.
*Available in normal mode
190-02072-01
Rev. 5
G5 Installation Manual
Page 8-45
Table 8-8 Autopilot Pitch Servo Configuration Settings
Configuration
Setting
Description
Fine Adjust Amount
(expert
configuration)
The GSA 28 pitch servo is capable of making very small adjustments to fine tune
the elevator position. The Fine Adjust Amount is the amount in which these
adjustments are made. Use the Fine Adjust Amount and Fine Adjust Time to
correct very small oscillations in the aircraft.
Fine Adjust Amount is an expert configuration setting, and should generally be
not be changed by the installer. The default value is 0.
Fine Adjust Time
(expert
configuration)
The GSA 28 pitch servo is capable of making very small adjustments to fine tune
the elevator position. The Fine Adjust Time is the rate at which these
adjustments are made. Use the Fine Adjust Amount and Fine Adjust Time to
correct very small oscillations in the aircraft.
Fine Adjust Time is an expert configuration setting, and should generally be not
be changed by the installer. The default value is 0.20.
Minimum Airspeed
Limit*
The GSA 28 pitch servo has a configurable minimum airspeed limit. This
determines the lowest airspeed at which the pitch servo will allow the aircraft to
fly. If the airspeed drops below this limit, the pitch servo will lower the nose of the
aircraft to keep the airspeed at or above the Minimum Airspeed Limit.
The Minimum Airspeed Limit should be set above the aircraft stall speed with
some margin.
Maximum Airspeed
Limit*
The GSA 28 pitch servo has a configurable maximum airspeed limit. This
determines the fastest airspeed at which the pitch servo will allow the aircraft to
fly. If the airspeed rises above this limit, the pitch servo will raise the nose of the
aircraft to keep the airspeed at or below the Maximum Airspeed Limit.
The Maximum Airspeed Limit should be set below the aircraft maximum speed
with some margin.
Vertical Speed
Gain*
The GSA 28 pitch servo is capable of holding the aircraft at a desired vertical
speed.
The Vertical Speed Gain should be increased if the aircraft struggles to hold the
desired vertical speed target when the flight director is in VS, ALT, or LVL modes.
The Vertical Speed Gain should be decreased if the aircraft is overly aggressive
when trying to hold the desired vertical speed.
Vertical
Acceleration Gain*
The GSA 28 pitch servo is capable of holding the aircraft at a desired vertical
speed.
The Vertical Acceleration Gain should be increased if the aircraft is overshooting
the desired vertical speed target when closing on the bug when the flight director
is in VS mode.
The Vertical Acceleration Gain should be decreased if the aircraft appears to
back off from the desired vertical speed target when closing on the bug.
*Available in normal mode
190-02072-01
Rev. 5
G5 Installation Manual
Page 8-46
Table 8-8 Autopilot Pitch Servo Configuration Settings
Configuration
Setting
Description
Airspeed Gain*
The GSA 28 pitch servo is capable of holding the aircraft at a desired airspeed.
The Airspeed Gain should be increased if the aircraft is lazy and struggles to hold
the desired airspeed target when the flight director is in IAS mode.
The Airspeed Gain should be decreased if the aircraft is overly aggressive when
trying to hold the desired airspeed target.
Airspeed
Acceleration Gain
(expert
configuration)
The GSA 28 pitch servo is capable of holding the aircraft at a desired airspeed.
The Airspeed Acceleration Gain should be increased if the aircraft is
overshooting the desired airspeed target when closing on the bug when the flight
director is in IAS mode.
The Airspeed Acceleration Gain should be increased if the aircraft appears to
back off from the desired airspeed target when closing on the bug.
Airspeed Tracking
Gain (expert
configuration)
The GSA 28 pitch servo is capable of holding the aircraft at a desired airspeed.
The Airspeed Tracking Gain should be increased if the aircraft is overly sluggish
while tracking airspeed when the airspeed error is less than 5 knots.
The Airspeed Tracking Gain should be decreased if the aircraft is overly
aggressive while tracking airspeed when the airspeed error is less than 5 knots.
*Available in normal mode
190-02072-01
Rev. 5
G5 Installation Manual
Page 8-47
Yaw Damper Configuration Page
The installer needs to make the following yaw damper configuration selections when setting up the
GSA 28 based autopilot system. All selections are available in configuration mode using the Yaw Damper
page. Selections available in the normal mode Setup menu are noted with an asterisk in Table 8-9.
Figure 8-32 Yaw Damper Configuration Page
Table 8-9 Yaw Damper Configuration Settings
Configuration
Setting
Description
Maximum Torque*
The GSA 28 yaw damper has a configurable maximum torque setting. This
determines how much torque the servo will output before the electronic slip
clutch begins to slip.
The Maximum Torque setting should be set high enough to not slip during inflight air loading, but low enough for the pilot to override the autopilot if required.
The Maximum Torque setting can be adjusted from 15% to 100% in 5% steps.
Servo Gain*
The GSA 28 yaw damper has a configurable servo gain setting. This determines
how aggressively the yaw servo will move the rudder surface.
The Servo Gain should be set high enough to dampen the yaw rates, but low
enough to avoid being overly aggressive in the rudder movements.
The servo gain setting can be adjusted from 0.00 to 10.00 in steps of 0.05.
Servo Direction
The GSA 28 yaw damper has a configurable servo direction.
The Servo Direction should be set to Normal if a clockwise movement of the
servo arm causes a nose left rudder movement.
The Servo Direction should be set to Reverse if a counterclockwise movement of
the servo arm causes a nose left rudder movement.
After selecting the proper servo direction, the installer should engage the yaw
damper in normal mode and verify proper rudder response by the tail of the
aircraft back and forth.
*Available in normal mode
190-02072-01
Rev. 5
G5 Installation Manual
Page 8-48
Table 8-9 Yaw Damper Configuration Settings
Configuration
Setting
Description
Clutch Monitor
The GSA 28 yaw damper has the ability to monitor itself for a stuck clutch
situation.
If the servo has a large amount of side loading (typically due to a capstan
installation), this can occasionally lead to invalid stuck clutch failures.
The Clutch Monitor should be enabled for all control arm installations.
The Clutch Monitor can be disabled for capstan installations with larger side
loads to prevent invalid stuck clutch failures.
Trim Motor Control
The GSA 28 yaw damper has the ability to control an auxiliary rudder trim motor.
The Trim Motor Control should be enabled if the GSA 28 yaw damper is
connected to an elevator trim motor.
The Trim Motor Control should be disabled if the GSA 28 yaw damper is not
connected to an auxiliary trim motor.
Trim Motor
Direction
The GSA 28 yaw servo has a configurable trim motor direction. Select the
Normal or Reversed setting depending on which is required for the proper trim
motor movement when using the aircraft trim motor switches on the ground with
the autopilot disengaged (servos powered).
Fastest Trim Motor
Speed
The GSA 28 yaw servo will control the rudder trim on the aircraft.
The Fastest Trim Motor Speed is the speed at which the yaw damper will run the
auxiliary trim motor when at or below the corresponding airspeed.
Expressed as a percentage of the maximum auxiliary trim motor speed. The
Fastest Trim Motor Speed can be adjusted from 5% to 100% in 5% steps.
Slowest Trim Motor
Speed
The GSA 28 yaw servo will control the rudder trim on the aircraft.
The Slowest Trim Motor Speed is the speed at which the yaw damper will run the
auxiliary trim motor when at or above the corresponding airspeed.
Expressed as a percentage of the maximum auxiliary trim motor speed. The
Slowest Trim Motor Speed can be adjusted from 5% to 100% in 5% steps.
Slowest Auto Trim
Motor Speed
(expert
configuration)
The GSA 28 yaw damper has the ability to drive the auxiliary rudder trim motor at
various speeds.
The Slowest Auto Trim Motor Speed should be set so the auxiliary trim motor will
move as slowly as possible. The slowest possible movement will ensure that
there is no noticeable aircraft response when the auxiliary trim motor is run
during autotrim.
The Slowest Auto Trim Motor Speed can be adjusted from 5% to 100% in 5%
steps.
Maximum Trim Run
Time
The GSA 28 servos can limit the maximum continuous run time of the trim motor.
This can be used to help prevent the potential for a trim runaway situation.
The Maximum Trim Run Time Limit is the maximum amount of time the trim
servo will be run continuously when a manual electric trim input is detected. If
the maximum time is exceeded, the pilot will need to release the Manual Electric
Trim (MET) control and then reassert it to continue running trim.
*Available in normal mode
190-02072-01
Rev. 5
G5 Installation Manual
Page 8-49
Table 8-9 Yaw Damper Configuration Settings
Configuration
Setting
Description
Ball Centering Gain
(expert
configuration)
The GSA 28 yaw damper is capable of zeroing the aircraft’s lateral acceleration
or centering the ball as well as dampening aircraft yaw rates.
