Garmin Approach G5 - GPS-Enabled Golf Handheld User manual

190-01112-11 May 2020 Revision 7
Garmin G5
Electronic Flight Instrument
Part 23 AML STC Maintenance Manual
Including Instructions for Continued
Airworthiness

Garmin G5 Electronic Flight Instrument Part 23 AML STC Maintenance Manual 190-01112-11
Rev. 7
Page A
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Telephone:[phone]
Technical Support and Field Service Engineers: 888.606.5482
www.flyGarmin.com
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Garmin G5 Electronic Flight Instrument Part 23 AML STC Maintenance Manual 190-01112-11
Rev. 7
Page B
RECORD OF REVISIONS
Revision
Revision Date
Description
1
7/22/16
InitialRelease
2
03/14/17
Revised to add G5 DG/HSI, supporting equipment and associated
functions.
3
10/18/17
Revised to cover changes associated with the addition of the G5/GAD
29B third party autopilot interfaces.
4
12/15/17
Revised to cover changes associated with Software 5.00, support for
GFC500
5
7/20/18
Miscellaneous minor updates to harmonize with STC Installation Manual
190-01112-10.
6
7/19/19
Added GAD13 and GTP59 information
7
05/08/20
Add Lightning Protection Module, alternative software loading procedures,
added glareshield GPS antenna information, corrected non-Garmin OAT
probe model in 2.4, updated Appendix A configuration tables, minor
updates and clarification
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Garmin G5 Electronic Flight Instrument Part 23 AML STC Maintenance Manual 190-01112-11
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Page i
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 beexported, released, or disclosed to foreign nationals inside or outsideof the United
States without first obtaining an export license. A violation of the EAR may be subject to a penalty of
up to 10 years imprisonment and a fine of up to $1,000,000 under Section 2410 of the Export
Administration Act of 1979. Include this notice with any reproduced portion of this document.
DEFINITIONS OF WARNINGS, CAUTIONS, AND NOTES
WARNING
This product, its packaging, and its components contain chemicals known to the State of
California to cause cancer, birth defects, or reproductive harm. This notice is being provided in
accordance with California's Proposition 65. If you have any questions or would like additional
information, please refer to our web site at www.garmin.com/prop65.
WARNING
Perchlorate Material –special handling may apply, See www.dtsc.ca.gov./hazardouswaste/
perchlorate.
WARNING
Warnings are used to bring to the installer’s immediate attention not only damage
to the equipment but personal injury may occur if the instruction is disregarded.
CAUTION
Cautions are used to alert the individual damage to equipment may result if the
procedural step is not followed to the letter.
NOTE
Notes are used to expand and explain the preceding step and provide further
understanding of the reason for the particular operation.

Garmin G5 Electronic Flight Instrument Part 23 AML STC Maintenance Manual 190-01112-11
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Page ii
BATTERY WARNINGS:
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.
The G5 has an operating temperature range of -4˚F to 140˚F (-20˚C to +60˚C). The G5 will
prevent operation from the battery when the battery is outside of this temperature range.
For maximum battery longevity, store within a temperature range of 32˚ to 77˚F (from 0˚ to
25˚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.
CAUTION:
The display uses a lens with a special coating that may be sensitive to skin oils, waxes, and
abrasive cleaners. CLEANERS CONTAINING AMMONIA WILL HARM THE ANTI-
REFLECTIVE COATING. It is very important to clean the lens using a clean, lint-free cloth and
a 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 may 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:
Use of polarized eyewear may cause the display to appear dim or blank.
NOTE
All images used in this document are current at the time of publication but are subject to change
and may not be up to date.

