Garmin AT GDL90A1H GDL 90 Universal Access Transceiver User Manual 560 1049 00 Rev B GDL90 Install Manual

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GDL 90 UAT Data Link Sensor
Installation Manual
April 2004
560-1049-00 Rev B
 2004 Garmin Ltd. or its subsidiaries. All rights reserved. Printed in the U.S.A.
Garmin International, Inc., 1200 East 151st Street, Olathe Kansas 66062, U.S.A.
Tel: 913/397.8200
Fax: 913/397.8282
Garmin (Europe) Ltd., Unit 5, The Quadrangle, Abbey Park Industrial Estate, Romsey, Hampshire S051
9DL, U.K.
Tel: 44/1794.519944
Fax: 44/1794.519222
Garmin Corporation, No. 68, Jangshu 2nd Road, Shijr, Taipei County, Taiwan
Tel: 886/02.2642.9199
Fax: 886/02.2642.9099
Garmin AT, Inc., 2345 Turner Road, S.E., Salem, OR 97302, U.S.A.
Tel: 800/525.6726
Fax: 503/364.2138
Canada Tel: 800/654.3415
International Tel: 503/391.3411
Cage Code: 0XCJ6
Visit our web page at http://www.garmin.com
Send comments about this manual by email to: techpubs.salem@garmin.com
Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted,
disseminated, downloaded or stored in any storage medium, for any purpose without the express written
permission of Garmin. Garmin hereby grants permission to download a single copy of this manual and of
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complete text of this copyright notice and provided further that any unauthorized commercial distribution
of this manual or any revision hereto is strictly prohibited.
Information in this document is subject to change without notice. Garmin reserves the right to change or
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any person or organization of such changes or improvements.
Garmin, Garmin AT, and GDL are trademarks of Garmin Ltd. or its subsidiaries. These trademarks
may not be used without the express permission of Garmin.
HISTORY OF REVISIONS
Revision
-A
Date
3/17/04
4/07/04
4/30/04
Description
Initial release
Update environmental categories (1.3.3, A.1), FCC waiver (1.4.3),
APM p/n (Table 1-3). Add missing lines (Figure 2-1), APM weight
(Table 2-6), APM environmental qualification form (A.2).
Remove “STC Pending watermark”. Clarify output of data (1.2). Add
transmitter caution (1.3.7.2, 2.1, 2.5.2, 2.6.2, 2.8.1, 3.2.2, 4.). Add
washer to install kit (Table 1-3). Limit APM wire length to 4 inches,
clarify APM tests, update lightning categories (2.5.2, 2.8.2, A.1, A.2,
Fig C-1). Add exploded-view diagrams (Fig. 2-4, 2-5). Correct MX20
manual refs (4.2.2, 4.3.1.2.2).
ORDERING INFORMATION
To receive additional copies of GDL 90 publications, order the following part numbers:
GDL 90 Installation Manual
UAT Antenna Installation Guide
A-33 GPS Antenna Installation Guide
A-34 GPS Antenna Installation Guide
GDL 90 Product CD
GDL 90 Installation Manual
560-1049-xx
560-0215-xx
560-0949-xx
560-5047-xx
140-0063-xx
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GDL 90 Installation Manual
Table of Contents
TABLE OF CONTENTS
GENERAL INFORMATION ................................................................................................................................. 1-1
1.1
ABOUT THIS MANUAL .................................................................................................................................. 1-1
1.1.1
MANUAL ORGANIZATION ......................................................................................................................... 1-1
1.1.2
SCOPE ...................................................................................................................................................... 1-1
1.2
EQUIPMENT DESCRIPTION............................................................................................................................. 1-2
1.2.1
FEATURES ................................................................................................................................................ 1-2
1.2.2
SYSTEM INTERFACES ............................................................................................................................... 1-2
1.3
SPECIFICATIONS ............................................................................................................................................ 1-4
1.3.1
ELECTRICAL ............................................................................................................................................. 1-4
1.3.2
PHYSICAL................................................................................................................................................. 1-4
1.3.3
ENVIRONMENTAL..................................................................................................................................... 1-4
1.3.4
GPS/WAAS RECEIVER PERFORMANCE ................................................................................................... 1-5
1.3.5
UAT PERFORMANCE ............................................................................................................................... 1-5
1.3.6
AVIONICS INTERFACES ............................................................................................................................. 1-6
1.3.7
ANTENNA REQUIREMENTS ....................................................................................................................... 1-7
1.4
REGULATORY COMPLIANCE.......................................................................................................................... 1-9
1.4.1
TSO AND ADVISORY CIRCULAR REFERENCES ......................................................................................... 1-9
1.4.2
TSO AUTHORIZATION .............................................................................................................................. 1-9
1.4.3
FCC GRANT OF EQUIPMENT AUTHORIZATION ......................................................................................... 1-9
1.4.4
GDL 90 STC AUTHORIZATION .............................................................................................................. 1-10
1.5
UNPACKING THE EQUIPMENT ...................................................................................................................... 1-10
1.6
PACKAGE CONTENTS .................................................................................................................................. 1-10
1.7