Ball Centering Gain is an expert configuration setting and should only be
changed by the installer if the yaw damper is not properly zeroing the aircraft’s
lateral acceleration.
Increasing the Ball Centering Gain will cause the yaw damper to more
aggressively respond to non-zero lateral acceleration. Decreasing the Ball
Centering Gain will cause the yaw damper to respond less aggressively to nonzero lateral acceleration.
Yaw Rate Filter
Constant (expert
configuration)
The GSA 28 yaw damper is capable of dampening yaw body rates to keep the
aircraft from shaking its tail. The Yaw Rate Filter Constant is used to filter the
aircraft yaw body rate.
Yaw Rate Filter Constant is an expert configuration setting, and should generally
be not be changed by the installer. The default value is 0.08.
Yaw Acceleration
Filter Constant
(expert
configuration)
The GSA 28 yaw damper is capable of zeroing the lateral acceleration of the
aircraft. The Yaw Acceleration Filter Constant is used to filter the aircraft lateral
acceleration.
Yaw Acceleration Filter Constant is an expert configuration setting, and should
generally be not be changed by the installer. The default value is 0.16.
*Available in normal mode
190-02072-01
Rev. 5
G5 Installation Manual
Page 8-50
8.4.8
Flight Director Configuration Page
This page allows for configuration of certain options for the flight director. It will only appear in
installations that include an autopilot.
Figure 8-33 Flight Director Configuration Page
Table 8-10 Flight Director Configuration Settings
Configuration
Setting
Description
Indicator Type
Controls whether the flight director command indicator on the PFD uses a singlecue or dual-cue presentation.
Altitude Controls
Select Normal (default) or Simplified. Selecting Simplified results in a simpler set
of behaviors for altitude hold mode.
When Altitude Controls is set to Normal, ALT Mode User Select Action and ALT
Mode User Up/Down Action will appear.
When Altitude Controls is set to Simplified, the ALT Mode User Select Action and
ALT Mode User Up/Down Action settings do not appear. In their places,
selections for the default climb and descent vertical speeds are displayed.
ALT Mode User
Select Action
Select Normal or Sync Selected Altitude. This setting controls the actions that
occur when the user selects altitude hold mode by pressing the ALT key on the
GMC Mode Controller. When set to Sync Selected Altitude, the selected altitude
(altitude bug) will be automatically set to the current aircraft altitude when the
user selects altitude hold mode manually by pressing the ALT key on the GMC
Mode Controller.
ALT Mode User Up/
Down Action
Select Normal or Select VS Mode. This setting controls the actions that occur
when the flight director is in altitude hold mode and the user moves the pitch
wheel on the GMC Mode Controller. When set to Select VS Mode, moving the
pitch wheel on the GMC Mode Controller results in a change to VS mode for a
climb or descent to a new altitude.
Maximum Bank
Angle
Used to limit the maximum roll attitude commanded by the flight director for
aircraft that have unusual attitude limitations. This setting should not be adjusted
from the default of 30° except for very high performance aircraft that have bank
angle limitations at high speeds.
190-02072-01
Rev. 5
G5 Installation Manual
Page 8-51
8.4.9
Electronic Stability Protection Configuration Page
This page allows for configuration of certain options for the ESP (Electronic Stability Protection) function.
It will only appear in installations that include an autopilot with Garmin servos. ESP is an optionally
enabled feature that is intended to assist the pilot in maintaining the aircraft in a stable flight condition.
This feature will only function when the aircraft is above 200 feet AGL and the autopilot is not engaged.
ESP engages when the aircraft exceeds one or more conditions (pitch, roll, airspeed) beyond the normal
flight parameters. Enhanced stability for each condition provides a force to the appropriate control surface
to return the aircraft to the normal flight envelope. This is perceived by the pilot as resistance to control
movement in the undesired direction when the aircraft approaches a steep attitude or high airspeed. As the
aircraft deviates further from the normal attitude and/or airspeed, the force increases (up to an established
maximum) to encourage control movement in the direction necessary to return to the normal attitude and/
or airspeed range.
See the G5 Pilot’s Guide (190-02072-00) for details of ESP operation.
Table 8-11 ESP Configuration Settings
Configuration
Setting
Description
Roll Attitude
Protection
Select Enabled or Disabled (all other fields remain blank when Disabled).
Roll Limit
Enter desired Bank Limit of aircraft (range 45°to 60°, this limit will appear as
Guardrails on the PFD.
Pitch Attitude
Protection
Select Enabled or Disabled.
Pitch Up Limit
Enter desired Pitch Limit of aircraft. Allowable range of +10° to +25° (default
setting +20°)
Pitch Down Limit
Enter desired Pitch Limit of aircraft. Allowable range of -10°to -25° (default
setting -15°)
Airspeed Protection
Select Enabled or Disabled.
Note that the minimum airspeed setting should be set to a value lower than the
minimum airspeed that is anticipated during approach while above 200 ft AGL.
Minimum Airspeed
Limit
Enter minimum airspeed of aircraft, minimum setting is 50 kt
Maximum Airspeed
Limit
Enter maximum airspeed of aircraft, maximum setting is 999 kt
Default ESP
Powerup State
Select Enabled or Disabled. Setting determines whether the ESP is functioning
upon power up. If disabled, ESP can still be enabled in normal operating mode.
Auto Engage LVL
Mode
Select Enabled or Disabled. When enabled, the autopilot will engage with the
flight director in Level Mode to bring the aircraft into level flight if ESP has been
engaged for more than 15 seconds of a 30 second time period.
190-02072-01
Rev. 5
G5 Installation Manual
Page 8-52
8.4.10 Backlight Configuration Page
Figure 8-34 Backlight Configuration Page
Table 8-12 Backlight Configuration Settings
Configuration
Setting
Description
Current Mode
Used to set the backlight mode to automatic or manual. This setting is also
available at any time by pressing the power button.
Automatic mode sets the backlight intensity (display brightness) based on the
photocell (ambient light sensor) input on the G5. Manual mode allows for setting
the backlight intensity by changing the Backlight percentage directly. Manual
brightness control is available at any time by pressing the power button.
Default Mode
Used to set the backlight mode that will be active each time the unit is powered
on.
Minimum Photocell
Input
Sets the photocell reading that will result in the minimum display brightness in
automatic mode. The default is 10%.
Minimum Display
Brightness
Sets the minimum display brightness setting that will occur in automatic mode.
The default value is 20%.
Maximum Photocell
Input
Sets the photocell reading that will result in the maximum display brightness in
automatic mode. The default is 70%.
Maximum Display
Brightness
Sets the maximum display brightness setting that will occur in automatic mode.
The default value is 100%.
Filter Time
Constant
Adjusts the speed (in seconds) that the brightness level responds to changes in
the photocell input.
Photocell Input
Displays the current input on the unit's light sensor (0%-100%).
Display/Manual
Brightness
Displays the current backlight level (0%-100%). Naming convention depends on
the current backlight mode selected.
190-02072-01
Rev. 5
G5 Installation Manual
Page 8-53
8.4.11 Display Configuration Page
Figure 8-35 Display Configuration Page
Table 8-13 Display Configuration Settings
Configuration
Setting
Description
HSI Page
Enables and disables access to the HSI page in normal mode.
Powerup Page
Sets the default page (PFD or HSI) displayed at unit power on. The HSI page
cannot be configured as the default powerup page on the #1 G5 in a G3X
system.
190-02072-01
Rev. 5
G5 Installation Manual
Page 8-54
8.4.12 Battery Configuration Page
Figure 8-36 Battery Status Page
In addition to the configuration settings listed in Table 8-14, this page also displays the following
battery information:
Battery Status
Charge Level
Temperature
Voltage
Charge Cycles
Lifetime Remaining
Table 8-14 Battery Configuration Settings
Configuration
Setting
Description
Show Battery
Status
Select When Using Battery to only display the status of the G5 backup battery
when the unit is operating from the battery (i.e. aircraft power has been
removed).
Select Always to constantly display the status of the G5 backup battery. The
battery status will be displayed regardless of the status of aircraft power or
whether a battery is connected to the G5.
Automatic Power
Off
Select Always to initiate the external power lost countdown timer anytime the G5
loses power.
Select On Ground Only to initiate the external power lost countdown timer only
when the G5 loses power and the airspeed is less than 20 kts.
190-02072-01
Rev. 5
G5 Installation Manual
Page 8-55
8.4.13 GPS Configuration Page
Figure 8-37 GPS Configuration Page
Table 8-15 GPS Configuration Settings
Configuration
Setting
Description
Internal GPS
Receiver
Enables and disables the internal GPS receiver on the G5. The internal receiver
is typically disabled in installations where the mounting location leads to poor
GPS reception and an external GPS antenna is not installed.
