Garmin | G5 Electronic Flight Instrument for Certificated Aircraft | Garmin G5 Electronic Flight Instrument for Certificated Aircraft Install Manual - G5 Electronic Flight Instrument Part 23 AML STC

Garmin G5 Electronic Flight Instrument for Certificated Aircraft Install Manual - G5 Electronic Flight Instrument Part 23 AML STC
Garmin G5
Electronic Flight Instrument
Part 23 AML STC Installation Manual
190-01112-10
December 2017
Page 1
Revision 11
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Garmin International, Inc
1200 E. 151st Street Olathe, KS 66062 USA
Telephone: 913-397-8200
Technical Support and Field Service Engineers: 888.606.5482
www.flyGarmin.com
Garmin (Europe) Ltd.
Liberty House
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Southampton, SO40 9LR, UK
Telephone: +44 (0) 23 8052 4000
Fax: +44 (0) 23 8052 4004
Garmin AT, Inc.
2345 Turner Rd. SE
Salem, OR 97302 USA
Telephone: 503.581.8101
Garmin G5 Electronic Flight Instrument Part 23 AML STC Installation Manual
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RECORD OF REVISIONS
Revision
Revision Date
Description
1
07-14-2016
Initial Release
2
07-21-2016
Revised to incorporate comments and changes driven by document
reviews.
3
08-08-2016
Removed shock mount installation limitation in section 2.1, removed
shock mount replacement instructions in section 4.1 and added
engine run up details in section 5.3.7.2.
4
01-05-2017
Updated Section 1.5 to show software P/N 006-B2304-02, revised
section 3.4.1 to add clarification on GPS receiver configuration,
updated Table 5-1 to add clarification on GPS receiver configuration.
5
03-07-2017
Revised to add G5 DG/HSI, supporting equipment and associated
functions.
6
04-26-2017
Updated GAD 29 and GMU 11 Part Numbers
7
06-20-2017
Updated GMU 11 & GAD 29 Dimensions and EMI Test Harness
8
10/14/2017
Revised to cover changes associated with the addition of the
G5/GAD 29B third party autopilot interfaces.
9
10/26/2017
Update third party autopilot configurations and minor typographical
corrections.
10
11/02/2017
Corrected Cessna Third Party autopilot model coverage and minor
wiring typographical fixes.
11
12/04/2017
Changed the configuration sections to match the changes from SW
5.00 and minor typographical fixes.
This area intentionally blank
Garmin G5 Electronic Flight Instrument Part 23 AML STC Installation Manual
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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.
This area intentionally blank
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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.
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 should only be made by an
authorized Garmin service center. Unauthorized repairs or modifications could result in
permanent damage to the equipment and void both the warranty and the authority to operate this
device under FAA, FCC, and other applicable regulations.
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NOTE:
Use of polarized eyewear may cause the display to appear dim or blank.
NOTE
All screen shots used in this document are current at the time of publication. Screen shots are
intended to provide visual reference only. All information depicted in screen shots, including
software file names, versions, and part numbers, is subject to change and may not be up to date.
This area intentionally blank
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TABLE OF CONTENTS
SECTION ................................................................................................................................... PAGE
1 GENERAL DESCRIPTION ........................................................................................................... 12
1.1 Introduction .......................................................................................................................... 12
1.2 Acronyms and Abbreviations ................................................................................................. 12
1.3 Reference Documents .......................................................................................................... 13
1.4 STC Permission.................................................................................................................... 13
1.5 Scope .................................................................................................................................. 13
1.6 System Overview.................................................................................................................. 14
1.7 Technical Specifications ........................................................................................................ 21
2 LIMITATIONS .............................................................................................................................. 22
2.1 Installation Limitations ........................................................................................................... 22
2.2 Operational Limitations .......................................................................................................... 23
3 INSTALLATION OVERVIEW ........................................................................................................ 24
3.1 Introduction .......................................................................................................................... 24
3.2 Installation Materials ............................................................................................................. 24
3.3 Test Equipment .................................................................................................................... 27
3.4 Installation Considerations..................................................................................................... 27
4 INSTALLATION PROCEDURES................................................................................................... 34
4.1 Mechanical Installation .......................................................................................................... 34
4.2 Antenna Cable Installation and Connections ........................................................................... 64
4.3 Electrical Installation ............................................................................................................. 65
4.4 Weight and Balance .............................................................................................................. 72
4.5 Electrical Load Analysis ........................................................................................................ 72
4.6 Electrical Bonding ................................................................................................................. 81
5 SYSTEM INTERCONNECTS ....................................................................................................... 86
5.1 G5 Interconnect Notes .......................................................................................................... 87
5.2 Power and Ground................................................................................................................ 88
5.3 G5 (Attitude Indicator) with External GPS Antenna .................................................................. 89
5.4 G5 (Attitude Indicator) with GPS Position Input ....................................................................... 91
5.5 G5 (Attitude Indicator) and GMU 11 with GPS Position Input ................................................... 94
5.6 G5 (Attitude Indicator or DG), GMU 11 and GPS Antenna ....................................................... 97
5.7 G5 (HSI) with VHF Navigator ............................................................................................... 100
5.8 G5 (HSI) with GPS/VHF Navigator ....................................................................................... 103
5.9 Dual G5 without Navigator ................................................................................................... 108
5.10 Dual G5 with VHF Navigator ................................................................................................ 111
5.11 Dual G5 with GPS/VHF Navigator ........................................................................................ 115
5.12 GAD 29B Interface to Third-Party Autopilots ......................................................................... 120
6 SYSTEM CONFIGURATION AND CHECKOUT PROCEDURES .................................................. 131
6.1 Overview ............................................................................................................................ 131
6.2 Mounting, Wiring, and Power Checks ................................................................................... 131
6.3 Post-Installation Checkout Procedures ................................................................................. 131
6.4 Documentation Checks ....................................................................................................... 153
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FIGURES
Figure
Page
Figure 1-1, G5 Electronic Flight Instrument (Attitude) .............................................................. 15
Figure 1-2 G5 Standby Battery .............................................................................................. 16
Figure 1-3 G5 Electronic Flight Instrument (DG/HSI) ............................................................... 18
Figure 1-4 GMU 11 ............................................................................................................... 20
Figure 1-5 GAD 29/29B ......................................................................................................... 21
Figure 3-1 CAN Bus Backbone .............................................................................................. 30
Figure 3-2 Correct CAN BUS Wiring Example and Node Connections ...................................... 30
Figure 3-3 Incorrect CAN Wiring Example .............................................................................. 31
Figure 3-4 CAN Bus Termination (011-02887-00) for G5 and GMU 11 ..................................... 31
Figure 3-5 CAN Bus Termination for GAD 29/29B ................................................................... 31
Figure 4-1 Typical G5 Installations for IFR Approved Aircraft .................................................. 35
Figure 4-2 G5 Mounting Ring ................................................................................................ 36
Figure 4-3 Maximum Misalignment of the G5 in the Lateral Axis.............................................. 36
Figure 4-4 Maximum Misalignment of the G5 in the Longitudinal Axis ...................................... 37
Figure 4-5 Maximum Misalignment of the G5 in the Vertical Axis............................................. 37
Figure 4-6 G5 Alignment Pin.................................................................................................. 38
Figure 4-7 G5 Hex Driver Insertion......................................................................................... 38
Figure 4-8 G5 Captive Mounting Screw Replacement ............................................................. 39
Figure 4-9 Required Vertical Spacing Between G5 Units ......................................................... 40
Figure 4-10 Instrument Panel Modification .............................................................................. 40
Figure 4-11 G5 Adapter Plate ................................................................................................ 41
Figure 4-12 G5 Adapter Plate Assembly ................................................................................. 41
Figure 4-13, G5 Instrument Hole Dimensions ......................................................................... 42
Figure 4-14, Clearance for Connections ................................................................................. 43
Figure 4-15 Recessed Adapter Plate ...................................................................................... 43
Figure 4-16 Recessed Adapter Plate Template Reference Holes ............................................. 44
Figure 4-17 Single G5 Recessed Adapter Plate Installation ..................................................... 45
Figure 4-18 Single G5 Recessed Installation .......................................................................... 45
Figure 4-19 Dual Vertical G5 Recessed Adapter Plate Installation............................................ 46
Figure 4-20 Dual Vertical G5 Recessed Installation ................................................................. 46
Figure 4-21 Dual Horizontal G5 Recessed Installation ............................................................ 47
Figure 4-22, Instrument Panel Limitations............................................................................... 48
Figure 4-23 Instrument Panel; View looking forward ................................................................ 49
Figure 4-24 Instrument Panel view with instruments removed .................................................. 49
Figure 4-25 Recessed Adapter Plate located on panel ............................................................ 50
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Figure 4-26 Match drilling through panel, using adapter plate as template ................................ 50
Figure 4-27 Preliminary trimming of adapter plate ................................................................... 51
Figure 4-28 Adapter plate located on far side of instrument panel ............................................ 51
Figure 4-29 Additional trimming of adapter plate required ........................................................ 52
Figure 4-30 Trimmed adapter plate ........................................................................................ 52
Figure 4-31 Adapter plate mounting holes .............................................................................. 53
Figure 4-32 Dual G5 panel cutout, using match drilled holes for reference ................................ 53
Figure 4-33 Instrument panel after cutout for dual vertical G5 units .......................................... 54
Figure 4-34 Adapter plate installed......................................................................................... 54
Figure 4-35 Dual vertical G5 units installed ............................................................................. 55
Figure 4-36 G5 flush mount adapter plate printable template ................................................... 56
Figure 4-37 GMU 11 Pitch and Roll Requirements .................................................................. 58
Figure 4-38 GMU 11 Heading Alignment Requirements .......................................................... 59
Figure 4-39 GMU 11 Mounting Hardware ............................................................................... 60
Figure 4-40 GAD 29/29B Mounting Hardware ......................................................................... 62
Figure 4-41 GAD 29B Inline Transformer Mounting Instructions ............................................... 62
Figure 4-42 Wiring Harness Connector Assembly ................................................................... 69
Figure 4-43 Shield Termination Methods ................................................................................ 70
Figure 4-44 Ammeter Placement for Current Measurements.................................................... 75
Figure 4-45 Blank Electrical Load Tabulation Form, Sheet 1 of 2.............................................. 77
Figure 4-46 Blank Electrical Load Tabulation Form, Sheet 2 of 2.............................................. 78
Figure 4-47 Sample Completed Electrical Load Tabulation Form, Sheet 1 of 2.......................... 79
Figure 4-48 Sample Completed Electrical Load Tabulation Form, Sheet 2 of 2.......................... 80
Figure 4-49 Fiberglass Insulation for Carbon Fiber Material ..................................................... 82
Figure 4-50 Aluminum Tape Joint .......................................................................................... 83
Figure 4-51 Aluminum Tape Ground Termination .................................................................... 84
Figure 4-52 GAD 29/29B Aluminum Tape Installation .............................................................. 84
Figure 5-1 G5 Interconnect Notes .......................................................................................... 87
Figure 5-2 Power and Ground................................................................................................ 88
Figure 5-3 G5 (Attitude Indicator) with External GPS Antenna.................................................. 89
Figure 5-4 G5 (Attitude Indicator) with GPS Position Input ....................................................... 91
Figure 5-5 G5 (Attitude Indicator) and GMU 11 with GPS Position Input ................................... 94
Figure 5-6 G5 (Attitude Indicator or DG), GMU 11 and GPS Antenna ....................................... 97
Figure 5-7 G5 (HSI) with VHF Navigator ............................................................................... 100
Figure 5-8 G5 (HSI) with GPS/VHF Navigator ....................................................................... 103
Figure 5-9 G5 (HSI) with GPS/VHF Navigator Notes ............................................................. 104
Figure 5-10 Dual G5 without Navigator ................................................................................. 108
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Figure 5-11 Dual G5 with VHF Navigator .............................................................................. 111
Figure 5-12 Dual G5 with GPS/VHF Navigator ...................................................................... 115
Figure 5-13 Dual G5 with GPS/VHF Navigator Notes ............................................................ 116
Figure 5-14 GAD 29B Interface to Century Autopilots Sheet 1 of 2 ......................................... 121
Figure 5-15 GAD 29B Interface to Century Autopilots Sheet 2 of 2 ......................................... 122
Figure 5-16 GAD 29B Interface to Cessna Autopilots Sheet 1 of 2 ......................................... 124
Figure 5-17 GAD 29B Interface to Cessna Autopilots Sheet 2 of 2 ......................................... 125
Figure 5-18 GAD 29B Interface to Garmin Autopilots............................................................. 126
Figure 5-19 GAD 29B Interface to Honeywell Autopilots ........................................................ 127
Figure 5-20 GAD 29B Interface to S-TEC Autopilots ............................................................. 129
Figure 6-1, Attitude Calibration Example............................................................................... 137
Figure 6-2, Example of Calibration Equations ....................................................................... 137
Figure 6-3 Engine Vibration Test Failure Indication ............................................................... 139
Figure 6-4 Example EMC Source/Victim Matrix ..................................................................... 150
Figure 6-5 J51 on the G5..................................................................................................... 155
Figure 6-6 J111 on the GMU 11 ........................................................................................... 156
Figure 6-7 J291 on the GAD 29/29B .................................................................................... 158
Figure 6-8 J292 on the GAD 29/29B .................................................................................... 158
Figure 6-9 G5 Outline Drawing ............................................................................................ 161
Figure 6-10 G5 Installation Drawing ..................................................................................... 162
Figure 6-11 G5 Panel Cutout Measurements (Not to Scale) ................................................... 163
Figure 6-12 GAD 29/29B Outline Drawing ............................................................................ 164
Figure 6-13 GAD 29/29B Install Breakdown .......................................................................... 165
Figure 6-14 GMU 11 Outline Drawing................................................................................... 166
Figure 6-15 GMU 11 Install Breakdown ................................................................................ 167
Figure 6-16 Magnetic Interference Test Harness................................................................... 169
Figure 6-17 GMU 11 Overbraid Installation ........................................................................... 173
Figure 6-18 GMU 11 Overbraid Termination ......................................................................... 174
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TABLES
Table
Page
Table 1-1: Reference Documents........................................................................................... 13
Table 1-2 G5 Attitude and G5 DG/HSI Equipment ................................................................... 14
Table 1-3: Physical Characteristics ........................................................................................ 21
Table 1-4: Power Requirements............................................................................................. 22
Table 3-1: Contents of the G5 Installation Kit (011-03892-00) .................................................. 24
Table 3-2: Contents of the GMU 11 Installation Kit (011-04349-90) .......................................... 24
Table 3-3: Contents of the Connector Kit (011-03002-00) ........................................................ 24
Table 3-4: Contents of the GAD 29/29B Connector Kit (011-03271-00) .................................... 25
Table 3-5: G5 Adapter Plate .................................................................................................. 25
Table 3-6: G5 Recessed Adapter Plate .................................................................................. 25
Table 3-7 Supported Garmin Antennas .................................................................................. 28
Table 3-8 Supported Non-Garmin Antennas ........................................................................... 28
Table 3-9 GPS Antenna Minimum Requirements .................................................................... 28
Table 3-10: G5 and Supporting LRU Circuit Breaker Labels..................................................... 29
Table 4-1 GMU 11 Supporting Hardware ................................................................................ 58
Table 4-2 GAD 29/29B Supporting Hardware ......................................................................... 61
Table 4-3: Contact Crimp Tooling........................................................................................... 65
Table 4-4: G5 (1P51, 2P51) and GMU11 (P111) Connector Parts ............................................ 66
Table 4-5: GAD 29/29B 9-pin (P291) Connector Parts ............................................................. 67
Table 4-6: GAD 29/29B 25-pin (P292) Connector Parts ........................................................... 68
Table 4-7: LRU Weights ........................................................................................................ 72
Table 4-8: Sample Net Electrical Load Change Calculation ..................................................... 73
Table 5-1: Third-Party Autopilots.......................................................................................... 120
Table 6-1: Post-Installation Calibration Procedure Summary.................................................. 135
Table 6-2: Heading Verification ............................................................................................ 142
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1
1.1
GENERAL DESCRIPTION
Introduction
The G5 is an electronic instrument display capable of operating as a primary attitude indicator,
backup attitude indicator with primary rate-of-turn indicator, DG or HSI. This STC approves
the installation of the G5(s) in the existing instrument panel.
In the attitude application, the Garmin G5 indicator can replace an existing vacuum attitude
indicator or rate-of-turn indicator. The G5 can also replace existing vacuum driven DGs or
existing HSI’s, either standalone or in combination with a G5 attitude display.
When installed as a DG/HSI, the G5 can interface with third party autopilots using the GAD
29B.
The G5 is designed to be installed into a standard 3 1/8” instrument hole in place of the
existing indicators mentioned previously. The other primary flight instruments remain in the
current approved locations. The G5 cannot replace an existing primary attitude indicator that
has a Flight Director; however, if the existing attitude indicator is interfaced to the autopilot
and it does not include a Flight Director, that existing attitude indicator can be moved to the
rate-of-turn indicator location and the G5 installed as the primary attitude indicator.
Alternatively, for installations that do not install the G5 as a replacement primary attitude
indicator, the G5 can be installed as a second attitude indicator in place of the existing rate-ofturn indicator. If the existing rate-of-turn indicator is interfaced with the autopilot, it cannot
be replaced by a G5. The G5 can only be installed in the locations specified in this STC. It is
the installer’s responsibility to ensure the installation limitations are considered prior to
modifying the aircraft.
NOTE
Throughout this document the term “rate-of-turn indicator” will be used and could be speaking
to either a turn coordinator or turn and bank indicator. Typically these instruments are used to
cross-check the attitude indicator and directional gyro for bank information. However, these
instruments only provide information that the aircraft is in a turn and whether the turn is at the
standard rate (a standard rate turn is 3 degrees per second, or 2 minutes for a full 360-degree
circle). They do not provide information on the bank angle. Regardless of the specific
instrument installed the G5 is capable of replacing either configuration of a turn coordinator or
turn and bank indicator.
The software versions and information in this document are subject to change without notice.
Visit www.Garmin.com and navigate to the Aviation Product/General Aviation/Indicators/G5
page for current updates and supplemental information concerning operation of the G5 attitude
indicator.
1.2
Acronyms and Abbreviations
The following acronyms and abbreviations are used in this manual:
AFMS
ALT
AML
CAN
DG
Airplane Flight Manual Supplement
Altitude (mode)
Approved Model List
Controller Area Network
Directional Gyro
HSI
ICA
I/O
LRU
STC
Horizontal Situation Indicator
Instructions for Continued Airworthiness
Input/Output
Line Replaceable Unit
Supplemental Type Certificate
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CFR
FAA
GPS
1.3
Code of Federal Regulations
Federal Aviation Administration
Global Positioning System
TSO
WAAS
Technical Standard Order
Wide Area Augmentation System
Reference Documents
Table 1-1: Reference Documents
Title
Document Number
FAA Advisory Circular, Acceptable Methods, Techniques, and Practices
– Aircraft Inspection and Repair
AC 43.13-1B
FAA Advisory Circular, Acceptable Methods, Techniques, and Practices
– Aircraft Alterations
AC 43.13-2B
Aerospace Systems Electrical Bonding and Grounding for
Electromagnetic Compatibility and Safety
SAE ARP1870
Standard Guide for Aircraft Electrical Load and Power Source Capacity Analysis
ASTM F 2490-05
GTN 6XX/7XX Install Manual
190-01007-A3
GNS 400W Series Installation Manual
190-00356-08
GNS 500W Series Installation Manual
190-00357-08
Garmin GPS and XM® Antenna STC Installation Manual
190-01284-00
Garmin G5 Electronic Flight Instrument Part 23 AML STC Maintenance Manual
including Instructions for Continued Airworthiness
190-01112-11
Pilots Guide, Garmin G5 Electronic Flight Instrument, Part 23 AML STC
190-01112-12
Airplane Flight Manual Supplement Garmin G5 Electronic Flight Instrument Part
23 AML STC
190-01112-13
1.4
STC Permission
A permission letter to use this STC data is available for download for each authorized G5
installation. The STC Installation Kit contains instructions for downloading the STC permission
letter from www.Garmin.com. Contact a local Garmin Dealer for G5 Attitude, G5 DG and G5
HSI STC Kit Part Numbers.
1.5
Scope
This manual applies to the modification of an aircraft listed on the Part 23 AML STC
SA01818WI for the installation of equipment listed below. Only the interfaces between the
Garmin G5 Electronic Flight Instrument and equipment listed in this manual are approved by the
STC.
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Table 1-2 G5 Attitude and G5 DG/HSI Equipment
Model
Nomenclature
Unit P/N
Catalog P/N
G5
Electronic Flight Instrument
011-03809-00
010-01485-00
Software P/N
and Version
006-B2304-XX*
G5
Installation Kit
011-03892-00
010-12493-10
N/A
G5
Battery pack
011-03893-00
010-12493-00
N/A
GMU 11
Magnetometer
011-04349-01
010-01788-01
006-B2770-XX*
GMU 11
GMU 11 Installation Kit
011-04349-90
010-12598-00
N/A
GAD 29
Data Bus Converter
011-03236-01
010-01172-01
006-B1760-XX*
GAD 29B**
Data Bus Converter
011-03236-11
010-01172-11
006-B1760-XX*
GAD 29/29B
GAD 29/29B Connector Kit
011-03271-00
N/A
N/A
* The approved G5 Part 23 AML STC Electronic Flight Instrument software is P/N 006-B2304-XX. XX
denotes the specific version P/N, i.e. 006-B2304-02 is software version 2.60. The G5 Electronic
Instrument, GMU 11 Magnetometer and GAD 29/29B listed above is shipped with approved software. To
verify the latest approved software visit www.Garmin.com and navigate to the Aviation /General
Aviation/Flight Instruments & Indicators/G5 page. Select ‘Software” in the overview tab.
** The GAD 29B is only required in installations that utilize the G5 heading and course output to a third party
autopilot.
1.6
System Overview
1.6.1 G5 Attitude Indicator
The G5 Electronic Flight Instrument configured as an attitude indicator, is shown in Figure 1-1.
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. The G5 contains integrated attitude/air data sensors that provide display of
attitude and secondary display of air data information. The G5 has battery backup and in the
case of aircraft power loss will sustain G5 operation with up to 4 hours of emergency power.
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Figure 1-1, G5 Electronic Flight Instrument (Attitude)
1.6.1.1
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 attitude functions are shown below:
•
•
Pitch
Roll
1.6.1.2
Turn Rate
The Turn Rate Indicator is located at the bottom of the display. A magenta Turn Rate Trend
Vector shows the current turn rate. A standard-rate turn (3 deg/sec) is shown on the indicator by
the trend vector stopping at the standard turn rate tick mark.
1.6.1.3
Slip/skid
The Attitude Indicator displays slip/skid information as indicated by the location of the ball at
the lower center portion of the indicator.
1.6.1.4
GPS Aiding
The G5 requires GPS for attitude aiding. It contains an internal GPS receiver that can be
connected to an external antenna or optionally can use external GPS input if available.
As installed in this STC, the G5 receives the GPS position for aiding via the following
methods:
•
•
•
•
•
Previously installed and approved GPS antenna (See Section 3.4.1)
GTN 6XX/7XX series navigators (See section 1.6.1.11)
GNS 4XX(W)/5XX(W) series navigators (See section 1.6.1.11)
GNS 480 series navigator (See section 1.6.1.11)
GTX 3x5 w/GPS transponder with software version 2.10 or later. (See section 1.6.1.11)
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Additionally, the G5 functions provided by the GPS are shown below:
•
•
Ground Track
Ground Speed (GS)
1.6.1.5
Air Data
The G5 unit is connected to the aircraft Pitot / Static system. See section 4.1.2.4 for details.
The G5 functions provided by the air data are shown below:
•
•
•
•
•
•
•
•
•
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
1.6.1.6
Standby Battery
The standby battery is required. The G5 has an externally mounted lithium – ion battery that
sustains the G5 flight display with up to 4 hours of emergency power.
Figure 1-2 G5 Standby Battery
1.6.1.7
G5 Attitude Interfaced to GMU 11
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 in place of track,
but would not allow the removal of the existing DG.