DEFINITIONS & ACRONYMS ........................................................................................................................ 1-11
INSTALLATION ................................................................................................................................................. 2-1
2.1
PRE-INSTALLATION INFORMATION................................................................................................................ 2-1
2.2
INSTALLATION OVERVIEW ............................................................................................................................ 2-1
2.3
MATERIALS NOT SUPPLIED ........................................................................................................................... 2-1
2.3.1
MATERIALS REQUIRED BUT NOT SUPPLIED ............................................................................................. 2-1
2.4
SPECIAL TOOLS REQUIRED ........................................................................................................................... 2-2
2.5
EQUIPMENT MOUNTING ................................................................................................................................ 2-3
2.5.1
CABLING AND WIRING ............................................................................................................................. 2-3
2.5.2
MOUNTING TRAY INSTALLATION ............................................................................................................. 2-3
2.5.3
UNIT INSERTION & REMOVAL .................................................................................................................. 2-7
2.6
ANTENNA INSTALLATION AND CONNECTIONS .............................................................................................. 2-7
2.6.1
GPS ANTENNA......................................................................................................................................... 2-8
2.6.2
UAT ANTENNAS ...................................................................................................................................... 2-9
2.7
ELECTRICAL CONNECTIONS ........................................................................................................................ 2-10
2.7.1
INTERFACE CONNECTOR DEFINITION ..................................................................................................... 2-11
2.8
FUNCTIONAL DESCRIPTIONS ....................................................................................................................... 2-14
2.8.1
POWER ................................................................................................................................................... 2-14
2.8.2
MICRO AIRCRAFT PERSONALITY MODULE (µAPM) .............................................................................. 2-14
2.8.3
STATUS LEDS ........................................................................................................................................ 2-14
2.8.4
DISCRETE OUTPUT ................................................................................................................................. 2-15
2.8.5
DISCRETE INPUTS................................................................................................................................... 2-16
2.8.6
SERIAL INTERFACES ............................................................................................................................... 2-17
2.8.7
AUDIO .................................................................................................................................................... 2-18
2.8.8
SUPPRESSION OUTPUT ........................................................................................................................... 2-18
2.9
WEIGHT AND BALANCE .............................................................................................................................. 2-19
2.10
ELECTRICAL LOAD ANALYSIS ..................................................................................................................... 2-21
LIMITATIONS ................................................................................................................................................... 3-1
3.1
OPERATION ................................................................................................................................................... 3-1
3.2
INSTALLATION .............................................................................................................................................. 3-1
3.2.1
GPS ANTENNA......................................................................................................................................... 3-1
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3.2.2
3.2.3
3.2.4
3.2.5
UAT ANTENNA ........................................................................................................................................3-1
ANTENNA INSTALLATION – GENERAL ......................................................................................................3-1
EQUIPMENT INTERFACED TO THE GDL 90................................................................................................3-2
PRESERVATION OF PREVIOUS SYSTEMS....................................................................................................3-2
POST INSTALLATION CONFIGURATION & CHECKOUT PROCEDURES ............................................................4-1
4.1
MOUNTING AND WIRING CHECK ...................................................................................................................4-1
4.2
EQUIPMENT SETUP AND CONFIGURATION .....................................................................................................4-1
4.2.1
MAINTENANCE MODE ..............................................................................................................................4-2
4.2.2
MX20 SETUP ............................................................................................................................................4-7
4.3
EQUIPMENT OPERATIONAL/FUNCTIONAL TEST .............................................................................................4-7
4.3.1
SYSTEM CHECKOUT – GROUND CHECKS ..................................................................................................4-7