When the internal GPS receiver is disabled, the G5 is still able to receive GPS
data from an external navigation source such as other Garmin LRUs (e.g.
GDU37X/4XX, GPS 20A, or secondary G5).
GPS Status
Displays the status of the internal GPS receiver on the G5. A green check mark
indicates a valid GPS fix has been acquired.
External Antenna
Displays the connection status of the external GPS antenna (if equipped).
GPS Data Fields
Shows and hides the GPS data from the PFD. When hidden, GPS data is still
used for attitude validation (when available).
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8.4.13.1 GPS Signal Reception
G5 installations generally have better GPS reception when using an external GPS antenna versus the
internal GPS antenna. The GPS Configuration page can be used to determine the quality of GPS reception
using either antenna. Gray signal strength bars and the lack of a green check mark indicate weak GPS
signal reception. Green bars and a green check mark indicate good GPS signal reception. Taller bars
indicate better reception than shorter bars. More signal strength bars produce a better position fix than
fewer bars.
Figure 8-38 shows an example of an installation that receives inadequate GPS signal reception (note that
all signal strength bars are gray indicating weak signal). The received signal is not sufficient to improve the
attitude measurement, although it is sufficient to determine and display the basic track and ground speed
information.
Figure 8-38 GPS Configuration Page Showing Inadequate Signal Reception
Figure 8-39 is an example of an installation with marginally acceptable GPS signal reception. Five or more
green signal strength bars must be consistently displayed before the G5 can use GPS data to improve the
attitude measurement.
Figure 8-39 GPS Configuration Page Showing Marginally Acceptable Signal Reception
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Figure 8-40 is an example of an installation that has good GPS signal reception with many more than the
minimum required five green signal strength bars displayed. A 3D Differential position fix is the goal for
G5 installations when using the internal GPS receiver. A 3D Differential position fix cannot be calculated
in areas/countries that do not use SBAS (Satellite Based Augmentation Systems), in those areas, receiving
the most green bars is the most important indication.
Figure 8-40 GPS Configuration Page Showing Good Signal Reception
8.4.13.2 Testing the GPS Receiver for COM Interference
This test must be conducted outside, as the use of a GPS repeater inside a hangar may result in a failed test.
1. Ensure a valid GPS position fix is obtained by monitoring the GPS status. The following status
indications are valid fixes for this test.
◦
◦
2.
3.
4.
5.
3D Fix
3D Differential
Select 121.150 MHz on the COM transceiver.
Transmit for a period of 30 seconds while monitoring the GPS status.
During the transmit period, verify that the GPS status does not lose a valid GPS position fix.
Repeat steps 2 through 4 for the following frequencies:
◦
◦
◦
◦
◦
121.175 MHz
121.200 MHz
131.250 MHz
131.275 MHz
131.300 MHz
6. Repeat steps 2 through 5 for all other installed COM transceivers (if applicable).
7. If an installed COM supports 8.33 MHz channel spacing, increase the transmit period to 35
seconds and repeat steps 3 through 5 for the following frequencies:
◦
◦
◦
◦
121.185 MHz
121.190 MHz
130.285 MHz
131.290 MHz
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8. Repeat step 7 for all other installed COM transceivers supporting 8.33 MHz channel spacing (if
applicable).
NOTE
The signal strength bars at the bottom of the GPS Configuration page are a real-time
representation of GPS signal strength, which may be useful for troubleshooting a failed COM
interference test.
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8.4.13.3 Navigation Configuration Page
This page is only available if a navigation data source is configured via RS-232 or ARINC 429.
Figure 8-41 Navigation Configuration Page
Table 8-16 Navigation Configuration Settings
Configuration
Setting
Description
Navigation Data
For a standalone unit (not part of a G3X system), this setting enables and
disables the display of navigation data in normal mode. Navigation data cannot
be hidden when autopilot servos are configured.
For a backup unit (part of a G3X system), this setting controls how the G5 selects
the navigation data source to display when communicating with a G3X display.
Select Auto to display navigation data from the #1 ARINC 429 source when the
G3X display is showing the same navigation data. If the G3X display's
navigation source is changed to internal GPS or a navigation source not
supported by the G5, then no navigation data will be displayed on the G5. This
prevents the G5 and G3X display from showing different sources of navigation
data simultaneously.
Select Always Display to always show the navigation data the G5 is receiving
over RS-232 and/or the #1 ARINC 429 source, even if that data is different that
what is shown on the G3X display.
Regardless of the Navigation Data setting, when no G3X displays are present,
the G5 will always display the navigation data it is receiving over RS-232 and/or
the #1 ARINC 429 source, or when dual navigation sources are installed, the G5
will display the navigation data from the selected source.
Selected Course
For a standalone unit (not part of a G3X system) this setting determines whether
the G5 can perform course selection for external navigation sources. Select
"Disabled" if a mechanical CDI or HSI is connected to the navigator, otherwise
select "Enabled".
VNAV Deviation
Scale
For a standalone unit (not part of a G3X system) this setting determines the fullscale value for VNAV deviation data received from an external navigator (+/- 500
feet or +/- 1000 feet). This should be configured to match the navigator's VNAV
deviation scale configuration.
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8.4.13.4 Units Configuration Page
This page allows for configuration of the displayed units. The units for each measurement can be selected
using the knob on the G5.
Figure 8-42 Units Configuration Page
The Units Configuration page also allows for the selection of Normal or Alternate Data Field Units
Display. Normal corresponds to unit labeling that is consistent with the G3X system - color-matched to the
value and displayed to the right of the value.
Figure 8-43 Normal Data Field Units
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Selecting Alternate will slightly change the display of the data field units. On the PFD page, the unit
symbols will be removed from the groundspeed, selected altitude, and barometric setting fields.
Figure 8-44 Alternate Data Field Units on PFD Page
If the units for airspeed and groundspeed are not the same, the title for the groundspeed field will be moved
above the value and updated to include the unit (color-matched to the title).
Figure 8-45 Non-Matching Airspeed and Groundspeed Units
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On the HSI page, all data field titles will be moved above the value and updated to include the unit (colormatched to the title).
Figure 8-46 Alternate Data Field Units on HSI Page
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8.4.13.5 RS-232 Configuration Page
This page allows for configuration of the serial communication port on the G5. Both the input and output
serial port formats can be configurated independently. Some input/output formats will also allow for a
configurable baud rate.
A green checkmark will appear next to the input format selection when the RS-232 port is receiving valid
data. A green checkmark will not appear if data has not yet been received by the unit. A red "X" is
displayed if no data has been received after an initial time-out period, or if data has been received and is
then interrupted.
Figure 8-47 RS-232 Configuration Page
Table 8-17 RS-232 Input Configuration Settings
Configuration
Setting
Description
Aviation
The proprietary format used for input of navigation data to the G5 at a fixed baud
rate of 9600 from an FAA certified Garmin panel mount unit. If the external GPS
navigator supports both the Aviation and MapMX formats, the MapMX format is
recommended.
Garmin Instrument
Data
Used for connecting to compatible Garmin LRUs (e.g. GMC 305/307).
Garmin VHF Nav
Radio
Receives lateral and vertical NAV deviation signals as an input format. Transmits
GPS data and selected course to a GNC 255 or SL 30 NAV radio.
MapMX
The preferred input format when interfacing with an external navigator. This
format is only available from Garmin units equipped with a WAAS GPS receiver.
MapMX Format 1 and MapMX Format 2 are also acceptable formats for the
navigator serial port configuration when using MapMX format on the G5. In a
dual GNS/GTN installation, connect the MapMX output from unit #1 to the G5.
NMEA
Supports the input and output of standard NMEA 0183 version 3.01 data at a
configurable baud rate of either 4800 or 9600. The G5 outputs GPS data via
NMEA sentences. This input format is used when interfacing a portable GPS
navigation unit like a Garmin Aera 660.
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Table 8-18 RS-232 Output Configuration Settings
Configuration
Setting
Description
Altitude Encoder
Outputs altitude encoder data to a compatible transponder. Both Icarus and
Shadin-format messages are output when using this setting.
Garmin Instrument
Data
Used for connecting to compatible Garmin LRUs (e.g. GMC 305/307).
Garmin VHF Nav
Radio
Receives lateral and vertical NAV deviation signals as an input format. Transmits
GPS data and selected course to a GNC 255 or SL 30 NAV radio.
NMEA
Supports the input and output of standard NMEA 0183 version 3.01 data at a
configurable baud rate of either 4800 or 9600. The G5 outputs GPS data via
NMEA sentences.
