Garmin | G5 Electronic Flight Instrument for Certificated Aircraft | Garmin G5 Electronic Flight Instrument for Certificated Aircraft Maintenance Manual w/ICA - G5 Electronic Flight Instrument Part 23 AML STC

Garmin G5 Electronic Flight Instrument for Certificated Aircraft Maintenance Manual w/ICA - G5 Electronic Flight Instrument Part 23 AML STC
Garmin G5
Electronic Flight Instrument
Part 23 AML STC Maintenance Manual
Including Instructions for Continued
Airworthiness
190-01112-11
July 2019
Revision 6
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Telephone: 913-397-8200
Technical Support and Field Service Engineers: 888.606.5482
www.flyGarmin.com
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Telephone: 503.581.8101
Garmin G5 Electronic Flight Instrument Part 23 AML STC Maintenance Manual
Page A
190-01112-11
Rev. 6
RECORD OF REVISIONS
Revision
Revision Date
Description
1
7/22/16
Initial Release
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
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Garmin G5 Electronic Flight Instrument Part 23 AML STC Maintenance Manual
Page B
190-01112-11
Rev. 6
INFORMATION SUBJECT TO EXPORT CONTROL LAWS
This document may contain information which is subject to the Export Administration Regulations
(“EAR”) issued by the United States Department of Commerce (15 CFR, Chapter VII, Subchapter C)
and which may not be exported, released, or disclosed to foreign nationals inside or outside of the United
States without first obtaining an export license. 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
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.
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.
Garmin G5 Electronic Flight Instrument Part 23 AML STC Maintenance Manual
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Rev. 6
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.
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 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 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.
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Rev. 6
TABLE OF CONTENTS
SECTION .............................................................................................................................................. PAGE
1 INTRODUCTION ..................................................................................................................................... 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
2 SYSTEM 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
3 BASIC CONTROL & OPERATION .......................................................................................................... 8
4 INSTRUCTIONS 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
5 TROUBLESHOOTING ........................................................................................................................... 13
5.1 G5 Electronic Flight Instrument...................................................................................................... 13
5.2 Outline and Installation Drawings .................................................................................................. 20
5.3 G5 Interconnect Drawings.............................................................................................................. 22
6 EQUIPMENT 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........................................................................................................................................... 27
6.8 GTP 59 ........................................................................................................................................... 28
7 EQUIPMENT CONFIGURATION & TESTING ...................................................................................... 29
7.1 Recommended Test Equipment .................................................................................................... 29
7.2 Pitot Static System Leak Check ..................................................................................................... 29
7.3 G5 Software ................................................................................................................................... 29
7.4 G5 Configuration Mode .................................................................................................................. 30
7.5 G5 Calibration Procedures ............................................................................................................. 31
7.6 Compass Rose Swing .................................................................................................................... 35
7.7 Altimeter System Test .................................................................................................................... 36
7.8 GMU 11 .......................................................................................................................................... 36
8 SYSTEM RETURN TO SERVICE PROCEDURE ................................................................................. 38
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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....................................................................................................................... 4
Figure 2-4 GMU 11 .......................................................................................................................... 5
Figure 2-5 GAD 29/29B.................................................................................................................... 5
Figure 5-1 Incorrect CAN Wiring Example ..................................................................................... 19
Figure 5-2 Correct CAN Bus Terminator Example......................................................................... 19
Figure 5-3 G5 Outline Drawing (side view) .................................................................................... 20
Figure 5-4 G5 Outline Drawing (back view) ................................................................................... 21
Figure 5-5 G5 Exploded View ........................................................................................................ 21
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 ........................................................................................ 26
Figure 7.1, Attitude Calibration Example ....................................................................................... 33
Figure 7.2, Example of Calibration Equations................................................................................ 33
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 ........................................................................... 15
Table 5-2, GAD 29/29B Status LED Indications ........................................................................... 16
Table 5-3 Status LED Indications .................................................................................................. 19
Table 7-1: Calibration Procedure Summary................................................................................... 31
Table 7-2: Heading Verification ...................................................................................................... 35
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1
1.1
INTRODUCTION
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
AFMS
CAN
DG
CFR
FAA
1.4
Approved Model List
Automatic Flight Control System
Controller Area Network
Directional Gyro
Code of Federal Regulations
Federal Aviation Administration
GPS
HSI
ICA
OAT
STC
TAS
Global Positioning System
Horizontal Situation Indicator
Instructions for Continued Airworthiness
Outside Air Temperature
Supplemental Type Certificate
True Airspeed
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
Garmin G5 Electronic Flight Instrument Part 23 AML STC Maintenance Manual
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Rev. 6
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 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, as 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)
2.1.3 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.
Figure 2-3 G5 Battery
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2.1.4 Installation Location
The G5 is installed in the pilot’s instrument panel in the primary attitude indicator location, in the rateof-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.
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.
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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
• EDC-10A (Dynon)
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)
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Rev. 6
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 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
G5 unit
G5 battery
Description/Procedure
Manual Section No.
Interval
Removal & Installation
6.1
On Condition
Altimeter System Test
7.7
24 calendar months
Removal & Installation
0
On Condition
4.2.7
12 calendar months
Capacity Check
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
Removal & Installation
6.8
On Condition
Special Inspection
Requirements
4.4
On Condition
GTP 59 unit
4.2.7 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
G5
GMU 11
GAD 29 / 29B
GAD 13
GTP 59
Measurement Location (2)
J51 backshell to local structure adjacent to the
ground stud (1)
P111 backshell to local structure adjacent to the
ground stud (1)
Chassis mounting screw to adjacent aircraft ground
Chassis mounting screw to adjacent aircraft ground
Probe and adjacent local metal structure for metal
and tube and fabric aircraft.
For composite aircraft no bonding requirement
Result
(milliohm)
mΩ
mΩ
mΩ
mΩ
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).
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5
TROUBLESHOOTING
5.1
G5 Electronic Flight Instrument
5.1.1 General
NOTE
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
If a Red-X appears on the display or anywhere in the configuration mode menus, the following
troubleshooting steps may be used to help identify the cause.