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1.6.1.8
G5 Attitude Interface Summary
The G5 Electronic Flight Instrument when configured as an attitude indicator in this STC
installation uses 14VDC or 28 VDC power, ground, RS-232, CAN BUS and coax(1) connection
for external mounted GPS antennas. The following list is a summary of interfaces used by the
G5 Attitude indicator.
•
•
•
•
•
•
Aircraft Power and Ground
Aircraft Pitot/Static
GPS Coax connection (1)
One RS-232 connection
One CAN Bus connection
Standby battery
(1) Used only in installations utilizing an external GPS antenna for GPS input to the G5.
1.6.1.9
G5 Attitude Power and Ground Interface Summary
The G5 uses 14VDC or 28 VDC power and aircraft ground. Reference Section 5 for wiring
details.
1.6.1.10
G5 Attitude Pitot/Static Interface Summary
The G5 requires pitot and static inputs for the altitude and airspeed functions. Reference
Section 4.1.4 for installation specifics.
1.6.1.11
G5 Attitude RS-232 Interface Summary
The G5 Attitude indicator can utilize RS-232 connections when available to receive GPS data.
When a G5 HSI is installed, the G5 Attitude indicator can utilize the RS-232 connection for
GPS and VHF navigation information.
If an existing connection is made to the RS-232 port, the G5 connection can be spliced into
the existing wiring at the connector. For specific wiring information refer to Section 5.
For specific configuration settings for RS-232 refer to Section 5.
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1.6.1.12
G5 Attitude CAN BUS Interface Summary
The G5 Attitude indicator can utilize CAN BUS connections when specified by a specific
equipment configuration to allow heading information from the GMU 11, communication of
navigation data from the GAD 29/29B and communication between the G5 Attitude indicator
and the G5 HSI.
For specific wiring information refer to Section 5.
1.6.2 G5 DG/HSI Indicator
The G5 Electronic Flight Instrument configured as an HSI, is shown in Figure 1-3. 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. The G5 contains integrated attitude/air data sensors that provide a backup
display of attitude and air data information. The G5 has battery backup and in the case of
aircraft power loss will sustain G5 operation with up to 4 hours of emergency power. When the
G5 is installed as a DG/HSI the battery backup is optional.
Figure 1-3 G5 Electronic Flight Instrument (DG/HSI)
The Garmin G5 indicator can replace an existing vacuum-driven or electro mechanical
DG/HSI. In this location the G5’s primary function is the display of slaved compass, #1 VHF
NAV and/or #1 GPS NAV. The possible configurations for a G5 DG/HSI are discussed below.
(Note: The VHF navigators and GPS navigators interfaced by this STC are not installed by this
AML STC. Only the interface of the VHF NAV, GPS NAV and G5 Attitude and G5 DG/HSI
are approved with this STC.)
1.6.2.1
G5 Slaved DG
The basic installation is a G5 in the DG indicator location and a GMU 11.
•
In this configuration the G5 is installed as a slaved compass with no NAV information.
•
The G5 DG can be used as a backup Attitude/Airspeed/Altitude Indicator.
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1.6.2.2
G5 HSI VHF NAV
For installations where the G5 HSI is being used for basic VHF NAV, the G5 HSI is installed
with a GNC255 or SL30.
•
The G5 HSI will be a situationally correct display of VHF NAV course information
with the heading of the aircraft
•
The G5 HSI will be used to input OBS/Course information
•
•
The G5 HSI can be used as a backup Attitude/Airspeed/Altitude Indicator
If installed, a G5 Attitude indicator can also present VHF NAV lateral and vertical
deviation
1.6.2.3
G5 HSI GPS NAV
For installations where the G5 HSI is being used for GPS NAV, the G5 will be installed with a
Garmin GPS navigator and the GAD 29/29B
•
The G5 HSI will be a situationally correct display of GPS NAV information with the
heading of the aircraft
•
•
The G5 HSI will be used to input OBS/Course information
The G5 HSI can be used as a backup Attitude/Airspeed/Altitude Indicator
•
If installed, a G5 Attitude indicator can also present GPS NAV lateral and vertical
deviation
1.6.2.4
G5 HSI VHF NAV and GPS NAV
For installations where the G5 HSI is being used for full VHF NAV and GPS NAV, the G5 will
be installed with a Garmin GPS/VHF navigator and the GAD 29/29B.
•
The G5 HSI will be a situationally correct display of VHF NAV or GPS NAV
information with the heading of the aircraft
•
The G5 HSI will be used to input OBS/Course information
•
The G5 HSI can be used as a backup Attitude/Airspeed/Altitude Indicator
•
If installed, a G5 Attitude indicator can also present VHF NAV or GPS NAV lateral
and vertical deviation
1.6.2.5
Backup Attitude Indicator
All of the functions listed in 1.6.1 are also available by selecting the G5 HSI Menu via the
knob and selecting PFD.
1.6.2.6
•
•
•
•
•
•
G5 DG/HSI Interface Summary
Aircraft Power and Ground
Aircraft Pitot/Static
GPS Coax connection (1)
One RS-232 connection
One CAN Bus connection
Standby battery (optional)
(1) Used only in installations utilizing an external GPS antenna for GPS input to the G5.
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1.6.2.7
G5 DG/HSI Power and Ground Interface Summary
The G5 uses 14VDC or 28 VDC power and aircraft ground. Reference Section 5 for wiring
details.
1.6.2.8
G5 DG/HSI Pitot/Static Interface Summary
The G5 requires pitot and static inputs for the backup altitude and airspeed functions.
Reference Section 4.1.4.
1.6.2.9
G5 DG/HSI RS-232 Interface Summary
The G5 DG/HSI can utilize RS-232 connections when available to receive
• GPS data for aiding.
• VHF navigation information, both lateral and vertical.
For specific configuration settings for RS-232 refer to Section 5.
If an existing connection is made to the RS-232 port, the G5 connection can be spliced into
the existing wiring at the connector. For specific wiring information refer to Section 5.
1.6.2.10
G5 DG/HSI CAN BUS Interface Summary
The G5 DG/HSI can utilize CAN BUS connections when specified by a specific equipment
configuration to allow heading information from the GMU 11, communication of navigation
data from the GAD 29/29B and communication between the G5 Attitude instrument and the
G5 HSI.
For specific wiring information refer to Section 5.
1.6.2.11
Standby Battery
The standby battery is optional for the DG/HSI installation. The G5 has an externally mounted
lithium – ion battery that sustains the G5 flight display with up to 4 hours of emergency power.
1.6.3 GMU 11 Magnetometer
The Garmin GMU 11 Magnetometer is a remote mounted device that interfaces with a Garmin
G5 to provide heading data to the G5 Attitude and/or G5 DG/HSI. The Garmin G5 and GMU
11 magnetometer replaces traditional rotating mass instruments. 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 1-4 GMU 11
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1.6.4 GAD 29/29B
The GAD 29/29B is a light-weight, remote-mount unit that allows interface to IFR navigators
such as the GNS and GTN series. The GAD 29/29B has a 25 pin D-sub connector and a 9 pin
D-sub connector. These connectors provide the following functionality:
• 2 Low Speed ARINC 429 Transmitters
• 4 Low Speed ARINC 429 Receivers
• 1 CAN Network Port
• *Analog Outputs
• *Excitation Pass Through
*GAD29B only
For the G5 Attitude and/or G5 DG/HSI installation the GAD 29/29B will receive either
ARINC 429 data from the navigator interfaced and transmit that information onto the CAN
bus to be consumed by the G5. The GAD 29/29B can run on 14 volt DC or 28 volt DC.
The GAD 29B contains the same characteristics and function of the GAD 29 as well as
providing autopilot heading and course datum to allow a G5 DG/HSI to be interfaced with
third party auto pilots. Reference section 5.12 for approved autopilot interfaces.
Figure 1-5 GAD 29/29B
1.7
Technical Specifications
1.7.1 Physical Characteristics
All width, height, and depth measurements are taken with unit rack, if applicable, and
connectors.
Table 1-3: Physical Characteristics
Weight of
Unit and
Connector
Configuration
Width
Height
Depth
Unit
Weight
G5 with Battery
3.42 in
3.60 in
3.03 in*
0.83 lb
0.98 lb**
GAD 29
6.10 in
1.48 in
5.54 in
0.38 lb
0.63 lb
GAD 29B
6.10 in
1.48 in
5.54 in
0.40 lb
0.65 lb
GMU 11
2.74 in
0.92 in
6.19 in
0.16 lb
0.26 lb
*Depth behind aircraft panel
**Weight includes mounting ring
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1.7.2 Power Requirements
Table 1-4: Power Requirements
LRU
G5
GMU 11
GAD29/29B
2
2.1
Characteristics
Average Current Draw @ 14 VDC
Max Current Draw @ 14 VDC
Average Current Draw @ 28 VDC
Max Current Draw @ 28 VDC
Average Current Draw @ 14 or 28 VDC
Max Current Draw @ 14 or 28 VDC
Average/Max Current Draw @ 14 VDC
Average/Max Current Draw @ 28 VDC
Specifications
.200 A
.250 A
.100 A
.125 A
.100 A
.100 A
.200 A
.100 A
LIMITATIONS
Installation Limitations
It is the installer’s responsibility to ensure the installation will meet the requirements in this
manual prior to modification of the aircraft.
The installation of the G5 requires the retention of the mechanical airspeed indicator,
altimeter, and vertical speed indicator.
• For installations in aircraft approved for IFR operations:
• If the G5 is installed as the primary attitude indicator, the existing rate of turn
indicator must be retained.
• If the G5 is installed as the rate of turn indicator, the existing primary attitude
indicator must be retained.
• For installations in aircraft approved for VFR-only operations;
• The G5 can be installed as the attitude indicator and rate of turn indicator without
retention of either the existing attitude indicator or rate of turn indicator.
As installed by this STC, the G5:
• is NOT approved in FAA certified aircraft that:
• are approved for Flight Into Known Icing (FIKI) conditions
• have a gross take-off weight more than 6000 lbs
• have more than 6 seats including pilot/copilot
• must be installed in an aircraft with an electrical power generating system capable of
supplying
14 VDC or 28 VDC
• if a G5 is being installed as an attitude indicator and an existing attitude indicator is
retained, the G5 pointer type must be configured to match the existing indicator pointer
type
o Fixed Pointer Type / G5 Config = Ground
o Movable Pointer Type / G5 Config = Sky
• cannot replace a primary attitude indicator that includes a flight director or is part of an
autopilot system (an existing attitude indicator in the primary location that is part of an
autopilot but without flight director may be moved to the turn coordinator location and a
G5 installed in the primary location)
• cannot replace the turn coordinator that is part of an autopilot system
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•
•
•
•
•
2.2
cannot replace a DG/HSI that is part of an autopilot system that is not an approved
autopilot, see Table 5-1.
cannot replace the non-stabilized magnetic compass (Whiskey Compass must be retained
in the aircraft)
must be installed in an instrument panel constructed of aluminum with a minimum
thickness of .040 inches.
is only approved to interface with aircraft systems specified in this manual
must not have interface cables and wiring installed in fuel bays
Operational Limitations
Refer to the Airplane Flight Manual Supplement (AFMS) for operational limitations.
This area intentionally blank
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3
3.1
INSTALLATION OVERVIEW
Introduction
The following section contains an overview of the steps required for the installation of the G5
Electronic Flight Instrument. This section includes requirements for selection of proper locations
in the aircraft, as well as requirements for supporting structure, mechanical alignment and
wiring. Any restrictions on nearby equipment and requirements are also specified.
3.2
Installation Materials
The installation kit listed in Table 3-1 is required for each G5 installation.
Table 3-1: Contents of the G5 Installation Kit (011-03892-00)
Item
Garmin P/N
Quantity
Connector Kit, 9 Pin, w/CAN Term*
011-03002-00
1
Mounting Ring, G5
115-02251-03
1
Screw, 6-32, 0.500”
211-60207-12
3
*NOTE: Not all items included in kit P/N 011-03002-00 are used in this
installation.
The installation kit listed in Table 3-2 is required any time a GMU 11 is installed.
Table 3-2: Contents of the GMU 11 Installation Kit (011-04349-90)
Item
Garmin P/N
Quantity
Connector Kit, 9 Pin, w/CAN Term
011-03002-00
1
Nylon Locking 6-32 Nut
210-10008-08
4
Screw, 6-32, 0.500”
211-60207-12
4
Flat 6-32 Washer
212-00024-06
4
Table 3-3: Contents of the Connector Kit (011-03002-00)
Item
Garmin P/N
Quantity
Sub-Assy, Bkshl w/Hdw, Jackscrew,
9 pin
011-01855-00
1
Sub Assy, CAN Termination Kit*
011-02887-00
1
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Conn, Rcpt, D-Sub, Crimp Socket, 9
Ckt
330-00625-09
1
Contact, Sckt, D-Sub, Crimp, Size 20,
20-24 AWG
330-00022-02
9
*NOTE: Not all items included in kit P/N 011-02887-00 are used in this
installation
The installation kit listed in Table 3-4 is required whenever a GAD 29/29B is installed.
Table 3-4: Contents of the GAD 29/29B Connector Kit (011-03271-00)
Item
Garmin P/N
Quantity
Backshell w/Hdw, Jackscrew, 9 Pin
011-01855-00
1
Backshell w/Hdw, Jackscrew, 25 Pin
011-01855-02
1
Conn, Plug, D-Sub, Crimp Pin, 25 Place
330-00624-25
1
Conn, Rcpt, D-Sub, Crimp Sckt, 9 Place
330-00625-09
1
Contact, Socket, Military Crimp, Size 20
336-00022-02
11
Contact, Pin, Military Crimp, Size 20
336-00024-00
27
The item listed in Table 3-5 will be supplied when a G5 DG/HSI is ordered. The adapter
plate is used whenever a G5 is installed and any instrument panel modification has taken
place or a G5 is installed in an instrument hole with cutouts for instrument knobs.
Alternatively the installer can field fabricate the adapter as needed. Reference 4.1.2.4 for
installation details.
Table 3-5: G5 Adapter Plate
Item
G5 Adapter Plate
Garmin P/N
Quantity
115-02642-00
As required
The item listed in Table 3-6 is optional. It can be ordered from Garmin or fabricated in
accordance with Section 4.1.2.6. The recessed adapter plate is only used when recessing
the G5 into the instrument panel. This same part can be used when installing single or dual
recessed G5 units. Reference 4.1.2.6 for installation details.
Table 3-6: G5 Recessed Adapter Plate
Item
G5 Recessed Adapter Plate
Garmin P/N
Quantity
115-02733-00
As required
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3.2.1 Materials Required but Not Supplied
The following installation materials are required, but are not available from Garmin:
•
Insulated stranded wire (MIL-W-22759/34 or MIL-W-22759/16)
•
Shielded wire (MIL-C-27500 cable utilizing M22759/34 wire (SD) and ETFE jacket or
MIL-C-27500 cable utilizing M22759/16 wire (TE) and ETFE jacket )
•
Push/pull manually resettable circuit breakers.
Aircraft with 14 VDC or 28 VDC electrical systems require the following circuit
breaker:
o
MS26574-5 (5 Amp, G5, GMU 11, GAD 29/29B)
•
Tie wraps or lacing cord
•
MS25036 ring terminals (for grounding and circuit breaker connections)
•
Shield terminators (AS83519/1-X or AS83519/2-X or equivalent)
•
Silicon fusion tape, A-A-59163 (MIL-I-46852C or equivalent)
•
Environmental splice (M81824/1-X, where X=size or equivalent)
•
Flat braid, 1/16” (AA59569F36T0062 or equivalent)
•
Tubing and fittings are required to connect pitot and static air to the G5. Pitot and
Static plumbing parts are aircraft specific, see Section 4.1.4.
The following installation materials may be required depending on the installation, but are not
available from Garmin:
•
2024-T3 aluminum alloy sheet per AMS-QQ-A-250/4 or clad 2024-T3 aluminum alloy
sheet per AMS-QQ-A-250/5. Minimum sheet thickness requirements:
•
0.032" for GMU 11 magnetometer supporting structure.
•
0.040" for GAD 29/29B supporting structures.
•
Aircraft grade fasteners e.g., AN525 screws, MS20426AD rivets, MS21059 rivet nut
plates, MS21071 reduced rivet spacing nut plates. NAS1832, NAS1834, or NAS1836
potted inserts maybe required if honeycomb core panels are used to support the
installation of G5 components.
•
Coaxial cable (RG-400, RG142B or equivalent) (refer to Section 3.4.5.3).
•
Connector, TNC, male, crimp (M39012/26-0503, 225555-6, 31-4452 or equivalent).
•
Connector, BNC, male, crimp (M39012/16-0503, 225395-6 or equivalent).
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3.3
Test Equipment
The following test equipment is required to complete the G5 installation and to perform postinstallation checkout of the system:
•
Ground power cart (capable of supplying power to the aircraft systems and avionics)
•
Air data test set (e.g. Barfield DPS450 or similar)
•
VHF NAV test set
•
Low resistance ohmmeter
•
Digital Level (or equivalent)
The following equipment may be required based on the units being installed and the particular
aircraft, see Section 4.1 for information:
•
Laser Square
•
Protractor Tool
•
Plumb Bob
•
Aircraft Jack Set
3.4
Installation Considerations
The installation instructions are intended to be used in coordination with the avionics
installation practices in AC 43.13-1B and AC 43.13-2B.
•
Modification of existing plastic instrument panel overlays may be required to install the
G5 electronic flight instrument.
•
Fabrication of a wiring harness is required.
•
Sound mechanical and electrical methods and practices are required to achieve
optimum system performance.
3.4.1 GPS Antenna
A GPS signal is required. The G5 can use an external GPS antenna or GPS data from one of the
GPS navigators or GTX 3x5 listed in Section 5.
In a dual G5 installation only the G5 Attitude requires the GPS position input. The GPS
information is communicated to the G5 DG/HSI over the CAN Bus.
If a GPS Navigator or a GTX 3x5 is used for a GPS signal, disable the internal GPS receiver of
the G5. If an external GPS antenna is connected to the G5, enable the internal GPS receiver.
See Section 5 for configuration settings.
This STC approves the interface to antennas shown in Table 3-7 and Table 3-8.
This STC does not approve the installation of a GPS antenna. A separate airworthiness
approval for antenna installation is required except for existing or previously approved
installations. One means of installation approval is Garmin Antenna STC SA02018SE-D
for mounting GPS antennas.
Other antennas that meet the specifications listed in Table 3-9 will work with the G5, but it
is the installer’s responsibility to ensure that their choice of antenna meets FAA standards
according to this specific installation.
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3.4.1.1
GARMIN ANTENNAS
Table 3-7 lists Garmin antennas supported by the G5. The GA35 and GA36 meet the
requirements of TSO/ETSO-C144.
Table 3-7 Supported Garmin Antennas
Model
GA35
GA36
GA56
3.4.1.2
Connector Type
TNC
TNC
TNC
Part Number
013-00235-0X
013-00244-0X
011-00134-00
NON-GARMIN ANTENNAS
Table 3-8 lists non-Garmin antennas supported by the G5. For non-Garmin antennas, follow
the manufacturer’s installation instructions.
Table 3-8 Supported Non-Garmin Antennas
Model
Antenna Type
Mfr
Part Number
Comant 2480-201 VHF/GPS*
VHF COM/ GPS Comant
CI 2480-201
*The GPS antenna connector is TNC type. The VHF COM antenna
connector is BNC type.
An antenna meeting the specifications in Table 3-9 is capable of receiving both GPS and
WAAS signals when connected to the G5.
Table 3-9 GPS Antenna Minimum Requirements
Characteristics
Frequency Range
Gain
Noise Figure
Nominal Output Impedance
Supply Voltage
Supply Current
Specifications
1565 to 1585 MHz
16 to 25 dB typical, 40 dB max
Less than 4.00 dB
50 Ω
4.5 to 6.5 VDC
up to 60 mA
3.4.2 Considerations for Vacuum System
If a vacuum driven instrument is removed, the vacuum source must be capped and the system
checked for leaks. See the aircraft specific maintenance manual for procedure.
The vacuum system and associated parts may be removed if there is no remaining need for
vacuum. See the aircraft specific maintenance manual and AC 43.13-2B for guidance when
removing the vacuum system. If the vacuum pump is removed, the engine accessory port must
be properly covered. See specific engine maintenance and parts manuals for guidance.
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3.4.3 Switches
There are no switches added by this STC installation.
3.4.4 Placards and Labels
All placards and labels should be readable in all lighting conditions. Ambient flood lighting is
acceptable. The new circuit breaker installed for the G5 unit and supporting equipment must be
labeled as noted in the interconnect drawings in Section 5. These labels are summarized in
Table 3-10.
Table 3-10: G5 and Supporting LRU Circuit Breaker Labels
Description
G5 (Attitude Indicator)
G5 (DG/HSI)
GMU 11
GAD 29/29B
Label
Single G5 Installation
Dual G5 Installation
ATT [1]
ATT [1]
HSI or
HSI or
DG
DG
[2]
[2]
GAD
GAD
[1] Circuit breaker is labeled “ATT” when the G5 is installed in the primary
attitude position. When an existing primary attitude indicator is retained
the G5 installed in the Turn Coordinator position should be labelled #2
ATT. Alternate spellings of “ATT” is acceptable.
[2] When a single G5 is installed, the GMU 11 is powered from the same
breaker as the G5. When two G5s are installed, the GMU 11 is powered
from the same breaker as the G5 in the DG/HSI position.
3.4.5 Cable and Wiring Considerations
Select wire in accordance with AC 43.13-1B Chapter 11, Sections 5 through 7. Mark wire in
accordance with AC 43.13-1B Chapter 11 Section 16. Mark harness connectors in accordance
with AC 43.13 Chapter 11 Section 17. Install wiring in accordance with AC 43.13-1B Chapter
11, Sections 8 through 13. Record the aircraft wire routing in Appendix C of Garmin G5
Electronic Flight Instrument Part 23 AML STC Maintenance Manual including Instructions for
Continued Airworthiness, P/N 190-01112-11. Use the following guidelines to prevent damage
to the aircraft and systems:
•
Do not route the wire harness near flight control cables, high electrical capacity lines,
high-energy sources or fuel lines.
•
Locate the wire harness in a protected area of the aircraft.
•
Make sure the wire harness does not come in contact with sources of high heat or be
routed adjacent to RF coaxial cables.
•
Make sure there is ample space for the wire harness and mating connectors.
•
Avoid sharp bends.
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3.4.5.1
Pressurized Aircraft Considerations
In pressurized aircraft, wiring that penetrates the pressure vessel must be installed in
accordance with the Type Design of the aircraft. Any wires that penetrate the pressure bulkhead
must use existing provisions such as spare pins in the existing bulkhead connectors, or existing
sealed wire thoroughfares in accordance with the AMM. Substantiation for additional holes in
the pressure vessel is beyond the scope of this manual and would require additional data from
the aircraft manufacturer or other FAA approved data.
3.4.5.2
CAN Bus
The primary digital interface used to exchange data between the G5 Attitude indicator,
GMU 11 and GAD 29/29B is the Controller Area Network, also known as the CAN bus. CAN
was developed by Bosch GmbH in the 1980s, and its specifications are currently governed by
ISO 11898-2. CAN is widely used in aviation, automotive, and industrial applications due to
its simplicity and reliability.
CAN BUS ARCHITECTURE
The electrical architecture of the CAN bus takes the form of a linear “backbone” consisting of
a single twisted wire pair with an LRU connected (terminated) at each end (Figure 3-1). The
installer should attempt to make this “backbone” as short as practical. The maximum overall
length of the CAN bus from end to end should be 85 feet. At each of the two extreme ends of
the CAN bus, a 120 Ω resistor is installed to “terminate” the bus. Termination resistors are
either provided via termination adapters that plug into an LRUs CAN connection or are
internal to the LRU.
Figure 3-1 CAN Bus Backbone
Multiple LRU’s may be connected in a daisy chain manner along the backbone of the CAN
bus (Figure 3-2).