Garmin G5 Electronic Flight Instrument Part 23 AML STC Maintenance Manual 190-01112-11
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Page iii
TABLE OF CONTENTS
SECTION ..............................................................................................................................................PAGE
1INTRODUCTION .....................................................................................................................................1
1.1 Introduction ......................................................................................................................................1
1.2 Organization.....................................................................................................................................1
1.3 Acronyms and Abbreviations...........................................................................................................1
1.4 Publications......................................................................................................................................1
1.5 Revision and Distribution .................................................................................................................2
2SYSTEM DESCRIPTION.........................................................................................................................2
2.1 G5 Electronic Flight Instrument........................................................................................................2
2.2 GMU 11 Magnetometer....................................................................................................................5
2.3 GAD 29/29B.....................................................................................................................................5
2.4 GAD 13 ............................................................................................................................................6
2.5 GTP 59 Temperature Probe ............................................................................................................7
2.6 Glareshield Mounted antenna..........................................................................................................7
3BASIC CONTROL & OPERATION..........................................................................................................8
4INSTRUCTIONS FOR CONTINUED AIRWORTHINESS .......................................................................9
4.1 Airworthiness Limitations .................................................................................................................9
4.2 Servicing Information .......................................................................................................................9
4.3 Electrical Bonding Test..................................................................................................................11
4.4 Special Inspection Requirements ..................................................................................................12
5TROUBLESHOOTING...........................................................................................................................13
5.1 G5 Electronic Flight Instrument......................................................................................................13
5.2 Outline and Installation Drawings ..................................................................................................21
5.3 G5 Interconnect Drawings .............................................................................................................22
6EQUIPMENT REMOVAL & INSTALLATION.........................................................................................23
6.1 G5 Unit...........................................................................................................................................23
6.2 G5 Battery......................................................................................................................................25
6.3 G5 Mounting Ring Replacement....................................................................................................25
6.4 GPS Antenna.................................................................................................................................26
6.5 GMU 11..........................................................................................................................................26
6.6 GAD 29/29B...................................................................................................................................27
6.7 GAD 13 ..........................................................................................................................................28
6.8 GTP 59...........................................................................................................................................28
6.9 Lightning Protection Component Installation .................................................................................28
7EQUIPMENT CONFIGURATION & TESTING......................................................................................36
7.1 Recommended Test Equipment ....................................................................................................36
7.2 Pitot Static System Leak Check.....................................................................................................36
7.3 G5 Software...................................................................................................................................36
7.4 G5 Configuration Mode..................................................................................................................37
7.5 G5 Calibration Procedures.............................................................................................................38
7.6 Compass Rose Swing....................................................................................................................42
7.7 Altimeter System Test....................................................................................................................43

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7.8 GMU 11..........................................................................................................................................43
8SYSTEM RETURN TO SERVICE PROCEDURE.................................................................................45
FIGURES
FIGURE PAGE
Figure 2-1 G5 Electronic Flight Instrument (Attitude) ......................................................................2
Figure 2-2 G5 Electronic Flight Instrument (DG/HSI)......................................................................4
Figure 2-3 G5 Battery.......................................................................................................................5
Figure 2-4 GMU 11 ..........................................................................................................................5
Figure 2-5 GAD 29/29B....................................................................................................................6
Figure 2-6 GPS Antenna (011-04036-10 shown)............................................................................7
Figure 5-1 Incorrect CAN Wiring Example.....................................................................................19
Figure 5-2 Correct CAN Bus Terminator Example ........................................................................20
Figure 5-3 G5 Outline Drawing (side view)....................................................................................21
Figure 5-4 G5 Outline Drawing (back view)...................................................................................21
Figure 5-5 G5 Exploded View........................................................................................................22
Figure 6-1 G5 Hex Driver...............................................................................................................23
Figure 6-2 G5 Captive Mounting Screw.........................................................................................24
Figure 6-3 G5 Mounting Ring.........................................................................................................25
Figure 6-4 GMU 11 Mounting Hardware........................................................................................27
Figure 6-5 G5 Resistor Method A Buildup.....................................................................................30
Figure 6-6 Method A Placement of G5 CAN Bus Resistors ..........................................................31
Figure 6-7 Method B G5 Resistor Preparation...............................................................................31
Figure 6-8 Method B Placement of G5 CAN Bus Resistors (G5 not CAN bus terminator)...........32
Figure 6-9 Method B Placement of CAN Bus Components (G5 as CAN bus terminator).............33
Figure 6-10 G5 Power Diode Buildup (Both Wire Types)..............................................................34
Figure 6-11 Placement of G5 Power Diode (Both Wire Types).....................................................35
Figure 7-1, Attitude Calibration Example.......................................................................................40
Figure 7-2, Example of Calibration Equations...............................................................................40
TABLES
TABLE PAGE
Table 1-1, Recommended Documents...........................................................................................1
Table 4-1, Maintenance Intervals..................................................................................................10
Table 4-2 –Electrical Bonding Procedure .....................................................................................11
Table 5-1, GAD 29/29B Status LED Indications...........................................................................16
Table 5-2, GAD 29/29B Status LED Indications...........................................................................17
Table 5-3 Status LED Indications ..................................................................................................19