1. Review the airframe logbook to verify if any G5 or other avionics or electrical maintenance has
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. Check that all connectors are fully seated, and that the jack screw connectors are fully tightened
on both sides of all connectors.
4. 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.
5. Ensure that the G5 is mounted securely.
6. 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.
7. Look for evidence of water or fluid contamination in the area around the G5.
8. Unplug the connector on the G5 or any affected LRU and check for bent pins.
9. Inspect the wire harness clamp on the rear of all connectors to verify that it is not too tight and
smashing/shorting the wires.
5.1.2 Attitude
If the attitude is failed and shows a Red-X condition, follow the troubleshooting steps in the previous
section. If this does not resolve the issue, gather answers to the following questions. This information
may be helpful to the customer, the avionics dealer, or to Garmin Aviation Product Support in
troubleshooting the failure.
1) What specifically was the nature of the failure? Was it a Red-X of 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 exactly was the aircraft doing in the two minutes that preceded the failure (taxiing 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 hangar using GPS repeaters?
4) How long did the failure last? Was it brief or sustained? If it was repetitive, about how many
times did it happen? Did it happen on more than one day?
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5) Was the problem correlated with a specific maneuver or a specific geographic area?
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?
5.1.3 Air Data
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.
5.1.3.1 Air Data (Installation with a GAD 13 and GTP 59 Installed)
If the OAT, TAS and WINDS annunciations show a Red-X condition:
1) Inspect GTP 59 OAT probe and connections for faults.
2) Replace the GTP OAT probe.
3) If the problem persists, replace the GAD 13 with a known good unit.
5.1.4 Heading Information (Installations with a GMU 11 Installed)
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). Localized sources of
interference on the ground may consistently cause a Red-X to be displayed on the heading in the
same spot while taxiing, and this is not caused by a failure of the GMU 11 or its calibration.
2) Check to see if any new equipment has been installed on the aircraft. If there has been, conduct
the magnetic interference test in Section 7.8.1 to see if the new equipment is causing magnetic
interference with the GMU 11.
3) On the G5 in configuration mode, select the Device Information page, select MAG and verify
there is a Green Check by MAG. If there is a Red-X by MAG, proceed to the next step.
4) Inspect and verify the CAN Bus wiring between the G5 and GMU 11.
a. With power removed, remove a connector from one of the devices that is not located at
either of the extreme ends of the CAN bus.
b. Using an ohm meter, verify that the resistance between the CAN HI and CAN LO pins on
the connector is 60 ohms. This will verify that the CAN backbone is properly terminated
at each end (two 120 ohm terminating resistors in parallel).
c. A resistance of 120 ohms indicates that one of the two required CAN terminations is
missing.
d. A resistance of 40 ohms or less indicates that too many terminations are installed.
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e. Verify that the CAN HI and CAN LO signals are not swapped, shorted together, or opencircuited at any LRU connector.
f.
Verify that the CAN HI and CAN LO signals are not shorted to ground (this can happen
when shielded wire is installed incorrectly).
5) If the problem persists, replace the GMU 11 with a known good unit.
5.1.5 VHF Navigation Information (Installations without a GAD 29/29B Installed)
If the VHF navigation information is removed from the G5 HSI display:
1) On the G5 in configuration mode, select the RS-232 configuration page, verify there is a Green
Check by ‘Input Format, Garmin VHF NAV Radio’ and ‘Output Format, Garmin VHF NAV
Radio’. If there is a Red-X by either of these items, proceed to the next step.
2) Check the RS-232 wiring connected between the G5 and the VHF Navigator using the instructions
in the General section above.
3) Verify the VHF Navigator configuration has not changed from the initial installation. Reference
APPENDIX A .
4) If the problem persists, replace the G5 or VHF Navigator with a known good unit.
5.1.6 VHF Navigation Information (Installations with a GAD 29/29B Installed)
If the VHF navigation information is removed from the G5 HSI display:
1) On the G5 in configuration mode, select the Device Information page, select A429 and verify
there is a Green Check by A429. If there is a Red-X by A429, proceed to the next step.
2) Check the ARINC 429 wiring connected between the G5 and the GAD 29/29B using the
instructions in the General section above.
3) The GAD 29/29B has an LED on the outer case that indicates the LRUs current status. The status
indications are:
Table 5-1, GAD 29/29B 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 similar devices are
configured with the same unit ID
4) If the LED indication is ‘No Light’, verify the circuit breaker, power and ground wiring between
the GAD 29/29B circuit breaker and GAD 29/29B. If proper power is available to the GAD
29/29B, replace the GAD 29/29B with a known good unit.
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5) If the LED indication is ‘Steady Green’, inspect and verify the CAN Bus wiring between the G5
and GAD 29/29B.
a. With power removed, remove a connector from one of the devices that is not located at
either of the extreme ends of the CAN bus.
b. Using an ohm meter, verify that the resistance between the CAN HI and CAN LO pins on
the connector is 60 ohms. This will verify that the CAN backbone is properly terminated at
each end (two 120 ohm terminating resistors in parallel).
c. A resistance of 120 ohms indicates that one of the two required CAN terminations is
missing.
d. A resistance of 40 ohms or less indicates that too many terminations are installed.
e. Verify that the CAN HI and CAN LO signals are not swapped, shorted together, or opencircuited at any LRU connector.
f.
Verify that the CAN HI and CAN LO signals are not shorted to ground (this can happen
when shielded wire is installed incorrectly).
6) If the LED indication is ‘Red’, replace the GAD 29/29B with a known good unit.
7) If the LED indication is ‘Alternating Red/Green’, verify the Unit ID strapping on the G5 units.
Reference Section 5.3 wiring interconnects for the appropriate Unit ID strapping.
8) Verify the VHF Navigator configuration has not changed from the initial installation. Reference
APPENDIX A .
9) If the problem persists, replace the GAD 29/29B with a known good unit.
5.1.7 GPS Navigation Information (Installations with a GAD 29/29B Installed)
5.1.7.1 GPS VFR Displayed on G5
If the GPS navigation information is removed from the G5 HSI display and GPS VFR is displayed:
1) On the G5 in configuration mode, select the Device Information page, select A429 and verify
there is a Green Check by A429. If there is a Red-X by A429 proceed to the next step.
