Garmin | GMA™ 35 | Garmin GMA™ 35 Instructions for Continued Airworthiness GTN 6XX/7XX – MD369E/F/FF

Garmin GMA™ 35 Instructions for Continued Airworthiness GTN 6XX/7XX – MD369E/F/FF
Instructions for Continued Airworthiness
GTN 6XX/7XX - MD369E/F/FF
As installed in
(Make and Model Aircraft)
Reg. No. ___________
S/N __________
Dwg. Number:
190-01007-KB Rev.2
Garmin International, Inc.
1200 E. 151st Street
Olathe, Kansas 66062 USA
Record of Revision
Rev.
Date
Description of Change
1
2
10/17/2013
3/31/2016
Initial Release
Updated Figures in Section 2.8 and Appendix A, Added instructions to
disable Airspace Altitude Labels
Company Proprietary Information
This drawing and the specifications contained herein are the property of Garmin International or its
subsidiaries and may not be reproduced or used in whole or in part as the basis for manufacture or sale
of products without written permission.
Copyright  2016 Garmin Ltd. or its subsidiaries. All rights reserved.
Garmin International, Inc.
1200 E. 151st Street
Olathe, Kansas 66062 U.S.A.
Page ii
190-01007-KB Rev.2
Instructions for Continued Airworthiness GTN 6XX/7XX - MD369E/F/FF
Table of Contents
1. INTRODUCTION .....................................................................................................................1
1.1 Purpose .................................................................................................................................. 1
1.2 Scope ..................................................................................................................................... 1
1.3 Document Control ................................................................................................................... 1
1.4 Permission to Use Certain Documents ...................................................................................... 1
1.5 Definitions .............................................................................................................................. 1
1.6 Terminology ........................................................................................................................... 1
2. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS............................................................2
2.1 Introduction............................................................................................................................ 2
2.2 Description of Alteration .......................................................................................................... 2
2.3 Control, Operation, and Testing Information ............................................................................. 3
2.4 Servicing Information .............................................................................................................. 3
2.5 Periodic Maintenance .............................................................................................................. 4
2.6 Troubleshooting Information.................................................................................................... 9
2.7 Removal and Replacement Information .................................................................................... 9
2.8 Equipment Location and Access ............................................................................................. 10
2.8.1 GTN STC Installation Equipment Layout ......................................................................... 10
2.8.2 GTN Navigator Installation ............................................................................................ 11
2.8.3 Circuit Breaker and HTAWS Annunciator Installation ....................................................... 13
2.8.4 Wire Routing ................................................................................................................ 16
2.9 Weight and Balance .............................................................................................................. 17
2.10 Diagrams .............................................................................................................................. 18
2.11 Special Inspection Requirements ............................................................................................ 18
2.12 Application of Protective Treatments ...................................................................................... 18
2.13 Data Relative to Structural Fasteners...................................................................................... 18
2.14 Special Tools ........................................................................................................................ 18
2.15 Additional Instructions ........................................................................................................... 18
2.16 Overhaul Period .................................................................................................................... 18
2.17 ICA Revision and Distribution ................................................................................................. 19
2.18 Assistance ............................................................................................................................ 19
2.19 Implementation and Record Keeping ...................................................................................... 19
3. AIRWORTHINESS LIMITATIONS SECTION .........................................................................20
4. APPENDIX A - EQUIPMENT LOCATIONS AND WIRE ROUTING ...........................................21
Table of Tables
Table
Table
Table
Table
Table
Table
Table
1.
2.
3.
4.
5.
6.
7.
Page iii
Maintenance Intervals for GTNs and GMA 35 ........................................................................... 4
Maintenance Intervals for Antennas Replaced Under this STC ................................................... 7
Bill of Materials for GTN Navigators and Optional GMA Audio Panel ......................................... 11
GTN Circuit Breaker Labels ................................................................................................... 13
Bill of Materials for Circuit Breaker in MD369 Series ................................................................ 14
Bill of Materials for HTAWS Annunciators in MD369 Series ...................................................... 15
Typical Weight and Balance of GTN and GMA 35 Installed in MD369 Series ............................. 17
190-01007-KB Rev.2
Instructions for Continued Airworthiness GTN 6XX/7XX - MD369E/F/FF
1.
INTRODUCTION
1.1 Purpose
This document provides Instructions for Continued Airworthiness compliant with requirements of 14 CFR
§27.1529, and Part 27 Appendix A. This ICA is to be used by the agency installing Garmin GTN 6XX/7XX
navigators, GMA 35 audio panel, and additional equipment under the GTN 6XX/7XX Part 27 Approved
Model List (AML) STC, and includes information required by the operator to adequately maintain installed
items.
