Garmin | GDL® 88 | Garmin GDL® 88 Instructions for Continued Airworthiness GDL 84/88 Part 23 AML STC

Garmin GDL® 88 Instructions for Continued Airworthiness GDL 84/88 Part 23 AML STC
Instructions for Continued Airworthiness
GDL 84/88 Part 23 AML STC
as installed in
(Make and Model Airplane)
Reg. No. ___________
S/N __________
Dwg. Number:
190-01310-01 Rev. 3
Garmin International, Inc.
1200 E. 151st Street
Olathe, Kansas 66062 USA
Record of Revision
Rev.
Date
1
2
3
11/21/2012
1/7/2015
10/22/2015
Description of Change
Initial Release
Updated to add GDL 84
Update to add Flight Stream
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  2012-2015 Garmin Ltd. or its subsidiaries. All rights reserved.
Garmin International, Inc.
1200 E. 151st Street
Olathe, Kansas 66062 U.S.A.
Page ii
Instructions for Continued Airworthiness GDL 84/88 Part 23 AML STC
190-01310-01 Rev. 3
Table of Contents
1.
2.
3.
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................................................................................................................................... 2
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ..................................................................... 2
2.1
Introduction.................................................................................................................................... 2
2.2
Description of Alteration ................................................................................................................ 2
2.3
Control, Operating, and Testing Information ................................................................................. 3
2.4
Servicing Information .................................................................................................................... 4
2.5
Periodic Maintenance .................................................................................................................... 4
2.6
Troubleshooting Information ......................................................................................................... 7
2.7
Removal and Replacement Information ........................................................................................ 7
2.8
Diagrams ....................................................................................................................................... 7
2.9
Special Inspection Requirements.................................................................................................. 8
2.10
Application of Protective Treatments ............................................................................................ 8
2.11
Data Relative to Structural Fasteners ........................................................................................... 8
2.12
Special Tools ................................................................................................................................. 8
2.13
Additional Instructions ................................................................................................................... 8
2.14
Overhaul Period ............................................................................................................................ 8
2.15
ICA Revision and Distribution ....................................................................................................... 8
2.16
Assistance ..................................................................................................................................... 8
2.17
Implementation and Record Keeping ............................................................................................ 8
AIRWORTHINESS LIMITATIONS SECTION ....................................................................................... 9
APPENDIX A
EQUIPMENT LOCATIONS AND WIRE ROUTING........................................................ 10
Table of Figures
Figure 1. GDL 84/88 System Block Diagram ................................................................................................ 3
Table of Tables
Table 1. Maintenance Intervals ..................................................................................................................... 4
Page iii
Instructions for Continued Airworthiness GDL 84/88 Part 23 AML STC
190-01310-01 Rev. 3
1.
INTRODUCTION
1.1 Purpose
This document is designed for use by the installing agency of the Garmin GDL 84/88 as Instructions for
Continued Airworthiness in response to 14 CFR §23.1529, and Part 23 Appendix G. This ICA includes
information required by the operator to adequately maintain the Garmin GDL 84/88 with optional Flight
Stream 110/210 installed under Approved Model List (AML) STC.