2) Check the ARINC 429 wiring connected between the G5 and the GAD 29/29B using the
instructions in the General section above.
3) The GAD 29/29B has an LED on the outer case that indicates the LRUs current status. The status
indications are:
Table 5-2, GAD 29/29B 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
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Alternating Red/Green
CAN bus network error two similar devices are
configured with the same unit ID
4) If the LED indication is ‘No Light’ verify the circuit breaker, power and ground wiring between
the GAD 29/29B circuit breaker and GAD 29/29B. If proper power is available to the GAD
29/29B replace the GAD 29/29B with a known good unit.
5) If the LED indication is Steady Green Inspect and verify the CAN Bus wiring between the G5 and
GAD 29/29B
a. With power removed, remove a connector from one of the devices that is not located at
either of the extreme ends of the CAN bus.
b. Using an ohm meter, verify that the resistance between the CAN HI and CAN LO pins on
the connector is 60 ohms. This will verify that the CAN backbone is properly terminated at
each end (two 120 ohm terminating resistors in parallel).
c. A resistance of 120 ohms indicates that one of the two required CAN terminations is
missing.
d. A resistance of 40 ohms or less indicates that too many terminations are installed.
e. Verify that the CAN HI and CAN LO signals are not swapped, shorted together, or opencircuited at any LRU connector.
f.
Verify that the CAN HI and CAN LO signals are not shorted to ground (this can happen
when shielded wire is installed incorrectly).
6) If the LED indication is ‘Red’, replace the GAD 29/29B with a known good unit.
7) If the LED indication is ‘Alternating Red/Green’, verify the Unit ID strapping on the G5 units.
Reference Section 5.3 wiring interconnects for the appropriate Unit ID strapping.
8) Verify the GPS Navigator configuration has not changed from that set in the initial installation.
Reference APPENDIX A .
9) If the problem persists, replace the GAD 29/29B with a known good unit.
5.1.8 Loss of Non Garmin Autopilot Heading and/or Course Datum (Installations
with GAD 29B Installed)
If the Non-Garmin autopilot loses the capability to couple and track Heading and/or Course Datum:
1) Complete troubleshooting as directed and applicable in Section 5.1.4 for loss of Heading Datum,
Section 5.1.6 for loss of Course Datum and Section 5.1.7 for loss of GPSS Datum. If these all
indicate there is no problem continue to the next step.
2) Inspect and verify the ARINC 429 Bus wiring between the GPS Navigator, GAD 29B and
autopilot computer.
3) Inspect and verify the Analog wiring between the GAD 29B and the autopilot computer.
4) Verify the G5 and GPS Navigator configurations has not changed from that set in the initial
installation. Reference APPENDIX A .
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5) Verify the autopilot computer is functioning properly. Reference autopilot manufacturers
troubleshooting procedures.
6) If the problem persists, replace the GAD 29B with a known good unit.
5.1.9 GFC 500 Failure Messages
During operation of the GFC 500 AFCS, the G5 may annunciate a failure or fault that is specific to the
GFC 500 AFCS. Refer to the GFC 500 AFCS Maintenance Manual/ICA, 190-02291-01, for assistance
in troubleshooting the problem.
5.1.10 GPS position information removed (Units with no NAV interface)
If the GPS position information is removed from the G5 Attitude or HSI display (no GPS track or
Ground Speed).
1) On the G5 in configuration mode, select the RS-232 Configuration page, select Input Format and
verify there is a Green Check by MapMX. If there is a Red-X by MapMX, proceed to the next
step.
2) Check the RS 232 wiring connected between the G5 and the GPS Navigator using the instructions
in the General section above.
3) Verify the GPS Navigator configuration has not changed from the initial installation. Reference
APPENDIX A .
4) If the problem persists, replace the G5 with a known good unit.
5.1.11 MicroSD Card
A stuck or sticking microSD™ card in the G5 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. If the second card sticks, the microSD™ socket board inside the
unit may be misaligned with the overlay and the G5 will require repair. Garmin recommends using
SanDisk® brand cards.
5.1.12 Data Logging
Data logging on the G5 may be used to help troubleshoot issues. Operational data is gathered from the
G5 during flight or on ground and is stored in *.csv log files on the microSD™ card (if installed).
This area intentionally left blank
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5.1.13 CAN Bus Troubleshooting
If problems are occurring within the CAN bus network, the following steps can help to identify the
issue.
Review the status LED on the GAD29/29B. the status LED indications are listed in Table 5-3
Table 5-3 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)
1) Ensure the CAN bus is daisy-chained between CAN devices around the system, and CAN devices
are not connected via a single point or routed through a hub device (Figure 5-1). This can cause
unwanted signal reflections and “orphan” some devices on the bus and prevent their
communication.
Figure 5-1 Incorrect CAN Wiring Example
2) Ensure the CAN bus is terminated in only two locations, and only at the extreme ends of the CAN
bus (Figure 5-2).
Figure 5-2 Correct CAN Bus Terminator Example
3) 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.
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a. Using an Ohm meter, verify the resistance between the CAN-H and CAN-L pins on the
connector is 60 Ω. This will verify the CAN backbone is properly terminated at each end
(two 120 Ω terminating resistors in parallel).
b. A resistance of 120 Ω indicates one of the two required CAN terminations is missing.
c. A resistance of 40 Ω or less indicates too many terminations are installed.
4) Verify the CAN-H and CAN-L signals are not swapped, shorted together, or open-circuited at any
LRU connector.
5) Verify the CAN-H and CAN-L signals are not shorted to ground.
6) Highlight each device on the configuration mode Device Information page on the #1 G5 unit and
verify the value displayed for Network Error Rate is a steady 0%.
7) Power up 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.
5.2
Outline and Installation Drawings
Figure 5-3 G5 Outline Drawing (side view)
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Figure 5-4 G5 Outline Drawing (back view)
Figure 5-5 G5 Exploded View
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5.3
G5 Interconnect Drawings
For G5 system interconnect drawings reference Garmin Document 190-01112-10.
5.3.1 Connector Layout
For G5 system connector layout reference Garmin Document 190-01112-10.
This area intentionally blank
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6
EQUIPMENT REMOVAL & INSTALLATION
This section describes how to remove and install the equipment associated with this STC.