5.1
5.2
TROUBLESHOOTING .........................................................................................................................................5-1
TROUBLESHOOTING PROCEDURE ..................................................................................................................5-1
CONTACTING THE FACTORY FOR ASSISTANCE ..............................................................................................5-2
6.1
6.2
6.3
PERIODIC MAINTENANCE ................................................................................................................................6-1
EQUIPMENT CALIBRATION ............................................................................................................................6-1
CLEANING .....................................................................................................................................................6-1
BATTERY REPLACEMENT ..............................................................................................................................6-1
APPENDIX A - CERTIFICATION DATA .......................................................................................................................1
A.1
GDL 90 ENVIRONMENTAL QUALIFICATION......................................................................................................1
A.2
MICRO APM ENVIRONMENTAL QUALIFICATION ..............................................................................................2
APPENDIX B - TROUBLESHOOTING FLOWCHARTS ..................................................................................................1
APPENDIX C - INTERCONNECT DIAGRAMS ..............................................................................................................1
APPENDIX D - CONSTRUCTION & VALIDATION OF STRUCTURES ...............................................................................1
LIST OF TABLES
TABLE 1-1. TSO AUTHORIZATION.............................................................................................................1-9
TABLE 1-2. PACKAGE CONTENTS ............................................................................................................1-10
TABLE 1-3. INSTALLATION KIT CONTENTS (PN 424-6081-100) .............................................................1-10
TABLE 1-4. OPTIONAL PARTS ..................................................................................................................1-11
TABLE 2-1. CRIMP TOOL FOR P/N 245-0027 .............................................................................................2-2
TABLE 2-2. INTERFACE CONNECTORS .....................................................................................................2-10
TABLE 2-3. CRIMP CONTACT SPECIFICATIONS ........................................................................................2-10
TABLE 2-4. MAIN SYSTEM CONNECTOR PIN-OUT (P1)...........................................................................2-12
TABLE 2-5. I/O CONNECTOR PIN-OUT (P2) .............................................................................................2-13
TABLE 2-6. UNIT WEIGHTS ......................................................................................................................2-19
TABLE 2-7. UNIT POWER LOADS .............................................................................................................2-21
TABLE 4-1. MAINTENANCE MODE COMMANDS ........................................................................................4-2
TABLE 4-2. DATA ITEMS FOR APM INITIALIZATION .................................................................................4-4
TABLE 4-3. GDL 90 POST-INSTALLATION CHECKOUT LOG ....................................................................4-10
TABLE 5-1. TROUBLESHOOTING GUIDE.....................................................................................................5-1
TABLE D-1. STATIC TEST LOAD ...................................................................................................................1
LIST OF ILLUSTRATIONS
FIGURE 1-1.
FIGURE 2-1.
FIGURE 2-2.
FIGURE 2-3.
iv
SAMPLE GDL 90 SYSTEM DIAGRAM .....................................................................................1-3
SINGLE ENGINE AIRCRAFT GDL 90 MOUNTING LOCATIONS................................................2-4
MULTI-ENGINE AIRCRAFT GDL 90 MOUNTING LOCATIONS ................................................2-4
GDL 90 MOUNTING TRAY & DIMENSIONS ...........................................................................2-5
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FIGURE 2-4: GDL 90 TRAY & CONNECTORS ............................................................................................ 2-6
FIGURE 2-5: GDL 90 TRAY & OPTIONAL COVER ..................................................................................... 2-7
FIGURE 2-6. ANTENNA PLACEMENT.......................................................................................................... 2-8
FIGURE 2-7. RIGHT ANGLE COAX CONNECTOR ASSEMBLY ..................................................................... 2-9
FIGURE 2-8. REAR CONNECTOR LAYOUT................................................................................................ 2-11
FIGURE 2-9. 15-PIN CONNECTOR ............................................................................................................ 2-12
FIGURE 2-10. 37-PIN CONNECTOR ........................................................................................................... 2-13
FIGURE 2-11. GDL 90 CENTER OF GRAVITY........................................................................................... 2-20
FIGURE C-1. INTERCONNECT DIAGRAM FOR INSTALLATION W/ MX20 MFD.............................................. 3
FIGURE D-2. UPWARD STATIC LOAD TEST .................................................................................................. 2
FIGURE D-3. FORWARD STATIC LOAD TEST ................................................................................................ 2
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General Information
1 GENERAL INFORMATION
1.1 ABOUT THIS MANUAL
This manual describes the installation and checkout procedures for the GDL 90 UAT Data Link Sensor.