Text
Outputs attitude, air data, and GPS position/velocity text data as described in
Section 11.4
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8.4.13.6 ARINC 429 Configuration Page
This page allows for configuration of the 2 ARINC 429 output and 4 ARINC 429 input ports on the G5.
Figure 8-48 ARINC 429 Configuration Page
Table 8-19 ARINC 429 Outputs
Configuration
Setting
EFIS/Airdata 1
(SDI 1, SDI 2,
common)
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Description
Outputs EFIS and air data labels. The transmitted labels are as follows:
100P Selected GPS Course
101
Selected Heading
102
Selected Altitude
110
Selected VLOC Course
203
Pressure Altitude
204
Baro Corrected Altitude
205
Mach Number
206
Indicated Airspeed
210
True Airspeed
211
Total Air Temperature
212
Vertical Speed
213
Static Air Temperature
235
Baro Setting (BCD)
320
Magnetic Heading
371G Manufacturer ID
377
Equipment ID
G5 Installation Manual
Page 8-66
Table 8-19 ARINC 429 Outputs
Configuration
Setting
Description
EFIS/Airdata 2
(SDI 1, SDI 2,
common)
Outputs EFIS and air data labels. The transmitted labels are as follows:
100P Selected Course (GPS or VLOC)
101
Selected Heading
102
Selected Altitude
110
Selected VLOC Course
203
Pressure Altitude
204
Baro Corrected Altitude
205
Mach Number
206
Indicated Airspeed
210
True Airspeed
211
Total Air Temperature
212
Vertical Speed
213
Static Air Temperature
235
Baro Setting (BCD)
320
Magnetic Heading
371G Manufacturer ID
377
Equipment ID
EFIS Course
(SDI 1, SDI 2,
Common)
100P
371G
377
Selected GPS Course
Manufacturer ID
Equipment ID
Table 8-20 ARINC 429 Inputs
Configuration Setting
Description
Garmin GPS
(SDI 1, SDI 2, Common)
Receives GPS labels from a GNS 4XX/5XX or GTN 6XX/7XX series unit.
Garmin VOR/ILS
(SDI 1, SDI 2, Common)
Receives VOR/ILS labels from a GNS 4XX/5XX, GTN 6XX/7XX, or
GNC 255 unit.
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9 TROUBLESHOOTING
In this manual, the term ‘Red-X’ refers to a red “X” that appears on different areas of the display to
indicate the failure of that particular function.
For additional assistance, contact your local avionics dealer. If further help is needed, contact Garmin
Aviation Product Support at US Toll Free Number 1-888-606-5482, or US 1-913-397-8200.
NOTE
The information in this section is for troubleshooting use only and does not supersede any
approved maintenance or other installation instructions.
9.1 General Troubleshooting
1. Review the airframe logbook to verify if any G5 or other avionics or electrical maintenance had
been performed recently that may have contributed to the failure.
2. Check for loose wire terminals on the circuit breaker connections on the power wire(s) causing
intermittent power connections. Also, check for intermittent circuit breakers.
3. Have ground power put on the aircraft.
4. Turn on the G5 and record the system software version displayed on the start up page.
5. After the system is initialized, note any Red-X’s on the display or anywhere in the configuration
mode menus.
If the failure cannot be verified, proceed to the following physical inspection.
1. Power cycle the G5 or any affected LRU by removing aircraft power, waiting 30 seconds, then
reapplying power.
2. Check that all connectors are fully seated, and that the jack screw connectors are fully tightened on
both sides of all connectors.
3. Check for a loose wire harness that is able to move around during flight. This condition may cause
the wire to pull on or vibrate the connector, making intermittent connections.
4. Ensure that the G5 or any affected LRU is mounted securely. Use the appropriate tool to check the
tightness of all mounting hardware.
5. Look for any heavy objects that may not be fastened tight to the aircraft structure that could be
inducing vibration in the G5's attitude sensors.
6. Look for evidence of water or fluid contamination in the area around the G5 or any affected LRU.
7. Unplug the connector on the G5 or any affected LRU and check for bent pins.
8. Inspect the wire harness clamp on the rear of all connectors to verify that it is not too tight and
smashing/shorting the wires. If the wire clamp is installed upside down, it has sharp edges that can
cut into the wires. Verify the presence of protective wire wrap between the wires and the clamp.
If the condition is not resolved by following the preceding instructions, contact Garmin Product Support
for additional assistance. A Garmin Field Service Engineer may ask the technician to email any fault or
data logs back to Garmin to help determine if the condition is caused by a G5, a different LRU, or a source
elsewhere in the aircraft installation.
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9.2 SD Card Slot
A stuck or sticking microSD™ card issue can sometimes be caused by the card thickness variability
(especially if there is more than one label on the card). This is usually caused by the card sticking in the
overlay opening, not by the card sticking to the socket inside the unit. Try another card (without a label, if
possible) to confirm the problem before returning. If the second card sticks, the microSD™ socket board
inside the unit may be misaligned with the overlay and the G5 will require repair. If the thickness of the
card was the cause, see if more than one label was on the card. If the labels weren’t the cause, determine
what brand of microSD™ card was being used (Garmin recommends using SanDisk® brand cards).
9.3 Unit Communication Error
Communication errors can occur in systems with two G5s due to software versions and unit ID strapping.
Multiple G5s connected together should have the same software version installed. Differing versions will
be annunciated with a message in normal mode (e.g. "Software version mismatch") and a Red-X in
configuration mode. More than one G5 strapped as the same unit (i.e. both unit 1 or both unit 2) will be
annunciated with a message (e.g. "Communication error" or "Network address conflict") in normal mode
and a Red-X in configuration mode.
9.4 Air Data Troubleshooting
Under normal operating conditions, the G5 provides the following air data information:
•
•
•
Indicated Airspeed (IAS)
Barometric Altitude
Vertical Speed
NOTE
IAS information can only be displayed at speeds greater than 20 knots.
If the airspeed and/or altitude is failed and shows a Red-X condition:
1. Inspect the pitot/static plumbing integrity.
2. Inspect the pitot/static ports and all associated equipment.
3. If the problem persists, replace the G5 with a known good unit.
9.5 Attitude Failure Troubleshooting
To assist with troubleshooting an attitude or track failure, gather answers to the following questions, being
as specific as possible. This information may be helpful to the installer/pilot, the avionics dealer, or to
Garmin Aviation Product Support in troubleshooting the failure.
1. What was the nature of the failure? Was it a Red-X of only heading, only GPS track, only pitch/
roll, or a combination?
2. If there was a Red-X of pitch or roll information, did the unit display an alignment message (which
is indicative of a reset), or a failure message (which is indicative of an invalidated output)?
3. What was the aircraft doing in the two minutes that preceded the failure (taxing on the ground,
flying straight-and-level flight, turning, climbing, etc.)? If the problem occurred on the ground,
was it within 100 feet of a hanger using GPS repeaters?
4. How long did the failure last? Was it brief or sustained? Was it repetitive in nature? If it was
repetitive, about how many times did it happen? Did it happen on more than one day?
5. Was the problem correlated with a specific maneuver or a specific geographic area?
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6. Can the problem be repeated reliably?
7. Did the onset of the problem occur shortly after a software upload to the G5?
8. Was there a loss of the GPS position lock?
9.6 Heading Failure Troubleshooting (with GMU 11)
If a Red-X (steady or intermittent) is displayed in the heading field on the G5, check the following while
the aircraft is on the ground:
1. When taxiing, heading performance is susceptible to the presence of magnetic anomalies (metal
buildings, underground steel culverts, steel grates in the ramp, rebar, etc.). Localized sources of
interference on the ground may consistently cause a Red-X to be displayed on the heading in the
same location while taxiing; this is not caused by a failure of the GMU 11 or its calibration.
2. If any new equipment has been installed on the aircraft, conduct the magnetometer interference
test procedure (see Section 8.4.6.5) to see if the new equipment is causing magnetic interference
with the GMU 11.
3. With the G5 in configuration mode, select the Device Information page and verify there is a green
checkmark next to MAG. If there is a Red-X next to MAG, inspect and verify the CAN bus wiring
between the G5 and GMU 11. See the CAN bus troubleshooting steps in Section 2.2.8.
4. If the problem persists, replace the GMU 11 with a known good unit.
9.7 G5 Data Logging
Data logging on the G5 may be used to help troubleshoot issues. Operational data can be gathered from
the G5 during flight or on-ground and is stored in *.csv log files on the microSD™ card.