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 Part 23 AML STC Installation Manual.
6.1
G5 Unit
CAUTION:
When removing and/or installing the G5, always ensure that aircraft power is off. Unplug any
auxiliary power supplies.
Removal
Removal and reinstallation procedure for a standard G5 installation or a G5 recessed into the panel is
identical.
1. Insert a hex drive tool through the access hole in the front cover of the G5 as shown in Figure 6-1
loosen the unit from the mounting ring.
Figure 6-1 G5 Hex Driver
2. Disconnect the pitot and static lines from the G5 unit.
3. Disconnect the electrical connector and GPS coaxial cable connector (if installed) from the G5
unit.
4. Remove the G5 unit.
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Reinstallation
1. Inspect the electrical and coaxial connectors and pins for signs of damage. Repair any damage.
2. Reconnect the electrical connector and GPS coaxial connector (if installed) to the G5 unit.
3. Reconnect the pitot and static lines to the G5 unit. The ports are labeled on the unit using the
abbreviations “P” and “S” respectively.
4. Insert 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.
5. Insert a hex drive tool through the access hole in the front cover of the G5 as shown in Figure 6-1
and tighten the unit to the instrument panel using 10-12 in-lbs torque.
6. Proceed to Section 0 for configuration and testing.
If a replacement G5 unit is being installed in an instrument panel greater than 0.150 inch thick, the
captive mounting screw must be replaced with a longer #6-32 hex socket head screw. To replace the
captive mounting 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 6-2. Install a longer #6-32 hex socket head screw and
reinstall the screw mount plate. Ensure correct orientation of the screw mount plate before applying 6-8
in-lb. of torque to the #4-40 mount plate screws.
Figure 6-2 G5 Captive Mounting Screw
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6.2
G5 Battery
Removal
1. Loosen the G5 unit per Section 6.1. Do not remove the pitot and static lines or the electrical and
GPS coaxial cable connectors from the G5 unit if access to the battery can be gained while these
items remain connected.
2. Use a screwdriver to loosen the battery jackscrews on the back of the unit (reference Figure 5-5.)
3. Remove the battery from the G5 unit.
Reinstallation
1. Locate the battery on the back of the G5 unit.
2. Use a screwdriver to tighten the battery jackscrews to back of the G5 unit.
3. Reinstall the G5 unit per Section 6.1.
6.3
G5 Mounting Ring Replacement
Removal
1. Loosen the G5 unit per Section 6.1. Do not remove the pitot and static lines or the electrical and
GPS coaxial cable connectors from the G5 unit if access to the mounting ring can be gained while
these items remain connected.
2. Remove the three #6-32 screws that secure the mounting ring to the instrument panel.
3. Remove the G5 mounting ring.
Reinstallation
1. Locate the new mounting ring, and secure to the instrument panel using the three #6-32 screws.
2. Evenly torque the screws to 10-12 in-lbs.
3. Reinstall the G5 unit per Section 6.1.
Figure 6-3 G5 Mounting Ring
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6.4
GPS Antenna
Refer to the data which installed the GPS antenna for removal and installation of the GPS antenna.
6.5
GMU 11
CAUTION:
When removing and/or installing the GMU11, always ensure that aircraft power is off. Unplug
any auxiliary power supplies.
Removal
1. Gain access to the GMU 11. Refer to the location information recorded in APPENDIX B of this
document and maintained with the aircraft records.
2. Disconnect the GMU 11 connector.
3. Unscrew the 4 fasteners that hold the GMU 11 to the mounting location.
NOTE
Make sure the hardware removed from the GMU 11 mounting is retained for reinstallation. If hardware
needs to be replaced, reference Figure 6-4 for appropriate Hardware part numbers.
NOTE
Be sure to use non-magnetic tools to avoid harming the GMU.
Reinstallation
1. Place the GMU 11 in its mounting location and align its holes with the mounting holes.
2. Insert the 4 mounting screws and secure the GMU 11 in place with washers and nuts. Tighten
screws until snug, plus 1/4 turn.
3. Inspect the electrical connector and pins for signs of damage. Repair any damage.
4. Connect the wiring harness to the GMU 11.
5. Conduct the Magnetometer calibration procedure (Section 7.5.3), the Compass Rose Swing
(Section 7.6 ) and the Magnetic interference check (Section 7.8.1).
Figure 6-4 GMU 11 Mounting Hardware
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6.6
GAD 29/29B
CAUTION:
When removing and/or installing the GAD 29/29B, always ensure that aircraft power is off.
Unplug any auxiliary power supplies.
Removal
1. Gain access to the GAD 29/29B. Refer to the location information recorded in APPENDIX B of
this document and maintained with the aircraft records.
2. Disconnect the GAD 29/29B connectors.
3. Unscrew the 4 fasteners that hold the GAD 29/29B to the mounting location.
Reinstallation
1. Place the GAD 29/29B in its mounting location and align its holes with the mounting holes.
2. Insert the 4 mounting screws and secure the GAD 29/29B in place.
3. Inspect the electrical connectors and pins for signs of damage. Repair any damage.
4. Connect the wiring harness to the GAD 29/29B.
5. Conduct the system return to service procedure in Section 8.
6.7
GAD 13
CAUTION:
When removing and/or installing the GAD 13, always ensure that aircraft power is off. Unplug
any auxiliary power supplies.
Removal
1. Gain access to the GAD 13. Refer to the location information recorded in APPENDIX B of this
document and maintained with the aircraft records.
2. Disconnect the GAD 13 connectors.
3. Unscrew the 2 fasteners that hold the GAD 13 to the mounting location.
Reinstallation
1. Place the GAD 13 in its mounting location and align its holes with the mounting holes.
2. Insert the 2 mounting screws and secure the GAD 13 in place.
3. Inspect the electrical connectors and pins for signs of damage. Repair any damage.
4. Connect the wiring harness to the GAD 13.
5. Conduct the system return to service procedure in Section 8.
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6.8
GTP 59
CAUTION:
When removing and/or installing the GTP 59, always ensure that aircraft power is off. Unplug
any auxiliary power supplies.