It is intended for use by persons certified by the Federal Aviation Administration (FAA) to install
avionics devices.
1.1.1
MANUAL ORGANIZATION
SECTION 1
Provides GENERAL INFORMATION about the GDL 90 unit. TSO certification
information is also included in this section.
SECTION 2
Includes INSTALLATION PROCEDURES.
SECTION 3
Includes LIMITATIONS for the equipment and installation.
SECTION 4
Includes POST-INSTALLATION CONFIGURATION AND CHECKOUT.
SECTION 5
Includes TROUBLESHOOTING information.
SECTION 6
Includes PERIODIC MAINTENANCE requirements.
APPENDIX A
Includes CERTIFICATION DATA.
APPENDIX B
Includes TROUBLESHOOTING FLOWCHARTS.
APPENDIX C
Includes INTERCONNECT DIAGRAMS.
APPENDIX D
Includes CONSTRUCTION & VALIDATION of structures.
1.1.2
SCOPE
The information in this manual is STC approved. Only the equipment interfaces covered in this manual
are within the scope of this STC. Other equipment may be suitable for use with the GDL 90, but use of
such equipment is beyond the scope of this STC – additional FAA approval may be required if equipment
not covered in this manual is used to interface to the GDL 90.
Antenna installation in the pressure vessel of pressurized aircraft is also beyond the scope of the GDL 90
STC. Additional manufacturer's data may be necessary and FAA approval may be required to cover the
installation of the antenna.
Refer to Section 3 Limitations for additional information.
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1.2 EQUIPMENT DESCRIPTION
The Garmin GDL 90 is a remote-mounted product that contains a GPS/WAAS engine and a Universal
Access Transceiver. The GDL 90 will transmit ownship data via the UAT data link. It will receive data
from other UAT-equipped aircraft, as well as FIS-B weather – the received data may be output to an
appropriate display.
1.2.1
FEATURES
The features of the GDL 90 UAT Data Link Sensor include:
• 10-40 VDC Power Capability
•
978 MHz Universal Access Transceiver data link radio designed to support ADS-B, TIS-B and FIS-B
airborne and ground applications
•
GPS/WAAS engine for state-of-the-art fast, accurate navigation and precision approach (15-channel,
3 WAAS decoders, 5 Hz update of position, time, and velocity)
•
Interface to Altitude Encoder via RS232 bus
•
Interface to Garmin MX20 Multi-function Display
1.2.2
SYSTEM INTERFACES
The interfaces for a typical GDL 90 are shown in Figure 1-1. The available interfaces are further
described in the following sections.
1-2
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Figure 1-1. Sample GDL 90 System Diagram
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General Information
1.2.2.1
Multi-function Display
The GDL 90 is capable of driving one MX20 Display with traffic and weather information.
1.2.2.2
Altitude Encoder
The GDL 90 is capable of interfacing to an altitude encoder to obtain altitude data via a RS232 bus.
1.2.2.3
Annunciator Outputs and Switch Inputs
The GDL 90 can drive one external annunciator lamp and receive inputs from various switches to control
its operation.
1.2.2.4
Maintenance Interface
The GDL 90 has a RS232 communication port that is used to configure and check status of the GDL 90
system. Refer to other sections of this manual for more description.
1.2.2.5
Audio Alert
The GDL 90 has one 500 Ω audio output that can be connected to an audio panel to provide audible
messages to the pilot. This is a future feature and currently not operational.
1.3 SPECIFICATIONS
This section includes detailed electrical, physical, environmental and performance specifications for the
GDL 90.
1.3.1
ELECTRICAL
Input voltage.................................................. 10 - 40 VDC
Input current (typical) ................................... 1.5 A at 14 VDC
750 mA at 28 VDC
1.3.2
PHYSICAL
Height............................................................ 7.42 inches (18.84 cm)
Width............................................................. 3.54 inches (8.97 cm)
Depth............................................................. 12.64 inches (32.11 cm)
Weight........................................................... 6.4 lb (2.9 kg) with mounting tray
1.2 lb (0.54 kg) mounting tray only
1.3.3
ENVIRONMENTAL
The GDL 90 is designed and tested to meet appropriate categories as shown in the Environmental
Qualification Form included in Appendix A.