To enable logging on the G5:
1. Power on the unit in configuration mode.
2. Navigate to the Data Log Configuration page (via the Device Information and Diagnostics pages).
3. Select Enabled for the Data Card Log setting.
9.8 Sending Troubleshooting Data to Garmin
To assist with troubleshooting an issue, it may be helpful to send pictures and/or the log files stored on the
microSD™ card to Garmin. This data can be especially useful to troubleshoot autopilot, attitude, and air
data related issues. This data can be sent to g3xpert@garmin.com for troubleshooting assistance.
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10 MAINTENANCE
Periodic maintenance for the G5 is limited to the air data system as listed in Section 10.1. All other
maintenance is "on condition" only. Instructions for Continued Airworthiness (ICA) are not required per
14 CFR Part 21 for these products as they have received no FAA approval or endorsement. Garmin
recommends that the G5 be inspected for proper operation, secure attachment, integrity of connectors and
wiring, cleanliness, leakage of hoses and tubes, and any evidence of damage as part of the required annual
or periodic aircraft inspection. For more general inspection guidance, please refer to the applicable
sections of CFR Part 43 Appendix D and Chapter 12 of AC 43.13-1B.
10.1
G5 Air Data Periodic Maintenance
Per Part 43 Appendix E, paragraph (b)(2), Garmin recommends a test procedure equivalent to Part 43
Appendix E, paragraph (b)(1), with two exceptions. The tests of sub-paragraph (iv) (Friction) and (vi)
(Barometric Scale Error) are not applicable because the digital outputs of the G5 are not susceptible to
these types of errors. This procedure is recommended when the static system is opened up (i.e. whenever
the G5 is removed or replaced). Garmin also recommends that a leak test be performed following any
maintenance action in which the pitot system is opened up.
NOTE
If the G5 is moved or replaced, the Post Installation Calibration Procedures (Section 8.4.6)
must be repeated.
10.2
G5 Battery Periodic Maintenance
For maximum battery longevity, store within a temperature range of -4˚F to 68˚F (from -20˚C to 20˚C).
The G5 battery should be kept partially charged when unused for longer periods of time and should not be
stored when completely discharged. Charge the battery to 30% within 1 year of receipt and recharge to
30% every 2 years thereafter if the G5 is not in use.
10.3
Return to Service Information
These return to service procedures are intended to verify the serviceability of the appliance only. These
tests alone do not verify or otherwise validate the airworthiness of the installation.
NOTE
A pitot/static check as outlined in 14 CFR 91.411 and Part 43 Appendix E must be completed
if the pitot/static lines are broken.
10.3.1 Original G5 is Reinstalled
No software or calibration is required if the original G5 is reinstalled in its original mounting location.
10.3.2 New G5 is Installed
Any time a new G5 is installed, or an existing G5 is moved to a different mounting location, the pitch/roll
offset calibration procedure (Section 8.4.6.1) must be performed. The correct G5 software version will
automatically be loaded into the G5 from a connected GDU (if applicable). If a GDU is not connected, the
unit software will need to be loaded via the front-facing microSD™ card slot. All unit configuration
options will need to be selected as the G5 does not support a configuration module.
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10.3.3 G5 installations With a GMU 11
For G5 installations that include a GMU 11, verify the heading display is accurate as indicated by the white
numbers displaying the magnetic heading. Any time a GMU 11 is moved or reinstalled, a new
magnetometer calibration is required (Section 8.4.6.6).
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11 PERFORMANCE SPECIFICATIONS/LICENSING/COMPLIANCE
11.1 GPS Specifications
Table 11-1 G5 GPS Specifications
Characteristics
Specifications
Acquisition Time
a) Warm Start (position known to 10 nm, time known to 10 minutes, with valid
almanac and ephemeris): Less than 5 seconds
b) Cold Start (position known to 300 nm, time known to 10 minutes, with valid
almanac): Less than 45 seconds
c) Always Locate™ (with almanac, without initial position or time): Less than
60 seconds
Update Rate
5 Hz (continuous)
Positional Accuracy
< 10 meters
11.2 G5 Environmental Specifications
The G5 has an operating temperature range of -20°C to +60°C. The G5 will prevent operation from the
battery when the battery is outside of this temperature range.
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11.3 G5 Performance Specifications
Table 11-2 G5 Performance Specifications
Characteristic
Specifications
Pressure Altitude Range
-1,400 feet to 30,000 feet
Vertical Speed Range
±20,000 fpm
Airspeed Range
300 knots (indicated)
Mach Range
< 1.00 mach
Pitch/Roll Range
±360°
Pitch/Roll Accuracy
±1° (straight and level flight)
±2.5° (normal dynamic maneuvering)*
Rotation Rate Range
±499°/second (automatic recovery when exceeded)
Heading Accuracy (with
Optional GMU 11)
±3° (straight and level flight)
±6° (normal dynamic maneuvering)*
Backup Battery (Optional)
Rechargeable Lithium-ion
Battery Life
Up to 4 hours
*Normal dynamic maneuvering is defined as bank angles less than 35° and pitch angles less than 15°.
Due to variations in the Earth's magnetic fields, the operational accuracy of the G5's heading (with optional
GMU 11) is unknown in the following regions:
•
•
•
•
•
•
North of 72° N for all longitudes
South of 70° S for all longitudes
North of 65° N between 75° W and 120° W (northern Canada)
North of 70° N between 70° W and 128° W (northern Canada)
North of 70° N between 85° E and 114° E (northern Russia)
South of 55° S between 120° E and 165° E (south of Australia and New Zealand)
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11.4 RS-232 Text Output Format
11.4.1 Electrical Interface
The output signals are compatible with RS-232C. Data is generated at the configured baud rate with a
word length of 8 bits, one stop bit, and no parity.
11.4.1.1 General Message Output Format
The general text output message format is as follows:
• Escape character ('=' symbol [0x3D hex])
• ID character
• Version character
• Data characters (length determined by message ID)
• Checksum (2-character [1-byte] ASCII hex value that is the sum of all previous bytes including the
escape character)
• Carriage return (0x0D hex)
• Line feed (0x0A hex)
An exception to the above is the GPS Data message, which is backwards compatible with the Garmin
Simple Text Output format described at: http://www8.garmin.com/support/text_out.html. The GPS Data
message has the following format:
• Escape character ('@' symbol [0x40 hex])
• Data characters
• Carriage return (0x0D hex)
• Line feed (0x0A hex)
All text output messages use only printable ASCII characters. For all messages, a value that is out of range,
missing, not configured, uncalibrated, or otherwise invalid is indicated by replacing the corresponding
bytes within the message with the underscore character ('_' symbol [0x5F hex]).
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11.4.2 Attitude/Air Data Message Format
The Attitude/Air Data message is transmitted approximately 10 times per second.
Table 11-3 Attitude/Air Data Message Format
Field Name
Offset
Width
Min
Max
Escape Character
0
1
'='
Sentence ID
1
1
'1'
Sentence Version
2
1
'1'
UTC hour
3
2
hours
00
23
UTC minute
5
2
minutes
00
59
UTC second
7
2
seconds
00
59
UTC second
fraction
9
2
10 ms
00
99
Pitch
11
4
0.1 degrees
positive = up
-900
+900
Roll
15
5
0.1 degrees
positive = right
-1800
+1800
Heading
20
3
degrees
magnetic (G3X
backup install only)
000
359
Airspeed
23
4
0.1 knots
0000
9999
Pressure altitude
27
6
feet
-01000
+60000
Rate of turn
33
4
0.1 deg/sec
positive = right
-999
+999
Lateral acceleration
37
3
0.01 G
positive = leftward
-99
+99
Vertical
acceleration
40
3
0.1 G
positive = upward
-99
+99
Unused
43
2
Vertical speed
45
4
10 fpm
positive = up
-999
+999
Unused
49
3
Altimeter setting
52
3
0.01 inHg
offset from 27.50°
000
400
Checksum
55
2
ASCII hex
sum of prev bytes
CR/LF
57
2
Total Length
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11.4.3 GPS Data Message Format
The GPS Data message is transmitted once per second.