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Table 7-1: Calibration Procedure Summary...................................................................................38
Table 7-2: Heading Verification......................................................................................................42

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1 INTRODUCTION
1.1 Introduction
This document provides Instructions for Continued Airworthiness (ICA) for the Garmin G5 Electronic
Flight Instrument as installed in Part 23 aircraft under STC SA01818WI. This document satisfies the
requirements for continued airworthiness as defined by 14 CFR Part 23.1529 and Appendix G.
Information in this document is required to maintain the continued airworthiness of the G5.
1.2 Organization
The following outline briefly describes the organization of this manual:
Section 2: System Description
Provides a complete description of the type design change associated with installing the G5. An
overview of the system interface is also provided.
Section 3: Control & Operation
Presents basic control and operation information specifically tailored to maintenance practices.
Section 4: Instructions for Continued Airworthiness
Provides maintenance instructions for continued airworthiness of the G5.
Section 5: Troubleshooting
Provides troubleshooting information to aid in diagnosing and resolving potential problems with the G5.
Section 6: Equipment Removal & Installation
Gives instructions for the removal and installation of the G5.
Section 7: Equipment Configuration & Testing
Gives instructions for loading software, configuring, and testing of G5.
Section 8: Return to Service Procedure
Specifies return-to-service procedures to be performed upon completion of maintenance of the G5.
1.3 Acronyms and Abbreviations
The following acronyms are used in this manual:
AML
Approved Model List
GPS
Global Positioning System
AFMS
Automatic Flight Control System
HSI
Horizontal Situation Indicator
CAN
Controller Area Network
ICA
Instructions for Continued Airworthiness
CFR
Code of Federal Regulations
LPM
Lightning Protection Module
DG
Directional Gyro
OAT
Outside Air Temperature
FAA
Federal Aviation Administration
STC
Supplemental TypeCertificate
TAS
True Airspeed
1.4 Publications
The following documents are recommended to be available when performing maintenance on the G5.
Table 1-1, Recommended Documents
Part Number
Garmin Document
190-01112-12
G5 Electronic Flight Instrument, Pilot's Guide for Certified Aircraft
190-01112-10
Garmin G5 Part 23 AML STC Installation Manual

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1.5 Revision and Distribution
This document is required for maintaining the continued airworthiness of the aircraft. When this
document is revised, every page will be revised to indicate current revision level.
Owner/operators may obtain the latest revision of this document from the Garmin website,
www.garmin.com.
2 SYSTEM DESCRIPTION
The G5 System equipment part numbers approved by STC SA01818WI-A are found in Table 1-2 of
Garmin document 190-01112-10, Garmin G5 Electronic Flight Instrument Part 23 AML STC
Installation Manual.
2.1 G5 Electronic Flight Instrument
2.1.1 G5 Attitude Indicator
The G5 Electronic Flight Instrument configured as an attitude indicator is shown in Figure 2-1. The G5
is an electronic flight instrument display operating as a standalone flight display. 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.
The G5 contains integrated attitude/air data sensors that provides display of attitude and secondary
display of air data information. The G5 Attitude indicator configuration is determined at the time of
installation as defined by the AML STC installation data and recorded in APPENDIX A of this
document and maintained with the aircraft records.
Figure 2-1 G5 Electronic Flight Instrument (Attitude)
The G5 calculates aircraft attitude using information from its built-in inertial sensors. If the G5 senses
that the attitude solution is valid, but not yet within the internal accuracy limits, "ALIGNING" is
displayed. The G5 can align itself both while taxiing and during level flight.
The G5 will also use GPS and airspeed data to provide the most accurate attitude information. If none of
these additional sources of information are available, attitude calculations will still be valid but accuracy
may be slightly affected.