1.2 Scope
This document provides the Instructions for Continued Airworthiness for aircraft modified by the
installation of the Garmin GDL 84/88 with optional Flight Stream 110/210 under 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 2.15 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 GDL 84/88 with
optional Flight Stream 110/210 to use and reference appropriate STC documents to accomplish the
Instructions for Continued Airworthiness and show compliance with STC engineering data. 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)
2)
3)
4)
5)
6)
7)
8)
9)
10)
11)
12)
13)
14)
15)
16)
17)
18)
19)
20)
21)
22)
23)
ADS-B: Automatic Dependent Surveillance-Broadcast
AML: Approved Model List
BIT: Built-In Test
CDTI: Cockpit Display of Traffic Information
CFR: Code of Federal Regulations
CPU: Central Processing Unit
FAA: Federal Aviation Administration
GDL: Garmin Datalink Transceiver
GPS: Global Positioning System
ICA: Instructions for Continued Airworthiness
IM: Installation Manual
I/O: Input/Output
LRU: Line Replaceable Unit
MHz: Mega Hertz
PMI: Principal Maintenance Inspector
RX: Receive
SBAS: Satellite-Based Augmentation System
STC: Supplemental Type Certificate
TAS: Traffic Awareness System
TCAS: Traffic Collision Avoidance System
TSO: Technical Standard Order
TX: Transmit
UAT: Universal Access Transceiver
Page 1 of 12
Instructions for Continued Airworthiness GDL 84/88 Part 23 AML STC
190-01310-01 Rev. 3
1.6 Terminology
The GDL 84 is a remote-mounted unit available in one variant that does not support diversity (TSOC154c Class A1S) and contains an internal GPS/SBAS receiver.
The GDL 88 is a remote-mounted unit available in four variants. The variants support diversity
(TSO-C154c Class A1H) or do not support diversity (TSO-C154c Class A1S) and contain internal
GPS/SBAS receiver or utilizes external GPS/SBAS source.
Except where specifically noted, references made to the ‘GDL 84/88’ apply equally to all units: GDL 84,
GDL 88, GDL 88D, GDL 88 with GPS/SBAS, and GDL 88D with GPS/SBAS.
The Flight Stream 110 and Flight Stream 210 bring Bluetooth® connectivity to the cockpit, allowing
portable electronics to stream data to and from the installed avionics. Specific to the interface to the
GDL 84/88, the Flight Stream 110 and Flight Stream 210 provide FIS-B weather, ADS-B traffic, and GPS
position from the GDL 84/88 to portable electronics.
Except where specifically noted, references made to the ‘Flight Stream 110/210’ applies equally to the
Flight Stream 110 and Flight Stream 210.
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
GDL 84/88 and optional Flight Stream 110/210.
Applicability:
Applies to aircraft altered by installation of the
Garmin GDL 84/88 and optional Flight Stream
110/210.
Definition of Abbreviations:
See Section 1.5 and Section 1.6.
Precautions:
None
Units of measurement:
None
Referenced publications:
Garmin 190-01310-00 Rev. 6, “Installation
Manual, GDL 84/88 Part 23 AML STC” or later
revisions;
Garmin 190-01122-03 Rev. E, “GDL 84/88 ADS-B
Transceiver Pilot’s Guide” or later revisions.
Retention:
This document, or the information contained
within, will be included in the aircraft’s permanent
records.
The GDL 84/88 AML STC Installation Manual (190-01310-00) is referenced extensively throughout this
document. To improve readability, references to the installation manual are abbreviated as GDL-IM.
2.2 Description of Alteration
The GDL 84/88 is a remote-mounted UAT Datalink Transceiver that provide ADS-B functionality as part of
an ADS-B Out configuration, ADS-B In configuration, or ADS-B Out and In configuration. ADS-B Out
transmissions are via 978 MHz UAT and ADS-B In reception is via 978 MHz UAT and 1090 MHz
extended squitter. In addition, the GDL 88 correlates traffic from multiple sources and provides traffic to a
cockpit display (CDTI). The Flight Stream 110/210 interfaces with the GDL 84/88 through RS-422.
Installation configuration is dependent on desired functionality and access to required sensors and
Page 2 of 12
Instructions for Continued Airworthiness GDL 84/88 Part 23 AML STC
190-01310-01 Rev. 3
equipment and also antenna inputs. The GDL 84/88 System Block Diagram in Figure 1 shows the various
interfaces for the GDL 84/88.
Figure 1. GDL 84/88 System Block Diagram
2.3 Control, Operating, and Testing Information
See the GDL 84/88 Pilot’s Guide for system operating information. See Section 2.1 for document part
numbers. See GDL-IM for a system description and system limitations.
See GDL-IM, Section 5 for system configuration and checkout information. See GDL-IM, Sections 5.7 and
5.8 for general ground checks and system test procedures.