Table 11-4 GPS Data Message Format
Field Name
Offset
Width
Units
Escape character
0
1
UTC year
1
2
years
UTC month
3
2
UTC day
5
UTC hour
Notes
Min
Max
00
99
months
01
12
2
days
01
31
7
2
hours
00
23
UTC minute
9
2
minutes
00
59
UTC second
11
2
seconds
00
59
Latitude
hemisphere
13
1
Latitude degrees
14
2
degrees
0
90
Latitude minutes
16
5
0.001
minutes
0
59999
Longitude
hemisphere
21
1
Longitude degrees
22
3
degrees
0
180
Longitude minutes
25
5
0.001
minutes
0
59999
000
999
-99999
+99999
0000
9999
'@'
last two digits of UTC
year
'N' = north
'S' = south
minutes x 1000
'E' = east
'W' = west
minutes x 1000
'g' = 2D GPS position
'G' = 3D GPS position
Position status
30
'd' = 2D diff GPS position
1
'D' = 3D diff GPS position
'S' = simulated position
'_' = invalid position
Horizontal position
error
31
3
meters
Altitude
34
6
meters
East/west velocity
direction
40
1
East/west velocity
magnitude
41
4
190-02072-01
Rev. 5
Height above/below MSL
'E' = east
'W' = west
0.1 m/
sec
G5 Installation Manual
Page 11-5
Table 11-4 GPS Data Message Format
Field Name
Offset
Width
North/south velocity
direction
45
1
North/south velocity
magnitude
46
4
Vertical velocity
direction
50
1
Vertical velocity
magnitude
51
4
CR/LF
55
2
Total length
190-02072-01
Rev. 5
Units
Notes
Min
Max
0000
9999
0000
9999
'N' = north
'S' = south
0.1 m/
sec
'U' = up
'D' = down
0.01 m/
sec
0x0D/0x0A
57
G5 Installation Manual
Page 11-6
APPENDIX A
GAD 13 OAT PROBE INTERFACE MODULE
INSTALLATION
This section contains general information as well as installation information for the optional GAD 13.
Figure A-1 GAD 13 Unit View
A.1 Equipment Description
The GAD 13 is a small unit used to interface to OAT (Outside Air Temperature) probes. The GAD 13
provides a standard three-wire or two-wire interface that can be connected to the following OAT probes:
• Garmin GTP 59
• AD590 based probes such as EDMO 655 and Davtron C307PS
OAT analog information from the GAD 13 is converted to digital information and passed to other G5
system LRUs using CAN communication. Addition of the GAD 13 enables the G5 to display TAS, OAT,
and wind information. The GMU 11 magnetometer is required for wind information.
A.1.1 Equipment Available
The GAD 13 is available by the part numbers listed in Table A-1.
Table A-1 Available LRU Part Numbers
LRU
GAD 13
190-02072-01
Rev. 5
Assembly Part Number
Unit Only Part Number
010-02203-00
011-04938-00
G5 Installation Manual
Page A-1
A.1.2 Additional Equipment Required
The following accessories are not provided with the GAD 13 unit. The Connector Kit (Table A-2) is
recommended to install the unit.
Table A-2 GAD 13, PMA Accessories
Item
Garmin P/N
Connector Kit, 9 Pin, w/CAN TERM, PMA
011-03002-10
Table A-3 Contents of Connector Kit (011-03002-10)
Item
Garmin P/N
Connector Kit, 9 Pin, w/CAN TERM
011-03002-00
Table A-4 Contents of Connector Kit (011-03002-00)
Item
Garmin P/N
Quantity
Sub-Assy, Backshell w/Hdw, Jackscrew, 9/15 pin
011-01855-00
1
Sub-Assy, CAN Termination Kit
011-02887-00
1
Connector, Rcpt, D-Sub, Crimp Socket, Commercial, 09 CKT
330-00625-09
1
Contact, Socket, Mil Crp, Size 20, 20-24 AWG, RoHS
336-00022-02
9
A.2 General Specifications
See Table A-5 for voltage/current specifications. See Table A-6 for dimension/weight specifications.
Table A-5 GAD 13 Power Requirements*
14 V (Avg/Max)
28 V (Avg/Max)
0.050 A
0.120 A
*Includes GTP 59 Oat Probe
Table A-6 GAD 13 Physical Specifications
Width
Height
Depth*
Unit Weight
Weight of Unit
and Connector
Kit
1.43 in
(36.2 mm)
0.79 in
(20.0 mm)
1.85 in
(47.1 mm)
0.14 lbs
(0.064 kg)
0.25 lbs
(0.113 kg)
*Harness connector not included
190-02072-01
Rev. 5
G5 Installation Manual
Page A-2
A.3 Mounting and Wiring Requirements
A.3.1 Unit Installation
The GAD 13 should be mounted to a surface known to have sufficient structural integrity to withstand
additional inertial forces imposed by the weight of the unit.
In order to satisfy the structural mounting requirements for the GAD 13, the following conditions must be
met:
1. The mounting structure, existing or new, must be electrically bonded to the airframe.
2. Any supporting structure must be rigidly connected to the aircraft primary structure through strong
structural members capable of supporting substantial loads.
3. Mounting platform shall not span greater than 12" in width or length without direct attachment to
primary structure. If mounting platform does span greater than 12", add necessary stringers,
doublers, bulkhead flange reinforcements, etc., to provide adequate support. Existing honeycomb
core sandwich panels with aluminum face sheets are adequate and do not require additional
reinforcement.
4. A minimum of 3" between the GAD 13 connector end and any object must be maintained to
ensure clearance for connectors and wire harness.
5. If a support bracket or shelf needs to be fabricated, it should be fabricated and attached to the
aircraft structure in accordance with the methods outlined in AC43.13-2B Chapter 1 and 2,
AC43.13-1B Chapter 4, and the following requirements:
a) Material shall be 2024-T3 aluminum alloy sheet per AMS-QQ-A-250/4 or Clad 2024-T3
aluminum alloy sheet per AMS-QQ-A-250/5.
b) The material shall be minimum 0.032 inch thick.
c) Material shall have some type of corrosion protection (primer, alodine, etc.)
d) It shall be attached to primary aircraft structure with a minimum of 4 fasteners listed in
Table A-7.
190-02072-01
Rev. 5
G5 Installation Manual
Page A-3
Table A-7 GAD 13 Mounting Hardware Used in Figure A-2
Hardware
Screws
Minimum Specifications
MS35206-XXX (#6-32, Length A/R)
Washers
NAS1149FN632P
MS21042L06 or MS21044N06
OR
Any Standard Mil-Spec Part Number #6 Nutplate
(not available from Garmin)
Nuts
Using the hardware called out in Table A-7, mount the GAD 13 to the chosen mounting location.
Recommended torque of fasteners is 10 +/- 1 in-lbs.
SCREW
GAD 13
EXISTING OR
FABRICATED SHELF
NUT AND WASHER
OR NUTPLATE
Figure A-2 GAD 13 Mounting Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page A-4
A.3.2 Wiring
The 9 pin connector, pins, and backshell supplied in the GAD 13 installation kit are used to add wiring for
the GAD 13. See Section 7 for interconnect drawings and Section A.4 for pinout information.
A.4 J131 Connector
1
5
6
9
Figure A-3 J131 on GAD 13, as viewed looking at connector on unit
Table A-8. J131 Connector
Pin
Pin Name
I/O
1
CAN HI
I/O
2
CAN LO
I/O
3
GTP 59 IN HI
In
4
OAT PROBE IN
In
5
OAT PROBE OUT
6
GTP 59 IN LO
In
7
AIRCRAFT POWER
In
8
GTP 59 POWER OUT
9
POWER GROUND
A.4.1
Out
Out
--
Power
This section covers the power input requirements. The GAD 13 is compatible with 14V and 28V systems.
Table A-9. Power Pins
Pin Name
Connector
Pin
I/O
AIRCRAFT POWER
J131
7
In
POWER GROUND
J131
9
--
190-02072-01
Rev. 5
G5 Installation Manual
Page A-5
A.4.2
CAN Bus
The GAD 13 CAN bus conforms to the BOSCH standard for Controller Area Network (CAN) 2.0-B and
ISO 11898. See Section 2.2.2 for details. The CAN bus connection on the GAD 13 is used to connect the
GAD 13 to one (or two) G5 units.
Table A-10. CAN Bus Pins
Pin Name
Connector
Pin
I/O
CAN HI
J131
1
I/O
CAN LO
J131
2
I/O
A.4.3
OAT Probe Interface
The GAD 13 has three pins (3, 6, 8) for interface to a passive (RTD type) probe and two pins (4, 5) for
interface to an active OAT probe. This interface provides excitation voltage/current, and temperature
sensing capabilities for an OAT probe. For specific wiring information, refer to Figure 7-9. .
Table A-11. OAT Probe Pins
Pin Name
Connector
Pin
I/O
GTP 59 IN HI
J131
3
In
GTP 59 IN LO
J131
6
In
GTP 59 POWER OUT
J131
8
Out
OAT PROBE IN
J131
4
In
OAT PROBE OUT
J131
5
Out
190-02072-01
Rev. 5
G5 Installation Manual
Page A-6
2X
190-02072-01
Rev. 5
.162±.003 4.11±0.08
SEE NOTE 3
1.125±.010 28.58±0.25
1.43 36.2
.40 10.2
CENTER OF
GRAVITY
.79 20.0
.70 17.8
CENTER OF
GRAVITY
4.13 105.0
WITH CAN TERMINATOR
3.66 [93.0]
WITHOUT CAN TERMINATOR
1.85 47.0
WITH CAN TERMINATOR
1.55 [39.4]
WITHOUT CAN TERMINATOR
CENTER OF GRAVITY
2X .15 3.8
1.71 43.3
1.85 47.1
.39 9.9
TYPICAL THICKNESS
BENEATH FASTENER HEAD
NOTES:
1. DIMENSIONS: INCHES[mm]. METRIC VALUES ARE FOR REFERENCE
ONLY.