Figure 3-2 Correct CAN BUS Wiring Example and Node Connections
Daisy-chained LRUs (LRUs not at the extreme ends of the CAN bus) connect to the CAN
backbone through short “stub” or “node” connections ( Figure 3-2 ). The length of each node
connection should 3 inches or less, the maximum allowed distance from a splice to a
connector.
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Multiple devices must not connect to the CAN bus backbone at the same point. Rather than
splicing two or more stub node connections together, the CAN bus should instead be daisychained from one device to the next ( Figure 3-2 ).
Figure 3-3 Incorrect CAN Wiring Example
CAN BUS WIRING
Wiring used for the CAN bus should be shielded twisted-pair cable, MIL-C-27500. The
shields for each CAN bus wire segment should be interconnected, forming a continuously
connected shield from one end of the CAN bus to the other end of the CAN bus. The CAN
bus shield should always be grounded to the device connector backshells for all devices
connected the CAN bus.
CAN BUS TERMINATION
At each of the two extreme ends of the CAN bus backbone, a 120 Ω resistor is installed to
terminate the bus. In the G5 system, separate resistors are not required. Instead, termination
resistors are provided either via termination adapters that plug into an LRU’s CAN connection
or via an internal resistor.
•
•
The G5 and GMU 11 installation kits provide a 9-pin termination adapter that
provides termination when attached to the device’s main connector. The termination
adapter contains a 120 Ω resistor that is connected between pins 1 and 2 (Figure 3-4).
The GAD29/29B contains a 120 Ω resistor inside the unit that provides termination
when the two CAN TERM pins are connected together (Figure 3-5). Alternatively the
GAD29/29B can be terminated externally using a termination adapter, Garmin P/N
011-02887-00 (Figure 3-4).
Figure 3-4 CAN Bus Termination (011-02887-00) for G5 and GMU 11
Figure 3-5 CAN Bus Termination for GAD 29/29B
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Both ends of the CAN bus must have a CAN bus terminator installed (Figure 3-2), but devices
that are not at the ends of the CAN bus should not have a CAN bus terminator installed .
CAN BUS INSTALLATION GUIDELINES
For maximum reliability of the CAN bus, the following guidelines should be followed:
•
The CAN bus backbone must be a single linear path with exactly two distinct ends.
CAN bus connections should be “daisy chained” from device to device. Avoid “star”
and “Y” topologies, and do not use a hub device (see Figure 3-3).
The overall length of the bus should not exceed 85 feet.
Do not connect more than one device to the CAN bus backbone at the same point.
Instead, daisy chain the CAN bus backbone from one device to the next.
Observe proper wiring, shielding, and grounding requirements as described above.
Terminate the CAN bus at the two extreme ends of the bus, as described above.
When adding a new device to the CAN bus, evaluate proposed modifications to the
CAN bus wiring connections to ensure compliance with all above requirements.
•
•
•
•
•
3.4.5.3
Coaxial Cable Considerations
When routing coaxial cables, observe the following precautions:
•
•
•
All cable routing should be kept as short and as direct as possible.
Avoid sharp bends.
Avoid routing cables near power sources (e.g. 400 Hz generators, trim motors, etc.) nor
near power for fluorescent lighting.
Refer to Section 3.2.1 for recommended coaxial cable types.
3.4.6 Cooling Requirements
While no forced cooling air is required for the G5, GMU 11 or GAD 29/29B it is highly
recommended that the air behind the panel be kept moving (by ventilation or a fan). Units
tightly packed in the avionics stack heat each other through radiation, convection, and
sometimes by direct conduction. Even a single unit operates at a much higher temperature in
still air than in moving air. Fans or some other means of moving the air around electronic
equipment are usually a worthwhile investment.
NOTE
Avoid installing LRUs near heat sources. If this is not possible, ensure that additional
cooling is provided. Allow adequate space for installation of cables and connectors.
The installer will supply and fabricate all of the cables. Install wiring in accordance
with FAA AC 43.13-1B and AC 43.13-2B.
3.4.7 Compass Safe Distance
After reconfiguring the avionics in the cockpit panel, if the unit is mounted less than 12 inches
from the compass, recalibrate the compass and make the necessary changes for noting
correction data.
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3.4.8 Shield Termination Considerations
For G5 installations utilizing the RS-232, CAN bus and ARINC 429 interfaces, terminate the
shield to the G5, GMU 11 and GAD 29/29B connector backshells as shown in Figure 4-42 and
Figure 4-43. For shield terminations at the GPS or VHF Navigator follow the appropriate
installation techniques as indicated by the manufacturers installation instructions for that unit. If
there are any interposing connectors then the shields must have continuity through the
interposing connector. This can be achieved by
1) Terminating the shields to the backshell of the connector if both mating connectors and
both backshells are metal.
2) Terminating the shield to aircraft ground directly
3) Passing the shield through pins in the connector. This is the least preferred method.
3.4.9 Audio Interference
This STC installation does not interface to audio signals. Attention to harness installation and
routing as specified in Section 3.4.5 should be considered for Audio interference mitigation.
This area intentionally blank
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4
INSTALLATION PROCEDURES
4.1
Mechanical Installation
4.1.1 Special Tools Required
Laser Square
For GMU 11 magnetometer installations it is recommended (but optional) to use a laser square
with a line accuracy of ± 3/32 inches end-to-end, at 15 feet perpendicular distance (or better). A
Stanley Laser Level Square 77-188 S2 meets the line accuracy requirement.
Digital Level
It is recommended to use a digital level when installing GMU 11 magnetometer.
Protractor Tool
A protractor tool may be required to measure the angle offset during the magnetometer
installation.
Plumb Bob
A plumb bob may be required for leveling and installing the magnetometer unit.
Aircraft Jack Set
A set of aircraft jacks may be required for stabilizing the aircraft after it is leveled.
4.1.2 G5 Mounting Requirements
NOTE
It is important that the G5 is installed perpendicular to the aircraft's longitudinal axis
(display bezel parallel to the wing spar carry thru) and as close to level in the roll axis
as possible. Small roll offsets and pitch offsets, up to 15°, can be corrected for during
calibration.
In addition to the installation limitations in Section 2.1, consider the following when selecting a
mounting location for the G5:
•
•
•
•
Protect the mounting location for the G5 from rapid thermal transients, in particular
large heat loads from nearby high-power equipment.
Do not install the G5 within 1 inch of magnetically mounted antennas, speaker
magnets, or other strongly magnetic items.
If installing dual G5s above and below each other, a minimum spacing of 3.6 inches
center to center is required, see Section 4.1.2.4 for more information.
Two Adapter Plates must be used if installing the G5 in an instrument hole with any
cutout for instruments knobs. See Figure 4-10 and Figure 4-12 for more information.
One or two G5s may be installed. See Figure 4-1 for typical installation configurations in an
IFR approved aircraft.
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Figure 4-1 Typical G5 Installations for IFR Approved Aircraft
A G5 can be installed in an instrument panel that does not have an existing attitude indicator or
DG/HSI. In these cases, the G5 must be located on the Pilot’s instrument panel, and centered
as nearly as practicable about the vertical plane of the pilot’s forward vision. If the G5 is
installed as an;
•
•
Attitude indicator, it must be located as close to the top center position of the pilot’s
instrument panel as practical.
DG/HSI, it shall be located adjacent to and directly below the instrument in the top
center position when possible.
4.1.2.1
Mounting Ring Installation
The G5 Mounting Ring (115-02251-03) can be used as a template when marking the panel for
cutout. For complete cutout dimensions see Figure 6-11.
Secure the mounting ring to the aircraft panel using the supplied #6-32 pan head Phillips
mounting screws. Evenly torque the mounting screws to 10-12 in-lbs.
• The G5 must be leveled to within 15.0° in the longitudinal axis (Pitch).
(Reference Figure 4-4 )
• The G5 must be leveled to within 2.0° in the lateral axis (Roll).
(Reference Figure 4-3 )
• Mount the G5 with the connector aligned to within 1.0° of the vertical axis (Yaw) of
the aircraft (display bezel parallel to the wing spar carry thru). (Reference Figure 4-5 )
An aircraft leveling and offset calibration procedure must additionally be carried out prior to
flight.
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Figure 4-2 G5 Mounting Ring
Figure 4-3 Maximum Misalignment of the G5 in the Lateral Axis
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Figure 4-4 Maximum Misalignment of the G5 in the Longitudinal Axis
Figure 4-5 Maximum Misalignment of the G5 in the Vertical Axis
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4.1.2.2
G5 Installation
The G5 is installed by inserting the alignment pin located at the top of the unit into the mating
hole in the mounting ring, pushing the unit flush with the instrument panel, and fastening the
captive 3/32” hex socket head screw to the mounting ring as shown in Figure 4-6. To fasten
the captive screw to the mounting ring, insert a 3/32” hex drive tool through the access hole in
the front cover of the G5 as shown in Figure 4-7. Torque the captive mounting screw to 10-12
in-lbs.
Figure 4-6 G5 Alignment Pin
Figure 4-7 G5 Hex Driver Insertion
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4.1.2.3
Optional #6-32 Captive Mounting Screw
The captive 3/32” hex socket head screw can be used for panel thicknesses up to 0.150”. For
installations with a panel thickness greater than 0.150”, the captive mounting screw can be
replaced with a standard #6-32 hex socket head screw (MS16995). To replace the screw,
remove the two #4-40 flat head Phillips mount plate screws, the G5 screw mount plate, and the
captive screw as shown in Figure 4-8. Reverse this process to install the longer #6-32 hex
socket head screw. Ensure correct orientation of the screw mount plate before applying 6-8 inlb. of torque to the #4-40 mount plate screws.
NOTE: Standard #6-32 hex socket head screws use a 7/64” hex drive feature. The access hole
in the G5 bezel is large enough to accommodate this increase in hex tool size.
Figure 4-8 G5 Captive Mounting Screw Replacement
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4.1.2.4
Dual G5 Installations Requiring Instrument Panel Modification
The minimum vertical distance needed between two G5 units is 3.6 inches center to center.
Some instrument panels may require modification of existing holes to gain the needed 3.6 inch
spacing.
Figure 4-9 Required Vertical Spacing Between G5 Units
The panel may be modified by enlarging one hole or both, up to a maximum of 0.25 inch per
instrument hole. The proposed positions must be such that neither G5 unit is obscured by the
glareshield, control yoke or other object.
Figure 4-10 Instrument Panel Modification
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The G5 Adapter Plate, (115-02642-00) is shown in Figure 4-11. Each installation of a G5 in a
DG/HSI will include 2 adapter plates. Two G5 adapter plates must be installed as shown in
Figure 4-12 when
• any instrument panel modification has taken place
• G5 is installed in an instrument hole with cutouts for instrument knobs
The G5 adapter plate is fabricated from 0.050 thick 2024-T3 aluminum per the dimensions
shown in Figure 4-11. Apply a finish coat of paint to adaptor plates as desired prior to final
installation. These may be field fabricated if needed and must have some type of corrosion
protection (primer, alodine, etc.).
Figure 4-11 G5 Adapter Plate
Figure 4-12 G5 Adapter Plate Assembly
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4.1.2.5
Cutting a New Instrument Hole for G5 Installation
For G5 installations in aircraft approved for VFR-only operation, there may be the need to cut a new
instrument hole.
If it is desired to mount the G5 recessed, refer to Section 4.1.2.6 for instructions and limitations.
In order to satisfy the structural requirements when cutting a new instrument hole in the existing panel,
the following conditions must be met:
1)
2)
3)
4)
5)
6)
7)
8)
9)
Modification of the instrument panel must be in accordance with AC 43.13-2B, Chapter 2.
The instrument panel must be a minimum of 0.040 inches thick.
The dimensions and limitations of the hole must be as shown in Figure 4-13.
The new location must satisfy the alignment requirements shown in Figure 4-3, Figure 4-4, and
Figure 4-5.
There must be at least 0.25 inches between the main instrument hole or the screw holes and any
adjacent holes or the edges of the panel.
The instrument panel must be structurally capable of supporting the weight of the installed units.
The location of the hole must allow for sufficient clearance for the G5 electrical and pneumatic
connections, see Figure 4-14.
The location must be free from rapid thermal transients, in particular, large heat loads from electrical
loads.
Do not mount the G5 within 1 inch of magnetically mounted antennas, speaker magnets, or other
strongly magnetic items.
Figure 4-13, G5 Instrument Hole Dimensions
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Figure 4-14, Clearance for Connections
4.1.2.6
G5 Recessed Mount Option
The G5 unit may be recessed into the instrument panel which positions the display flush with
the instrument panel. A full understanding of this modification is required before starting. A
recessed adapter plate and modification of the instrument panel will be needed. Some
instrument panels may not be capable of supporting this modification. See section 4.1.2.6.5 for
suggested adapter plate modification procedure.
Figure 4-15 Recessed Adapter Plate
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Recessed Adapter Plate, 115-02733-00, is required when a G5 unit is recessed in the panel.
The plate can be ordered from Garmin, or field fabricated. If field fabricated, it must be 0.090
thick 2024-T3 aluminum per Figure 4-15 and must have some type of corrosion
protection (primer, alodine, etc.). The Recessed Adapter Plate includes reference holes and can
be used as a template for creating the recessed cutout.
Figure 4-16 Recessed Adapter Plate Template Reference Holes
4.1.2.6.1 Recess Mounting Single G5
Install a single recessed G5 as illustrated by Figure 4-17 and Figure 4-18. A G5 installation in
the attitude position is shown, but the same instructions can be used when installing a G5 in the
DG or turn coordinator positions. Modify 115-02733-00 adapter for single G5 installation per
Figure 4-16. A minimum of four No. 6 MS35206-2XX screws must be used to secure the
modified mounting adapter plate in place. Maintain 1.5D edge distance minimum.
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Figure 4-17 Single G5 Recessed Adapter Plate Installation
Install G5 unit per section 4.1.2.2.
Figure 4-18 Single G5 Recessed Installation
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4.1.2.6.2 Recess Mounting Dual G5 Vertically
Install dual recessed G5s as illustrated by Figure 4-19 and Figure 4-20. A minimum of six
No. 6 MS35206-2XX screws must be used to secure the modified mounting adapter plate in
place. Maintain 1.5D edge distance minimum.
Figure 4-19 Dual Vertical G5 Recessed Adapter Plate Installation
Install G5 units per section 4.1.2.2.
Figure 4-20 Dual Vertical G5 Recessed Installation
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4.1.2.6.3 Recess Mounting Dual G5 Horizontally
In an installation where the G5 Attitude indicator is in the Turn Coordinator position and a G5
DG/HSI is installed as well (ref Figure 4-21), the dual G5s may be installed recessed
horizontally in a similar manner to the dual vertical recessed installation. A horizontal recessed
adapter plate will need to be field fabricated in order to fit the existing installation. This plate
must be fabricated of 0.090 thick 2024-T3 aluminum and must have some type of corrosion
protection (primer, alodine, etc.). A minimum of six No. 6, MS35206-2XX screws must be
used to secure the modified mounting adapter plate in place. Maintain 1.5D edge distance
minimum.
Figure 4-21 Dual Horizontal G5 Recessed Installation
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4.1.2.6.4 Instrument Panel Modification Limitations
The modification required for recess mounting a G5, whether it is single, dual vertical or dual horizontal
must meet the following conditions:
1) The mounting location must satisfy the alignment requirements shown in Figure 4-3, Figure 4-4,
Figure 4-5.
2) The proposed location must allow for sufficient clearance for the G5 unit and connections as
shown in Figure 4-14.
3) The hole must meet the limitations and minimums as shown in Figure 4-22.
4) The modification must be completed in accordance with AC 43.13-2B, Chapter 2.
Any modification of subsequent structure or parts other than the instrument panel as defined in these
instructions are beyond the scope of this manual. Additional data from the aircraft manufacturer or other
FAA approved data would be required for these situations.
Figure 4-22, Instrument Panel Limitations
4.1.2.6.5 Modifying Recess Mount Adapter Plate
This section illustrates a suggested procedure for modifying the G5 Recessed Adapter Plate and
instrument panel. Dual vertical G5 installation shown; dual horizontal and single installation
procedure is similar.
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Figure 4-23 Instrument Panel; View looking forward
Figure 4-24 Instrument Panel view with instruments removed
Temporarily remove instruments adjacent to proposed G5 location and/or as needed.
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.
Figure 4-25 Recessed Adapter Plate located on panel
Place 115-02733-00, Recessed Adapter Plate, at desired location, keeping in mind distance to
instrument panel frame and other instruments.
Figure 4-26 Match drilling through panel, using adapter plate as template
When ready, mark adapter plate and match drill instrument panel 4x, .098 diameter through
adapter plate reference holes
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Figure 4-27 Preliminary trimming of adapter plate
Figure 4-28 Adapter plate located on far side of instrument panel
Use reference holes from adapter plate to align adapter plate behind panel.
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Figure 4-29 Additional trimming of adapter plate required
Mark adapter plate where trimming is needed in order to avoid interference with any adjacent
instrument or other item.
Figure 4-30 Trimmed adapter plate
Trim adapter plate as needed; remove only enough material to allow adapter plate to fit without
interference.
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Figure 4-31 Adapter plate mounting holes
Drill 6 mounting holes through both adapter plate and panel; maintain minimum 1.5D edge
distance for No. 6 hardware.
Figure 4-32 Dual G5 panel cutout, using match drilled holes for reference
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Figure 4-33 Instrument panel after cutout for dual vertical G5 units
Figure 4-34 Adapter plate installed
Deburr and finish instrument panel and adapter plate as needed, then install adapter plate per
Section 4.1.2.6.1 or 4.1.2.6.2.
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Figure 4-35 Dual vertical G5 units installed
Install G5 units per Section 4.1.2.2.
This area intentionally blank
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Figure 4-36 G5 flush mount adapter plate printable template
The figure above may be photocopied and scaled as needed to match the full size part. This paper copy
may be used along with the instructions on Section 4.1.2.6.5 to verify the proposed installation of the G5
units will meet the installation requirements.
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4.1.2.7
GMU 11 Magnetometer Mounting Requirements
The GMU 11 is an extremely sensitive magnetic sensor, more sensitive to magnetic disturbances
than a flux gate magnetometer. For this reason, when choosing a location, distance from
possible magnetic disturbances is critical to a successful installation.
Consider the following items when choosing a mounting location:
•
•
•
•
Maintain as much distance as possible from electric motors, ferromagnetic materials,
electrical devices drawing more than 100 mA and electrical conductors
Ensure that any electrical conductor near the GMU 11 is shielded
The GMU 11 must not be mounted on an access panel
Mounting of the GMU 11 in the wing is preferred
CAUTION
After a location has been selected and a GMU 11 mounting method chosen, a location
survey must be performed at that location prior to fabricating or assembling any parts
for the GMU 11 mounting. It is possible that the location will fail the survey and the
installation will require a new location, with different installation requirements. See
Section 4.1.2.8 for Magnetic Interference Survey instructions.
CAUTION
Failure to meet these specifications may result in a failed magnetometer calibration.
For the installation of the GMU 11 level the aircraft in both the longitudinal and lateral axes.
Refer to the aircraft’s maintenance manual for leveling instructions. It is preferred that the
aircraft is placed on jacks while leveled to avoid inadvertently placing the aircraft in a nonlevel position when entering, exiting or working the aircraft.
The GMU 11 should be mounted to a surface known to have sufficient structural integrity to
withstand additional inertial forces imposed by the 0.26-pound unit.
In order to satisfy the structural mounting requirements for the GMU 11, the following
conditions must be met:
1) The mounting location must satisfy the alignment requirements shown in Figure 4-37 and
Figure 4-38
2) The mounting structure, existing or new, must be electrically bonded to the airframe per
Section 4.6.
3) Any supporting structure must be rigidly connected to the aircraft primary structure through
strong structural members capable of supporting substantial loads.
4) Mounting platform shall not span greater than 12" in width or length without direct
attachment to primary structure. If mounting platform does span greater than 12", add
necessary stringers, doublers, bulkhead flange reinforcements, etc., to provide adequate
support. Existing honeycomb core sandwich panels with aluminum face sheets are adequate
and do not require additional reinforcement.
5) A minimum of 3" between the connector end of the GMU 11 and any object must be
maintained to ensure clearance for connector and wire harness.
6) If a support bracket or shelf needs to be fabricated, it should be fabricated and attached to
the aircraft structure in accordance with the methods outlined in AC43.13-2B Chapter 1 and
2, AC43.13-1B Chapter 4, and the following requirements:
a) Material shall be 2024-T3 aluminum alloy sheet per AMS-QQ-A-250/4 or Clad 2024T3 aluminum alloy sheet per AMS-QQ-A-250/5.
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b) Material shall be minimum 0.032 inch thick.
c) Material shall have some type of corrosion protection (primer, alodine, etc.)
d) It shall be attached to primary aircraft structure with a minimum of 4 non-magnetic
fasteners or rivets from Table 4-1.
Table 4-1 GMU 11 Supporting Hardware
Hardware
Minimum Specifications
Rivets
MS20470AD3-X (3/32 Diameter, Length A/R)
Screws
MS51957-XX (#6-32, Stainless Steel, Length A/R)
Washers
NAS1149CN632R (#6-32, Stainless Steel)
Nuts
MS21044C06 (#6-32, Stainless Steel)
In general, wing mounting of the GMU 11 magnetometer is preferred. Fuselage mounting is
permitted, but NOT within two feet of the cabin area because of numerous potential
disturbances that can interfere with accurate operation. The GMU 11 must be mounted in a
serviceable location in the aircraft (e.g., accessible through an access panel).
The GMU 11 must be oriented with the mounting flanges facing down to within 3.0° of the
aircraft pitch and roll axis as show in Figure 4-37.
Figure 4-37 GMU 11 Pitch and Roll Requirements
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Lateral orientation can be such that the connector faces forward, aft, left or right, but must be
within 2° of the longitudinal axis of the aircraft, see Figure 4-38.
Figure 4-38 GMU 11 Heading Alignment Requirements
4.1.2.8
Magnetic Interference Survey
1. Temporarily place the GMU 11 in the proposed mounting location maintaining
orientation as described in Figure 4-37 and Figure 4-38.
2. Secure in place using tape if needed. Do not use clamps or other devices that are
ferrous or magnetic.
3. Run the magnetic interference survey in accordance with APPENDIX C. If the survey
passes, the location is considered reliable for the installation of the GMU 11.
If the test fails, the location should be considered unreliable until the source of the magnetic
interference is identified, remedied and the location is retested and passes the test. If the
magnetic interference cannot be remedied, another location should be chosen and tested.
This area intentionally blank
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4.1.2.9
GMU 11 Mounting
CAUTION
Care should be taken when tightening the mounting screws of the GMU 11. Excessive
tightening may damage the mounting flange or break the screws. Fasteners should be
tightened until snug, plus one-quarter turn.
GMU should not be mounted in a composite wing.
It may be mounted in a wing constructed of metal so long as any hardware used to
attach the GMU or its bracket do not penetrate the fuel tank. For installation in a
composite wing tip, of a metal wing, see APPENDIX D.
Using the hardware called out in Figure 4-39, mount the GMU 11, and replace any magnetic
fasteners within 1.5 feet with nonmagnetic equivalents (e.g. replace zinc-plated steel screws
used to mount wing covers or wing tips with nonmagnetic stainless steel screws).
Figure 4-39 GMU 11 Mounting Hardware
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4.1.3 GAD 29/29B Mounting Requirements
The GAD 29/29B should be mounted to a surface known to have sufficient structural integrity
to withstand additional inertial forces imposed by the 0.63-pound unit.
In order to satisfy the structural mounting requirements for the GAD 29/29B, the following
conditions must be met:
1) The mounting structure, existing or new, must be electrically bonded to the airframe per
Section 4.6.
2) Any supporting structure must be rigidly connected to the aircraft primary structure through
strong structural members capable of supporting substantial loads.
3) Mounting platform shall not span greater than 12" in width or length without direct
attachment to primary structure. If mounting platform does span greater than 12", add
necessary stringers, doublers, bulkhead flange reinforcements, etc., to provide adequate
support. Existing honeycomb core sandwich panels with aluminum face sheets are adequate
and do not require additional reinforcement.