Removal:
1. Ensure power is removed from the GAD 13.
2. Remove the mounting nut and washer from the GTP 59 probe.
3. Pull the GTP 59 from the mounting hole.
Reinstallation:
1. Place the GTP 59 on the previous installation location.
2. Install the washer and nut.
3. Torque nut to 100 +/- 20 in-lbs.
4. Conduct the system return to service procedure in Section 8.
This area intentionally blank
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7
EQUIPMENT CONFIGURATION & TESTING
This section contains instructions for configuration and checkout of the G5(s) and supporting equipment
after reinstallation or replacement. The steps which are not applicable to a particular installation may be
skipped.
The person performing these procedures must be familiar with the aircraft, have a working knowledge of
typical avionics systems, and has experience using the test equipment defined in this section.
7.1
Recommended Test Equipment
The following test equipment is recommended to conduct the procedures in this section:
• Air data test set (pitot/static ramp tester)
• Digital Multi-Meter
• Ground power unit capable of supplying 14/28 Vdc power to the aircraft systems and avionics
• Digital Level or equivalent
• VHF NAV Test Set
NOTE
All test equipment must have current calibration records.
7.2
Pitot Static System Leak Check
If the pitot and/or static system lines were removed from any G5 unit, perform a pitot static system leak
check in accordance with the aircraft manufacturer’s approved data.
CAUTION
To avoid damaging the G5 pressure sensors, both the pitot and static ports must be connected to
the air data test set.
7.3
G5 Software
This section contains procedures for loading software to the G5 unit.
7.3.1 Loader Card Creation
To create a software loader card, follow the procedures outlined below.
1. To obtain the latest software version approved for this STC, visit www.Garmin.com and navigate
to the Aviation Product/General Aviation/Indicators/G5 page. Do not download software from
the Experimental Aircraft web page.
2. Download the self-extracting update file onto your hard drive.
3. Insert a FAT32-formatted microSD™ card with at least 20 MB of free space into your card
reader.
4. Open the self-extracting update file and follow the instructions provided by the installer
application. You will be prompted to specify the drive letter of the microSD card you wish to use
for the update. When the transfer is complete, safely eject the microSD card.
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7.3.2 Software Loading Procedure
NOTE
If two G5’s are installed, this procedure must be completed on both G5’s. If both G5 units
software do not match, the G5 will post a “Software Version Mismatch” message on the display.
This message will be removed when both units have been loaded with matching software.
1. Power on the G5, then insert the software loader card created in Section 7.3.1 into the microSD™
card slot.
2. If the version of software on the card is newer than the version currently on the unit, a software
update pop-up will appear on the screen. Select OK to begin the update.
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 will be displayed while the unit powers on or in the configuration mode
menu.
7.4
G5 Configuration Mode
To enter configuration mode, hold down the knob while powering on the G5. Configuration selections
are made by rotating and pressing the knob on the face of the G5 as necessary to select the correct
configurations.
7.4.1 Configuration Pages Summary
When in configuration mode, the G5 displays the following configurations pages:
• Device Information – used to display device specific information such as the software version and
basic indicator configuration.
• Attitude – used to configure Indicator Type, Pitch Display preferences, and User Pitch offset.
• Air Data – used to enable/ disable the G5 Air Data Sensors and configure the Vertical Speed rate.
• Magnetometer – allows configuration of magnetometer and magnetometer positioning.
• Airspeed – allows for configuration of the reference speeds.
• Flight Controls – used to configure the system for Garmin and Non-Garmin autopilots if installed.
• Backlight – used to configure backlight configuration parameters.
• Display – used to configure the display format of the G5.
• Battery – used to set backup battery status and power off modes.
• GPS – used to configure the internal GPS receiver.
• Navigation – used to configure the display of navigation information
• Units – This page is used to configure the units type to display altitude, airspeed, ground speed,
vertical speed and pressure displays.
• RS-232 – used to configure the RS-232 input and output ports used of the G5.
• ARINC 429 - used to configure the ARINC 429 input and output ports used of the G5.
• Exit Configuration Mode – used to exit configuration mode.
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7.4.2 G5 configuration
Before replacing a G5 unit, the technician should obtain the most current G5 configuration settings
which are typically kept with the aircraft records (reference APPENDIX A ). If the existing
configuration setting record is not available, set the configuration to match the values and units indicated
in the aircraft’s AFM or other operational information. If any changes are made to the configuration
settings, record the new settings in APPENDIX A and keep in the aircraft records for future reference.
7.5
G5 Calibration Procedures
Table 7-1 describes the calibration procedures to be performed for the G5 unit after maintenance is
performed.
Table 7-1: Calibration Procedure Summary
Calibration
Procedure
Procedure
Description
Procedure Name
A
Pitch/Roll Offset Compensation
Level aircraft
C
Air Data Static Pressure
Calibration
Altitude calibration
GMU 11 Magnetometer
Calibration
Magnetometer
Calibration
D
Requirement
Procedure A is required if a new
G5 unit is installed
Procedure C is recommended if
the G5 altimeter does not match
primary altimeter
Procedure D is only required if a
GMU 11 was installed and
interfaced to either G5.
7.5.1 Calibration Procedure A: Pitch/Roll Offset Compensation
NOTE
If two G5’s are installed, this procedure must be done on both and can be done concurrently.
See Section 7.5.1.1 for example of this calibration procedure.
Using the following procedure, complete these equations.
1. *Consult the aircraft’s maintenance manual and locate the longitudinal (ROLL) and lateral
(PITCH) leveling points.
2. Using a digital level, document the Aircraft Roll and Pitch offsets. (Do not enter, exit, or move
the aircraft at this point.) Use a negative number for left wing up or nose up readings. Use a
positive number for left wing down or nose down readings.
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3. Select the Attitude Configuration Page.
4. Select Calibrate Pitch/Roll.
5. Ensure that aircraft and the unit comply with all on-screen instructions then select Start.
-Disregard item 1, leveling the aircraft is not necessary.
6. A progress screen will then be displayed. There is a 30 second countdown timer for the procedure
that resets if the aircraft moves.
7. When the calibration is complete, a successful status message will be displayed along with the
new pitch and roll offsets.
8. If the leveling offsets documented from Step 2 were both 0.0, the calibration is complete. If
either new offset were other than 0.0, continue to step 9.