2. DIMENSIONS ARE NOMINAL AND TOLERANCES ARE NOT IMPLIED
UNLESSSPECIFICALLY STATED.
3. MOUNTING HOLES FOR #6 PAN HEAD OR HEX HEAD FASTENERS.
FASTENERS NOT SUPPLIED.
A.5 Outline and Installation Drawings
Figure A-4 GAD 13 Outline Drawing
G5 Installation Manual
Page A-7
Figure A-5 GAD 13 Installation Drawing
190-02072-01
Rev. 5
G5 Installation Manual
Page A-8
CAN TERMINATOR
011-02887-00
SEE NOTE 1
9 PIN D-SUB CONNECTOR
330-00625-09
9 PIN BACKSHELL
011-01855-00
CONNECTOR KIT
011-03002-10
GAD 13
011-04938-00
NOTE:
1. CAN TERMINATOR IS OPTIONAL, REFER
TO THE CAN BUS TERMINATION SECTION
FOR INFORMATION ON WHEN A CAN
TERMINATOR IS INSTALLED.
APPENDIX B GMC 507 (AFCS MODE CONTROLLER) INSTALLATION
This section contains general information as well as installation information for the optional GMC 507.
Figure B-1 GMC 507 Unit View (-00 version)
B.1 Equipment Description
The GMC 507 is a Garmin Automatic Flight Control System (AFCS) Mode Controller that can be used in
a G5 autopilot installation. The GMC 507 provides a user interface for the autopilot function. The
GMC 507 can be mounted to the aircraft instrument panel in a rectangular cutout or mounted using the
optional installation rack (Table B-3).
B.1.1 Equipment Available
The GMC 507 is available by the part numbers listed in Table B-1.
Table B-1 Available LRU Part Numbers
LRU
Assembly Part Number
Unit Only Part Number
010-01946-00
011-04548-00
GMC 507
B.1.2 Additional Equipment Required
The following accessories are not provided with the GMC 507 unit. The Connector Kit (Table B-2) is
required to install the unit.
Table B-2 Contents of Connector Kit (011-01824-01)
Item
Garmin P/N
Quantity
Backshell w/Hdw, Jackscrew, 9/15 Pin
011-01855-00
1
Connector, Male, High Density D-Sub,15 CKT
330-00366-15
1
Contact, Pin, Military Crimp, Size 22D
336-00021-00
15
190-02072-01
Rev. 5
G5 Installation Manual
Page B-1
B.1.3 Optional Equipment
Table B-3 GMC 507 Installation Rack Kit (010-12700-10)
Item
GMC 507 Installation Rack
Garmin P/N
Quantity
115-02774-00
1
B.2 General Specifications
See Table B-4 for power/current specifications. See Table B-5 and the drawings in Section B.5 for
dimension/weight specifications.
Table B-4 GMC 507 Power Requirements
14 V (Maximum)
14 V (Typical)
28 V (Maximum)
28 V (Typical)
0.20 A, 2.8 W
0.11 A, 1.54 W
0.11 A, 3.08 W
.06 A, 1.68 W
Table B-5 GMC 507 Physical Specifications
Width
Height
Depth*
Unit Weight
Weight of Unit
and Connector
Kit
6.25 in
(158.8 mm)
2.10 in
(53.3 mm)
2.61 in
(66.3 mm)
0.68 lbs
(0.308 kg)
0.78 lbs
(0.354 kg)
*Harness connector not included
B.3 Mounting and Wiring Requirements
B.3.1 Panel Cutout Template
Figure B-7 can be used as a template when marking the panel for cutout. Dimensions on the figure are to
verify accuracy of printout only, see Figure B-6 for complete cutout dimensions. A .dxf version of the
drawing is also available for download at https://support.garmin.com/support/manuals.
CAUTION
Exercise caution when installing the rack in the instrument panel. Deformation of the rack
will make it difficult to install and remove the GMC 507.
NOTE
If the front edges of the installation rack are behind the front surface of the aircraft panel,
the GMC 507 pawl latches may not fully engage.
NOTE
The GMC 507 install rack may be used as a template for drilling the mounting holes.
190-02072-01
Rev. 5
G5 Installation Manual
Page B-2
B.3.2 Unit Installation
Fabrication of a wiring harness is required. Sound mechanical and electrical methods and practices are
recommended for installation of the GMC 507. Refer to Section 2.2 for wiring considerations, and to
Appendix B.4 for pinouts.
B.3.2.1 Panel Cutout Installation
1. Per Figure B-2, ensure the pawl latch fasteners are fully retracted and in the vertical position.
2. Insert the unit into the instrument panel cutout so that the backside of the bezel rests against the
instrument panel. Orient the install rack as shown in Figure B-9.
3. Using a 3/32" hex drive tool turn each of the two pawl latches clockwise until tightened to
20 +/-2 in-lbs. When tightened, the pawl latches are in the horizontal position (see Figure B-2).
B.3.2.2 Radio Stack Installation
The GMC 507 Install Rack (115-02774-00) is to be used when installing the GMC 507 unit into a radio
stack. Figure B-10 shows the various radio stack cutout configurations that will accommodate the Install
Rack.
1. Ensure the left and right front edges of the install rack are flush with the front surface of the
instrument panel.
2. Secure the install rack to a rigid, primary aircraft structure using (qty. 4) #6 100° flat head machine
screws as noted in Figure B-8. The screws are inserted from the inside of the installation rack and
may be secured using self-locking hex nuts on the outside.
3. With the pawl latch fasteners retracted, insert the GMC 507 into the Install Rack until the bezel
contacts the front edges of the Install Rack.
4. Using a 3/32" hex drive tool turn each of the two pawl latches clockwise until tightened to
20 +/-2 in-lbs. When tightened, the pawl latches are in the horizontal position (see Figure B-2).
CAUTION
To remove the GMC from the instrument panel, turn each of the two pawl latches
counterclockwise, not exceeding 15 in-lbs of torque.
Figure B-2. Pawl Latch
B.3.3 Wiring
The 15 pin connector, pins, and backshell supplied in the GMC 507 installation kit are used to add wiring
for the GMC 507. See Section 7 for interconnect drawings and Section B.4 for pinout information.
190-02072-01
Rev. 5
G5 Installation Manual
Page B-3
B.4 J7001 Connector
Figure B-3 J7001 on GMC 507, as viewed looking at connector on unit
Pin
Pin Name
I/O
1
RESERVED
--
2
RESERVED
--
3
CAN HI
I/O
4
CAN LO
I/O
5
SONALERT
Out
6
CAN BUS TERM 2
--
7
AIRCRAFT POWER 1
In
8
CAN BUS TERM 1
--
9
AIRCRAFT POWER 2
In
10
TO/GA DISCRETE IN
In
11
LIGHTING BUS HI
In
12
AP DISCONNECT IN/OUT
I/O
13
AUDIO HI
Out
14
AUDIO LO
Out
15
POWER GROUND
190-02072-01
Rev. 5
--
G5 Installation Manual
Page B-4
B.4.1
Power
This section covers the power input requirements. The GMC 507 is compatible with 14V and 28V
systems. AIRCRAFT POWER 1 and AIRCRAFT POWER 2 are “diode ORed” to provide power
redundancy.
Pin Name
Connector
Pin
I/O
AIRCRAFT POWER 1
J7001
7
In
AIRCRAFT POWER 2
J7001
9
In
POWER GROUND
J7001
15
--
B.4.2
CAN Bus
The G5 CAN bus conforms to the BOSCH standard for Controller Area Network 2.0-B and ISO 11898.
See Section 2.2.2 for details. To enable the internal CAN terminator when the GMC 507 is installed at one
of the two ends of the CAN bus, a wire must be installed to short pin 6 to pin 8.
Pin Name
Connector
Pin
I/O
CAN HI
J7001
3
I/O
CAN LO
J7001
4
I/O
CAN BUS TERM 1
J7001
8
--
CAN BUS TERM 2
J7001
6
--
B.4.3
Lighting
The GMC 507 supports two internal backlighting buses, one for the mode (indicator) lights above the
buttons, and one for the button text, panel text, and knob backlighting.