1.2 Scope
This document provides the Instructions for Continued Airworthiness for MD 369E/F/FF series rotorcraft,
modified by the installation of the Garmin GTN 6XX/7XX and optional GMA 35 under the AML STC.
1.3 Document Control
This document shall be released, archived, and controlled in accordance with the Garmin document
control system. When this document is revised, refer to Section 2.17 for information on how to gain FAA
acceptance or approval and how to notify customers of changes.
1.4 Permission to Use Certain Documents
Permission is granted to any corporation or person applying for approval of a Garmin GTN 6XX/7XX to
use and reference appropriate STC documents to accomplish the Instructions for Continued Airworthiness
and show compliance with STC engineering data. This permission does not construe suitability of the
documents. It is the responsibility of the applicant to determine the suitability of the documents for the
ICA.
1.5 Definitions
The following terminology is used within this document:
1) ACO:
2) AEG:
3) BIT:
4) COM:
5) CFR:
6) FAA:
7) GPS:
8) ICA:
9) LED:
10) LRU:
11) NAV:
12) MFD:
13) PMI:
14) POI:
15) STC:
16) TSO:
17) WAAS:
Aircraft Certification Office
Aircraft Evaluation Group
Built-In Test
Communications
Code of Federal Regulations
Federal Aviation Administration
Global Positioning System
Instructions for Continued Airworthiness
Light Emitting Diode
Line Replaceable Unit
Navigation
Multi-Function Display
Principal Maintenance Inspector
Principal Operations Inspector
Supplemental Type Certificate
Technical Standard Order
Wide Area Augmentation System
1.6 Terminology
Except where specifically noted, references made to the ‘GTN’ will equally apply to the GTN
625/635/650/725/750. Also, ‘GTN 7XX’ refers specifically to the GTN 725 and GTN 750, and ‘GTN 6XX’
refers specifically to the GTN 625, GTN 635, and GTN 650.
Also, except where specifically noted, references made to the ‘MD 369 Series’ will apply equally to the MD
369E, MD 369F, and MD 369FF.
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Instructions for Continued Airworthiness GTN 6XX/7XX - MD369E/F/FF
Page 1 of 21
2.
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
2.1 Introduction
Content, Scope, Purpose and
Arrangement:
This document identifies the Instructions for Continued Airworthiness
for the modification of the aircraft by installation of the Garmin GTN
6XX/7XX Part 27 AML STC.
Applicability:
Applies to aircraft altered by installation of the Garmin GTN 6XX/7XX
and GMA 35 Part 27 AML STC.
Definition of Abbreviations:
See Section 1.5 and Section 1.6
Precautions:
None
Units of measurement:
None
Referenced publications:
(or their later revisions)
Retention:
1)
Garmin 190-01007-B1 Rev.1, “GTN 6XX/7XX Part 27 AML STC
System Maintenance Manual”
2)
Garmin 190-01004-03 Rev. D, “GTN 625/635/650 Pilot’s Guide”
3)
Garmin 190-01007-03 Rev. D, “GTN 725/750 Pilot’s Guide”
4)
MDHI Model Helicopters Models 369D/E/FF – 500/600N, Basic
Handbook of Maintenance Instructions, CSP-HMI-2 Servicing and
Maintenance Rev 44, 5 July 2011
5)
MDHI Model Helicopters Models 369D/E/FF – 500/600N, Basic
Handbook of Maintenance Instructions, CSP-HMI-3 InstrumentsElectrical-Avionics Rev 13, 20 December 2005
6)
MDHI Model Helicopters Models 369D/E/FF – 500/600N,
Structural Repair Manual CSP-SRM-6, Reissued No. 3, 26 May
2006
This document, or the information contained within, will be included in
the aircraft’s permanent records.
2.2 Description of Alteration
The GTN navigators are a family of aviation panel mounted retro-fit products. GTN units utilize a
touchscreen as the primary control interface. Traditional knobs and buttons have been minimized to
simplify access to the color multi-function display (MFD), NAV and COM transceiver, and GPS/WAAS
navigator functions.
The GTN 625/635/650 Navigators (Garmin Touch Navigation) are a family of 2.65-inch tall aviation panel
mounted retro-fit products that are intended to supersede the Garmin 400W Series Navigators. The GTN
6XX product family consists of the GTN 625 GPS/WAAS navigator, the GTN 635 GPS/WAAS/COM
navigator, and the GTN 650 GPS/WAAS/NAV/COM navigator.