9. Document the “New Roll Offset” and “New Pitch Offset” numbers and complete the equation.
10. Press “Done” and adjust the values of the “Roll Calibration” and the “Pitch Calibration” values to
the answers from the equations.
NOTE
It is recommended that the adjusted “Roll Calibration” and the “Pitch Calibration” values from
step 10 be recorded in Appendix A and retained with the aircraft permanent records.
11. Exit Configuration Mode.
12. This completes the Attitude Calibration Procedure.
*In flight level cruse attitude is not necessarily the same as the leveling points provided by the
manufacturer. Adjustments to the pitch and roll offsets can be made to compensate for the aircraft flight
characteristics.
7.5.1.1 Attitude Calibration Example
In Figure 7.1, the aircraft is sitting 5.2° nose up and 1.4° left wing up, (both negative number). Also, the
G5 is mounted in the pilot’s panel, which has an 8° forward tilt. After completing the Calibration
Procedure in Step 7, the value in the Pitch Calibration field on the G5 is 2.8° and -1.4° in the Roll
Calibration field. See Figure 7.2 for the completed equations.
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Figure 7.1, Attitude Calibration Example
Figure 7.2, Example of Calibration Equations
7.5.2 Calibration Procedure C: Air Data Static Pressure Calibration
NOTE
All selections made in configuration mode in this section are made on the G5 ID strapped as #1.
In a single G5 installation, Unit ID #1 is always the single G5 unit. In a Dual G5 installation,
Unit ID #1 is the G5 in the Attitude or Turn Coordinator position.
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.
The static pressure calibration requires the use of a pressure control system (test set) with an altitude
accuracy of at least ±5 ft. at sea level and ±20 ft. at 30,000 ft. It is necessary to re-calibrate to sea level
(0 ft.), 10,000 ft., 20,000 ft., and optionally to 30,000 ft. The operator is allowed to finish the calibration
at the end of the 20,000 ft. calibration if the aircraft operational ceiling is below 20,000 ft.
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.
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2. Select Calibrate Static Pressure.
3. Ensure all on-screen instructions have been complied with, then press Start.
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.
7.5.3 CALIBRATION PROCEDURE D: GMU 11 Magnetometer Calibration
NOTE
All selections made in configuration mode in this section are made on the G5 ID strapped as #1.
In a single G5 installation, Unit ID #1 is always the single G5 unit. In a Dual G5 installation,
Unit ID #1 is the G5 in the Attitude or Turn Coordinator position.
CAUTION
This magnetometer calibration procedure should be carried out on a compass rose to guarantee
measurements free of environmental magnetic disturbances. If a compass rose is not available a
sight compass can be used. Attempting to carry out this procedure on a typical ramp area may
not yield a successful calibration. The accuracy of the heading display on the G5 cannot be
guaranteed if this calibration is not performed on a magnetically clean and level surface.
NOTE
A magnetometer calibration failure is indicated by a “Magnetometer not Calibrated” message on
the G5 on power up. If necessary, move the aircraft to a different location and attempt the
magnetic calibration again.
1.
2.
3.
4.
5.
6.
7.
Start the aircraft engine in accordance with the aircraft AFM or POH.
After aircraft engine startup, taxi the aircraft to a properly calibrated compass rose.
At the compass rose, align the aircraft to a heading of magnetic north (+/- 10°).
Restart the G5 in configuration mode.
Go to the “Magnetometer” page Group on the G5 unit.
Select the “Calibrate Magnetometer…” page.
The G5 will display instructions. Follow the on-screen instructions and select “Next” to cycle
through each page of instructions.
8. On the final page, select “Start” to begin the calibration.
9. The G5 display advises the operator when to turn the aircraft, when to stop, and when to turn
again.
10. Upon instruction to turn, taxi the aircraft in a right turn. After approximately 25° to 30° of turn
from the last heading, the G5 display advises the operator when to stop the aircraft.
NOTE
If smooth accurate turns are not made, the G5 may incorrectly interpret a station and instruct to
“Hold current position…” prior to or after completion of the heading change. If this scenario is
encountered, it is best for the operator to temporarily ignore the “Hold current position…”
command and instead use compass rose references to complete the heading change. Dwelling at
these 30° increments for the time recommended by the G5 should result in successful calibration.
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11. The G5 instructs the operator to dwell at multiple headings around a complete circle.
12. Repeat the turn-and-stop process until the G5 advises that a successful calibration is complete and
“Calibration: Success” is displayed on the G5.
13. Select “Done” on the G5 to conclude this procedure
14. Exit configuration mode.
15. Continue to Section 7.6.
7.6
Compass Rose Swing
After the Magnetic Calibration Procedure is successfully completed, a compass swing must be
performed to verify the GMU 11 heading accuracy. If each heading displayed on the G5 (or G5 #1 and
G5 #2) is within ±10° of the actual heading no further adjustments are necessary.
1. With the G5(or G5 #1 and G5 #2 for a dual G5 installation) in normal mode, all of the aircraft
and avionics systems powered and operating normally, position the aircraft on a known compass
rose at a heading 360° (North), or select a level and magnetically clean location and use a sight
compass to position the aircraft to a heading of 360° (North).
2. Record the heading displayed on the G5 (or G5 #1 and G5 #2 for a dual G5 installation) in Table
7-2. Also record the heading displayed on the standby compass (these values can be used to
complete the standby compass calibration card).
3. Repeat step 2 for each of the headings listed in Table 7-2.
4. Calculate the heading errors by subtracting the displayed (B) value from the actual (A) value for
each of the headings in Table 7-2.
Table 7-2: Heading Verification
Heading (A)
Displayed G5 Heading
(B)
Heading Error (A-B)
Stby Compass
Heading
360º (North)
30º
60º
90º (East)
120º
150º
180º (South)
210º
240º
270º (West)
300º
330º
5. If all calculated heading errors for the G5 are +/-6° from the surveyed heading, the installation is
acceptable and no further action is required. Proceed to Section 8.
6. If a Heading Error (A-B) is greater than +/- 6°, calculate the average error by adding all errors
and dividing by 12. This is the angle by which the GMU 11 must be physically rotated to correct
the installation or before changing the physical location, perform a Magnetometer Interference
Check in Section 7.5.3 to verify interference is not causing the error.