Mode Indicator Backlighting - The lighting level for the mode lights (indicator triangles) above the buttons
is controlled by the photocell only, and is not affected by the lighting bus input (pin 11). This ensures that
the mode selection lights on the panel are always visible (and are independent of the externally applied
lighting bus).
Button Text, Panel Text, and Knob Backlighting - The GMC 507 can be installed to use either the built-in
photocell or the 14-28V lighting bus input for backlight control of the button text, panel text, and knob
backlighting. The photocell controls all backlighting when the lighting bus input is below 1.4VDC (or
unconnected). If the lighting bus input voltage is greater than 1.4VDC, the GMC 507 uses the lighting bus
input voltage (1.4VDC-28.0VDC range) as a reference voltage (not power source) to adjust the
backlighting for these items.
Pin Name
LIGHTING BUS HI
190-02072-01
Rev. 5
Connector
Pin
I/O
J7001
11
In
G5 Installation Manual
Page B-5
B.4.4
Audio Out
Audio output provides an autopilot disconnect tone and other aural alerts. Connect this output to an
unused audio alert input on an audio panel.
Pin Name
Connector
Pin
I/O
AUDIO HI
J7001
13
Out
AUDIO LO
J7001
14
B.4.5
Sonalert
May be connected to a Sonalert when an audio panel is not available to use with the audio output.
Pin Name
SONALERT
B.4.6
Connector
Pin
I/O
J7001
5
Out
TO/GA Discrete In
Provides an active low discrete input which may optionally be connected to a TO/GA button.
Pin Name
DISCRETE IN
B.4.7
Connector
Pin
I/O
J7001
10
In
Connector
Pin
I/O
J7001
12
I/O
AP Disconnect In/Out
This pin is used for certified installations only.
Pin Name
AP DISCONNECT IN/OUT
190-02072-01
Rev. 5
G5 Installation Manual
Page B-6
190-02072-01
Rev. 5
6.25 158.8
5.99 152.1
3.13 79.4
C.G. (NOTE 3)
2.10 53.3
.03 0.6
C.G. (NOTE 3)
.13 3.3
2 PLACES
FRONT SURFACE OF
AIRCRAFT PANEL
NOTES:
1.
DIMENSIONS: INCHES[mm]. METRIC VALUES ARE FOR REFERENCE ONLY.
2.
DIMENSIONS ARE NOMINAL AND TOLERANCES ARE NOT IMPLIED UNLESS SPECIFICALLY STATED.
3.
CENTER OF GRAVITY (C.G.) LOCATION IS WITHOUT CONNECTOR KIT INSTALLED.
1.11 28.1
3.14 79.7
.54 13.6
1.75 44.6
1.27 32.3
.03 0.6
C.G. (NOTE 3)
1.05 26.7
C.G. (NOTE 3)
.26 6.7
.87 22.1
1.90 48.3
B.5 Outline and Installation Drawings
Figure B-4 GMC 507 Outline Drawing (no installation rack)
G5 Installation Manual
Page B-7
Figure B-5 GMC 507 Installation Drawing (no installation rack)
190-02072-01
Rev. 5
G5 Installation Manual
Page B-8
INCLUDED IN 011-01824-01
CONNECTOR KIT
INSTALLATION NOTES:
1.
THE PAWL LATCH FASTENERS WILL ACCOMMODATE PANEL THICKNESSES FROM
.075[1.91] TO .140[3.56] THICK AND REQUIRE NO ADDITIONAL MOUNTING HARDWARE.
2.
THE FASTENERS ARE ENGAGED AND DISENGAGED BY USE OF A 3/32" HEX TOOL.
3.
TORQUE FASTENERS TO 20±2 IN-LBS ON INSTALLATION.
4.
TO DISENGAGE THE UNIT, ROTATE FASTENERS CCW. DO NOT EXCEED 15 IN-LBS OF TORQUE.
GMC 507 UNIT
011-04548-00 SHOWN
AIRCRAFT PANEL
(NOTE 1)
330-00366-15
011-01855-00
Figure B-6 GMC 507 Cutout Drawing, No Installation Rack (Not to Scale)
190-02072-01
Rev. 5
G5 Installation Manual
Page B-9
TOLERANCE:
INCH
mm
.XX ±.02
.X ±0.5
.XXX ±.010 .XX ±0.25
GMC 507 RECOMMENDED PANEL CUTOUT
HATCHED AREAS INDICATE SURFACE ON BACKSIDE
OF PANEL THAT WILL BE USED AS ELECTRICAL
BONDING FOR THE PAWL-LATCH FASTENERS.
THESE AREAS TO BE FREE OF PAINT (2 PLACES)
2X .15 3.8
.68 17.3
2X .50 12.7
6.020 152.9
BEZEL OUTLINE
(REF.)
.79 20.1
1.930 49.0
4X R .063 1.6
GMC 507 PANEL CUTOUT
IMPORTANT!
ENSURE THE PAGE SCALING SETTING IS SET TO NONE
WHEN PRINTING THIS PAGE. VERIFY DIMENSIONS OF
PRINTED TEMPLATE ARE ACCURATE BEFORE CUTTING
PANEL.
1.930 49.0
6.020 152.9
CUT OUT PANEL
TO INSIDE LINE
BEZEL OUTLINE
(REF.)
NOTES:
1. DIMENSIONS: INCHES [mm]. METRIC VALUES ARE FOR REFERENCE ONLY.
2. TOLERANCES: INCH
mm
.XX ±.02
.X ±0.5
.XXX ±.010 .XX ±0.25
Figure B-7 GMC 507 Panel Cutout Template (no installation rack)
190-02072-01
Rev. 5
G5 Installation Manual
Page B-10
Figure B-8 GMC 507 Outline Drawing with Installation Rack
190-02072-01
Rev. 5
G5 Installation Manual
Page B-11
.515 13.1
NOTE 4
2X .437 11.1
.415 10.5
1.15 29.2
3.14 79.7
6.25 158.8
BEZEL
3.28 83.3
C.G. (NOTE 3)
2.10 53.3
BEZEL
2X .437 11.1
.515 13.1
.415 10.5
1.27 32.3
FRONT SURFACE OF
AIRCRAFT PANEL
.02 0.5
C.G. (NOTE 3)
NOTES:
1.
DIMENSIONS: INCHES[mm]. METRIC VALUES ARE FOR REFERENCE ONLY.
2.
DIMENSIONS ARE NOMINAL AND TOLERANCES ARE NOT IMPLIED UNLESS SPECIFICALLY STATED.
3.
CENTER OF GRAVITY (C.G.) LOCATION IS WITHOUT CONNECTOR KIT INSTALLED.
4.
MOUTING HOLES ARE FOR #6 FLAT HEAD 100 CSK SCREWS (4 PLACES)
.69 17.6
1.91 48.5
6.30 160.0
RACK
.02 0.5
C.G. (NOTE 3)
1.15 29.1
C.G. (NOTE 3)
.26 6.7
.87 22.1
2.09 53.1
RACK
(NOT INCLUDING DIMPLES)
Figure B-9 GMC 507 Installation Drawing with Installation Rack
190-02072-01
Rev. 5
G5 Installation Manual
Page B-12
NOTES:
1.
THE FASTENERS ARE ENGAGED AND DISENGAGED BY USE OF A 3/32" HEX TOOL.
2.
TORQUE FASTENERS TO 20±2 IN-LBS ON INSTALLATION.
3.
TO DISENGAGE THE UNIT, ROTATE FASTENERS CCW. DO NOT EXCEED 15 IN-LBS OF TORQUE.
GMC 507 UNIT
011-04548-00 SHOWN
INCLUDED IN 011-01824-01
CONNECTOR KIT
GMC 507 INSTALL RACK
115-02774-00
330-00366-15
011-01855-00
Figure B-10 GMC 507 Panel Cutout Template for Installation with Installation Rack
190-02072-01
Rev. 5
G5 Installation Manual
Page B-13
OPTION 1:
3.
2.
2.12 53.8
2.14 54.4
TOLERANCES:
INCHES
mm
.XX ± .02
XX ± 0.5
.XXX ± .010
.XX ± 0.25
MAXIMUM AIRCRAFT PANEL THICKNESS IS .125[3.2].
NOTES:
1.
DIMENSIONS: INCHES [mm]
RADIO CUTOUT (RACK INSTALLED
FROM BACK OF AIRCRAFT PANEL
ONLY)
OPTION 3:
RADIO CUTOUT (RACK INSTALLED
FROM FRONT OF AIRCRAFT PANEL)
OPTION 2:
STACK CUTOUT (RACK INSTALLED
FROM FRONT OF AIRCRAFT PANEL)
6.21 157.7
6.33 160.8
6.33 160.8
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