The GTN 725/750 Navigators (Garmin Touch Navigation) are a family of 6.00-inch tall aviation panel
mounted retro-fit products that are intended to supersede the Garmin 500W Series Navigators. The GTN
7XX product family consists of the GTN 725 GPS/WAAS navigator, and the GTN 750 GPS/WAAS/NAV/COM
navigator.
The optional GMA 35 is an audio panel with a Marker Beacon receiver. The GMA 35 in conjunction with a
GTN 7XX provide full audio panel capability, for communication and navigation radios, headsets,
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Instructions for Continued Airworthiness GTN 6XX/7XX - MD369E/F/FF
Page 2 of 21
microphones, and speakers. The GMA 35 is mounted in a notch behind the GTN 7XX to free up mounting
space in the flight deck instrument panel.
If optional HTAWS function is enabled on the GTN, HTAWS terrain caution/warning indicator and HTAWS
status annunciation are required, unless the rotorcraft is equipped with a GDU 620. These annunciators
serve as the visual indication of a terrain/obstacle caution or warning alert, HTAWS failure and HTAWS
mode status.
2.3 Control, Operation, and Testing Information
See Garmin 190-01004-03 Rev. D, “GTN 625/635/650 Pilot’s Guide” and Garmin 190-01007-03 Rev. D,
“GTN 725/750 Pilot’s Guide” for information on how to operate the system in normal mode.
See the Section 3 of the GTN 6XX/7XX PART 27 AML STC SYSTEM MAINTENANCE MANUAL, Section 3 for
details on how to operate and access configuration mode and diagnostic pages, and Section 2.1 for
document part numbers. See Section 6 for general ground checks and system test procedures.
See GTN 6XX/7XX PART 27 AML STC SYSTEM MAINTENANCE MANUAL for a system description.
2.4 Servicing Information
None. In the event of system failure, troubleshoot the GTN 6XX/7XX and GMA 35 in accordance with
Section 4 of the GTN 6XX/7XX PART 27 AML STC SYSTEM MAINTENANCE MANUAL.
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Instructions for Continued Airworthiness GTN 6XX/7XX - MD369E/F/FF
Page 3 of 21
2.5 Periodic Maintenance
The GTN and GMA 35 are designed to detect internal failures. A thorough self-test is executed
automatically upon application of power to the units, and built-in tests (BIT) are continuously executed.
Detected errors are indicated as failure annunciations, system messages, or a combination of the two.
Operation of the GTN 6XX/7XX and GMA 35 is not permitted unless the inspections described in this
section have been completed within time intervals prescribed in Table 1. All antennas connected to the
GTN should be maintained in accordance with maintenance and inspection data appropriate for the
antenna installation.
Table 1. Maintenance Intervals for GTNs and GMA 35
ITEM
INTERVAL
1. EQUIPMENT REMOVAL &
REPLACEMENT
ON CONDITION
DESCRIPTION/PROCEDURE
Removal and replacement of the following items.
(1) GTN 6XX/7XX or GMA 35 units
(2) NAV antenna cable splitter
(3) NAV antenna cable diplexer
(4) Fan
See Section 5 of the GTN 6XX/7XX PART 27 AML STC SYSTEM
MAINTENANCE MANUAL for instructions.
2. DISPLAY BACKLIGHT
ON CONDITION
The display backlight LEDs are rated by the manufacturer as having a
usable life of at least 36,000 hours. This life may be more or less than the
rated time depending on the operating conditions of the GTN. Over time,
the backlight lamp may dim and the display may not perform as well in
direct sunlight conditions.
The user must determine by observation when the display brightness is not
suitable for its intended use. Contact the Garmin factory repair station when
the backlight lamp requires service.
3. BATTERY REPLACEMENT
ON CONDITION
The GTN has an internal keep-alive battery that will last about 10 years. The
battery is used for GPS system information. Regular planned replacement is
not necessary.
The GTN will display a low battery’ message when replacement is required.
Once the low battery message is displayed, the battery should be replaced
within 1 to 2 months. If the battery is not replaced and becomes totally
discharged, the GTN unit will remain fully operational, but the GPS signal
acquisition time may be increased. There is no loss of function or accuracy
of the GTN unit with a dead battery.
The battery must be replaced by the Garmin factory repair station or factory
authorized repair station.
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Instructions for Continued Airworthiness GTN 6XX/7XX - MD369E/F/FF
Page 4 of 21
ITEM
INTERVAL
4. ELECTRICAL BONDING
CHECK, GTN/GMA
BOND CHECK TO BE
PERFORMED IN
ALIGNMENT WITH MD
369E/F/FF
MAINTENANCE SCHEDULE.