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The G5 attitude functions are shown below:
•Pitch
•Roll
The G5 has a Turn Rate Indicator located at the bottom of the PFD Page. Tick marks to the left and right
of the displayed heading denote standard turn rates (3 deg/sec). A magenta Turn Rate Trend Vector
shows the current turn rate. A standard-rate turn is shown on the indicator by the trend vector stopping at
the standard turn rate tick mark.
The G5 displays slip/skid information as indicated by the location of the ball at the lower center portion
of the indicator.
The G5 receives a GPS input for attitude aiding via one of the following methods:
•GPS antenna
•GTN 6XX/7XX series navigator
•GNS 4XXW/5XXW series navigator
•GNS 480 series navigator
•GTX 3x5 transponder
•GPS 175/GNX 375 series navigators
The following functions are provided by the GPS input:
•Ground Track
•Ground Speed (GS)
When the G5 attitude is installed with a G5 HSI, the G5 attitude can also be interfaced to GPS NAV
and/or VHF NAV for display of lateral and vertical guidance.
The G5 installation is connected to the aircraft Pitot / Static system. The GTP 59 temperature probe is
optionally connected to the GAD 13 for Outside Air Temperature (OAT) information. The following
functions are provided:
•Secondary Airspeed indicator
•Secondary Barometric altimeter
•Secondary Vertical speed
•Secondary Altimeter Barometric Setting
•Secondary Altimeter
•Secondary Altitude Display
•Selected altitude setting, bug and visual altitude alerting
•Secondary Vertical Speed Indicator
•Vspeed references
•True Airspeed (TAS)
•Crosswind speed and direction
•OAT
The GMU 11 magnetometer can be installed as an optional interface for a standalone G5 attitude
display. This will allow the display of heading on the attitude display, but does not allow the removal of
the existing DG.

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2.1.2 G5 DG/HSI Indicator
The G5 Electronic Flight Instrument configured as a DG/HSI, is shown in Figure 2-2. The G5 is an
electronic instrument display operating as a standalone flight display. 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. In this
location the G5’s primary function is the display of slaved compass, VHF NAV and/or GPS NAV,
system #1 or #2. The G5 also contains integrated attitude/air data sensors that provide reversionary
display of attitude and secondary display of air data information. In the event the G5 attitude display
powers down, the G5 DG/HSI will automatically revert to displaying the attitude information.
The G5 DG/HSI configuration is determined at the time of installation as defined by the AML STC
installation data and recorded in APPENDIX A of this document and maintained with the aircraft
records.
Figure 2-2 G5 Electronic Flight Instrument (DG/HSI)
2.1.2.1 G5 Lightning Protection Module (LPM)
The G5 CAN bus inputs require additional and external protection from the effects of lightning. Earlier
installations used discrete components installed in the wiring harness (see Section 6.9.2). Later
installations utilize a modified backshell called a Lightning Protection Module (LPM), this was
introduced to replace the wire harness discrete component installation requirements.
2.1.3 Battery
The G5 has an external lithium-ion battery that provides up to 4 hours of emergency power. The battery
is required for the G5 used as an attitude display, but optional for the G5 used in the DG and HSI
position.

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Figure 2-3 G5 Battery
2.1.4 Installation Location
The G5 is installed in the pilot’s instrument panel in the primary attitude indicator location, in the rate-
of-turn indicator location, or in the DG/HSI location. The term “rate-of-turn indicator” refers to either a
turn coordinator or turn and bank indicator.
2.2 GMU 11 Magnetometer
The Garmin GMU 11 Magnetometer is a remote mounted device that interfaces with a G5 to provide
heading data to the G5 Attitude and/or G5 DG/HSI. The GMU 11 Magnetometer uses magnetic field
measurements to create electronically stabilized heading data. The GMU 11 is required when a G5 is
installed as a DG/HSI.
Figure 2-4 GMU 11
2.2.1 Installation Location
The GMU 11 installation location is determined at the time of installation as defined by the AML STC
installation data and recorded in APPENDIX B of this document and maintained with the aircraft
records. Installation is optional for the G5 as an attitude indicator and required for the G5 as a DG/HSI.
2.3 GAD 29/29B
The GAD 29/29B is a remote-mount unit that allows interface to IFR navigators such as the GNS and
GTN series. For installations with a G5 DG/HSI or a G5 DG/HSI and G5 attitude the GAD 29/29B will
receive ARINC 429 data from the navigator interfaced and transmit that information onto the CAN bus
to be consumed by the G5. The GAD 29B adds analog outputs and excitation pass through capability.
Installation is optional based on configuration of the system.