4) A minimum of 3" between the connector end of the GAD 29/29B and any object must be
maintained to ensure clearance for connectors and wire harness.
5) If a support bracket or shelf needs to be fabricated, it should be fabricated and attached to
the aircraft structure in accordance with the methods outlined in AC43.13-2B Chapter 1
and 2, AC43.13-1B Chapter 4, and the following requirements:
a) Material shall be 2024-T3 aluminum alloy sheet per AMS-QQ-A-250/4 or Clad 2024-
T3 aluminum alloy sheet per AMS-QQ-A-250/5.
b) Material shall be minimum 0.040 inch thick.
c) Material shall have some type of corrosion protection (primer, alodine, etc.)
It shall be attached to primary aircraft structure with a minimum of 4 fasteners or rivets
listed in Table 4-2.
Table 4-2 GAD 29/29B Supporting Hardware
Hardware
Rivets
Screws
Washers
Nuts
Minimum Specifications
MS20470AD3-X (3/32 Diameter, Length A/R)
MS35206-XXX (#6-32, Length A/R)
NAS1149FN632P
MS21042L06
Using the hardware called out in Figure 4-40, mount the GAD 29/29B to the chosen mounting
location. Recommended torque of fasteners is 20-25 in-lbs.
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Figure 4-40 GAD 29/29B Mounting Hardware
4.1.3.1
GAD 29B Transformer Mounting Instructions
For GAD 29B installations interfacing with certain Century and Cessna autopilots an inline
transformer may be required. Refer to Section 5.12 for further information on specific
autopilots.
Solder transformer leads to the appropriate wire per SAE AS4461, and cover with heat shrink
that extends the entire lead of the transformer and at least 0.5 inch of the insulated wire. Do this
for each transformer lead and then cover the entire assembly with heat shrink, extending at least
1 inch past the solder connections.
This assembly must then be secured to the existing aircraft wiring harness near the GAD 29B to
reduce strain on the components. Secure using a minimum of two cable ties, one over the body
of the transformer and one near the solder joints.
Figure 4-41 GAD 29B Inline Transformer Mounting Instructions
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4.1.4 Pneumatic Connections
The G5 Attitude indicator and G5 DG/HSI use pitot and static pressure for the secondary
display of altitude and airspeed. The installer must install the necessary hoses and fittings to
interface to the existing aircraft pitot and static pressure source. Below are guidelines to use for
this installation.
The G5 has two ports that are connected to the aircraft’s pitot and static pressure sources. The
ports are labeled on the unit using the abbreviations “P” and “S” respectively (Figure 6-9). The
pressure ports have 1/8-27 ANPT female threads. The mating fitting must have 1/8-27 ANPT
male threads.
Determine the hose/connection material that best interfaces with the existing aircraft
installation. Reference the appropriate aircraft parts manual to determine the current part
numbers associated with the aircraft installation of hose and connections used in the
pitot/static system.
Use appropriate tubing and fittings to connect the pitot and static lines to the unit. Avoid sharp
bends in the tubing and route hoses clear of aircraft control cables. The G5 must not be at the
low point of the pneumatic plumbing lines to avoid moisture or debris collecting at or near the
unit. Ensure that no deformations of the airframe surface have been made that would affect the
relationship between static air pressure and true ambient static air pressure for any flight
condition. Refer to 14 CFR Part 43, Appendix E and AC43.13-1B, Chapter 12, Section 4 for
approved practices while installing hoses and connections. If this static source had an alternate
static source selector switch, it must be retained.
For aircraft equipped with a single pitot-static system, the G5 must be connected to the pitotstatic system used by the pilot's instruments. For aircraft equipped with a dual pitot-static
system, the G5 must be connected to the pitot-static system that is independent from the
pilot’s instruments.
CAUTION
To avoid damaging the G5 pressure sensors, both the pitot and static ports must be
connected to the test set.
CAUTION
Verify sealant/tape is not present inside the plumbing upon assembly. Use care to avoid
getting fluids or particles inside the pneumatic lines or G5 ports.
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4.2
Antenna Cable Installation and Connections
NOTE
GPS antenna cable loss must be between 1.5 dB and 6.5 dB in order to maintain proper
rejection of interference signals. If RG-142B or RG-400 is used it must be between 6.5
and 35 feet long to meet the cable loss requirement. For longer lengths, use low-loss
double or triple-shielded, 50 Ω coaxial cable.
Proper selection of coaxial cable and assembly of connectors is critical to GPS signal
performance. Use a TNC connector, AMP P/N 31-4452, to connect the coaxial cable to the
GPS antenna. Use a BNC connector, AMP P/N 225395-6, to connect the coaxial cable to the
G5.
Additional loss from coaxial connectors and adapters, such as TNC to BNC, should be
considered when computing cable loss. A typical loss of 0.2 dB can be used for each
connection.
For very short runs, where the loss is less than 1.5 dB, additional cable should be used to
increase the loss to within 1.5 dB and 6.5 dB. This additional cable may be coiled, taking into
account the minimum bend radius of the cable.
4.2.1 Coaxial Cable Termination
Follow the steps below for installation of coaxial cables:
•
•
•
Secure the cable in accordance with AC 43.13-1B chapter 11, section 11.
Trim the coaxial cable to the desired length.
Install the TNC or BNC connectors per the manufacturer’s instructions.
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4.3
Electrical Installation
4.3.1 Special Tools
Crimp tools and positioners are required to ensure consistent, reliable crimp contact
connections for the D-sub connectors. The following crimp tools are recommended:
Table 4-3: Contact Crimp Tooling
Manufacturer
Crimp Tool P/N
Positioner P/N
Insertion/Extraction Tool P/N
MIL-Spec
M22520/2-01
M22520/2-08
M81969/1-02
Daniels
AFM8
K13-1
4.3.2 Power Distribution
The circuit protection device for the G5 and GAD 29/29B must be a push-pull manually
resettable circuit breaker or identically rated circuit protection device approved by the aircraft
type certificate. See Section 3.2.1 for required circuit breaker part numbers. The G5 must be
connected to the battery bus to supply power . (Note: some aircraft manufacturers may label
the battery bus as “essential bus” or “main bus”).
4.3.3 Wiring Harness Assembly
Allow adequate space for installation of the wiring harness and connectors. Construct the
wiring harness in accordance with the information contained in this and the following
sections. Mark wire in accordance with AC 43.13-1B Chapter 11 Section 16. Strip and insert
the wire into the contact and crimp with the recommended (or equivalent) crimping tools.
Insert the contacts into the connector as specified by the interconnect diagrams in Section 5.
Verify the contacts are properly engaged into the connector by gently tugging on the wire.
Mark harness connectors in accordance with AC 43.13 Chapter 11 Section 17. Route and
secure the wiring harness away from sources of electrical interference.
The tables below lists the parts required to complete the assembly of the G5, GMU 11 and
GAD 29/29B wiring harness connectors. Some of the parts required for this installation are
included in the connector kit, and some are to be provided by the installer. See the notes
below the tables for parts that are included in the connector kit. The Garmin connector
backshell gives the installer the ability to easily terminate shield grounds at the connector
backshell as shown in and Figure 4-43. Numbers referenced in Figure 4-42 and Figure 4-43
correspond to items listed in Table 4-4, Table 4-5, and Table 4-6.
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Table 4-4: G5 (1P51, 2P51) and GMU11 (P111) Connector Parts
Item
1
2
Description
Shield Termination, Solder Style, Insulated, HeatShrinkable, Environment Resistant (X = size)
Contact, Socket, MIL Crimp, Size 20
Part Number
AS83519/1-X
(SAE-AS83519)
M39029/63-368, or
336-00022-02
3
4
5
6
7
8
9
10
11
12
13
14
Insulation Tape, Electrical, Self-Adhering,
Unsupported Silicone Rubber
Terminal, Lug, Crimp Style, Copper, Insulated, Ring
Tongue, Bell Mouthed, Type II, Class I
Connector, Plug, D-Sub, MIL Crimp Socket
Backshell, Jackscrew, 9/15 Pin
Clamp, Backshell, Jackscrew, 9/15 Pin
Screw, 4-40x.375, PHP, SS/P, w/Nylon
Cover, Backshell, Jackscrew, 9/15 Pin
Screw, 4-40x.187, FLHP100, SS/P, w/Nylon
Screw, PHP, 8-32 x 0.312", Cad-Plated Steel, or
Screw, PHP, 8-32 x 0.312", Stainless
Split Washer, #8 (0.045" compressed thickness),
Cad-plated Steel, or
Split Washer, #8 (0.045" compressed thickness),
Stainless
Flat washer, Cad-plated Steel, #8, 0.032"
thick, 0.174" ID, 0.375" OD, or
Flat Washer, Stainless, #8, 0.032" thick, 0.174"
ID, 0.375" OD
Flat Braid, 1/16”
Notes
1
2
A-A-59163
(MIL-I-46852C)
MS25036-149
330-00625-09
125-00171-00
115-01078-00
211-60234-10
115-01079-00
211-63234-06
MS35206-242, or
MS51957-42
MS35338-42, or
2
2
2
2
2
2
MS35338-137
NAS1149FN832P,
or
NAS1149CN832R
AA59569F36T0062
1
Notes:
1. AS83519/1-X and braid are the preferred method for shield termination. Alternately,
AS83519/2-X with pre-installed shield drain may be used.
2. Garmin Part Number. Included in kit p/n 011-03002-00.
This area intentionally blank
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Table 4-5: GAD 29/29B 9-pin (P291) Connector Parts
Item
1
2
Description
Shield Termination, Solder Style, Insulated, HeatShrinkable, Environment Resistant (X = size)
Contact, Socket, MIL Crimp, Size 20
Part Number
AS83519/1-X
(SAE-AS83519)
M39029/63-368, or
336-00022-02
3
4
5
6
7
8
9
10
11
12
13
14
Insulation Tape, Electrical, Self-Adhering,
Unsupported Silicone Rubber
Terminal, Lug, Crimp Style, Copper, Insulated, Ring
Tongue, Bell Mouthed, Type II, Class I
Connector, Plug, D-Sub, MIL Crimp Socket
Backshell, Jackscrew, 9/15 Pin
Clamp, Backshell, Jackscrew, 9/15 Pin
Screw, 4-40x.375, PHP, SS/P, w/Nylon
Cover, Backshell, Jackscrew, 9/15 Pin
Screw, 4-40x.187, FLHP100, SS/P, w/Nylon
Screw, PHP, 8-32 x 0.312", Cad-Plated Steel, or
Screw, PHP, 8-32 x 0.312", Stainless
Split Washer, #8 (0.045" compressed thickness),
Cad-plated Steel, or
Split Washer, #8 (0.045" compressed thickness),
Stainless
Flat washer, Cad-plated Steel, #8, 0.032"
thick, 0.174" ID, 0.375" OD, or
Flat Washer, Stainless, #8, 0.032" thick, 0.174"
ID, 0.375" OD
Flat Braid, 1/16”
Notes
1
2
A-A-59163
(MIL-I-46852C)
MS25036-149
330-00625-09
125-00171-00
115-01078-00
211-60234-10
115-01079-00
211-63234-06
MS35206-242, or
MS51957-42
MS35338-42, or
2
2
2
2
2
2
MS35338-137
NAS1149FN832P,
or
NAS1149CN832R
AA59569F36T0062
1
Notes:
1. AS83519/1-X and braid are the preferred method for shield termination. Alternately,
AS83519/2-X with pre-installed shield drain may be used.
2. Garmin Part Number. Included in kit p/n 011-03271-00.
This area intentionally blank
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Table 4-6: GAD 29/29B 25-pin (P292) Connector Parts
Item
1
2
Description
Shield Termination, Solder Style, Insulated, HeatShrinkable, Environment Resistant (X = size)
Contact, Pin, MIL Crimp, Size 20
Part Number
AS83519/1-X
(SAE-AS83519)
M39029/64-369, or
336-00024-00
3
4
5
6
7
8
9
10
11
12
13
14
Insulation Tape, Electrical, Self-Adhering,
Unsupported Silicone Rubber
Terminal, Lug, Crimp Style, Copper, Insulated, Ring
Tongue, Bell Mouthed, Type II, Class I
Connector, Plug, D-Sub, MIL Crimp Socket
Backshell, Jackscrew, 9/15 Pin
Clamp, Backshell, Jackscrew, 9/15 Pin
Screw, 4-40x.375, PHP, SS/P, w/Nylon
Cover, Backshell, Jackscrew, 9/15 Pin
Screw, 4-40x.187, FLHP100, SS/P, w/Nylon
Screw, PHP, 8-32 x 0.312", Cad-Plated Steel, or
Screw, PHP, 8-32 x 0.312", Stainless
Split Washer, #8 (0.045" compressed thickness),
Cad-plated Steel, or
Split Washer, #8 (0.045" compressed thickness),
Stainless
Flat washer, Cad-plated Steel, #8, 0.032"
thick, 0.174" ID, 0.375" OD, or
Flat Washer, Stainless, #8, 0.032" thick, 0.174"
ID, 0.375" OD
Flat Braid, 1/16”
Notes
1
2
A-A-59163
(MIL-I-46852C)
MS25036-149
330-00625-09
125-00173-00
115-01078-02
211-60234-10
115-01079-02
211-63234-06
MS35206-242, or
MS51957-42
MS35338-42, or
2
2
2
2
2
2
MS35338-137
NAS1149FN832P,
or
NAS1149CN832R
AA59569F36T0062
1
Notes:
1. AS83519/1-X and braid are the preferred method for shield termination. Alternately,
AS83519/2-X with pre-installed shield drain may be used.
2. Garmin Part Number. Included in kit p/n 011-03271-00.
This area intentionally blank
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Figure 4-42 Wiring Harness Connector Assembly
NOTE: 78 pin D-sub connector shown, 9 pin and 25 pin D-sub connector similar.
This area intentionally blank
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Figure 4-43 Shield Termination Methods
Prepare all of the shielded wires using one of the shield termination methods shown in Figure
4-43. Keep the shield drains as short as practical (3” max total length). See Table 4-4, Table
4-5, and Table 4-6 regarding numbers in parentheses in the following procedure.
1.
Strip 2.5 inches (maximum) (2.0 inches maximum for 9-pin connectors) of the jacket to
expose the shield braid.
2.
Remove the exposed braid.
3.
Carefully score the jacket 1/4 to 5/16 inches and remove the jacket to leave the braid
exposed.
4.
Slide a shield terminator (1) onto the exposed shield braid and insert shield braid drain
(14) into shield terminator. Secure the shield terminator and braid drain to the shield
using a heat gun approved for use with solder sleeves.
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5.
Strip the signal wires approximately 0.17 inches.
6.
Crimp socket contacts (2) on to the signal wires.
7.
Crimp ring terminals (4) on to the shield drain wires.
8.
Repeat steps 1 through 7 as needed for the remaining shielded wires.
9.
Insert the signal wire socket contacts into the appropriate locations in the D-sub
connector (5).
10. Attach the shield drain ring terminals to the connector backshell shield block using the
supplied screws and washers (11)(12)(13).
11. Wrap the wiring harness with silicone fusion tape (3) at the point where the strain relief
clamp (7) and connector backshell (6) will contact the wiring harness.
12. Attach the strain relief clamp (7) to the connector backshell (6) using the supplied
screws (8).
CAUTION
Placing the concave side of the strain relief clamp across the wiring harness will
damage the wiring harness.
NOTE
Only two ring terminals should be attached to each screw on the connector backshell
shield ground. It is preferred that only two wires be terminated in each ring terminal.
This will necessitate the use of a ring terminal, #8, insulated, 14-16 AWG (MS25036153). If only a single wire is left or if only a single wire is needed for this connector a
ring terminal, #8, insulated, 18-22 AWG (MS25036-149) can be used. If more wires
exist for the connector than two per ring terminal, it is permissible to terminate three
wires per ring terminal.
13. Install the connector backshell cover (9) using the supplied screws (10).
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4.4
Weight and Balance
Weight and balance computations are required after the installation of the G5. Table 4-7 lists
the weights associated with the G5 Electronic Flight Instrument. Refer to AC 43.13-1B,
Chapter 10, for the weight and balance procedure covering the addition of equipment to the
aircraft.
Table 4-7: LRU Weights
4.5
Item
G5 with Battery, connector and
mounting ring
Weight
GMU 11
.26 lbs
GAD 29
.63 lbs
GAD 29B
.65 lbs
.98 lbs
Electrical Load Analysis
If the current draw of the G5 unit(s), GMU 11 or GAD 29/29B is less than the removed
equipment, then the aircraft’s electrical load capacity can be shown to be adequate by analysis.
If it is determined the modification results in an increase in electrical load, then it must be
verified the electrical generation and reserve battery capacity remain adequate to support
electrical loads essential to safe flight and landing of the aircraft.
4.5.1 Aircraft with Existing Electrical Load Analysis
If there is an existing electrical load analysis for the aircraft, it must be updated to reflect the
modification. It must show the electrical system has adequate capacity to supply power to the
modified systems in all expected conditions. Refer to the aircraft manufacturer’s
documentation for guidance on revising and maintaining the electrical load analysis.
4.5.2 Aircraft without Existing Electrical Load Analysis
Prior to undertaking a complete electrical load analysis, the net change to the electrical load
resulting from the G5 installation should be determined. See Table 4-8 for a sample
calculation. The results of this analysis will be used to determine how to proceed further.
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4.5.2.1
Electrical Load is Reduced Following Modification
If calculations show the overall load on the electrical system is reduced as shown in the
following example, no further analysis is required. This assumes the electrical system was
within all limits prior to the G5, GMU 11 and GAD 29/29B installation. Record the new
electrical load calculations.
Table 4-8: Sample Net Electrical Load Change Calculation
Items removed from aircraft:
Electrical Load (Amps)
1
SUBTOTAL
Items added to aircraft
G5
GMU11
GAD 29/29B
14 V (typical)
(1)
.200 A
28 V (typical)
(1)
.100 A
14 V (typical)
(1)
.100 A
28 V (typical)
(1)
.100 A
14 V (typical)
(1)
.200 A
28 V (typical)
(1)
.100 A
SUBTOTAL
NET CHANGE IN BUS LOAD
(NEW BUS LOAD – OLD BUS LOAD)
Notes:
(1) Use 14 V or 28 V typical current
draw depending on aircraft system
when performing this calculation.
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4.5.2.2
Electrical Load is Increased Following Modification
If it is determined the electrical load has increased an appreciable amount, a complete electrical
load analysis must be performed to show the capacity of the electrical system is sufficient for
the additional electrical load. For guidance on performing an electrical load analysis, refer to
ASTM F 2490-05, Standard Guide for Aircraft Electrical Load and Power Source Capacity
Analysis. Alternatively, the loads under various operating conditions may be measured, as
described in Section 4.5.2.3.
4.5.2.3
Performing an Electrical Load Analysis by Measurement
This section describes how to perform an electrical load analysis for a single alternator-single
battery electrical system. These procedures may be modified accordingly for aircraft with
multiple batteries or alternators, and it must be shown the maximum electrical demand does not
typically exceed 80% of the electrical system capacity.
In this section the following definitions are used:
normal operation: the primary electrical power generating system is operating normally.
emergency operation: the primary electrical power generating system is inoperative and a
back-up electrical power generating system is being used. This typically requires load shedding
of non-essential equipment to provide adequate electrical power to essential required equipment
for safe flight and landing of the airplane.
Either an in-circuit or clamp-on ammeter can be used for current measurement. The instrument
used must be calibrated and must be capable of reading current to the nearest 0.5 A, or better.
1. Record the continuous load rating for the alternator and battery.
2. Compile a list of electrical loads on the aircraft (generally, this is just a list of
circuit breakers and circuit breaker switches).
3. Identify whether each load is continuous (e.g. GPS) or intermittent (e.g. stall
warning horn, landing gear).
4. Using the worst-case flight condition, identify whether each load is used in a
particular phase of flight for normal operation. If some loads are mutually
exclusive and will not be turned on simultaneously (e.g. pitot heat and air
conditioning), use only those loads for the worst-case condition.
5. Identify whether each load is used in a particular phase of flight for emergency
operation. As a minimum, these systems generally include:
o
COM Radio #1
o
NAV Radio #1
o
Transponder and associated altitude source
o
Audio Panel
o
Stall Warning System (if applicable)
o
Pitot Heat
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o
Landing Light (switched on during landing only)
o
Instrument Panel Dimming
6. Insert/attach the ammeter in the line from the external power source to the master
relay circuit as shown in Figure 4-44. This will eliminate errors due to the
charging current drawn by the battery.
CAUTION
To avoid damage to equipment, ensure the ammeter is capable of handling the expected
load.
Figure 4-44 Ammeter Placement for Current Measurements
7. Ensure all circuit breakers are closed.
8. Apply external power to the aircraft. The voltage of the power source should be set
to the nominal alternator voltage (usually 13.8 VDC or 27.5 VDC).
9. Turn on the battery master switch.
NOTE
Intermittent electrical loads are not measured. It is assumed if additional current is
required beyond what the alternator can supply, this short-duration demand will be
provided by the battery.
10. Set the lighting as described below. These settings will be used for every current
measurement which follows:
o
Set instrument panel and flood lights to maximum brightness.
o
Set displays with a backlight to 50% brightness
11. Using the tabulation completed above, switch on all continuous electrical loads used
for the taxiing phase and record the current measured by the ammeter (measurement
(a) in Figure 4-45). The autopilot circuit breaker (if installed) should be closed, but
the autopilot should not be engaged.
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WARNING
Pitot heat should be switched on only long enough to take the current measurement and
then switched off to avoid injury to personnel or damage to the Pitot tube.
12. Using the tabulation completed above, switch on all continuous electrical loads used
for the normal takeoff/landing phase and record the current measured by the
ammeter. Measurements must be taken with the landing lights ON and OFF
(measurements (b1) and (b2) in Figure 4-45).
13. Engage the autopilot (if installed).
14. Using the tabulation completed above, switch on all continuous electrical loads
which are used for the normal cruise phase and record the current measured by the
ammeter (measurement (c) in Figure 4-45.
15. Using the tabulation completed above, switch on all continuous electrical loads used
for the emergency cruise phase and record the current measured by the ammeter.
16. Using the tabulation completed above, switch on all continuous electrical loads used
for the emergency landing phase and record the current measured by the ammeter.
17. Using the values measured and recorded, complete the ELA using the blank form in
Figure 4-45 and Figure 4-46.
18. Verify the maximum electrical load does not exceed 80% of the electrical system
capacity. See example in Figure 4-47 and Figure 4-48.
NOTE
Electrical loads in excess of 80% but not greater than 95% of electrical system
capacity are permitted during the takeoff/landing phase of flight when landing light(s)
are switched on.
This area intentionally blank
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Figure 4-45 Blank Electrical Load Tabulation Form, Sheet 1 of 2
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Figure 4-46 Blank Electrical Load Tabulation Form, Sheet 2 of 2
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Figure 4-47 Sample Completed Electrical Load Tabulation Form, Sheet 1 of 2
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Figure 4-48 Sample Completed Electrical Load Tabulation Form, Sheet 2 of 2
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4.6
Electrical Bonding
The GAD 29/29B is the only LRU installed by this STC that requires bonding. The following
sections present data on acceptable methods of electrical bonding for the GAD 29/29B.
Electrical bonding can be achieved with mounting hardware (rivets, bolts, nuts, washers, etc..)
or via bond straps. A reliable electrical bond rely on mated surfaces to be clean of any
primer/grease/dirt. When bolts are used to secure racks/brackets/etc.. and are relied upon for
electrical bond, in lieu of the mating surfaces of the racks/brackets/etc. then the area under the
head of the bolt/screw or washer must be free of primer and a spot face should be prepared
that is at least 0.125 inches wider than the head of the bolt or the washer (if used) under the
head. If primer or film was removed to achieve this then any exposed area still visible after the
bond is completed must be refinished with the original finish or other suitable film (eg primer)
or coating, ref ARP1870. If the bolt is secured with washer and nut then a similar spot face as
described above shall occur between the washer and the mounting structure. Rivets used to
mechanically attach brackets/shelves/etc.. provide an inherent electrical bond through the
rivets and require no additional bond preparation. Similarly riveted nut plates do not need any
special bonding preparation and can be relied upon to provide electrical bond between the
fastener and the nutplate. The top or bottom side of the Garmin racks or equipment flanges do
not need any special bond preparations. Additional details on how to accomplish electrical
bonding can also be found in SAE ARP1870 section 5.