EVERY 10 YEARS OR
EVERY 20TH 100 HOUR
INSPECTION, WHICHEVER
COMES FIRST
DESCRIPTION/PROCEDURE
Perform an electrical bonding check as follows:
1. Remove the GTN and GMA 35 (if installed) from the mounting rack(s)
2. Remove the backplate assembly from the rack(s) such that the
harnesses are disconnected
NOTE For GTN 7XX only, if the GMA 35 is installed, it must be removed
from its rack and the GMA 35 backplate assembly must be
removed prior to performing Step 3. When a GMA 35 bonding
check is planned, perform the GMA 35 bonding check prior to
reinstalling the GTN backplate assembly to the rack.
3. Measure the resistance between each mounting rack and nearby
exposed portion of metallic structure and verify that the resistance is
less than or equal to 10 milliohms.
In the event of bonding test failure, remove the rack and verify that the
countersunk areas around the holes, in the rack that are used to attach
the rack, are free of corrosion or any other debris. Clean the
countersunk areas using P-D-680 (CM234) as specified in MDHI Model
Helicopters Models 369D/E/FF – 500/600N, Basic Handbook of
Maintenance Instructions, CSP-HMI-3 Instruments-Electrical-Avionics.
Reattach the rack to the rails in the panel or pedestal. Re-verify the
resistance between the mounting rack and nearby exposed portion of
aircraft metallic structure and ensure that the resistance is less than or
equal to 2.5 milliohms.
4. Reinstall all backplate assemblies and reinstall the GTN in the mounting
rack.
5. VISUAL INSPECTION
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Instructions for Continued Airworthiness GTN 6XX/7XX - MD369E/F/FF
Page 5 of 21
ITEM
INTERVAL
TO BE PERFORMED IN
ALIGNMENT WITH MD
369E/F/FF
DESCRIPTION/PROCEDURE
The GTN unit, GMA 35 (if installed), switches, and wiring harnesses should
be inspected to ensure continued integrity of the installation in accordance
MDHI Model Helicopters Models 369D/E/FF – 500/600N, Basic Handbook of
MAINTENANCE SCHEDULE. Maintenance Instructions, CSP-HMI-3 Instruments-Electrical-Avionics Section
EVERY 100 FLIGHT
97.
HOURS OR EVERY 12
MONTHS, WHICHEVER
Visually inspect the following to ensure continued installation integrity OCCURS FIRST.
1. Inspect the GTN unit(s) and GMA 35 for security of attachment,
including visual inspection of mounting racks and rotorcraft instrument
panel or avionics console supporting structure to which the racks attach.
Verify the countersunk fastener heads are in full contact with unit
mounting rack holes. Inspect the condition of the console and unit
install rack around the rivets. Repair damage as necessary in
accordance with Section 53−00−00 of CSP−SRM−6, Structural Repair
Manual, 369D/E/FF − 500/600N Helicopters. Verify countersunk rivet
head is fully seated into the unit mounting rack fastener hole with no
slack. Verify the electrical bond using the procedure in item 4 above.
2. Inspect for signs of corrosion, and if corrosion is found, treat in
accordance with Section 20-40-00 of MDHI Model Helicopters Models
369D/E/FF – 500/600N, Basic Handbook of Maintenance Instructions,
CSP-HMI-2.
3. Inspect all switches, knobs, and buttons for damage. If knobs or
buttons are missing or damaged, return the unit to Garmin for repair.
4. Inspect placards and switch labels. Ensure that they are legible and
properly adhered. Replace any damaged labels as necessary.
5. Inspect condition of wiring, shield terminations, routing, and
attachment/clamping. Correct any issues identified by replacing
damaged wiring and re-attaching as necessary.
6. Check the fan intake slots on the sides and bottom of the GTN unit’s
bezel for dust, dirt, or obstructions. Clean as needed.
6. ELECTRICAL BONDING
CHECK OF HTAWS
ANNUNCIATORS (IF
INSTALLED)
TO BE PERFORMED IN
ALIGNMENT WITH MD
369E/F/FF
MAINTENANCE SCHEDULE.
EVERY 10 YEARS OR
EVERY 20TH 100 HOUR
INSPECTION, WHICHEVER
Perform an electrical bonding check as follows:
1. Measure the resistance between the metallic body of each annunciator
and the instrument panel and verify that the resistance is less than or
equal to 20 milliohms.