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7. If necessary, modify the installation to rotate the GMU 11 by the amount calculated in the
previous step. When looking down at the GMU 11, rotate clockwise for positive values, and
counterclockwise for negative values.
After physically correcting the GMU 11 installation, repeat the procedures in Section 7.8.1 and Section
7.5.3 and this section.
7.7
Altimeter System Test
If the G5 unit is replaced, in aircraft that are IFR certified, perform an altimeter system test of the G5 in
accordance with 14 CFR Part 43 Appendix E.
7.8
GMU 11
If the GMU 11 is removed and reinstalled or removed and replaced, the procedure in 7.5.3 must be
conducted.
7.8.1 Magnetometer Interference Check
This check is to be used as necessary to help troubleshoot GMU 11 discrepancies that may be related to
interference or when a GMU 11 is moved and the new mounting location needs to be verified for
acceptable interference levels.
With the G5 in configuration mode, initiate the magnetometer interference test procedure by performing
the following steps:
NOTE
All selections made in configuration mode in this section are made on the G5 ID strapped as #1.
In a single G5 installation, Unit ID #1 is always the single G5 unit. In a Dual G5 installation,
Unit ID #1 is the G5 in the Attitude or Turn Coordinator position.
1. Select the “Magnetometer” page group on the G5 #1
2. Select the “Interference Test…” page.
3. Follow the instructions on each page displayed on the G5. Select “Next” to cycle through the
pages and “Back” to go to the previous page.
NOTE
The last page instructs the operator to prepare a detailed test sequence list with precise start and
stop times for exercising all electronic devices. Only the electronic devices that are likely to affect
the operation of the GMU 11 magnetometer need be included in the test sequence. The list of
relevant electronic devices varies from aircraft to aircraft. An example survey sequence form is
located in APPENDIX D .
4. Select “Start” to begin the test procedure.
5. The operator should carry out the actions called for in the prepared test sequence.
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.
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6. After the “Begin test sequence” appears, wait approximately five seconds and perform each of the
actions listed in the test sequence table. Refer to APPENDIX D for an example of a test
sequence.
7. When the test sequence is completed, wait approximately five seconds and then select “Done” to
complete the test.
The G5 informs the operator if the installation has passed or failed the magnetometer interference test.
The results displayed indicate the worst case percentage of limit and the time at which it occurred. If the
test passes, no further action is required.
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 magnetometer maximum deviation value and its
corresponding timestamp. Compare the corresponding timestamp with the prepared test sequence to
identify which action produced the problem.
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, especially if the ground return path
through the aircraft structure passes near the GMU 11.
This area intentionally blank
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8
SYSTEM RETURN TO SERVICE PROCEDURE
After all G5 configuration and testing is completed per Section 0, complete the following steps:
1. Position the aircraft to allow a GPS signal to be received.
2. Apply power to the aircraft and aircraft systems and allow the aircraft systems to initialize.
3. If new software was updated, verify the correct software part number is displayed. To verify the
latest software version approved for this STC, visit www.Garmin.com and navigate to the
Aviation Product/General Aviation/Indicators/G5 page.
4. On the G5 Attitude display, verify the following;
•
•
•
No Red-X’s displayed
Attitude display
Heading display (if interfaced to a GMU 11) Ground Track display (if not interfaced to a
GMU 11)
• Airspeed Tape (Digital read out will be dashes)
• Altitude Tape (Digital readout should be reasonable to field elevation)
• Ground speed field
• Slip skid display
• Current track bug
• Barometric Pressure setting field
• TAS display (if interfaced to a GAD 13)
• OAT display (if interfaced to a GAD 13)
5. On the G5 HSI display, verify the following;
•
•
•
•
•
•
No Red-X’s displayed
Heading/Ground Track display
o Heading Display - if interfaced to a GMU 11, indicated by white numbers indicating
magnetic heading.
o Ground Track display (if not interfaced to a GMU 11, indicated by magenta numbers
indicating GPS ground track.
Ground speed field (configurations without a GPS input will not display Ground Speed)
Current track bug (configurations without a GPS input will not display Current Track bug)
Rotating compass rose.
Crosswinds display (if interfaced to a GAD 13)
This area intentionally blank
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APPENDIX A G5 AND GPS/VHF NAVIGATOR CONFIGURATION
DOCUMENTATION
Appendix A contains the following:
• A G5 configuration recording sheet (A1), in the case of a dual G5 installation a configuration
sheet should be completed for each G5 installed.
• A section to record the manually calculated Pitch and Roll Calibration settings (A2).
The documentation will be completed during the initial installation and maintained with the aircraft
records.
A.1 G5 ELECTRONIC FLIGHT INSTRUMENT
Date:
Aircraft Make/Model:
Aircraft Reg #/Serial #:
G5 Part #:
G5 Serial #:
G5 software version:
CONFIGURATION PAGE
CONFIGURATION OPTION
CONFIGURATION SETTING
Device Information
Installation Type
Certified Instrument
Diagnostics/Data Log
Indicator Type
Pitch Display
Roll Display
Standard Turn Roll Reference
Automatic Declutter
Air Data Sensors
Outside Air Temp Sensor
Vertical Speed Indicator
VNE
VNO
VSO
VS1
VFE
VA
VX
VY
VG
VR
VMC
VYSE
Magnetometer
Orientation
Garmin Autopilot Servos
Analog Autopilot Interface
Current Mode
Default Mode
Minimum Photocell Input
Minimum Display Brightness
Maximum Photocell Input
Maximum Display Brightness
Filter Time Constant
HSI Page
Power Up Page
Show Battery Status
Enabled
Normal
Normal
Attitude Configuration
Air Data
Airspeed
Note: Configure Units prior to setting
airspeeds
Magnetometer
Flight Controls
Backlight
Display
Battery
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Hide
Enabled
Automatic
Automatic
Default
Default
Default
Default
Default
When Using Battery
190-01112-11
Rev. 6
Date:
Aircraft Make/Model:
Aircraft Reg #/Serial #:
G5 Part #:
G5 Serial #:
G5 software version:
CONFIGURATION PAGE
CONFIGURATION OPTION
CONFIGURATION SETTING
Automatic Power Off
Internal GPS Receiver
On Ground Only
GPS
GPS Data Fields
Navigation
Units
RS-232
ARINC 429
Navigation Data
Selected Course
VNAV Deviation Scale
Altitude
Distance
Airspeed
Ground Speed
Ground Track
Vertical Speed
Pressure
Input Format
Output Format
Output 1
Output 2
Input 1
Input 2
Input 3
Input 4
Magnetic
A.2 ADJUSTED “ROLL CALIBRATION” AND “PITCH CALIBRATION” VALUES
If the method to manually calculate the adjusted “Roll Calibration” and “Pitch Calibration” values was
used, record the values here.