When equipment is mounted to honeycomb shelves, the face sheets must be metal. The
honeycomb material between the face sheets is not conductive and therefore care must be
taken to make sure proper bonding of the equipment has taken place. The top and bottom
faces sheets must be grounded to each other and one of the face sheets must be grounded to
the airframe.
The instrument panel must be of metal construction so that remotely mounted units have a
metal ground reference back to the other G5 interfacing equipment mounted on the instrument
panel. For metal aircraft the latter is achieved inherently through the metallic aircraft structure.
For composite aircraft a ground plane (or reference) may need to be created to achieve a
comparable ground. This procedure is described in Section 4.6.2.
All LRU bonding measurements must be made with the connector(s) disconnected from the
LRU.
4.6.1 Metal Aircraft
The GAD 29/29B and the support brackets require a resistance value of 2.5 milliohms or less
between individual mating surfaces. For general steps on how to prepare aluminum surfaces
for electrical bonding refer to Section 4.6.3.
If the instrument panel is attached by vibration mounts, verify that the mounts are grounded to
the metallic airframe structure by means of a bonding jumper. Ensure that the installed
bonding jumper meets the following specifications.
1. The braid is a 7/16" or wider tubular braid (part number QQB575R30T437, 24,120
circular mils) or a 3/4" or wider flat braid (part number QQB575F36T781, 20,800
circular mils).
2. The braid contains a terminal lug (mil-spec MS20659-130) at each end.
3. The strap length is as short as possible, not exceeding 6 inches.
Ensure that each terminal lug is secured to its respective mating surface with one #10 steel
bolt and one flat washer (part number AN970-3). Lugs and washers should be center-aligned
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and flush on all outside edges. These components should be in full contact with the mating
surface.
4.6.2 Nonmetallic Aircraft
NOTE
Carbon reinforced composite (with or without mesh) or fiberglass with mesh is
considered to be conductive. Wood, Kevlar and fiberglass without mesh is considered
to be non-conductive.
If the equipment is mounted in the metallic instrument panel then the bonding should be
accomplished like that for metal aircraft (Section 4.6.1). For composite areas of the aircraft the
GAD 29/29B must be electrically bonded to the metallic instrument panel either directly
through the unit remote install/mounting rack or with heavy-duty dead soft aluminum tape
such as 3M Heavy Duty Aluminum Foil Tape 438. The following guidance should be used for
locating and bonding the LRU:
1. Identify a location for the LRU which is close to the instrument panel or the grounding
structure for the instrument panel.
2. Identify a route between the LRU location and the instrument panel ground that will
accommodate a strip of aluminum tape with a width of at least four inches and a lengthto-width ratio of 7:1.
3. If the tape will come in contact with carbon composite material, the tape must be
electrically isolated from the carbon composite material to prevent corrosion due to
dissimilar materials. Secure a thin layer of fiberglass cloth to the carbon fiber with
fiberglass resin as shown in Figure 4-49.
Figure 4-49 Fiberglass Insulation for Carbon Fiber Material
4. Identify a grounding location. The ground must be a bare metal surface on the
instrument panel or grounding structure for the instrument panel. If it is impractical to
reach a grounding location with aluminum tape then:
a. The tape shall meet a 5:1 length to width ratio.
b. The bond strap shall be one inch wide and no longer than five inches.
5. Prepare the aluminum surface at the ground location outlined in Section 4.6.3 or
identify a ground stud to which the braid can be attached. Any new ground stud shall
also be prepared for electrical bonding.
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6. Route the tape between the LRU mount and the grounding location for the instrument
panel. If needed to maintain the 7:1 length-to-width ratio, the tape can be overlapped in
more than one strip.
7. If two pieces of tape need to be joined end-to-end, they can be joined as illustrated in
Figure 4-50.
Figure 4-50 Aluminum Tape Joint
8. Fold the end of the tape over twice for added thickness at the prepared grounding
location. Refer to Figure 4-51. Apply 3” wide tape over the seam as shown.
9. The tape shall not have any tears in the joint or along the length of the tape as tears will
degrade the bonding performance.
10. Electrical bond preparation for all aluminum-to-aluminum interfaces per SAE
ARP1870 section 5.1 and 5.5.
11. If a bonding strap will be used to reach the grounding location, secure the end of the
tape to the secondary composite surface as shown in Figure 4-51. Note that the
procedure for installing mounting bolts applies only to secondary aircraft structures, not
to primary structure or structural load-carrying members. The tape shall meet 5:1
length to width ratio if a bonding strap is used. The bonding strap shall be one inch
wide and no longer than five inches. Refer to Figure 4-51.
12. Terminate both ends of the bonding strap with MS20659-130 terminal lugs.
13. Install AN960C10 washer between the terminal lug and the mating metal surface and
secure with a #10 steel bolt. Ensure that the lug and washer are centered and in full
contact with the mating surface with no overhang when secured.
14. Secure the end of the tape in place using a 0.063” piece of aluminum using three bolts
and nuts. Refer to Figure 4-51.
15. Secure the aluminum tape to the GAD 29/29B or mounting rack as shown in Figure
4-52.
16. Verify that the resistance between tape and the local grounding location does not
exceed 2.5 mΩ.
This area intentionally blank
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Figure 4-51 Aluminum Tape Ground Termination
Figure 4-52 GAD 29/29B Aluminum Tape Installation
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4.6.3 Aluminum Surface Preparation
In order to prepare the aluminum surface for proper bonding, the following general steps
should be followed. For a detailed procedure, reference SAE ARP1870, Sections 5.1 and 5.5.
1. Clean grounding location with solvent.
2. Remove non-conductive films or coatings from the grounding location. When area is
cleaned around fastener heads or washers the area cleaned should be 0.125 inches
wider than the foot print of the washer or the bolt head.
3. Apply a chemical conversion coat such as Alodine 1200 to the bare metal.
4. Once the chemical conversion coat is dry, clean the area.
5. Install bonding aluminum tape or equipment at grounding location.
6. After the bond is complete, if any films or coatings were removed from the surface,
reapply a suitable film or coating to the surrounding area.
This area intentionally blank
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5
SYSTEM INTERCONNECTS
This section will provide the specific wiring interconnects for the various configuration
possibilities for the G5 Attitude indicator and G5 DG/HSI installations. Each installation
contains the specific G5 and or GPS/VHF Navigator configuration table. Power and Ground
wiring is identical for each installation and is only shown in Figure 5-2.
NOTE:
The configuration tables are presented in order as the configuration pages on the G5
are presented. To make configuration of the G5 easier configure the ARINC 429 and
or RS-232 options first. This allows for hidden configurations that require the ARINC
429 or RS-232 options to be selected as appropriate.
This area intentionally blank
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5.1
G5 Interconnect Notes
Figure 5-1 G5 Interconnect Notes
CAUTION
Check wiring connections for errors before connecting the wiring harness to the LRUs.
Incorrect wiring could cause component damage.
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5.2
Power and Ground
Figure 5-2 Power and Ground
This area intentionally blank
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5.3
G5 (Attitude Indicator) with External GPS Antenna
Figure 5-3 G5 (Attitude Indicator) with External GPS Antenna
5.3.1 Attitude Indicator Configuration
Config Page
Device Information
Config Option
Installation Type
Diagnostics/Data Log
Configuration Setting
Certified Instrument
Enabled
Attitude Configuration
Indicator Type
Pitch Display
Roll Display
Automatic Declutter
Normal
Normal
For Fixed Type Pointers G5 Config = Ground
or
For Movable Type Pointers G5 Config = Sky
Enabled
Air Data
Air Data Sensors
Vertical Speed Indicator
Enabled
(1)(2)
Airspeed
VNE
VNO
VSO
VS1
VFE
VA
VX
VY
VG
VR
VMC
VYSE
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
Magnetometer
Magnetometer
Disabled
Flight Controls
Autopilot Servos
Analog Autopilot Interface
None
None
Backlight
Current Mode
Default Mode
Minimum Photocell Input
Minimum Display Brightness
Maximum Photocell Input
Maximum Display Brightness
Filter Time Constant
Automatic
Automatic
Default
Default
Default
Default
Default
Display
HSI Page
Power Up Page
Disabled
PFD
Battery
Show Battery Status
Automatic Power Off
When Using Battery
On Ground Only
GPS
Internal GPS Receiver
GPS Data Field
Enabled
Show
Note: Configure Units prior to setting
airspeeds.
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Config Page
Config Option
Configuration Setting
Navigation
Navigation Data
Selected Course
VNAV Deviation Scale
Disable
(4)
(4)
Units
Altitude
Distance
Airspeed
Ground Speed
Ground Track
Vertical Speed
Pressure
(1)(2)
(1)(2)
(1)(2)(3)
(1)(2)
Magnetic
(1)(2)(3)
(1)(2)
RS-232
Input Format
Output Format
None
None
ARINC 429
Output 1
Output 2
Input 1
Input 2
Input 3
Input 4
None
None
None
None
None
None
Exit Configuration Mode
Note 1: Set configuration values and units to match the values indicated in the appropriate
AFM and document settings in the space provided.
Note 2: If the aircraft has no AFM set the values as determined by the existing placards,
instrument bugs or instrument markings.
Note 3: Existing placards related to airspeed limitations must be retained.
Note 4: Setting can remain at default setting, not supported in this configuration.
This area intentionally blank
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5.4
G5 (Attitude Indicator) with GPS Position Input
Figure 5-4 G5 (Attitude Indicator) with GPS Position Input
5.4.1 Attitude Indicator
Config Page
Device Information
Config Option
Installation Type
Diagnostics/Data Log
Configuration Setting
Certified Instrument
Enabled
Attitude Configuration
Indicator Type
Pitch Display
Roll Display
Automatic Declutter
Normal
Normal
For Fixed Type Pointers G5 Config = Ground
or
For Movable Type Pointers G5 Config = Sky
Enabled
Air Data
Air Data Sensors
Vertical Speed Indicator
Enabled
(1)(2)
Airspeed
VNE
VNO
VSO
VS1
VFE
VA
VX
VY
VG
VR
VMC
VYSE
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
Magnetometer
Magnetometer
Disabled
Flight Controls
Autopilot Servos
Analog Autopilot Interface
None
None
Backlight
Current Mode
Default Mode
Minimum Photocell Input
Minimum Display Brightness
Maximum Photocell Input
Maximum Display Brightness
Automatic
Automatic
Default
Default
Default
Default
Note: Configure Units prior to
setting airspeeds.
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Config Page
Config Option
Filter Time Constant
Configuration Setting
Default
Display
HSI Page
Power Up Page
Disabled
PFD
Battery
Show Battery Status
Automatic Power Off
When Using Battery
On Ground Only
GPS
Internal GPS Receiver
Show Data Fields
Disabled
Show
Navigation
Navigation Data
Selected Course
VNAV Deviation Scale
Disabled
(4)
(4)
Units
Altitude
Distance
Airspeed
Ground Speed
Ground Track
Vertical Speed
Pressure
(1)(2)
(1)(2)
(1)(2)(3)
(1)(2)
Magnetic
(1)(2)
(1)(2)
RS-232
Input Format
Output Format
MapMx (WAAS Units)
AVIATION (Non WAAS Units)
None
Output 1
Output 2
Input 1
Input 2
Input 3
Input 4
None
None
None
None
None
None
ARINC 429
Exit Configuration Mode
5.4.2 GTN 6XX/7XX Configuration
Config Page
Config Option
Configuration Setting
RS-232
RS-232 (x)
(x represents any available RS-232
Port )
Output = MapMX Format 2
5.4.3 GNS 4XX(W) / 5XX(W) Configuration
Config Page
Config Option
Configuration Setting
MAIN RS232 CONFIG Page
RS-232 (x)
(x represents any available RS-232
Channel )
Input = OFF
Output = MapMX (WAAS )
AVIATION (Non WAAS)
Config Option
Configuration Setting
5.4.4 GNS 480 Configuration
Config Page
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Config Page
GND Maint Serial Setup
Config Option
CH (x)
(x represents any available Serial
Channel )
Configuration Setting
Output = MapMX
Config Page
Config Option
Configuration Setting
Interface Group
RS-232 (x)
(x represents any available RS-232
Channel )
Output = MapMX
5.4.5 GTX 3x5 Configuration
Note 1: Set configuration values and units to match the values indicated in the appropriate
AFM and document settings in the space provided.
Note 2: If the aircraft has no AFM set the values as determined by the existing placards,
instrument bugs or instrument markings.
Note 3: Existing placards related to airspeed limitations must be retained.
Note 4: Setting can remain at default setting, not supported in this configuration.
This area intentionally blank
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5.5
G5 (Attitude Indicator) and GMU 11 with GPS Position Input
Figure 5-5 G5 (Attitude Indicator) and GMU 11 with GPS Position Input
5.5.1 Attitude Indicator Configuration
Config Page
Device Information
Config Option
Installation Type
Diagnostics/Data Log
Configuration Setting
Certified Instrument
Enabled
Attitude Configuration
Indicator Type
Pitch Display
Roll Display
Automatic Declutter
Normal
Normal
For Fixed Type Pointers G5 Config = Ground
or
For Movable Type Pointers G5 Config = Sky
Enabled
Air Data
Air Data Sensors
Vertical Speed Indicator
Enabled
(1)(2)
Airspeed
VNE
VNO
VSO
VS1
VFE
VA
VX
VY
VG
VR
VMC
VYSE
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
Magnetometer
Orientation
Enabled
Connector Aft
Or
Connector Forward
Or
Connector Port
Or
Connector Starboard
Note: Configure Units prior to
setting airspeeds.
Magnetometer
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Config Page
Flight Controls
Config Option
Autopilot Servos
Analog Autopilot Interface
Configuration Setting
None
None
Backlight
Current Mode
Default Mode
Minimum Photocell Input
Minimum Display Brightness
Maximum Photocell Input
Maximum Display Brightness
Filter Time Constant
Automatic
Automatic
Default
Default
Default
Default
Default
Display
HSI Page
Power Up Page
Disabled
PFD
Battery
Show Battery Status
Automatic Power Off
When Using Battery
On Ground Only
GPS
Internal GPS Receiver
Show Data Fields
Disabled
Show
Navigation
Navigation Data
Selected Course
VNAV Deviation Scale
Disabled
(4)
(4)
Units
Altitude
Distance
Airspeed
Ground Speed
Ground Track
Vertical Speed
Pressure
(1)(2)
(1)(2)
(1)(2)(3)
(1)(2)
Magnetic
(1)(2)
(1)(2)
RS-232
Input Format
Output Format
MapMx (WAAS Units)
AVIATION (Non WAAS Units)
None
Output 1
Output 2
Input 1
Input 2
Input 3
Input 4
None
None
None
None
None
None
ARINC 429
Exit Configuration Mode
5.5.2 GTN 6XX/7XX Configuration
Config Page
Config Option
Configuration Setting
RS-232
RS-232 (x)
(x represents any available RS-232
Port )
Output = MapMX Format 2
5.5.3 GNS 4XX(W) / 5XX(W) Configuration
Config Page
Config Option
Configuration Setting
MAIN RS232 CONFIG Page
RS-232 (x)
(x represents any available RS-232
Channel )
Input = OFF
Output = MapMX (WAAS )
AVIATION (Non WAAS)
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5.5.1 GNS 480 Configuration
Config Page
Config Option
Configuration Setting
GND Maint Serial Setup
CH (x)
(x represents any available Serial
Channel )
Output = MapMX
Config Page
Config Option
Configuration Setting
Interface Group
RS-232 (x)
(x represents any available RS-232
Channel )
Output = MapMX
5.5.2 GTX 3x5 Configuration
Note 1: Set configuration values and units to match the values indicated in the appropriate
AFM and document settings in the space provided.
Note 2: If the aircraft has no AFM set the values as determined by the existing placards,
instrument bugs or instrument markings.
Note 3: Existing placards related to airspeed limitations must be retained.
Note 4: Setting can remain at default setting, not supported in this configuration.
This area intentionally blank
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5.6
G5 (Attitude Indicator or DG), GMU 11 and GPS Antenna
Figure 5-6 G5 (Attitude Indicator or DG), GMU 11 and GPS Antenna
5.6.1 Attitude Indicator or DG Configuration
Config Page
Device Information
Config Option
Installation Type
Diagnostics/Data Log
Configuration Setting
Certified Instrument
Enabled
Attitude Configuration
Indicator Type
Pitch Display
Roll Display
Automatic Declutter
Normal
Normal
For Fixed Type Pointers G5 Config = Ground
or
For Movable Type Pointers G5 Config = Sky
Enabled
Air Data
Air Data Sensors
Vertical Speed Indicator
Enabled
(1)(2)
Airspeed
VNE
VNO
VSO
VS1
VFE
VA
VX
VY
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
Note: Configure Units prior to
setting airspeeds.
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Config Page
Config Option
VG
VR
VMC
VYSE
Configuration Setting
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
Magnetometer
Magnetometer
Orientation
Enabled
Connector Aft
Or
Connector Forward
Or
Connector Port
Or
Connector Starboard
Flight Controls
Autopilot Servos
Analog Autopilot Interface
None
None
Or
See Section 5.12 if a Third Party Autopilot is
interfaced
Backlight
Current Mode
Default Mode
Minimum Photocell Input
Minimum Display Brightness
Maximum Photocell Input
Maximum Display Brightness
Filter Time Constant
Automatic
Automatic
Default
Default
Default
Default
Default
Display (When used as an Attitude
or Turn Coord)
Display (When used as a DG)
HSI Page
Power Up Page
HSI Page
Power Up Page
Disabled
PFD
Enabled
HSI
Battery
Show Battery Status
Automatic Power Off
When Using Battery
On Ground Only
GPS
Internal GPS Receiver
GPS Data Fields
Enabled
Show
Navigation
Navigation Data
Selected Course
VNAV Deviation Scale
Disabled
Note: Only used if a third party autopilot is
configured.
If a third party autopilot interface is
configured ON, this configuration page is
set to ENABLED by default.
(4)
(4)
Units
Altitude
Distance
Airspeed
Ground Speed
Ground Track
Vertical Speed
Pressure
(1)(2)
(1)(2)
(1)(2)(3)
(1)(2)
Magnetic
(1)(2)
(1)(2)
RS-232
Input Format
Output Format
None
None
ARINC 429
Output 1
Output 2
Input 1
Input 2
Input 3
Input 4
None
None
None
None
None
None
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Config Page
Exit Configuration Mode
Config Option
Configuration Setting
Note 1: Set configuration values and units to match the values indicated in the appropriate
AFM and document settings in the space provided.
Note 2: If the aircraft has no AFM set the values as determined by the existing placards,
instrument bugs or instrument markings.
Note 3: Existing placards related to airspeed limitations must be retained.
Note 4: Setting can remain at default setting, not supported in this configuration.
This area intentionally blank
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5.7
G5 (HSI) with VHF Navigator
Figure 5-7 G5 (HSI) with VHF Navigator
5.7.1 G5 HSI Configuration (VHF Navigator)
Config Page
Device Information
Config Option
Installation Type
Diagnostics/Data Log
Configuration Setting
Certified Instrument
Enabled
Attitude Configuration
Indicator Type
Pitch Display
Roll Display
Automatic Declutter
Normal
Normal
For Fixed Type Pointers G5 Config = Ground
or
For Movable Type Pointers G5 Config = Sky
Disabled
Air Data
Air Data Sensors
Vertical Speed Indicator
Enabled
(1)(2)
Airspeed
VNE
VNO
(1)(2)(3)
(1)(2)(3)
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Config Page
Note: Configure Units prior to
setting airspeeds.
Config Option
VSO
VS1
VFE
VA
VX
VY
VG
VR
VMC
VYSE
Configuration Setting
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
Magnetometer
Magnetometer
Orientation
Enabled
Connector Aft
Or
Connector Forward
Or
Connector Port
Or
Connector Starboard
Flight Controls
Autopilot Servos
Analog Autopilot Interface
None
None
Or
See Section 5.12 if a Third Party Autopilot is
interfaced
Backlight
Current Mode
Default Mode
Minimum Photocell Input
Minimum Display Brightness
Maximum Photocell Input
Maximum Display Brightness
Filter Time Constant
Automatic
Automatic
Default
Default
Default
Default
Default
Display
HSI Page
Power Up Page
Enabled
HSI
Battery
Show Battery Status
Automatic Power Off
When Using Battery
On Ground Only
GPS
Internal GPS Receiver
GPS Data Fields
Enabled
Show
Navigation Data
Disabled
Note: Only used if a third party autopilot is
configured.
If a third party autopilot interface is
configured ON, this configuration page is
set to ENABLED by default.
Selected Course
VNAV Deviation Scale
(4)
(4)
Units
Altitude
Distance
Airspeed
Vertical Speed
Pressure
(1)(2)
(1)(2)
(1)(2)(3)
(1)(2)
(1)(2)
RS-232
Input Format
Output Format
Garmin VHF NAV Radio
Garmin VHF NAV Radio
ARINC 429
Output 1
None
Navigation
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Config Page
Config Option
Output 2
Input 1
Input 2
Input 3
Input 4
Configuration Setting
None
None
None
None
None
Exit Configuration Mode
5.7.2 GNC 255 Configuration
Config Page
Sys Configuration
Config Option
RS 232 Serial Port
Configuration Setting
IO Mode = NMEA
Attitude Configuration
CDI Indicator
TYPE = Serial
Config Page
Sys Configuration
Config Option
RS 232 Serial Port
Configuration Setting
No Setting
Attitude Configuration
Indicator Type
TYPE = Serial
5.7.3 SL30 Configuration
Note 1: Set configuration values and units to match the values indicated in the appropriate
AFM and document settings in the space provided.
Note 2: If the aircraft has no AFM set the values as determined by the existing placards,
instrument bugs or instrument markings.
Note 3: Existing placards related to airspeed limitations must be retained.
Note 4: Setting can remain at default setting, not supported in this configuration.
This area intentionally blank
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5.8
G5 (HSI) with GPS/VHF Navigator
Figure 5-8 G5 (HSI) with GPS/VHF Navigator
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Figure 5-9 G5 (HSI) with GPS/VHF Navigator Notes
5.8.1 G5 HSI Configuration (With GPS/VHF Navigator)
Config Page
Device Information
Config Option
Installation Type
Diagnostics/Data Log
Configuration Setting
Certified Instrument
Enabled
Attitude Configuration
Indicator Type
Pitch Display
Roll Display
Automatic Declutter
Normal
Normal
For Fixed Type Pointers G5 Config = Ground
or
For Movable Type Pointers G5 Config = Sky
Disabled
Air Data
Air Data Sensors
Vertical Speed Indicator
Enabled
(1)(2)
Airspeed
VNE
VNO
VSO
VS1
VFE
VA
VX
VY
VG
VR
VMC
VYSE
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
Magnetometer
Magnetometer
Orientation
Enabled
Connector Aft
Or
Connector Forward
Or
Connector Port
Or
Connector Starboard
Flight Controls
Autopilot Servos
None
Note: Configure Units prior to
setting airspeeds.
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Config Page
Config Option
Analog Autopilot Interface
Configuration Setting
None
Or
See Section 5.12 if a Third Party Autopilot is
interfaced
Backlight
Current Mode
Default Mode
Minimum Photocell Input
Minimum Display Brightness
Maximum Photocell Input
Maximum Display Brightness
Filter Time Constant
Automatic
Automatic
Default
Default
Default
Default
Default
Display
HSI Page
Power Up Page
Enabled
HSI
Battery
Show Battery Status
Automatic Power Off
When Using Battery
On Ground Only
GPS
Internal GPS Receiver
GPS Data Fields
Disabled
Show
Navigation
Navigation Data
Disabled
Note: If a third party autopilot interface is
configured ON, this configuration page is set
to ENABLED by default.