Page 3 of 12
Instructions for Continued Airworthiness GDL 84/88 Part 23 AML STC
190-01310-01 Rev. 3
2.4 Servicing Information
The GDL 84/88 and optional Flight Stream 110/210 do not require servicing.
2.5 Periodic Maintenance
All maintenance associated with the GDL 84/88 AML STC installation is on condition. The GDL 84/88 is
designed to detect internal failures. A thorough self-test is executed automatically upon application of
power to the unit, 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 GDL 84/88 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 GDL 84/88 should be
maintained in accordance with appropriate inspection data for the antenna installation.
Table 1. Maintenance Intervals
Item
Description/Procedure
Interval
Equipment Removal
& Replacement
Removal and replacement instructions for the GDL 84/88 are
contained in Section 2.7 of this document and in GDL-IM
Section 4.1.7.
Conduct a visual check of the GDL 84/88 unit, optional Flight
Stream 110/210, and associated wire harness to ensure
continued installation integrity.
On Condition
Equipment Visual
Check (Metallic
Aircraft)
12 Calendar
Months
1. Inspect the GDL 84/88 unit for security of attachment,
including visual inspection of mounting rack and other
supporting structure attaching the rack to aircraft
structure. For installations using countersunk
fasteners, verify the fastener heads are in full contact
with unit mounting rack holes. Re-torque mounting
fasteners to 12-15 in-lbs if required. If the Flight
Stream 110/210 is installed and screws are not
securely attached, tighten any loose Flight Stream
110/210 mounting screws as necessary to snug plus
one-quarter turn. If required, re-torque bonding strap
hardware to 12-15 in-lbs.
Note: Care should be taken when tightening the
mounting screws of the Flight Stream 110/210.
Excessive tightening may damage the mounting
flange.
2. Inspect for signs of corrosion.
3. Inspect condition of wiring, shield terminations,
routing, and attachment/clamping.
4. Inspect any bonding straps for corrosion, loose
connections, or signs of lightning damage. Rework as
needed.
Page 4 of 12
Instructions for Continued Airworthiness GDL 84/88 Part 23 AML STC
190-01310-01 Rev. 3
Item
Equipment Visual
Check (Non-metallic
Aircraft)
Description/Procedure
Conduct a visual check of the GDL 84/88 unit, optional Flight
Stream 110/210, and associated wire harness to ensure
continued installation integrity.
Interval
12 Calendar
Months
1. Inspect the GDL 84/88 unit for security of attachment,
including visual inspection of mounting rack and other
supporting structure attaching the rack to aircraft
structure. For installations using countersunk
fasteners, verify the fastener heads are in full contact
with unit mounting rack holes. Re-torque mounting
fasteners to 12-15 in-lbs if required. If the Flight
Stream 110/210 is installed and screws are not
securely attached, tighten any loose Flight Stream
110/210 mounting screws as necessary to snug plus
one-quarter turn. If required, re-torque bonding strap
hardware to 12-15 in-lbs.
Note: Care should be taken when tightening the
mounting screws of the Flight Stream 110/210.
Excessive tightening may damage the mounting
flange.
2. Inspect for signs of corrosion.
3. Inspect condition of wiring, shield terminations,
routing, and attachment/clamping.
4. For composite aircraft, inspect any aluminum foil tape
used to ground the GDL 84/88 and verify that it is not
torn, damaged or showing signs of corrosion. If any of
these occurs then the tape must be replaced.
5. Inspect any bonding straps for corrosion, loose
connections, or signs of lightning damage. Rework or
replace as needed. Bonding straps must be replaced
after a known or suspected lightning strike.
Page 5 of 12
Instructions for Continued Airworthiness GDL 84/88 Part 23 AML STC
190-01310-01 Rev. 3
Item
Electrical Bonding
Check
Description/Procedure
Perform an electrical bonding check for the GDL 84/88:
1. Perform electrical bond check between the GDL 84/88
and nearby exposed portion of the aircraft metallic
structure (or instrument panel for composite aircraft), and
verify that it is less than or equal to 10 milliohms.