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Figure 2-5 GAD 29/29B
2.3.1 Installation Location
The GAD 29/29B installation location is determined at the time of installation as defined by the AML
STC installation data and recorded in APPENDIX B of this document and maintained with the aircraft
records.
2.4 GAD 13
The GAD 13 is a small unit used to interface to OAT probes. The GAD 13 provides a standard three-wire
or two-wire interface that can be connected to the following approved OAT probes:
• GTP 59
• Davtron C307PS
OAT analog information from the GAD 13 is converted to digital information, and passed to other G5
system LRUs using CAN communication. Connection to GAD 13 enables the G5 to display TAS, OAT,
and crosswind information.
Figure 2-6 GAD 13

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2.5 GTP 59 Temperature Probe
The Garmin GTP 59 is an externally mounted temperature probe that provides raw outside air
temperature data. The device is a three-wire temperature probe interface with a pre-installed wire lead that
is 10 feet long.
Figure 2-7 GTP 59 (Temperature Probe)
2.6 Glareshield Mounted antenna
The optional glareshield-mounted GPS antenna (Garmin part number 011-04036-10 or 011-04036-00)
feeds a GPS receiver inside the G5 which provides position, velocity, and time data to support various
instrument information.
NOTE
If GPS antenna 011-04036-00 is installed, which has a TNC connector, a TNC/BNC Adapter (p/n
330-01754-00) is required to connect the GPS antenna to the G5.
Figure 2-6 GPS Antenna (011-04036-10 shown)
This area intentionally blank

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3 BASIC CONTROL & OPERATION
The G5 unit will turn on automatically when power is applied to the avionics bus. The unit will turn off
automatically 45 seconds after power is removed. Alternatively, holding the button on the left lower
corner of the unit for three seconds will turn the unit off.
The knob on the lower right corner of the unit is used for the following;
G5 Attitude
•adjust the barometric pressure setting.
•Set heading bug #
•Set altitude pre-select
#Only configurations utilizing a GMU 11
G5 DG/HSI
•Set heading bug
•Selected course *
•Enable/Disable bearing pointer *
•Set altitude pre-select
•Enter PFD reversion
* Only configurations utilizing VHF NAV or GPS NAV
Pressing the power button brings up the backlight controls as well as the current battery status. The
backlight level adjusts automatically via a photocell. Temporary adjustments to the backlight level can
be made by turning the knob on the lower right corner of the unit to adjust. When power is cycled to the
unit, the backlight level is reset to use the photocell.
The GMU 11, GAD 13 and GAD 29/29B units are remote mounted units that have no independent
control or operation. These units are supporting units for the G5 functions and their use is dependent on
the configuration of the installation.
This area intentionally blank