Selected Course
VNAV Deviation Scale
(5)
(5)
Units
Altitude
Distance
Airspeed
Ground Speed
Ground Track
Vertical Speed
Pressure
(1)(2)
(1)(2)
(1)(2)(3)
(1)(2)
Magnetic
(1)(2)
(1)(2)
RS-232
Input Format
MapMx (WAAS Units)
AVIATION (Non WAAS Units)
None
Output Format
ARINC 429
Output 1
Output 2
Input 1
Input 2
Input 3
Input 4
EFIS / AIRDATA 1 (SDI 1)
(Only used with GTN 6XX / 7XX and GNS
4XX(W) / 5XX(W) and no Third Party Autopilot
is interfaced)
EFIS / AIRDATA 2 (SDI 1)
(Always used with GNS 480 and GTN 6XX /
7XX and GNS 4XX(W) / 5XX(W) when Third
Party Autopilot is interfaced)
None
Garmin GPS (SDI 1)
Garmin VOR/ILS (SDI 1) (4)
None
None
Exit Configuration Mode
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5.8.2 GTN 6XX/7XX Configuration
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 )
(Only used when Third Party
Autopilot is interfaced)
ARINC 429 Out (x)
(x represents any available ARINC
429 Port )
Configuration Setting
Speed = Low
Data = EFIS Format 2
Speed = Low
Data = GAD Format 1
(Only used when Third Party Autopilot is interfaced)
Speed = Low
Data = GAMA Format 1
RS-232
RS-232 (x)
(x represents any available RS-232
Port )
Input = MapMX Format 2
Output = MapMX Format 2
Main Indicator (Analog) Configuration
CDI Key
Selected Course for GPS
Selected Course for VLOC
V-Flag State
Enabled
Allowed
Allowed
Normal
VOR/LOC/GS Configuration
Nav Radio
ARINC 429 Configuration
Enabled (4)
Tx Speed = Low
SDI = VOR/ILS 1
Main System
Heading Source Input
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.
Altitude Source Input
5.8.3 GNS 4XX(W) / 5XX(W) Configuration
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 )
(Only used when Third Party
Autopilot is interfaced)
OUT
Configuration Setting
Speed = Low
Data = EFIS / Airdata
Speed = Low
Data = Garmin GAD 42
(Only used when Third Party Autopilot is interfaced)
VNAV
Speed = Low
Data = GAMA 429
ENABLED
MAIN RS232 CONFIG Page
RS-232 (x)
(x represents any available RS-232
Channel )
Input = OFF
Output = MapMX (WAAS )
AVIATION (Non WAAS)
VOR/LOC/GS ARINC 429 CONFIG Page
SPEED
RX = Low
TX = Low (4)
VOR/ILS 1 (4)
SDI
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5.8.4 GNS 480 Configuration
Config Page
GND Maint Serial Setup
Config Option
CH (x)
(x represents any available Serial
Channel )
Configuration Setting
Output = MapMX
GND Maint ARINC 429 Setup
CH In (2)
(or any available 429 Port )
SEL = EFIS
SPEED = Low
SDI = SYS1
SEL = GAMA 429
SPEED = Low
SDI = SYS1
SEL = VOR / ILS
SPEED = Low
SDI = SYS1
CH Out (1)
(or any available 429 Port )
CH Out (2)
(or any available 429 Port )
GND Maint Resolver Interface Setup
Resolver
Not Installed
GND Maint Miscellaneous Setup
CDI Select
Use
Note 1: Set configuration values and units to match the values indicated in the appropriate
AFM and document settings in the space provided.
Note 2: If the aircraft has no AFM set the values as determined by the existing placards,
instrument bugs or instrument markings.
Note 3: Existing placards related to airspeed limitations must be retained.
Note 4: Not applicable to GPS navigators that has no VHF Navigation output. Reference Note
5 in Figure 5-9.
Note 5: Setting can remain at default setting, not supported in this configuration.
This area intentionally blank
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5.9
Dual G5 without Navigator
Figure 5-10 Dual G5 without Navigator
5.9.1 Attitude Indicator Configuration
Config Page
Device Information
Config Option
Installation Type
Diagnostics/Data Log
Configuration Setting
Certified Instrument
Enabled
Attitude Configuration
Indicator Type
Pitch Display
Roll Display
Automatic Declutter
Normal
Normal
For Fixed Type Pointers G5 Config = Ground
or
For Movable Type Pointers G5 Config = Sky
Enabled
Air Data
Air Data Sensors
Vertical Speed Indicator
Enabled
(1)(2)
Airspeed
VNE
VNO
VSO
VS1
VFE
VA
VX
VY
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
Note: Configure Units prior to setting
airspeeds.
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Config Page
Config Option
VG
VR
VMC
VYSE
Configuration Setting
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
Magnetometer
Magnetometer
Orientation
Enabled
Connector Aft
Or
Connector Forward
Or
Connector Port
Or
Connector Starboard
Flight Controls
Autopilot Servos
Analog Autopilot Interface
None
None
Or
See Section 5.12 if a Third Party Autopilot is
interfaced
Backlight
Current Mode
Default Mode
Minimum Photocell Input
Minimum Display Brightness
Maximum Photocell Input
Maximum Display Brightness
Filter Time Constant
Automatic
Automatic
Default
Default
Default
Default
Default
Display
HSI Page
Power Up Page
Disabled
PFD
Battery
Show Battery Status
Automatic Power Off
When Using Battery
On Ground Only
GPS
Internal GPS Receiver
GPS Data Fields
Enabled
Show
Navigation
Navigation Data
Selected Course
VNAV Deviation Scale
Disable
Note: If a third party autopilot interface is
configured ON, this configuration page is
set to ENABLED by default.
(4)
(4)
Units
Altitude
Distance
Airspeed
Ground Speed
Ground Track
Vertical Speed
Pressure
(1)(2)
(1)(2)
(1)(2)(3)
(1)(2)
Magnetic
(1)(2)
(1)(2)
RS-232
Input Format
Output Format
None
None
ARINC 429
Output 1
Output 2
Input 1
Input 2
Input 3
Input 4
None
None
None
None
None
None
Exit Configuration Mode
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5.9.2 G5 DG Configuration
Config Page
Device Information
Config Option
Installation Type
Diagnostics/Data Log
Configuration Setting
Certified Instrument
Enabled
Attitude Configuration
Automatic Declutter
Disabled
Backlight
Current Mode
Default Mode
Minimum Photocell Input
Minimum Display Brightness
Maximum Photocell Input
Maximum Display Brightness
Filter Time Constant
Automatic
Automatic
Default
Default
Default
Default
Default
Display
HSI Page
Power Up Page
Enabled
HSI
Battery
Show Battery Status
Automatic Power Off
When Using Battery
On Ground Only
GPS
Internal GPS Receiver
Disabled
RS-232
Input Format
Output Format
None
None
Exit Configuration Mode
Note 1: Set configuration values and units to match the values indicated in the appropriate
AFM and document settings in the space provided.
Note 2: If the aircraft has no AFM set the values as determined by the existing placards,
instrument bugs or instrument markings.
Note 3: Existing placards related to airspeed limitations must be retained.
Note 4: Setting can remain at default setting, not supported in this configuration.
This area intentionally blank
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5.10 Dual G5 with VHF Navigator
Figure 5-11 Dual G5 with VHF Navigator
This area intentionally blank
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5.10.1 Attitude Indicator Configuration
Config Page
Device Information
Config Option
Installation Type
Diagnostics/Data Log
Configuration Setting
Certified Instrument
Enabled
Attitude Configuration
Indicator Type
Pitch Display
Roll Display
Automatic Declutter
Normal
Normal
For Fixed Type Pointers G5 Config = Ground
or
For Movable Type Pointers G5 Config = Sky
Enabled
Air Data
Air Data Sensors
Vertical Speed Indicator
Enabled
(1)(2)
Airspeed
VNE
VNO
VSO
VS1
VFE
VA
VX
VY
VG
VR
VMC
VYSE
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
Magnetometer
Magnetometer
Orientation
Enabled
Connector Aft
Or
Connector Forward
Or
Connector Port
Or
Connector Starboard
Flight Controls
Autopilot Servos
Analog Autopilot Interface
None
None
Or
See Section 5.12 if a Third Party Autopilot is
interfaced
Backlight
Current Mode
Default Mode
Minimum Photocell Input
Minimum Display Brightness
Maximum Photocell Input
Maximum Display Brightness
Filter Time Constant
Automatic
Automatic
Default
Default
Default
Default
Default
Display
HSI Page
Power Up Page
Disabled
PFD
Battery
Show Battery Status
Automatic Power Off
When Using Battery
On Ground Only
GPS
Internal GPS Receiver
GPS Data Fields
Enabled
Show
Note: Configure Units prior to setting
airspeeds.
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Config Page
Navigation
Config Option
Navigation Data
Selected Course
VNAV Deviation Scale
Configuration Setting
Disabled
Note: If a third party autopilot interface is
configured ON, this configuration page is
set to ENABLED by default.
(4)
(4)
Units
Altitude
Distance
Airspeed
Ground Speed
Ground Track
Vertical Speed
Pressure
(1)(2)
(1)(2)
(1)(2)(3)
(1)(2)
Magnetic
(1)(2)
(1)(2)
RS-232
Input Format
Output Format
Garmin VHF NAV Radio
Garmin VHF NAV Radio
ARINC 429
Output 1
Output 2
Input 1
Input 2
Input 3
Input 4
None
None
None
None
None
None
Config Page
Device Information
Config Option
Installation Type
Diagnostics/Data Log
Configuration Setting
Certified Instrument
Enabled
Attitude Configuration
Automatic Declutter
Disabled
Backlight
Current Mode
Default Mode
Minimum Photocell Input
Minimum Display Brightness
Maximum Photocell Input
Maximum Display Brightness
Filter Time Constant
Automatic
Automatic
Default
Default
Default
Default
Default
Display
HSI Page
Power Up Page
Enabled
HSI
Battery
Show Battery Status
Automatic Power Off
When Using Battery
On Ground Only
GPS
Internal GPS Receiver
Disabled
RS-232
Input Format
Output Format
Garmin VHF NAV Radio
Garmin VHF NAV Radio
Exit Configuration Mode
5.10.2 G5 HSI Configuration
Exit Configuration Mode
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5.10.3 GNC 255 Configuration
Config Page
Sys Configuration
Config Option
RS 232 Serial Port
Configuration Setting
IO Mode = NMEA
Attitude Configuration
CDI Indicator
TYPE = Serial
Config Page
Sys Configuration
Config Option
RS 232 Serial Port
Configuration Setting
No Setting
Attitude Configuration
Indicator Type
TYPE = Serial
5.10.4 SL30 Configuration
Note 1: Set configuration values and units to match the values indicated in the appropriate
AFM and document settings in the space provided.
Note 2: If the aircraft has no AFM set the values as determined by the existing placards,
instrument bugs or instrument markings.
Note 3: Existing placards related to airspeed limitations must be retained.
Note 4: Setting can remain at default setting, not supported in this configuration.
This area intentionally blank
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5.11 Dual G5 with GPS/VHF Navigator
Figure 5-12 Dual G5 with GPS/VHF Navigator
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Figure 5-13 Dual G5 with GPS/VHF Navigator Notes
5.11.1 Attitude Indicator Configuration
Config Page
Device Information
Config Option
Installation Type
Diagnostics/Data Log
Configuration Setting
Certified Instrument
Enabled
Attitude Configuration
Indicator Type
Pitch Display
Roll Display
Automatic Declutter
Normal
Normal
For Fixed Type Pointers G5 Config = Ground
or
For Movable Type Pointers G5 Config = Sky
Enabled
Air Data
Air Data Sensors
Vertical Speed Indicator
Enabled
(1)(2)
Airspeed
VNE
VNO
VSO
VS1
VFE
VA
VX
VY
VG
VR
VMC
VYSE
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
(1)(2)(3)
Magnetometer
Orientation
Enabled
Connector Aft
Or
Connector Forward
Or
Connector Port
Or
Connector Starboard
Note: Configure Units prior to setting
airspeeds.
Magnetometer
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Config Page
Flight Controls
Config Option
Autopilot Servos
Analog Autopilot Interface
Configuration Setting
None
None
Or
See Section 5.12 if a Third Party Autopilot is
interfaced
Backlight
Current Mode
Default Mode
Minimum Photocell Input
Minimum Display Brightness
Maximum Photocell Input
Maximum Display Brightness
Filter Time Constant
Automatic
Automatic
Default
Default
Default
Default
Default
Display
HSI Page
Power Up Page
Disabled
PFD
Battery
Show Battery Status
Automatic Power Off
When Using Battery
On Ground Only
GPS
Internal GPS Receiver
GPS Data Fields
Disabled
Show
Navigation
Navigation Data
Selected Course
VNAV Deviation Scale
Disabled
Note: If a third party autopilot interface is
configured ON, this configuration page is
set to ENABLED by default.
(4)
(4)
Units
Altitude
Distance
Airspeed
Ground Speed
Ground Track
Vertical Speed
Pressure
(1)(2)
(1)(2)
(1)(2)(3)
(1)(2)
Magnetic
(1)(2)
(1)(2)
RS-232
Input Format
MapMx (WAAS Units)
AVIATION (Non WAAS Units)
None
Output Format
ARINC 429
Output 1
Output 2
Input 1
Input 2
Input 3
Input 4
EFIS / AIRDATA 1 (SDI 1)
(Only used with GTN 6XX / 7XX and GNS
4XX(W) / 5XX(W) and no Third Party Autopilot
is interfaced)
EFIS / AIRDATA 2 (SDI 1)
(Always used with GNS 480 and GTN 6XX /
7XX and GNS 4XX(W) / 5XX(W) when Third
Party Autopilot is interfaced)
None
Garmin GPS (SDI 1)
Garmin VOR/ILS (SDI 1)
None
None
Exit Configuration Mode
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5.11.2 HSI Configuration
Config Page
Device Information
Config Option
Installation Type
Diagnostics/Data Log
Configuration Setting
Certified Instrument
Enabled
Attitude Configuration
Automatic Declutter
Disabled
Backlight
Current Mode
Default Mode
Minimum Photocell Input
Minimum Display Brightness
Maximum Photocell Input
Maximum Display Brightness
Filter Time Constant
Automatic
Automatic
Default
Default
Default
Default
Default
Display
HSI Page
Power Up Page
Enabled
HSI
Battery
Show Battery Status
Automatic Power Off
When Using Battery
On Ground Only
GPS
Internal GPS Receiver
Disabled
RS-232
Input Format
MapMX (WAAS Units)
AVIATION (non WAAS Units)
None
Output Format
Exit Configuration Mode
5.11.3 GTN 650/750 Configuration
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 )
(Only used when Third Party
Autopilot is interfaced)
ARINC 429 Out (x)
(x represents any available ARINC
429 Port )
SDI
Configuration Setting
Speed = Low
Data = EFIS Format 2
Speed = Low
Data = GAD Format 1
(Only used when Third Party Autopilot is
interfaced)
Speed = Low
Data = GAMA Format 1
LNAV1
RS-232
RS-232 (x)
(x represents any available RS-232
Port )
Input = MapMX Format 2
Output = MapMX Format 2
Main Indicator (Analog) Configuration
CDI Key
Selected Course for GPS
Selected Course for VLOC
V-Flag State
Enabled
Allowed
Allowed
Normal
VOR/LOC/GS Configuration
Nav Radio
ARINC 429 Configuration
Enabled
Tx Speed = Low
SDI = VOR/ILS 1
Main System
Heading Source Input
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.
Altitude Source Input
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5.11.4 GNS 4XX(W) / 5XX(W) Configuration
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 )
(Only used when Third Party
Autopilot is interfaced)
OUT
Configuration Setting
Speed = Low
Data = EFIS / Airdata
Speed = Low
Data = Garmin GAD 42
(Only used when Third Party Autopilot is
interfaced)
VNAV
Speed = Low
Data = GAMA 429
ENABLED
MAIN RS232 CONFIG Page
RS-232 (x)
(x represents any available RS-232
Channel )
Input = OFF
Output = MapMX (WAAS )
AVIATION (Non WAAS)
VOR/LOC/GS ARINC 429 CONFIG Page
SPEED
SDI
RX = Low
TX = Low
VOR/ILS 1
Config Page
Config Option
Configuration Setting
GND Maint Serial Setup
CH (x)
(x represents any available Serial
Channel )
Output = MapMX
GND Maint ARINC 429 Setup
CH In (2)
(or any available 429 Port )
SEL = EFIS
SPEED = Low
SDI = SYS1
SEL = GAMA 429
SPEED = Low
SDI = SYS1
SEL = VOR / ILS
SPEED = Low
SDI = SYS1
5.11.5 GNS 480 Configuration
CH Out (1)
(or any available 429 Port )
CH Out (2)
(or any available 429 Port )
GND Maint Resolver Interface Setup
Resolver
Not Installed
GND Maint Miscellaneous Setup
CDI Select
Use
Note 1: Set configuration values and units to match the values indicated in the appropriate
AFM and document settings in the space provided.
Note 2: If the aircraft has no AFM set the values as determined by the existing placards,
instrument bugs or instrument markings.
Note 3: Existing placards related to airspeed limitations must be retained.
Note 4: Setting can remain at default setting, not supported in this configuration.
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5.12 GAD 29B Interface to Third-Party Autopilots
This section only applies to installations using a GAD 29B data converter and an interface to
one of the autopilots listed in Table 5-1. Specific configuration details are covered in the
following sections.
Table 5-1: Third-Party Autopilots
Autopilot Mfg
Century
Cessna
Garmin
Honeywell (Bendix /King)
S-TEC
Autopilot Model
Century 1C388*
Century 1C388M*
Century 1C388C*
Century 1C388MC*
Century 1C388-2*
Century 1C388-3*
Century 2000
Century 21
Century 31
Century 41
Century IV
* Radio Coupler P/N indicated and based on aircraft installation
could be interfaced in a Century I, II or III.
Cessna 300, 400 & 800 IFCS
Cessna 300B, 400B & 800B IFCS
GFC 600
Bendix King KAP 100
Bendix King KAP 140
Bendix King KAP 150
Bendix King KAP 200
Bendix King KFC 150
Bendix King KFC 200
Bendix King KFC 225
S-TEC System 20
S-TEC System 30
S-TEC System 40
S-TEC System 50
S-TEC System 55
S-TEC System 55X
S-TEC System 60
S-TEC System 65
This area intentionally blank
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5.12.1 GAD 29B Interface to Century Autopilots
Figure 5-14 GAD 29B Interface to Century Autopilots Sheet 1 of 2
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Figure 5-15 GAD 29B Interface to Century Autopilots Sheet 2 of 2
This area intentionally blank
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5.12.1.1
G5 Configuration Century Autopilots
Note: The Flight Controls Configuration shown below only needs to be set on the master G5.
In a single installation the master must be the G5 DG/HSI. In a dual installation the master is
the G5 Attitude indicator.
Config Page
Config Option
Flight Controls
Analog Autopilot
Interface
GPS Steering*
GPSS Scale Factor*
Configuration Setting
AP Model / Radio
G5 Config
Coupler P/N
1C388
Century 1C388
1C388-2
Century 1C388-2
1C388-3
Century 1C388-3
1C388C
Century 1C388C
1C388M
Century 1C388M
1C388MC
Century 1C388MC
Century 2000
Century 2000
Century 21
Century 21
Century 31
Century 31
Century 41
Century 41
Century IV (DC)
Century IV
Enabled
1.00
Interfacing Equipment
Configuration Information
Century A/P Config
As per the wiring interface in
Figure 5-14 & Figure 5-15
* GPS Steering and GPSS Scale Factor is configured the same for all listed Analog
Autopilot interfaces
---
---
This area intentionally blank
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5.12.2 GAD 29B Interface to Cessna Autopilots
Figure 5-16 GAD 29B Interface to Cessna Autopilots Sheet 1 of 2
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Figure 5-17 GAD 29B Interface to Cessna Autopilots Sheet 2 of 2
5.12.2.1 G5 Configuration Cessna Autopilots
Note: The Flight Controls Configuration shown below only needs to be set on the master G5.
In a single installation the master is the only G5 indicator installed. In a dual installation the
master is the G5 Attitude indicator.
Config
Page
Config Option
Configuration Setting
Flight
Controls
Analog Autopilot
Interface
AP Model
G5 Config
Cessna 300 IFCS
Cessna 300 (AC)
Cessna 400 & 800
Cessna 400 (AC)
IFCS
Cessna 300B
Cessna 300 (DC)
IFCS
Cessna 400B &
Cessna 400 (DC)
800B IFCS
Enabled
1.00
GPS Steering*
GPSS Scale
Factor*
Interfacing Equipment
Configuration Information
Cessna A/P Config
As per wiring interface in
Figure 5-16 & Figure 5-17
---
* GPS Steering and GPSS Scale Factor is configured the same for all listed Analog Autopilot interfaces
This area intentionally blank
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5.12.3 GAD 29B Interface to Garmin GFC 600 Autopilot
Figure 5-18 GAD 29B Interface to Garmin Autopilots
5.12.3.1 G5 Configuration GFC 600 Autopilots
Note: The Flight Controls Configuration shown below only needs to be set on the master G5.
In a single installation the master is the only G5 indicator installed. In a dual installation the
master is the G5 Attitude indicator.
Config
Page
Config Option
Flight
Controls
Analog Autopilot
Interface
GPS Steering*
GPSS Scale
Factor*
Configuration Setting
AP Model
GFC 600
Interfacing Equipment
Configuration Information
G5 Config
Bendix King KI
525 HSI
Enabled
1.00
GFC 600 A/P Config
Config Item – HSI/DG
Setting KI525
* GPS Steering and GPSS Scale Factor is configured the same for all listed Analog Autopilot interfaces
5.12.4 GAD 29B Interface to Garmin GFC 500 Autopilot
For information regarding interface of a GAD 29B to a GFC 500 autopilot, see GFC 500 AFCS
Installation Manual, 190-02291-00.
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5.12.4.1 G5 Configuration GFC 500 Autopilots
For configuration of a G5 when interfaced to a Garmin GFC 500 autopilot, see GFC 500 AFCS
Installation Manual, 190-02291-00.
5.12.5 GAD 29B Interface to Honeywell Autopilots
Figure 5-19 GAD 29B Interface to Honeywell Autopilots
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5.12.5.1 G5 Configuration Honeywell (Bendix King) Autopilots
Note: The Flight Controls Configuration shown below only needs to be set on the master G5.
In a single installation the master is the only G5 indicator installed. In a dual installation the
master is the G5 Attitude indicator.
Config Page
Config Option
Flight
Controls
Analog Autopilot Interface
GPS Steering*
GPSS Scale Factor*
Configuration Setting
AP Model
KAP 100
KAP 140
KAP 150
KAP 200
KFC 150
KFC 200
KFC 225 **
G5 Config
Bendix King KAP 100
Bendix King KAP 140
Bendix King KAP 150
Bendix King KAP 200
Bendix King KFC 150
Bendix King KFC 200
Bendix King KFC 225
Enabled
1.00
Interfacing Equipment
Configuration Information
KAP/KFC A/P Config
Must be configured to
operate with the KI-525
(KCS-55) heading system.
Must be configured to
operate with the KI-525
(KCS-55) heading system.
Must be configured for DC
analog heading
---
* GPS Steering and GPSS Scale Factor is configured the same for all listed Analog
Autopilot interfaces except KFC 225
** GPS Steering is not an available configuration for KFC 225
---
This area intentionally blank
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5.12.6 GAD 29B Interface to S-TEC Autopilots
Figure 5-20 GAD 29B Interface to S-TEC Autopilots
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5.12.6.1 G5 Configuration S-TEC Autopilots
Note: The Flight Controls Configuration shown below only needs to be set on the master G5.
In a single installation the master is the only G5 indicator installed. In a dual installation the
master is the G5 Attitude indicator.