2. In the event of bonding test failure,
(a) Clean the mating surfaces of both the annunciator mount and the
instrument panel per MD Helicopters Inc. CSP-HMI-2 Handbook of
Maintenance Instructions dated 31 October 1990, section 20-20-00.
(b) Verify that the resistance between the annunciators and the
instrument panel after prepping the bond surface is less than 10
milliohms.
COMES FIRST
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Table 2. Maintenance Intervals for Antennas Installed Under this STC
ITEM
INTERVAL
1. ELECTRICAL BONDING
CHECK, GPS ANTENNAS
(ONLY IF ANTENNA IS
INSTALLED BY THIS STC)
DESCRIPTION/PROCEDURE
An electrical bonding test must be performed on antennas installed by this
STC.
1. Gain access to the antenna installation.
2. Disconnect coaxial cable(s) from the antenna connector(s)
3. Measure the resistance between the antenna connector and a nearby
BOND CHECK TO BE
exposed portion of conductive aircraft structure (example: exposed
PERFORMED IN
rivet)
ALIGNMENT WITH MD
4. Verify the resistance is equal to or less than 10 milliohms.
369E/F/FF
5. Reconnect the coaxial cable(s) to the antenna connector(s) and ensure
MAINTENANCE SCHEDULE.
it is secured. In the event of bonding test failure, remove antenna, and
EVERY 10 YEARS OR
clean and prepare the mating surfaces and hardware as follows:
EVERY 20TH 100 HOUR
(a) For antennas that are secured with nuts and bolts, clean the
INSPECTION, WHICHEVER
fastener hole in the antenna and the underside of the fastener head
OCCURS FIRST
itself. Prep the area underneath the washer on the inner mould line
of the skin in accordance with CSP-HMI-3 96-00-00 Maintenance
Practice Section 6. If nutplates are used in lieu of a nut, the
technician is only required to clean the underneath of the fastener
head and the fastener hole.
(b) For antennas that use stud mounts, prep the area underneath the
washer on the inner mould line of the skin in accordance with CSPHMI-3 96-00-00 Maintenance Practice Section 6
6. Re-install using unit replacement procedures in the GTN 6XX/7XX PART
27 AML STC SYSTEM MAINTENANCE MANUAL Section 5. Any reworked
antenna installation shall have a resistance of less than or equal to 2.5
milliohms.
2. VISUAL INSPECTION, GPS Visual inspection on the antenna
ANTENNAS
1. Clean the antenna with water and mild soap.
(ONLY IF ANTENNA IS
2. Verify there are no cracks on the antenna and around attachment
INSTALLED BY THIS STC)
fasteners.
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Instructions for Continued Airworthiness GTN 6XX/7XX - MD369E/F/FF
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ITEM
INTERVAL
TO BE PERFORMED IN
ALIGNMENT WITH MD
369E/F/FF
MAINTENANCE SCHEDULE.
EVERY 100 FLIGHT
HOURS OR EVERY 12
MONTHS, WHICHEVER
OCCURS FIRST
PERFORM VISUAL
INSPECTION IN EVENT OF
SUSPECTED LIGHTNING
STRIKE
DESCRIPTION/PROCEDURE
3. Verify that all sealing fillets around the antenna are in good condition.
4. If the antenna is broken, cracked, or dented it must be replaced.
5. In the event attachment is not secure, re-attach antenna and complete
the Electrical Bonding Test.
6. In the event the antenna seal shows signs of damage, re-seal the
antenna and gasket by running a bead of the MIL-A-46146 NonCorrosive RTV Silicone Adhesive-Sealant along the edge of the antenna
where it meets the exterior aircraft skin. MIL-S-8802 Sealing Compound,
Temperature-Resistant, High Adhesion can be used as an alternative.
Use caution to insure that the antenna connectors are not contaminated
with sealant.
7. Visually inspect the rotorcraft exterior skin around installed antenna (a) Clean the exterior of the aircraft skin within a 10 inch radius of the
antenna with water and mild soap.
(b) Inspect aircraft skin around the antenna footprint to verify there are
no cracks and aircraft skin is not deformed.
(c) If the aircraft skin is cracked, or deformed, the internal structure
must also be inspected for degradation in the local area. Refer to
approved method defined in MDHI Model Helicopters Models
369D/E/FF-500/600N Structural Repair Manual.
8. Verify that antenna fasteners are not loose.
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2.6 Troubleshooting Information
If error indications are displayed on the GTN 6XX or 7XX, consult Section 4, Troubleshooting of the GTN
6XX/7XX PART 27 AML STC SYSTEM MAINTENANCE MANUAL. Refer to the GTN System Configuration
and Checkout Log retained in the aircraft permanent records for a list of the interfaced equipment and
system configuration data.