Interval
Every 2000
flight hours or
ten (10) years,
whichever is
first
2. Remove GDL 84/88 unit from mounting rack.
3. Measure the resistance between the mounting rack and
nearby exposed portion of aircraft metallic structure (or
instrument panel for composite aircraft), and verify it is
less than or equal to 10 milliohms.
4. Reinstall the GDL 84/88 unit in the mounting rack.
In the event of bonding test failure, remove the GDL 84/88
rack and clean the attachment points at both the GDL 84/88
rack and the aircraft structure per Section 3.5.3 of the GDLIM and reattach the rack. Re-verify the resistance between
the mounting rack and nearby exposed portion of aircraft
metallic structure (or instrument panel for composite aircraft),
and ensure it is less than or equal to 2.5 milliohms (for
metallic aircraft) or 5.0 milliohms (for composite aircraft).
Perform an electrical bonding check for the
Flight Stream 110/210, if installed in metallic or tube/fabric
aircraft:
1. Disconnect the shield terminations from the Flight
Stream connector backshell.
2. Measure the resistance between the connector and
nearby exposed portion of aircraft metallic structure and
check that it is less than or equal to 20 milliohms.
In the event of bonding test failure, remove the Flight Stream
connector bonding strap from the aircraft ground plane and
clean the attachment point with a bonding brush. Re-attach
the bonding strap to the aircraft ground plane, torque to 1215 in-lbs. Re-check the resistance between the Flight Stream
connector and aircraft structure, ensuring that the resistance
is less than or equal to 10 milliohms. If cleaning the far side
of the strap is not enough, remove, clean, and reattach on
the Flight Stream 110/210 side.
3. Connect the shield terminations to the Flight Stream
connector backshell.
Page 6 of 12
Instructions for Continued Airworthiness GDL 84/88 Part 23 AML STC
190-01310-01 Rev. 3
Item
Description/Procedure
Perform an electrical bonding check for the
Flight Stream 110/210, if installed in composite aircraft:
Interval
1. Disconnect the shield terminations from the Flight
Stream connector backshell.
2. Measure the resistance between the connector and
instrument panel (or other aircraft ground) and check that
it is less than or equal to 20 milliohms.
In the event of bonding test failure, remove the Flight Stream
connector bonding strap from the aircraft ground plane and
clean the attachment point with a bonding brush. Re-attach
the bonding strap to the aircraft ground plane, torque to 1215 in-lbs. Re-check the resistance between the Flight Stream
connector and aircraft ground, ensuring that the resistance is
less than or equal to 10 milliohms. If cleaning the far side of
the strap is not enough, remove, clean, and reattach on the
Flight Stream 110/210 side.
3. Connect the shield terminations to the Flight Stream
connector backshell.
2.6 Troubleshooting Information
If error indications are displayed on the GDL 84/88 annunciator, refer to the GDL-IM, Section 6,
Troubleshooting. Refer to the GDL 84/88 System Configuration and Checkout Log retained in the aircraft
permanent records for a list of the interfaced equipment and system configuration data (example log
provided in GDL-IM).
2.7 Removal and Replacement Information
For GDL 84/88 removal and replacement instructions, refer to GDL-IM Section 4.1.7.
If the GDL 84/88 is removed and reinstalled, verify that the power-up self-test sequence is successfully
completed and no failure messages are annunciated. If any work has been done on the aircraft that could
affect the system wiring, or any interconnected equipment, verify the GDL 84/88 system unit power-up
self-test sequence is successfully completed and no failure messages are annunciated. Also, if any work
has been done on the GDL 84/88 mounting rack, verify the integrity of electrical bonding is maintained in
accordance with Section 2.5 of this document.
For ADS-B annunciator removal and replacement instructions, refer to GDL-IM, Section 4.1.8.