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4.2.5 GTP 59 Temperature Probe
The GTP 59 unit maintenance is ‘on condition’ only. See section 6 for equipment removal and
installation. No component-level overhaul is required. Reference Table 4-1 for necessary tests or checks
and the specific intervals for the GTP 59.
4.2.6 Glareshield GPS Antenna
The Glareshield GPS antenna unit maintenance is ‘on condition’ only. See section 6 for equipment
removal and installation. No component-level overhaul is required. Reference Table 4-1 for necessary
tests or checks and the specific intervals for the Glareshield GPS Antenna.
4.2.7 Maintenance Intervals
Table 4-1 shows items installed by this STC which must undergo tests or checks at specific intervals.
Table 4-1, Maintenance Intervals
Item
Description/Procedure
Manual Section No.
Interval
G5 unit
Removal & Installation
6.1
On Condition
Altimeter System Test
7.7
24 calendar months
G5 battery
Removal & Installation
6.2
On Condition
Capacity Check
4.2.8
12 calendar months
G5 mounting ring
Removal & Installation
6.3
On Condition
GMU 11 unit
Removal & Installation
6.5
On Condition
GAD 29/29B unit
Removal & Installation
6.6
On Condition
GAD 13 unit
Removal & Installation
6.7
On Condition
GTP 59 unit
Removal & Installation
6.8
On Condition
Special Inspection
Requirements
4.4
On Condition
GPS Antenna
Removal & Installation
6.4
On Condition
4.2.8 Battery Capacity Check
1. Without power applied to the aircraft, turn on the G5 by pressing the power button in the lower
left corner of the unit.
2. Note the remaining battery capacity (%) at the top left corner of the display.
3. After about a minute, the remaining capacity will change from (%) to time (hour:min).
4. If the remaining capacity is less than one hour (1:00), allow the battery to charge until the
capacity shows greater than 95% and repeat the check.
5. If the remaining capacity is less than one hour (1:00) after charging, the battery must be replaced.

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4.3 Electrical Bonding Test
LRU electrical bonding must be checked every 2,000 flight hours or 10 years, whichever occurs first.
4.3.1 Requirements
•Disconnect any cables and connectors normally attached to the LRU.
•Resistance must be measured from a bare metal portion of the LRU (chassis or connector) to an
airframe grounding location.
•The airframe grounding location should be as close to the LRU as possible, unless otherwise
noted in Table 4-2.
4.3.2 Test Equipment
Calibrated 4 wire Milliohm meter and Kelvin probes are required for this test.
4.3.3 Electrical Bonding Test Procedures.
•Using a calibrated milliohm meter and Kelvin probes measure the resistance of each LRU
between the locations noted in
•
•Table 4-2, and record the result of each installed LRU. Some equipment on the list are optional
and may not be installed.
•Ensure the resistance does not exceed 10 milliohms except for the GTP that shall be less than 2.5
milliohms.
•If the measured resistance is greater 10 milliohms, bonding must be improved to meet applicable
requirements for a new installation in accordance with Section 4 of Garmin G5 Electronic Flight
Instrument Part 23 AML STC Installation Manual (190-01112-10).
Table 4-2 –Electrical Bonding Procedure
Unit
Measurement Location (2)
Result
(milliohm)
G5
J51 backshell to local structure adjacent to the
ground stud (1)
mΩ
GMU 11
P111 backshell to local structure adjacent to the
ground stud (1)
mΩ
GAD 29 / 29B
Chassis mounting screw to adjacent aircraft ground
mΩ
GAD 13
Chassis mounting screw to adjacent aircraft ground
mΩ
GTP 59
Probe and adjacent local metal structure for metal
and tube and fabric aircraft.
For composite aircraft no bonding requirement
mΩ
Notes:
(1) This is the ground stud to which the LRU bonding strap is connected
(2) For remote LRUs bonded to the back of the instrument panel via an installed aluminum foil ground plane,
the bonding measurement must be taken between the remote LRU and the instrument panel.

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4.4 Special Inspection Requirements
After a suspected lightning strike, the following actions must be performed for the specific LRU.
GTP 59 Temperature Probe
Inspect the GTP 59 temperature probe for signs of lightning damage. Check the self-sealing washer (P/N
212-00026-00) used on the probe tip outside of the aircraft for any evidence of melting or lack of seal.
Replace the washer if damaged. If there is evidence of lightning strike to the GTP 59 temperature probe
or any lightning damage, replace the probe.
Tube-and-fabric aircraft must replace the GTP 59 bond strap (if installed) in accordance with Section 4 of
the Garmin G5 Electronic Flight Instrument Part 23 AML STC Installation Manual (190-01112-10).
Lightning Protection Module (LPM)
The LPM shall be replaced. Reference Garmin G5 Electronic Flight Instrument Part 23 AML STC
Installation Manual, 190-01112-10 section 4 and 5 for connector assembly and wiring requirements of
LPM.
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