2.7 Removal and Replacement Information
When replacing a GTN unit or GTN configuration module, the configuration information for the
replacement unit must be set based on approved installation data to ensure proper configuration for this
STC. In particular, per FAA direction, the setting for Airspace Labels must be configured as “Disable”.
For removal and replacement instructions, refer to the GTN 6XX/7XX PART 27 AML STC SYSTEM
MAINTENANCE MANUAL Section 5, Equipment Removal and Replacement.
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2.8 Equipment Location and Access
2.8.1 GTN STC Installation Equipment Layout
Figure 2-1. Equipment Location in GTN STC
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2.8.2 GTN Navigator Installation
Typical installation of GTN navigator in MD369 series is shown in Figure 2 with corresponding bill of
material shown in Table 3.
Table 3. Bill of Materials for GTN Navigators and Optional GMA Audio Panel
(1)
(1)
(1)
(1)
1
1
1
1
(1)
(1)
(1)
(1)
1
-
1
-
1
-
1
1
1
-
21
20
19
18
17
16
15
14
13
12
11
10
9
8
7
6
5
011-02302-00
011-02300-00
011-02645-00
011-02299-00
011-02326-02
011-02326-00
011-02325-02
011-02325-01
011-02325-00
011-02246-02
1
011-02246-00
1
011-02245-02
1
011-02245-01
011-02245-00
1
115-01294-A0
1
1
115-01293-A0
011-02282-A0
011-02282-50
011-02282-00
1
4
011-02281-00
1
3
011-02256-A0
011-02256-50
011-02256-00
1
2
011-02255-00
1
1
011-02254-00
750 725 650 635 625 ITEM PART
NO. NUMBER
QTY. PER GTN MODEL
CONNECTOR KIT, GMA 35 AUDIO PANEL
BACKPLATE SUB-ASSEMBLY, GMA 35 AUDIO PANEL
INSTALL RACK KIT, GMA 35 AUDIO PANEL
GMA 35 AUDIO PANEL, REMOTE
CONNECTOR KIT, GTN 750 NAVIGATOR
CONNECTOR KIT, GTN 725 NAVIGATOR
CONNECTOR KIT, GTN 650 NAVIGATOR
CONNECTOR KIT, GTN 635 NAVIGATOR
CONNECTOR KIT, GTN 625 NAVIGATOR
BACKPLATE SUB-ASSEMBLY, GTN 750 NAVIGATOR
BACKPLATE SUB-ASSEMBLY, GTN 725 NAVIGATOR
BACKPLATE SUB-ASSEMBLY, GTN 650 NAVIGATOR
BACKPLATE SUB-ASSEMBLY, GTN 635 NAVIGATOR
BACKPLATE SUB-ASSEMBLY, GTN 625 NAVIGATOR
MOUNTING RACK, GTN 7XX SERIES NAVIAGATOR
MOUNTING RACK, GTN 6XX SERIES NAVIAGATOR
GTN 750 TOUCH SCREEN NAVIGATOR, NVIS
GTN 750 TOUCH SCREEN NAVIGATOR, GRAY BEZEL
GTN 750 TOUCH SCREEN NAVIGATOR
GTN 725 TOUCH SCREEN NAVIGATOR
GTN 650 TOUCH SCREEN NAVIGATOR, NVIS
GTN 650 TOUCH SCREEN NAVIGATOR, GRAY BEZEL
GTN 650 TOUCH SCREEN NAVIGATOR
GTN 635 TOUCH SCREEN NAVIGATOR
GTN 625 TOUCH SCREEN NAVIGATOR
DESCRIPTION
OR
OR
OR
OR
OR
OR
Note that ( ) indicate optional quantities.
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Figure 2-2. Typical GTN / GMA35 Installation in MD369 Series
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2.8.3 Circuit Breaker and HTAWS Annunciator Installation
Required circuit breaker labels are shown in Table 4.