Config
Page
Config Option
Flight
Controls
Analog Autopilot
Interface
GPS Steering*
GPSS Scale
Factor*
Configuration Setting
AP Model
System 20
G5 Config
S-TEC System
20
System 30
S-TEC System
30
System 40
S-TEC System
40
System 50
S-TEC System
50
System 55
S-TEC System
55
System 55X**
S-TEC System
55X
System 60
S-TEC System
60
System 65
S-TEC System
65
Enabled
1.00
Interfacing Equipment
Configuration Information
S-TEC A/P Config
Must be configured to operate with
the KI-525 (KCS-55) heading
system.
---
* GPS Steering and GPSS Scale Factor is configured the same for all listed Analog Autopilot interfaces except
System 55X
** GPS Steering is not an available configuration for System 55X
This area intentionally blank
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6
SYSTEM CONFIGURATION AND CHECKOUT PROCEDURES
6.1
Overview
This section contains instructions for configuration and checkout of the G5 Electronic Flight
Instrument, GMU11, and GAD 29/29B. The steps which are not applicable to a particular
installation may be skipped. A summary of the steps required for checkout of the G5 is as
follows:
•
Perform mounting, wiring, and power checks (see section 6.2)
•
Configure the G5 (see Section 6.3)
•
Perform post-installation checkout procedures (see Section 6.3)
•
Perform documentation checks (see section 6.4)
NOTE
Throughout the next sections, many screenshots and examples are used to illustrate the
software loading and configuration and checkout process. Changes may occur which
result in the examples being out of date.
6.2
Mounting, Wiring, and Power Checks
Verify all wire harnesses are properly secured and shields are connected to the shield blocks
of the connectors. Check the movement of the flight and engine controls to verify there is no
interference. Prior to powering up the G5 and supporting equipment, the wire harnesses must
be checked for proper connections to the aircraft systems and other avionics equipment. Point
to point continuity must be checked on all wiring to expose any faults such as shorting to
ground. Any faults or discrepancies must be corrected before proceeding.
After accomplishing a continuity check, perform power and ground checks. Remove power
from the aircraft upon completion of the wire harness checkout.
The G5 and supporting equipment can be installed after completion of the continuity and
power checks.
6.3
Post-Installation Checkout Procedures
The following procedures will verify the proper operation of the G5 and its intended function as
an attitude indicator or DG/HSI. The G5 can be installed in several different configurations
that affect the following testing. If a section of testing is not supported by the installed
configuration disregard that testing. It is assumed that the person performing these checks is
familiar with the aircraft, has a working knowledge of typical avionics systems, and has
experience using the test equipment defined in this section.
NOTE
For G5 operational instructions, see 190-01112-12, Pilot’s Guide, Garmin G5
Electronic Flight Instrument, Part 23 AML STC.
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NOTE
Some procedures in this section require that the GPS receiver is receiving sufficient
satellite signal to compute a present position. This requires outdoor line-of-site to GPS
satellite signals or a GPS indoor repeater.
NOTE
As these procedures involve engine run-up and moving the aircraft, it is recommended
that the installer read this entire section before beginning the checkout procedure.
NOTE
All test equipment should have current calibration records.
6.3.1 Recommended Test Equipment
The following test equipment is recommended to conduct and complete all post installation
checkout procedures in this section:
•
•
•
•
•
•
Pitot/static ramp tester
Digital Multi-Meter (DMM)
Ground power unit capable of supplying 14/28 Vdc power to the aircraft systems and
avionics
Outdoor line-of-sight to GPS satellite signals or GPS indoor repeater
Digital Level or equivalent
VHF NAV Test Set
6.3.2 Configuration Mode
All of the configuration and calibration procedures in this section are performed in
configuration mode. To enter configuration mode, hold down the knob while powering on the
G5. Configuration selections are made by rotating and pressing the knob on the face of the G5
as necessary to select the correct configurations.
6.3.3 Software Loader Card Creation
The software image is an executable self-extracting file which builds the correct file structure
onto a microSD card for use loading software to all installed G5’s. To obtain the current
software image is an executable self-extracting file follow the procedures outlined below.
NOTE
If the G5 units report the same software P/N and versions as indicated on the Aviation
Product/General Aviation/Indicators/G5 page, it is not required to complete this
section.
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.
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2.
Download the self-extracting update file onto your hard drive.
3.
Insert a FAT32-formatted micro SD 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 SD card you wish to
use for the update. When the transfer is complete, safely eject the SD card.
6.3.4 Initial Power On
1.
Apply power to the G5 unit(s).
2.
On the G5 attitude indicator, verify the attitude is displayed and there are no invalid
parameters (no red-X shown).
3.
On the G5 HSI/DG , verify heading information is displayed and there are no invalid
parameters (no red-X shown).
NOTE
On power-up, “Magnetometer not calibrated.” may be displayed on the G5 #1 if a
GMU11 is installed. This will cause the compass card on the HSI/DG to display GPS
track if installed as an HSI and nothing if installed as a DG. Magnetometer calibration
is completed later in section 6.3.7.4.
4.
Continue to Section 6.3.5.
6.3.5 SOFTWARE LOADING PROCEDURE
G5 software loading can be performed in either normal or configuration mode.
NOTE
If the G5 unit reports the same software P/N and version as indicated on the Aviation
Product/General Aviation/Indicators/G5 page, it is not required to complete this
section.
NOTE
If two G5’s are installed, this procedure must be completed on both G5’s and can be
done concurrently. 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 a properly formatted microSD™ card into the
microSD™ card slot.
NOTE
It is also acceptable to insert the microSD™ card before powering on the unit.
2.
A software update pop-up will appear on the screen. Select OK to begin the update.
NOTE
The software update pop-up will only be displayed if the version of software to be
loaded is newer than the version currently on the unit.
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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.
6.3.6 CONFIGURATION PAGES
6.3.6.1
Configuration Pages Summary
When in configuration mode the G5 displays the following configurations pages:
• Device Information – used to display LRU (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.
• Airspeed – allows for configuration of the reference speeds.
• Magnetometer – allows configuration of magnetometer and magnetometer positioning.
• Flight Controls – used to configure the system for autopilot servos 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.
6.3.6.2
G5 configuration
Reference Section 5 to select the corresponding equipment configuration that is installed in the
aircraft. The configuration settings are provided in the appropriate section for each installation
possibility. See Section 6.4.1 for information about recording the configuration settings to keep
in the aircraft records for future reference.
•
•
•
•
•
•
•
G5 (Attitude Indicator) with External GPS Antenna – Section 5.3
G5 (Attitude Indicator) with GPS Position Input (RS-232)
– Section 5.4
G5 (Attitude Indicator) and GMU11with GPS Position Input
(RS-232) – Section 5.5
G5 (Attitude Indicator or DG), GMU 11 and GPS Antenna – Section 5.6
G5 (HSI) with VHF Navigator Section - 5.7
G5 (HSI) with GPS/VHF Navigator Section - 5.8
Dual G5 without Navigator Section - 5.9
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•
•
•
Dual G5 with VHF Navigator - 5.10
Dual G5 with GPS/VHF Navigator Section - 5.11
G5 Interface to Third Party Autopilots Section - 5.12
6.3.7 G5 POST-INSTALLATION CALIBRATION PROCEDURES
After mechanical and electrical installation of the G5 has been completed, prior to operation, a
set of post-installation calibration procedures must be carried out. Table 6-1 describes the
required and optional calibration procedures.
Table 6-1: Post-Installation Calibration Procedure Summary
Calibration
Procedure
A
Procedure
Description
Level aircraft
Procedure Name
Pitch/Roll Offset
Compensation
Installations
Requiring
Procedure
Procedure A is
required for all
installations
B
Engine Run-Up
Vibration Test
Validate vibration
characteristics of
installation
Procedure B is
required for all
installations
C
Air Data Static
Pressure Calibration
Altitude Calibration
Procedure C is only
required if Section
6.3.8.2 results for the
G5 fall outside the
tolerances of the
Part 43 Appendix E
tests.
D
GMU 11
Magnetometer
Calibration
Magnetometer
Calibration
Procedure D is only
required if a GMU 11
was installed
This area intentionally blank
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6.3.7.1
CALIBRATION PROCEDURE A: PITCH/ROLL OFFSET
COMPENSATION
NOTE
The G5(s) must be installed within the tolerances shown in Figure 4-4 and Figure 4-5.
NOTE
If two G5’s are installed, this procedure must be done on both and can be done
concurrently.
See Section 6.3.7.1.1 for example of this calibration procedure.
Using the following procedure, complete these equations.
1.
2.
*Consult the aircraft’s maintenance manual and locate the longitudinal (ROLL) and
lateral (PITCH) leveling points.
Using a digital level, document the Aircraft Roll and Pitch offsets from these leveling
points as the aircraft sits on the landing gear. (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.
3.
4.
5.
Select the Attitude Configuration Page.
Select Calibrate Pitch/Roll.
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.
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.
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6.3.7.1.1 Attitude Calibration Example
In the Figure 6-1, 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 6-2 for the completed equations.
Figure 6-1, Attitude Calibration Example
Figure 6-2, Example of Calibration Equations
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6.3.7.2
CALIBRATION PROCEDURE B: ENGINE RUN-UP VIBRATION
TEST
NOTE
Calibration Procedure B is required for all installations to validate the vibration
characteristics of the installation.
NOTE
This section of the Calibration Procedure can be run in conjunction with the compass
rose swing (Section 6.3.7.4.1).
NOTE
If two G5’s are installed, this procedure must be done on both and can be done
concurrently.
Conduct the Engine Run-Up Vibration Test. The test is intended to help discover mounting
issues and does not account for all possible vibration profiles that may be encountered during
normal aircraft operation.
1.
Select the Attitude configuration page.
2.
Select Vibration Test.
3.
Ensure the aircraft complies with all on-screen instructions, then select Start.
4.
Gradually increase engine power from idle to full power and back to idle in 1-2
minutes. A screen will be displayed showing the test in progress.
5.
After the gradual increase and decrease in aircraft power verify for passing or failing
results.
a. If the green check mark remains during the engine power sequence, this
indicates Passing results, select Done. This checkout is complete.
i. Exit configuration mode.
b. Failing results will be indicated by a red "X" as shown in Figure 6-3 below.
Select Done when the test has been completed and follow the instructions in
Step 6 below.
This area intentionally blank
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Figure 6-3 Engine Vibration Test Failure Indication
6.
If failures are indicated, repeat the test. If failures persist, the installation is unreliable
until the source of the vibration problem is identified and remedied. Record the out of
range limit values for future reference.
The following are potential causes for failures of the engine run-up test:
a. Excessive flexing of the G5 mechanical mounting with respect to airframe
b. Vibration or motion of the G5 caused by neighboring equipment and/or supports.
c. Mounting of the G5 in a location that is subject to severe vibrations (e.g. close to an
engine mount).
d. Instrument panel shock mounts worn, broken, or permit excessive movement.
e. Mounting screws and other hardware for G5 not firmly attached.
f. G5 connector not firmly attached to unit.
g. Cabling leading to the G5 not firmly secured to a supporting structure.
h. An engine/propeller combination that is significantly out of balance.
NOTE
In some aircraft, attempting the engine run-up test on a day with very strong and/or
gusty winds may cause the test to occasionally fail. However, a failure during windy
conditions cannot not be taken as evidence that the test would pass in calm conditions;
an actual pass is required before the installation can be considered adequate.
6.3.7.3
CALIBRATION PROCEDURE C: AIR DATA STATIC PRESSURE
CALIBRATION
NOTE
Procedure C is only required if Section 6.3.8.2 results for the G5 fall outside the
tolerances of the Part 43 Appendix E tests.
NOTE
If two G5’s are installed, this procedure must be done on both and can be done
concurrently.
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The Air Data configuration page has a selection for static pressure calibration. This procedure
is used to perform an altimeter 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 recalibrate 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.
Prior to running the calibration procedure below perform a static system leak check in
accordance with 14 CFR Part 43 Appendix E.
2.
Select the Air Data configuration page.
3.
Select Calibrate Static Pressure.
4.
Ensure all on-screen instructions have been complied with, then press Start.
5.
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.
6.
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.
7.
Select Done when the static pressure calibration is successfully completed.
8.
Exit configuration mode.
6.3.7.4
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. Refer to APPENDIX A for details on ID strapping.
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.
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NOTE
The calibration procedure in Section 6.3.7.1 must be completed prior to performing
this procedure.
NOTE
A magnetometer calibration failure is indicated by a “Magnetometer not Calibrated”
message on the G5 on power up. In the event of a failure, verify that the installation
passes the magnetometer interference test in Section 6.3.8.3. If necessary, move the
aircraft to a different location and attempt the magnetic calibration again.
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
11.
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.
If the G5 installation being calibrated does not utilize a GPS input, go to the “GPS”
page group and “Enable” the Internal GPS Receiver.
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.
On the final page, select “Start” to begin the calibration.
The G5 display advises the operator when to turn the aircraft, when to stop, and when
to turn again.
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.
12. The G5 instructs the operator to dwell at multiple headings around a complete circle.
13. Repeat the turn-and-stop process until the G5 advises that a successful calibration is
complete and “Calibration: Success” is displayed on the G5.
14. Select “Done” on the G5 to conclude this procedure
15. If the Internal GPS receiver was “Enabled” above for G5 installations that do not utilize
a GPS input “Disable” the Internal GPS receiver before exiting configuration mode.
16. Exit configuration mode.
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6.3.7.4.1 Compass Swing
After the Magnetic Calibration Procedure is 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 6-2. 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 6-2.
4. Calculate the heading errors by subtracting the displayed (B) value from the actual (A)
value for each of the headings in Table 6-2.
Table 6-2: 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 +/-10° from the surveyed heading, the
installation is acceptable and no further work is required to correct the GMU 11
installation. Proceed to section 6.3.8.3.
6. If a Heading Error (A-B) is greater than +/- 10°, 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.
7. 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.
8. After physically correcting the GMU 11 installation, repeat the procedures in Section
6.3.7.4 and this section.
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6.3.8 G5 Post Installation Checks
6.3.8.1
Pitot Static System Leak Check
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.
6.3.8.2
Altimeter System Check
For aircraft that are IFR certified, perform an altimeter system test of the G5 in accordance
with 14 CFR Part 43 Appendix E.
6.3.8.3
Magnetometer Interference Check
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. Refer to APPENDIX A for details on ID strapping.
NOTE
All selections made in configuration mode in this section are made on the G5 ID strapped as
#1. Refer to APPENDIX A for details on ID strapping.
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.
This sequence is the same sequence developed for the magnetometer interference
survey in APPENDIX C.
4. Select “Start” to begin the test procedure.
5. The operator should carry out the actions called for in the prepared test sequence.
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NOTE
It is important that all actions are carried out in the order and at the precise elapsed
time as specified in the prepared test sequence.
6. After the “Begin test sequence” appears, wait approximately five seconds and perform
each of the actions listed in the test sequence table. Refer to Section C.3 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.
6.3.8.4
Initial Power On Checks
1. Apply power to the aircraft and aircraft systems and allow the aircraft systems to
initialize.
2. 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
3. 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.
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o
•
•
•
6.3.8.5
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
Rotating compass rose.
GPS Position Check (Installations using an External Antenna
interfaced to the G5)
This test must be conducted outside, as the use of a GPS repeater inside a hangar may result in
a failed test.
1. Apply power to the aircraft and aircraft systems and allow the aircraft systems to
initialize and the G5(s) to acquire sufficient satellites for a GPS solution.
2. Enter configuration mode on the G5 Attitude indicator and the G5 HSI if the optional
GPS antenna is interfaced, and navigate to the GPS Configuration Page.
3. Ensure a valid GPS position fix is obtained by monitoring the GPS status. The
following status indications are valid fixes for this test.
•
3D GPS
•
3D DIFFERENTIAL
6.3.8.6
GPS Position Check (Installations using a GPS Navigator
interfaced to the G5)
This test must be conducted outside, as the use of a GPS repeater inside a hangar may result in
a failed test.
1. Apply power to the aircraft and aircraft systems and allow the aircraft systems to
initialize and the GPS Navigator to acquire sufficient satellites for a GPS solution.
2. On the G5 Attitude display, verify the following;
•
•
Ground Track display (if not interfaced to a GMU 11)
Ground speed field
3. On the G5 HSI display, verify the following;
•
•
•
Ground Track display (if not interfaced to a GMU 11, indicated by magenta
numbers indicating GPS ground track.
Ground speed field
Current track bug
This area intentionally blank
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6.3.8.7
VOR/LOC/GS Check
This test is only performed for installations that have an HSI installed and interfaced to a VHF
navigation source.
Check the VOR, ILS, and Glideslope functions with ramp test equipment. Operate the
equipment according to the test equipment manufacturer’s instructions. Adjust the RF signal
to a level adequate to perform the test. Select the appropriate HSI source as required by the
VHF navigation source interfaced to the G5 HSI.
NOTE
The HSI does not show a course deviation bar unless a valid VHF navigation frequency
is tuned.
6.3.8.7.1 VOR
1. Apply power to the aircraft and aircraft systems and allow the aircraft systems to
initialize.
2. Tune the VHF NAV to the NAV/COM Test Set frequency for VOR operation.
3. On the G5 HSI set the CDI course to 360 degrees.
4. On the NAV ramp tester simulate a centered VOR needle presentation.
5. Verify the G5 HSI CDI displays a centered deviation bar for VOR.
6. On the NAV ramp tester simulate 355 degrees.
7. Verify the G5 CDI deviation bar is one dot left.
8. On the NAV ramp tester simulate 350 degrees.
9. Verify the CDI deviation bar is two dots left.
10. On the NAV ramp tester simulate 340 degrees.
11. Verify the G5 HSI CDI deviation bar is full scale to the left.
12. On NAV ramp tester simulate 005 degrees.
13. Verify the G5 HSI CDI deviation bar is one dot right.
14. On the NAV ramp tester simulate 010 degrees.
15. Verify the G5 HSI CDI deviation bar is two dots right.
16. On the NAV ramp tester simulate 020 degrees.
17. Verify the G5 HSI CDI deviation bar is full scale to the right.
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6.3.8.7.2 LOC/GS
1. Tune the VHF NAV to the NAV/COM Test Set frequency for LOC/GS operation.
2. On the NAV ramp tester simulate centered LOC and GS needles presentation.
3. Verify the G5 HSI CDI displays centered deviation for both LOC and GS.
4. On the NAV ramp tester simulate one dot left for LOC and one dot down for GS.
5. Verify G5 HSI CDI deviation bar is one dot left and the GS vertical deviation indicates
one dot down.
6. On the NAV ramp tester simulate two dots left for LOC and two dots down for GS.
7. Verify G5 HSI CDI displays two dots left and the GS vertical deviation indicates two
dots down.
8. On the NAV ramp tester simulate full scale left for LOC and full scale down for GS.
9. Verify G5 HSI CDI deviation bar is full scale left and the GS vertical deviation
indicates full scale down.
10. On the NAV ramp tester simulate one dot right for LOC and one dot up for GS.
11. Verify G5 HSI CDI deviation bar is one dot right and the GS vertical deviation
indicates one dot up.
12. On the NAV ramp tester simulate two dots right for LOC and two dots up for GS.
13. Verify G5 HSI CDI displays two dots right and the GS vertical deviation indicates two
dots up.
14. On the NAV ramp tester simulate full scale right for LOC and full scale up for GS.
15. Verify G5 HSI CDI deviation bar is full scale right and the GS vertical deviation
indicates full scale up.
6.3.8.8
GPS Navigation Interface Check
This test is only performed for installations that have an HSI installed and interfaced to a GPS
navigation source.
Conduct this test with the aircraft positioned where it can receive GPS signal.
1. Apply power to the aircraft and aircraft systems and allow the aircraft systems to
initialize and the GPS navigator to acquire sufficient satellites for the GPS solution 3D
Diff Nav.
2. Enter a simple flight plan that contains a GPS LPV approach and activate the approach.
3. On the G5 Attitude indicator, verify the following;
•
•
a lateral deviation indicator is displayed directly above the slip skid indicator and
a deviation pointer magenta in color.
A vertical deviation indicator to the right of the aircraft symbol.
4. On the G5 HSI verify the following:
•
•
A vertical deviation indicator to the right of the rotating compass rose.
GPS LPV displayed in magenta located in the top center of the rotating compass
rose.
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•
•
•
6.3.8.9
A lateral deviation indicator displayed in magenta.
A to/From indicator displayed in magenta.
A cyan bearing pointer. (Bearing Pointer may need to be activated on the HSI
Menu)
GPS Receiver COM Interference Check
This test must be conducted outside, as the use of a GPS repeater inside a hangar may result in
a failed test.
1. Apply power to the aircraft and aircraft systems and allow the aircraft systems to
initialize and the G5(s) or GPS navigator (if installed) to acquire sufficient satellites for
a GPS solution.
NOTE
For G5’s interfaced to a GPS navigator for position source access to the G5(s)
configuration page is not necessary. Monitoring the G5 Attitude and/or G5 HSI for a
loss of GPS information or amber LOI on the HSI is sufficient.
For G5’s interfaced to an external GPS antenna:
2. Enter configuration mode on the G5 Attitude indicator and the G5 HSI if the optional
GPS antenna is interfaced, and navigate to the GPS Configuration Page.
3. Ensure a valid GPS position fix is obtained by monitoring the GPS status. The
following status indications are valid fixes for this test.
•
3D GPS
•
3D DIFFERENTIAL
4. Select 121.150 MHz on the COM transceiver.
5. Transmit for a period of 30 seconds while monitoring the GPS status.
6. During the transmit period,
•
On G5(s) with a direct GPS antenna connected, verify that the GPS status does
not lose a valid GPS position fix.
•
On G5(s) interfaced to a GPS navigator for position source monitor the G5
Attitude indicator and/or G5 HSI for a loss of GPS information (ground speed
information) or amber LOI on the HSI.
7. Repeat steps 2 through 4 for the following frequencies:
•
121.175 MHz
•
121.200 MHz
•
131.250 MHz
•
131.275 MHz
•
131.300 MHz
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8. Repeat steps 2 through 5 for all other installed COM transceivers (if applicable).
9.
If an installed COM supports 8.33 MHz channel spacing, increase the transmit period
to 35 seconds and repeat steps 3 through 5 for the following frequencies:
•
121.185 MHz
•
121.190 MHz
•
130.285 MHz
•
131.290 MHz
10. Repeat step 7 for all other installed COM transceivers supporting 8.33 MHz channel
spacing (if applicable).
6.3.9 Electromagnetic Compatibility (EMC) Check
An EMC check must be conducted once the G5(s) and supporting equipment is installed and
all interfaces to external equipment are verified to be correctly working. The EMC check
makes sure the equipment is not producing unacceptable interference to the other avionics
systems, and other avionics systems are not producing unacceptable interference to the G5.
An example EMC Source/Victim matrix is shown in Figure 6-4.
1. Enter equipment installed in the aircraft into the Source row and Victim column of the
fillable form.
2. Apply power to all avionics systems except the equipment installed under this STC.
3. Make sure all existing avionics systems are properly functioning.
4. Apply power to the G5.
5. Remove power from all other avionics systems.
6. Apply power and/or operate the systems listed on the fillable form, one system at a
time. Make sure to pull/push circuit breakers or turn on/off large loads, e.g. heaters,
cycling flaps (if electrical) etc.
7. Make sure the G5 properly functions.
a. When the VHF COM is operating as a source, transmit on low/med/high
unused frequencies.
8. Make sure each radio properly functions.
a. For each VHF COM radio, monitor one local frequency, one remote (far field)
frequency, and one unused frequency.
b. Make sure there are no unintended squelch breaks or audio tones interfere with
communications.
c. For each VHF NAV radio, monitor one local frequency, one remote (far field)
frequency, and one unused frequency.
d. Make sure there are no guidance errors.
e. Make sure there are no audio tones that interfere with the station ID.
f. For each GPS Navigator, enter a simple flight plan and display as appropriate.
i.e. Navigator Display, G5, HSI, CDI etc., if installed.
g. Make sure there are no guidance errors.