For Flight Stream 110/210 removal and replacement instructions, refer to GDL-IM Section 4.1.9.
Refer to Appendix A of this document or the GDL 84/88 System Configuration and Checkout Log retained
in the aircraft permanent records for GDL 84/88 and Flight Stream 110/210 (if installed) equipment
locations.
Refer to the GDL-IM for removal/installation procedures and special handling precautions.
2.8 Diagrams
The installing agency should document aircraft specific locations for all LRUs, optional equipment, and
antennas installed by this STC. The installing agency should also provide wire routing diagram sketches
for all GDL 84/88 system wiring and cables installed by this STC.
GDL-IM Section 4 provides diagrams showing sample installation for LRU locations. Appendix B provides
point-to-point wiring diagrams for the GDL 84/88 and interfaced equipment.
Page 7 of 12
Instructions for Continued Airworthiness GDL 84/88 Part 23 AML STC
190-01310-01 Rev. 3
Refer to the GDL 84/88 System Configuration and Checkout Log retained in the aircraft permanent
records for a list of the interfaced equipment and unit configuration data (example log provided in GDLIM).
2.9 Special Inspection Requirements
After a suspected lightning strike, the following actions must be performed (if applicable):



2.10
Verify proper operation of ADS-B equipment and Traffic annunciators (if installed) following
procedures in accordance with GDL-IM Section 5.7.9.2 Discrete Outputs.
Inspect any aluminum foil used for grounding (if installed) in accordance with GDL-IM Sections
3.5.1, 3.5.2, or Appendix G.
Inspect any GDL 84/88 bonding strap (if installed) in accordance with GDL-IM Sections 3.5 or
Appendix G.
Application of Protective Treatments
The GDL 84/88 installation does not require the application of protective treatments.
2.11
Data Relative to Structural Fasteners
Refer to the GDL-IM, Appendix E, for structural fastener information.
2.12
Special Tools
A milliohm meter is required for electrical bonding checks.
2.13
Additional Instructions
Refer to the GDL-IM, Section 3.6, for electrical load information.
2.14
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 GDL 84/88 system. If an internal failure is detected, the unit may be removed
and replaced. Reference the GDL-IM, Section 6, for troubleshooting information.
2.15
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). A Garmin Service Bulletin describing ICA revision will be sent to
Garmin dealers if a revision is determined to be significant.
2.16
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.
2.17
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 aircraft scheduled maintenance program.
Page 8 of 12
Instructions for Continued Airworthiness GDL 84/88 Part 23 AML STC
190-01310-01 Rev. 3
APPENDIX A
A.1
EQUIPMENT LOCATIONS AND WIRE ROUTING
Equipment Locations
The table below describes the location of the GDL 84/88, antennas, and interfaced equipment. Document
all interfaced equipment (model/part number) and installed locations in the following table. Also sketch
equipment locations and wire routing on the diagrams in A.2 or A.3 as appropriate.
LRU
Installed
Location
Description of Location
(F.S.)
GDL 84/88
Page 10 of 12
Instructions for Continued Airworthiness GDL 84/88 Part 23 AML STC
190-01310-01 Rev. 3
A.2
GDL 84/88 Installation – Single Engine
The following diagram depicts approximate location of all LRUs and antenna(s) along with the wire
routing for the GDL 84/88 and Flight Stream 110/210 (if installed) throughout the aircraft structure for a
single-engine aircraft.
Page 11 of 12
Instructions for Continued Airworthiness GDL 84/88 Part 23 AML STC
190-01310-01 Rev. 3
A.3
GDL 84/88 Installation – Twin Engine
The following diagram depicts approximate location of all LRUs and antenna(s) along with the wire
routing for the GDL 84/88 and Flight Stream 110/210 (if installed) throughout the aircraft structure for a
twin-engine aircraft:
Page 12 of 12
Instructions for Continued Airworthiness GDL 84/88 Part 23 AML STC
190-01310-01 Rev. 3
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