Table 4. GTN Circuit Breaker Labels
LRU
GMA 35
GTN 650
GTN 750
GTN 625
GTN 725
POWER INPUT
ROTORCRAFT POWER ON CONNECTOR P3502
ROTORCRAFT POWER ON CONNECTOR P1001
ROTORCRAFT POWER ON CONNECTOR P1004
ROTORCRAFT POWER ON CONNECTOR P1003
ROTORCRAFT POWER ON CONNECTOR P1001
ROTORCRAFT POWER ON CONNECTOR P1001
GTN 635
ROTORCRAFT POWER ON CONNECTOR P1003
GTN INSTALLATION
SINGLE
DUAL1
Audio
GPS/NAV 1
GPS/NAV
GPS/NAV 2
COM 1
COM
COM 2
GPS 1
GPS
GPS 2
GPS 1
GPS
GPS 2
COM 1
COM
COM 2
1. Dual installation labeling applies to GTN LRUs only
Figure 2-3. GTN Circuit Breaker Labels in MD369 Series
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Table 5. Bill of Materials for Circuit Breaker in MD369 Series
(1)
C11000
MS35338-40
MS35214-23
7277-XX-3
(1)
2
7274-XX-3
7277-XX-5
2
2
1
7274-XX-5
7XX
6XX ITEM PART
NO.
NUMBER
QTY.
(4)
(4)
(4)
(4)
5
4
3
ASTM B187 COPPER BAR 0.25 INCH WIDE, 0.125 INCH THICK
WASHER, LOCK-SPRING, HELICAL, REGULAR SERIES 0.112
SCREW, MACHINE, PAN HEAD, CROSS-RECESSED, BRASS, 0.1380-32 UNC-2A
CIRCUIT BREAKER, LOW AMPERAGE, GENERAL APPLICATION, 3 AMP
CIRCUIT BREAKER, LOW AMPERAGE, HIGH PERFORMANCE, 3 AMP
CIRCUIT BREAKER, LOW AMPERAGE, GENERAL APPLICATION, 5 AMP
CIRCUIT BREAKER, LOW AMPERAGE, HIGH PERFORMANCE, 5 AMP
DESCRIPTION
Figure 2-4. GTN Circuit Breakers in MD369 Series
190-01007-KB Rev.2
Instructions for Continued Airworthiness GTN 6XX/7XX - MD369E/F/FF
Page 14 of 21
Table 6. Bill of Materials for HTAWS Annunciators in MD369 Series
1
2
1
1
1
1
1
1
2
1
QTY
10
9
8
7
18-440
18-200
LED-XX-17-11-E14G0
LED-40-17-XX-BBAKH
LED-41-11-KB-E11RF
6
LED-41-11-BB-E11ND
LED-40-17-KB-E12XT
5
LED-40-17-BB-E11R9
4
AN525-10R6
3
MS21070L3
2
MS204026AD3-3
1
190-01007-HB-04
ITEM PART NUMBER
NO.
PLUG, KEYED, QUICK CONNECT
PLUG, QUICK CONNECT
CAP, INDIATOR, HTAWS, STATUS
BODY, DEFINED LOGIC, MFB (0;DL2/NN/UU;0)
SWITCH, RP MODE, NVIS
SWITCH, RP MODE
INDICATOR, HTAWS, CAUTION AND WARNING, NVIS
INDICATOR, HTAWS, CAUTION AND WARNING
SCREW, WASHER HEAD, 0.1900-32UNF-3A, 3/8 IN LONG
NUT, SELF-LOCKING, PLATE, TWO LUG, FLOATING, LOW HEIGHT, STEEL
RIVET, SOLID, COUNTERSUNK 100 DEG, PRECISION HEAD
BRACKET, HTAWS ANNUNCIATORS RP MODE SWITCH
DESCRIPTION
Figure 2-5. HTAWS Annunciator Installation in MD369 Series
190-01007-KB Rev.2
Instructions for Continued Airworthiness GTN 6XX/7XX - MD369E/F/FF
Page 15 of 21
2.8.4
Wire Routing
The GTN/GMA 35 wiring harness power and
switch connections are routed as shown in Figure
5. Coaxial wire routing may differ slightly from
the depicted since the GTNs may be interfaced
with existing GPS antennas. Refer to the aircraft
wire routing worksheets and equipment location
forms that were filled out during initial GTN/GMA
35 installation for additional details.
GTN/GMA 35 installation racks, backplates with
connectors, and wiring harnesses may be
accessed by either removing the GTN LRUs as
specified in GTN 6XX/7XX PART 27 AML STC
SYSTEM MAINTENANCE MANUAL Section 5,
Equipment Removal and Replacement or by
removing the side panel of the MD 369 Series
console. Figure 6 depicts the installation with
the side panel removed.
Figure 2-6. GTN/GMA 35 Wire Routing
in MD 369E/F/FF
190-01007-KB Rev.2
Instructions for Continued Airworthiness GTN 6XX/7XX - MD369E/F/FF
Page 16 of 21
2.9 Weight and Balance
The location of equipment as well as the weight and moment arm for each item is depicted in Figure 6
and Table 7. Refer to Table 7 for weight and balance details.