9. Make sure all other avionics properly function.
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SOURCE
<add equipment here>
<add equipment here>
GTX 3X5
Audio Panel
Transponder
TAS/TCAS
Radar Altimeter
Hyd System
Eng Deicing
Gov RPM Incr / Decr
Ldg Lts
Anti Coll Lt
Pos Lt
Generator
Pulse Light
Pitot Heat
Fuel Valve
Engine Relight
Communication Radio(s)
Navigation Radio(s)
Autopilot / SAS
Power Plant Instruments
OAT Indicator
Clock
Magnetic Compass
GAD 29/29B (If installed)
GMU 11 (If installed)
G5 #1
G5 #2 (If installed)
VICTIM
G5 #1
G5 #2
(If installed)
GMU 11
(If installed)
GAD 29/29B
(If installed)
Magnetic
Compass
Clock
OAT Indicator
Power Plant
Instruments
Autopilot / SAS
Navigation
Radio(s)
Communication
Radio(s)
Engine Relight
Fuel Valve
Pitot Heat
Pulse Light
Generator
Pos Lt
Anti Coll Lt
Ldg Lts
Gov RPM Incr /
Decr
Eng Deicing
Hyd System
Radar Altimeter
TAS/TCAS
Transponder
Audio Panel
GTX 3X5
<add
equipment
here>
<add
equipment
here>
Figure 6-4 Example EMC Source/Victim Matrix
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6.3.10 Vacuum System Pressure Setting
If a vacuum instrument was removed by the installation of the G5 Electronic Flight Instrument
and there are other instruments using the vacuum system, follow the aircraft manufacturers
procedure to set instrument vacuum system pressure.
6.3.11 Third Party Autopilot Interface Tests
The G5 System can interface with various autopilots. Before proceeding with the autopilot
interface tests, verify that the G5 has been configured for the installed autopilot, if applicable,
as defined in Section 5.12. Only those interfaces which are directly affected by the G5 AML
STC are covered by this manual; if any other autopilot modifications were performed they are
outside the scope of this STC and must be checked in accordance with the autopilot installation
manual.
WARNING
It is important that the G5 System be properly configured in order to prevent signals
from the G5 System from damaging the autopilot computer. Refer to section 5.12.
NOTE
The following procedures are general in nature and it may be necessary to reference
the autopilot manufacturers testing instructions to allow the autopilot to be tested
properly.
6.3.11.1 Heading and Course Error Tests
6.3.11.1.1 Heading
1. Apply power to the aircraft and aircraft systems and allow the aircraft systems to
initialize.
2. On the G5 HSI, set the heading bug to the current aircraft heading.
3. Engage the autopilot in heading mode.
4. Adjust the heading bug to the left of the aircraft heading.
5. Verify that the flight controls move toward the left.
6. On the G5 HSI, adjust the heading bug to the right of the aircraft heading.
7. Verify the flight controls move toward the right.
8. Center the heading bug at the aircraft heading.
9. Disengage the autopilot.
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6.3.11.1.2 VOR Course
1. Apply power to the aircraft and aircraft systems and allow the aircraft systems to
initialize.
2. Tune the VHF NAV to the NAV/COM Test Set frequency for VOR operation.
3. Set the Course pointer on the G5 HSI 15 degrees to the left of aircraft heading and
ensure that the G5 HSI CDI is displaying VOR navigation information.
4. Simulate a VOR signal with a “TO” course equal to the aircraft heading.
5. Slowly adjust the course pointer on the G5 HSI CDI toward the aircraft heading until
VOR captures.
6. Center G5 HSI CDI course pointer on the aircraft heading.
7. Engage the autopilot in NAV mode.
8. Adjust the NAV ramp tester course and the G5 HSI CDI course pointer 20 degrees to
the left of current aircraft heading.
9. Verify that the flight controls move toward the left.
10. Adjust NAV ramp tester course to aircraft heading.
11. Adjust the NAV ramp tester course and the G5 HSI CDI course pointer 20 degrees to
the right of current aircraft heading.
12. Verify that the flight controls move toward the right.
13. Adjust the NAV ramp tester course to aircraft heading.
14. Disengage the autopilot.
6.3.11.1.3 LOC
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
11.
12.
Tune the VHF NAV to the NAV/COM Test Set frequency for LOC operation.
On the NAV ramp tester simulate centered LOC needle presentation.
Set the Course pointer on the G5 HSI to the current aircraft heading.
Verify the G5 HSI CDI displays centered deviation for LOC.
On the NAV ramp tester simulate 0.093 DDM Left LOC.
Verify G5 HSI CDI deviation bar is one dot left.
Verify that the flight controls turn to the left.
On the NAV ramp tester simulate 0.093 DDM Right LOC.
Verify G5 HSI CDI displays one dot right.
Verify that the flight controls turn to the right.
On the NAV ramp tester simulate centered LOC needle presentation.
Disengage the autopilot.
6.3.11.1.4 GPSS Course
This test is only performed for installations that are interfaced to a GPS navigation source and
the interfaced autopilot did not previously have a GPSS function. Conduct this test with the
aircraft positioned where it can receive GPS signal.
1. On the GPS navigator, enter a simple Direct-To flight plan with a waypoint that is on
the current aircraft heading and select the G5 HSI CDI to display GPS. If the navigator
has the capability to enter user waypoints, a user waypoint can be entered to facilitate
this test. It is suggested that the waypoint be within 5 miles of the current aircraft
position for best results.
2. On the G5 Attitude display, press the multifunction knob to display the G5 attitude
menu, highlight GPSS and press the multifunction knob to select GPSS.
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3. Verify the following;
On the G5 Attitude (if Installed)
• GPSS field in the menu has a green bar at the bottom indicating GPSS is
selected.
• The heading bug is a hollow cyan bug.
• An advisory display is presented in the upper left hand corner that shows a
normal heading bug crossed by a white X and GPSS in white next to the bug.
On the G5 HSI
• GPSS field in the menu has a green bar at the bottom indicating GPSS is
selected.
• The heading bug is a hollow cyan bug.
• An advisory display is presented in the upper left hand corner that shows a
normal heading bug crossed by a white X and GPSS in white next to the bug.
4. On the navigator select OBS to enter GPS OBS mode.
5. Set the OBS course for the current aircraft heading. (it is assumed the waypoint is on
the current aircraft heading)
6. Engage the autopilot in HDG mode.
7. Adjust the OBS course 20 degrees to the left of current aircraft heading.
8. Verify that the flight controls move toward the left.
9. Adjust the OBS course 20 degrees to the right of current aircraft heading.
10. Verify that the flight controls move toward the right.
11. Adjust the OBS course to aircraft heading.
12. Disengage the autopilot.
6.4
Documentation Checks
6.4.1 Instructions for Continued Airworthiness (ICA)
Ensure the appropriate aircraft information is recorded in Garmin G5 Electronic Flight
Instrument Part 23 AML STC Maintenance Manual including Instructions for Continued
Airworthiness, P/N 190-01112-11, Appendix A, Appendix B and Appendix C and is retained
with the aircraft permanent records.
Insert the completed Appendices of the STC MM/ICA into the aircraft permanent records.
6.4.2 Weight and balance
Addition of the G5(s) and supporting equipment must allow the empty weight center of gravity
(CG) to fall within the aircraft’s acceptable range (refer to the aircraft’s POH or AFM). Perform
a weight and balance computation and update the aircraft records.
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6.4.3 AFMS Autopilot Information Record
Ensure that the Airplane Flight Manual Supplement (AFMS) 190-01112-13 is completed and
inserted in the AFM or POH.
1. Fill in the required airplane information on the AFMS cover sheet.
2. In AFMS Section 4.4 (Autopilot Operations with the G5 HSI), fill in all applicable
checkboxes corresponding to the interfaces to the autopilot. More than one box may
be checked, depending upon the installation.
The G5 Electronic Flight Instrument installation in this aircraft provides the following
autopilot functions (check the appropriate boxes):
􀂅 This installation does not interface with the autopilot (basic wing leveling autopilot
or no autopilot is installed in the aircraft).
􀂅 A GAD 29B is installed in this aircraft.
􀂅 Course / NAV Selection coupling to the autopilot.
􀂅 Heading Bug coupling capability to the autopilot.
􀂅 Roll Steering (GPSS) emulated via heading mode.
OR
􀂅 Roll Steering capable autopilot (GPSS menu function for emulation not
applicable).
3. Insert the completed AFMS into the AFM or POH.
This area intentionally blank
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APPENDIX A CONNECTOR INFORMATION
A.1 G5
A.1.1 J51
Figure 6-5 J51 on the G5
J51 Pin Descriptions
Pin
1
2
3
4
5
6
7
8
9
Pin Name
CAN-H
CAN-L
UNIT ID
RS-232 RX 1
RS-232 TX 1
SIGNAL GROUND
AIRCRAFT POWER 1
AIRCRAFT POWER 2
POWER GROUND
I/O
I/O
I/O
In
In
Out
-In
In
--
A.1.2 Aircraft Power
The G5 operates using power from one 14 / 28 VDC input. Pin 8 (AIRCRAFT POWER 2) is not used as
a part of this STC.
NOTE
AIRCRAFT POWER 2 is for connecting to an alternate power source, such as on aircraft with
two electrical buses.
A.1.3 RS-232
The G5 has one RS-232 channel that may be used to interface to an existing GPS navigator or GPS
source to receive GPS data for attitude aiding. Also, the G5 RS-232 port can be used to receive
VHF and GPS navigation information.
For specific configuration settings for RS-232 refer to Section 6.3.6.2.
If an existing connection is made to the RS-232 port, the G5 connection can be spliced into the existing
wiring at the connector. For specific wiring information refer to Section 5.
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A.1.4 CAN
The G5 CAN bus conforms to the BOSCH standard for Controller Area Network (CAN) 2.0-B and ISO
11989. See Section 3.4.5.2 for details. The G5 can utilize CAN BUS connections when specified by a
specific equipment configuration to allow heading information from the GMU 11, communication of
navigation data from the GAD 29/29B and communication between the G5 Attitude or Turn Coordinator
and the G5 HSI.
For specific wiring information refer to Section 5.
A.1.5 Unit ID
The G5 detects its assigned unit type at startup by checking the UNIT ID pin. This pin can be
strapped into the following configurations. A maximum of two G5 units may be used in a single
installation.
Unit ID Configurations
Unit ID
Comment
Pin 3 No Connection
Ground pin 3
G5 #1
G5 #2
A.2 GMU 11
A.2.1 J111
Figure 6-6 J111 on the GMU 11
J111 Pin Descriptions
Pin
1
2
3
4
5
6
7
8
9
Pin Name
CAN-H
CAN-L
UNIT ID
RS-232 RX 1
RS-232 TX 1
SIGNAL GROUND
AIRCRAFT POWER 1
AIRCRAFT POWER 2
POWER GROUND
I/O
I/O
I/O
In
In
Out
-In
In
--
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A.2.2 Aircraft Power
The GMU 11 operates using power from one 14 / 28 VDC input. Pin 8 (AIRCRAFT POWER 2) is not
used as a part of this STC.
NOTE
AIRCRAFT POWER 2 is for connecting to an alternate power source, such as on aircraft with
two electrical buses.
A.2.3 RS-232
RS-232 is not used or approved for use by this STC.
A.2.4 CAN Bus
The GMU 11 CAN bus conforms to the BOSCH standard for Controller Area Network (CAN) 2.0-B
and ISO 11898. See Section 3.4.5.2 for details. The CAN bus connection on the GMU 11 is used to
connect the GMU 11 to one or two G5s and a GAD 29/29B.
For specific wiring information refer to Section 5.
A.2.5 Unit ID
The GMU 11 detects its assigned unit type at startup by checking the UNIT ID pin. Only one GMU 11
may be installed by this STC. Ensure pin 3 is not connected to allow the GMU 11 to properly detect its
assigned unit type.
Unit ID Configurations
Unit ID
GMU 11 #1
GMU 11 #2 (Not Used)
Comment
Pin 3 No Connection
Ground pin 3 (Not Used)
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A.3 GAD 29/29B
A.3.1 J291
Figure 6-7 J291 on the GAD 29/29B
J291 Pin Descriptions
Pin
1
2
3
4
5
6
7
8
9
Pin Name
CAN-H
CAN-L
RESERVED
RESERVED
RESERVED
GROUND
AIRCRAFT POWER 1
AIRCRAFT POWER 2
GROUND
I/O
I/O
I/O
----In
In
--
A.3.2 J292
Figure 6-8 J292 on the GAD 29/29B
J292 Pin Descriptions
Pin
1
2
3
4
5
6
Pin Name
AC REFERENCE HI
(GAD 29B ONLY)
AC REFERENCE LO
(GAD 29B ONLY)
HDG/CRS VALID
(GAD 29B ONLY)
ARINC 429 IN 4B
ARINC 429 IN 3B
ARINC 429 OUT 2B
I/O
In
In
Out
In
In
Out
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7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
ARINC 429 OUT 2B
HEADING ERROR HI
(GAD 29B ONLY)
CAN TERM 1
ARINC 429 IN 2B
ARINC 429 IN 1B
ARINC 429 OUT 1B
ARINC 429 OUT 1B
HEADING ERROR LO
(GAD 29B ONLY)
COURSE ERROR HI
(GAD 29B ONLY)
ARINC 429 IN 4A
ARINC 429 IN 3A
ARINC 429 OUT 2A
ARINC 429 OUT 2A
COURSE ERROR LO
(GAD 29B ONLY)
CAN TERM 2
ARINC 429 IN 2A
ARINC 429 IN 1A
ARINC 429 OUT 1A
ARINC 429 OUT 1A
Out
Out
-In
In
Out
Out
In
Out
In
In
Out
Out
In
-In
In
Out
Out
A.3.3 Aircraft Power
The GAD 29/29B operates using power from one 14 / 28 VDC input. Pin 8 (AIRCRAFT POWER 2) is
not used as a part of this STC.
NOTE
AIRCRAFT POWER 2 is for connecting to an alternate power source, such as on aircraft with
two electrical buses.
A.3.4 RS-232
RS-232 is not used or approved for use by this STC.
A.3.5 CAN Bus
The GAD 29/29B CAN bus conforms to the BOSCH standard for Controller Area Network (CAN) 2.0B and ISO 11898. See Section 3.4.5.2 for details. The CAN bus connection on the GAD 29/29B is used
to connect the GAD 29/29B to one or two G5s and a GMU 11.
For specific wiring information refer to Section 5.
A.3.6 ARINC 429
The ARINC 429 outputs conform to ARINC 429 electrical specifications when loaded with up to 5
standard ARINC 429 receivers. The G5 in conjunction with the GAD 29/29B can receive GPS and VHF
navigation data and send selected course when connected to a GPS or GPS/VHF navigator.
For specific wiring information refer to Section 5
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A.3.7 Autopilot Heading/Course (GAD 29B Only)
The GAD 29B can provide analog heading and course error outputs to third-party analog autopilots. In
the case of an AC autopilot, the GAD 29B has an AC REFERENCE signal input.
For specific wiring information refer to Section 5.
This area intentionally blank
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APPENDIX B OUTLINE AND INSTALLATION DRAWINGS
B.1 G5
Figure 6-9 G5 Outline Drawing
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Figure 6-10 G5 Installation Drawing
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Figure 6-11 G5 Panel Cutout Measurements (Not to Scale)
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B.2 GAD 29/29B
Figure 6-12 GAD 29/29B Outline Drawing
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Figure 6-13 GAD 29/29B Install Breakdown
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B.3 GMU 11
Figure 6-14 GMU 11 Outline Drawing
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Figure 6-15 GMU 11 Install Breakdown
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APPENDIX C MAGNETIC INTERFERENCE SURVEY
C.1 Introduction
The magnetic interference survey is used to identify a location within an aircraft with acceptable levels
of magnetic interference where the GMU 11 can be correctly installed. This appendix describes the
materials, precautions, setup, and procedures required to successfully conduct the magnetic interference
survey.
C.2 Required Materials
The following items are required to complete the magnetic interference survey.
DC Power Source
In order to perform the magnetic interference survey, it is required to use a DC power source capable of
supplying 8-36 VDC/350 mA to the G5 and GMU 11 magnetometer for test purposes.
G5
It is required to use a G5 to run the magnetic interference survey. If a G5 with charged battery attached
is used, the G5 does not need to be powered from the DC Power Source.
The GMU 11 will still need power from a DC Power Source. A good temporary power source would be
a 9 VDC battery.
Stopwatch or Watch with a Second Hand
During the survey test sequence, it is required to use a stopwatch, or watch with a second hand, in order
to measure the time for turning equipment on and off.
Magnetic Interference Survey Test Cable
In order to perform the magnetic interference survey, it is required to use a test cable fabricated by the
installer. Fabricate a test cable in accordance with Figure 6-16.
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Figure 6-16 Magnetic Interference Test Harness
C.3 Conducting the GMU 11 Location Survey
This section describes the setup and procedure required to successfully complete the GMU 11 location
survey using the G5.
C.3.1 Aircraft and GMU 11 Setup
Prepare the aircraft and GMU 11 for the location survey by completing the following steps:
1. Prepare a detailed survey sequence list with start and stop times for exercising all aircraft
components and devices that may affect the operation of the GMU 11 magnetometer through
movement of ferrous metal parts or electrical inductance. Aircraft components included on the list
will vary depending on aircraft model. An example survey sequence is provided below.
2. Position the aircraft in a magnetically quiet area. This step may involve repositioning large metal
objects including aircraft and ground support equipment away from the survey area.
3. Position the GMU 11 in the aircraft location to be surveyed.
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CAUTION
Do not permanently install the GMU 11 prior to successfully completing the GMU 11 location
survey. An unsurveyed location may be unsuitable for permanent installation and cause the GMU
11 to function incorrectly.
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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C.3.2 G5 Tool Setup Procedure and operation
Before beginning the survey, ensure that all items listed on the test sequence are in their pre-exercise
states (e.g. control surfaces neutral, flaps up, lights off). Perform the survey by completing the following
steps.
1. Power up the aircraft (master switch, avionics bus, etc.).
2. Connect the test harness to the G5 with a battery installed and an 8-36 VDC/350mA limited
power supply as shown in Figure 6-16 above.
3. Turn the G5 on in configuration mode.
4. Navigate to the “Magnetometer” page.
5. Select “Interference Test…”.
6. Follow the instructions displayed on the G5.
7. Select “Start” on the G5.
8. Perform each exercise on the survey sequence sheet. Perform each exercise at its specified
elapsed time and for its specified duration. This will help ensure correct identification of
magnetic field deviation sources after the survey is complete.
9. Monitor the magnetic field deviation percentage throughout the survey. If deviation levels exceed
thresholds, mark the survey sequence exercises during which these deviations occurred.
10. When all exercises in the survey sequence have been completed, the G5 status page will display
the worst case percentage of magnetic interference and the time stamp at which it occurred.
C.4 G5 Data Analysis
The G5 status page will display a “Test status:” of either “Pass” or “Fail” and the worst case percentage
of magnetic interference and the time stamp at which it occurred. Use this time stamp in conjunction
with the completed survey sequence to conclude which item created the highest magnetic interference.
If the test passes, then the location chosen for the test is a valid candidate for mounting the GMU 11. No
further testing is required.
If the test fails, the location chosen for the test should be considered unreliable until the source of
magnetic interference is identified and remedied. Compare the corresponding timestamp with the
prepared test sequence to identify which action produced the problem. If the source of the magnet
interference is not able to be identified or remedied, a new location for testing should be chosen. Repeat
the test until a suitable location is found.
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APPENDIX D GMU 11 MOUNTING IN NONMETALLIC WINGTIP
D.1 Overview
In some installations it is desirable to mount the GMU 11 magnetometer in the wingtip of a metal
aircraft that has non-metallic (e.g. fiberglass) wingtip covers. If this is the case, the following
requirements must be met:
• The aircraft must have wingtip navigation lights installed.
• Heavy overbraid must be installed over the wiring from the GMU to the entry into the wing.
• The overbraid must be terminated at this wing entry point using a #10 terminal lug and stud.
• The GMU 11 must be mounted to a metal rib that does not enclose a fuel bay.
• There must be at least one intermediate rib between the rib that encloses the fuel bay and the rib
on which the GMU 11 is installed.
• The GMU 11 mounting bracket must be electrically bonded to the wing using fasteners or rivets.
D.2 Materials Required but Not Supplied
The following materials (or equivalents) are required to install the GMU 11 in a non-metallic wingtip:
• Tinned copper flat braid, 1/4”, QQB575F36T0250
• Electrical tie-down strap, adjustable, MS3367-{1, 2, or 7}-X
• Terminal lug, #10, uninsulated, MS25036-108
• Terminal stud, #10
• Terminal lug, #8, uninsulated, MS25036-153
D.3 Overbraid Fabrication and Installation
The length of overbraid required is approximately equal to the length of the GMU 11 service loop
(measured from the wing rib to the collar of P111) plus 4 inches.
Refer to Figure 6-17 and Figure 6-18 while completing the following overbraid installation procedure:
NOTE
It is recommended this procedure is completed prior to terminating wires to connector P111. If
this procedure is completed before assembly of P111, proceed to step 3.
1.
2.
3.
4.
Disconnect P111 from the GMU 11.
De-pin wires from P111 to facilitate placing overbraid over wire bundle.
Slide the overbraid over wire bundle extending from wing rib.
Terminate the end nearest the metal wing rib with the overbraid in accordance with one of the
two methods in Section D.3.1 using a #8 terminal lug.
5. Secure the overbraid pigtail to the shield block of P111 when assembling P111 (Refer to Section
4.3.3).
6. Terminate the end nearest the GMU with the overbraid in accordance with one of the two
methods in Section D.3.1 using a #10 terminal lug.
7. Secure the overbraid pigtail to a #10 terminal stud. Refer to Section D.3.2 for stud location
instructions.
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D.3.1 Overbraid Termination Methods
Overbraid must be terminated with an appropriate lug by one of the two following approved methods.
Whichever method is used, overbraid pigtail length must not exceed two inches. Refer to Figure 6-18.
Method A
1. Carefully separate overbraid wire strands by hand to create an opening in the overbraid for
passage of the GMU 11 connector and cables.
CAUTION
Do not cut an opening in the overbraid strands. Loose overbraid wire ends can chafe the cable
and cause the GMU 11 to malfunction.
2. Trim the overbraid pigtail to a maximum length of two inches.
3. Terminate the braid pigtail in an appropriate terminal lug.
Method B
1. Comb out a maximum of two inches of overbraid pigtail.
2. Twist the pigtail and terminate it in an appropriate terminal lug.
D.3.2 Overbraid Terminal Bonding
Electrical bond preparation for all aluminum-to-aluminum interfaces must be done in accordance with
SAE ARP1870 section 5.1 and 5.5. The overbraid terminal lug must be electrically bonded to a #10 stud
installed in accordance with AC43.13-1B Section 11-189, as well as the following restrictions:
1. If possible, use an existing tooling hole to install the stud.
2. If no suitable tooling hole exists, use an existing fastener (#10 or larger).
3. If there is no suitable fastener, install a new #10 stud as follows:
a. When adding a new stud hole to the rib, the center of the hole must be located a
minimum of one inch away from any existing, non-stiffened rib hole.
b. The new stud hole must be located such that the terminal lug face, neck, or attaching
hardware will not intrude into the flange bend radius of any rib edge or stiffened rib hole.
Refer to MS25036 for terminal lug dimensions.
4. Verify overbraid terminal bonding by checking resistance between the overbraid and the rib.
Resistance should be less than 2.5 mΩ.
Figure 6-17 GMU 11 Overbraid Installation
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NOTES:
[1] Install #10 grounding hardware in accordance with AC 43.13-1B, section 11-89. If
there is an existing hole located in an appropriate area it may be utilized for the
grounding hardware. If there is no existing hole usable for this purpose then drill and
de-burr a 0.191”-0.203” hole.
[2] MS25036-103 terminal lug (or equivalent).
[3] Terminal lug face or connecting hardware must not interfere with bend radius of rib
edge or stiffened holes. Stud hole must be located a minimum 1” from unstiffened
holes. Refer to MS20559 for lug dimensions.
[4] Refer to Section 4.6 for electrical bonding requirements.
[5] The exposed cable not having overbraid in the wing tip areas must be less than 2
inches.
Figure 6-18 GMU 11 Overbraid Termination
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