Axis
Value
Pitch
Roll
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A.3 GTN 6XX/7XX CONFIGURATION (IF USED)
Config Page
ARINC 429
Config Option
ARINC 429 In (x)
(x represents any available ARINC
429 Port )
ARINC 429 In (x)
(x represents any available ARINC
429 Port )
ARINC 429 Out (x)
(x represents any available ARINC
429 Port )
Configuration Setting
Speed =
Data =
RS-232
RS-232 (x)
(x represents any available RS-232
Port )
Input =
Output =
Main Indicator (Analog) Configuration
CDI Key
Selected Course for GPS
Selected Course for VLOC
V-Flag State
VOR/LOC/GS Configuration
Nav Radio
ARINC 429 Configuration
Main System
Heading Source Input
Altitude Source Input
Speed =
Data =
Speed =
Data =
Tx Speed =
SDI =
Not Connected
This selection is made only if the GTN being
interfaced to has no other Heading input.
Connected
This selection is made only if the GTN being
interfaced to has no other Altitude input.
A.4 GNS 4XX(W) / 5XX(W) CONFIGURATION (IF USED)
Config Page
MAIN ARINC 429 CONFIG Page
Config Option
IN (x)
(x represents any available ARINC
429 Port )
IN (x)
(x represents any available ARINC
429 Port )
OUT
Configuration Setting
Speed =
Data =
Speed =
Data =
Speed =
Data =
VNAV
MAIN RS232 CONFIG Page
RS-232 (x)
(x represents any available RS-232
Channel )
MAIN CDI/OBS CONFIG Page
VOR/LOC/GS ARINC 429 CONFIG Page
Input =
Output =
Press Menu and then select “IGNORE SEL
CRS FOR VLOC?” Menu will display “ALLOW
SEL COURSE FOR VLOC?” when set
properly.
SPEED
RX =
TX =
SDI
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A.5 GNS 480 CONFIGURATION (IF USED)
Config Page
Config Option
Configuration Setting
GND Maint Serial Setup
CH (x)
(x represents any available Serial
Channel )
Output =
GND Maint ARINC 429 Setup
CH In (2)
(or any available 429 Port )
SEL =
SPEED =
SDI =
SEL =
SPEED =
SDI =
SEL =
SPEED =
SDI =
CH Out (1)
(or any available 429 Port )
CH Out (2)
(or any available 429 Port )
GND Maint Resolver Interface Setup
Resolver
GND Maint Miscellaneous Setup
CDI Select
A.6 GNC 255 CONFIGURATION (IF USED)
Config Page
Config Option
Sys Configuration
RS 232 Serial Port
Attitude Configuration
CDI Indicator
Configuration Setting
A.7 SL30 CONFIGURATION (IF USED)
Config Page
Config Option
Sys Configuration
RS 232 Serial Port
Attitude Configuration
Indicator Type
Configuration Setting
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APPENDIX B EQUIPMENT LOCATIONS
Appendix B contains a documentation sheet for recording LRU’s included in the installation and its
location on the aircraft. The document will be completed during the initial installation and maintained
with the aircraft records.
B.1
Equipment Locations
Date:
Aircraft Make/Model:
LRU
Aircraft Reg #/Serial #:
LRU included in this
installation?
Description of Location
G5 #1
G5 #2
GMU 11
GAD 29/29B
GAD 13
This area intentionally blank
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APPENDIX C WIRE ROUTING
Appendix C contains a generic aircraft drawing to be used for documenting the wire routing for the
installation of the G5, GMU 11 and GAD 29/29B. The drawing will be completed during the initial
installation and maintained with the aircraft records.
C.1
Wire Routing Single Engine
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C.2
Wire Routing Twin Engine
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APPENDIX D EXAMPLE MAGNOTOMETER INTERFERENCE SURVEY
SEQUENCE
Example Survey Sequence
A/C Reg.:__________________
Elapsed Time
Elapsed Time
(sec)
(min:sec)
0
0:00
20
0:20
30
0:30
40
0:40
50
0:50
60
1:00
70
1:10
80
1:20
90
1:30
100
1:40
110
1:50
120
2:00
140
2:20
160
2:40
180
3:00
190
3:10
200
3:20
210
3:30
220
3:40
230
3:50
240
4:00
250
4:10
260
4:20
270
4:30
280
4:40
290
4:50
300
5:00
310
5:10
320
5:20
330
5:30
340
5:40
350
5:50
360
6:00
370
6:10
380
6:20
390
6:30
400
6:40
410
6:50
420
7:00
430
7:10
Survey data file name:___________________________________________
Action
Test begins (calibration period – no activity permitted)
Calibration period ends
Aileron full right
Aileron full left
Aileron level
Rudder full right
Rudder full left
Rudder neutral
Elevators full up
Elevators full down
Elevators neutral
Flaps down
Flaps up
Landing gear up
Landing gear down
Speed brake up
Speed brake down
Navigation lights on
Navigation lights off
Landing lights on
Landing lights off
Taxi lights on
Taxi lights off
Air conditioning on
Air conditioning off
Landing lights and taxi lights on
Landing lights and taxi lights off
Strobes on
Strobes off
Recognition lights on
Recognition lights off
Turn on all wingtip lights simultaneously
Turn off all wingtip lights simultaneously
Beacon on
Beacon off
Autopilot engaged in a pitch and roll made (to engage servo clutches)
Autopilot disengaged
Pitot heat on
Pitot heat off
End of test
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