Figure 2-7. GTN and GMA 35 FS and BL Location in MD369 Series
Table 7. Typical Weight and Balance of GTN and GMA 35 Installed in MD369 Series
190-01007-KB Rev.2
Instructions for Continued Airworthiness GTN 6XX/7XX - MD369E/F/FF
Page 17 of 21
2.10 Diagrams
Aircraft specific LRU locations and wire routing diagram forms are contained in Appendix A of this
document. Completed forms are to be retained with the aircraft permanent records.
Point-to-point wiring diagrams for the GTN, GMA 35, and interfaced equipment included with the aircraft
permanent records.
GTN and GMA 35 locations are described in Section 2.8 of this document.
2.11 Special Inspection Requirements
If an antenna is replaced under this STC, an antenna visual inspection must be performed if there is a
suspected lighting strike on the aircraft. In the event of a suspected or actual lightning strike to the
aircraft, the GPS antenna(s) and its associated installation shall be inspected.
If the antenna was struck by lightning then the antenna and the surrounding installation shall be
inspected to ensure that there is no structural damage around the areas where lightning may have
struck. See Table 2 for inspection criteria.
Execute the system checkout procedure for the GPS/WAAS and/or XM system using the antenna, to
ensure the system(s) are operating correctly.
No action is required for hard landing inspections.
2.12 Application of Protective Treatments
None. N/A.
2.13 Data Relative to Structural Fasteners
Refer to Garmin P/N 190-01007-B1, GTN 6XX/7XX PART 27 AML STC SYSTEM MAINTENANCE MANUAL
Section 5 for fastener information.
2.14 Special Tools
A milliohm meter with an accuracy of +/- 0.1 milliohms ohms (or better) is required to measure the
electrical bonding between the GTN/GMA system components and aircraft ground.
2.15 Additional Instructions
None. N/A
2.16 Overhaul Period
The system does not require overhaul at a specific time period. Power on self-test and continuous BIT
will monitor the health of the GTN system. If any LRU indicates an internal failure, the unit may be
removed and replaced (Refer to Section 5 of the GTN 6XX/7XX PART 27 AML STC SYSTEM
MAINTENANCE MANUAL for Removal and Reinstallation instructions). See GTN 6XX/7XX PART 27 AML
STC SYSTEM MAINTENANCE MANUAL, Section 4 for Troubleshooting information.
190-01007-KB Rev.2
Instructions for Continued Airworthiness GTN 6XX/7XX - MD369E/F/FF
Page 18 of 21
2.17 ICA Revision and Distribution
To revise this ICA, Garmin will follow the Garmin ODA Procedures Manual SOP-0055/ACP-0016 for
Instructions for Continued Airworthiness. The latest revision of this ICA document is available on the
Garmin website (www.flyGarmin.com). To Access Aviation Manuals, select the ‘Support’ tab and then
select ‘Manuals’. You may also contact Garmin General Aviation Product Support at 866-739-5687 (US toll
free) 913-397-8200 or avionics@garmin.com. A Garmin Service Bulletin describing ICA revision will be
sent to Garmin dealers if a revision is determined to be significant.
2.18 Assistance
Flight Standards Inspectors or the certificate holder’s PMI have the required resources to respond to
questions regarding this ICA. In addition, the customer may contact Garmin with questions regarding this
equipment and its installation. Garmin Customer Support may be contacted during normal business hours
via telephone 913-397-8200 or from the Garmin web site at www.flyGarmin.com.
2.19 Implementation and Record Keeping
Modification of an aircraft by this Supplemental Type Certificate obligates the aircraft operator to include
the maintenance information provided by this document in the operator’s aircraft maintenance manual
and/or the operator’s rotorcraft scheduled maintenance program.
190-01007-KB Rev.2
Instructions for Continued Airworthiness GTN 6XX/7XX - MD369E/F/FF
Page 19 of 21
4.
APPENDIX A - EQUIPMENT LOCATIONS AND WIRE ROUTING
The following diagram must be completed to depict the location of all LRUs and antenna(s) along with the wire routing for the GTN 6XX/7XX and
GMA 35 throughout the aircraft structure for the MD 369 Series rotorcraft. All harnesses fabricated as part of this STC should be included in this
diagram.
190-01007-KB Rev.2
Instructions for Continued Airworthiness GTN 6XX/7XX - MD369E/F/FF
Page 21 of 21
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