Operating temperature................................... -20°C to +55°C
Storage temperature ...................................... -55°C to +85°C
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Temperature variation....................................5°C per minute
Humidity ........................................................95% at 65°C
Maximum continuous altitude .......................55,000 feet
Decompression ..............................................55,000 feet
External Cooling............................................Not required with internal fans operational and
vents unobstructed
Water-resistant...............................................with vertical mounting and optional cover
1.3.4
GPS/WAAS RECEIVER PERFORMANCE
TSO Compliance ...........................................TSO-C145a (RTCA/DO-229C)
Number of channels.......................................15 (12 GPS and 3 GPS/WAAS/SBAS)
Frequency ......................................................1575.42 MHz L1, C/A code
Sensitivity (acquisition).................................-116 dBm to -134.5 dBm GPS
-116 dBm to -135.5 dBm WAAS
Sensitivity (drop lock) ...................................-144 dBm
Dynamic range...............................................> 20 dB
Lat/Long position accuracy ...........................<1 meter RMS typical with WAAS
(horizontal/vertical)
Velocity .........................................................1000 knots maximum (above 60,000 ft)
TTFF (time to first fix) ..................................1:45 min. typical with current almanac, position, and
time
Reacquisition ....................................10 seconds typical
Position update interval ....................0.2 sec (5 Hz)
1 pps (pulse per second) ...................±275 nsec of UTC second
Datum ...............................................WGS-84
SATCOM compatibility ...................Compatible on aircraft equipped with SATCOM
Antenna power supply ......................35 mA typical, 40 mA max at 4.7 VDC
1.3.5
UAT PERFORMANCE
TSO Compliance ...........................................TSO-C154 (RTCA/DO-282)
Frequency ...................................................... 978.00 MHz
Transmit Power.............................................. 50 W (+47 dBm)
Frequency Tolerance .....................................+/- 20 PPM
Modulation.....................................................Continuous Phase FSK, h = 0.6, Raised Cosine
shaping, a = 0.5
Data Rate .......................................................1.04 Mbps
99% Power Bandwidth ..................................1.3 MHz
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60 dB bandwidth ........................................... 3.3 MHz (estimated)
Receiver Sensitivity ...................................... -96 dBm for 90% MSR
1.3.6
AVIONICS INTERFACES
Annunciator Outputs ..................................... Open collector output capable of sinking up to 400
mA for turning ON annunciator lamp
Multi-function Display.................................. RS-422 asynchronous serial
Altitude Encoder ........................................... RS-232 asynchronous serial
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1.3.7
ANTENNA REQUIREMENTS
1.3.7.1
GPS Antennas
1.3.7.1.1 A-33 (590-1104)
Early production runs of PN 590-1104 were marked with TSO-C129a. This antenna was re-qualified to
TSO-C144 with no changes to the antenna. P/N 590-1104 antennas marked with TSO-C129a
identification are identical to those marked with TSO-C144.
Applicable TSO: .........................................................TSO-C144 (RTCA/DO-228 with Change No. 1)
Frequency: .....................................................1575 MHz
Polarization:...................................................Right Hand Circular
Axial Ratio:....................................................3 dB Max at bore site
Radiation Coverage: ......................................Elevation Angle
Minimum Gain
>15º
10º
5º
0º
-2.0 dBic
-3.0 dBic
-4.5 dBic
-7.5 dBic
Finish: ............................................................Polyurethane Enamel
Weight: .........................................................3.9 oz. (0.11 kg)
Height: ..........................................................0.61 inches (1.55 cm)
Operating Temperature: ................................-55°C to +85°C
Operating Altitude: .......................................55,000 feet (16,764m) max.
Amplifier:
Gain.........................................................26.5 dB ±2 dB
Noise Figure:...........................................2.5 dB Max
Impedance: ..............................................50 ohms
VSWR (Dry): ..........................................< 1.5:1
VSWR (Rain):.........................................< 2.0:1
Band Rejection:.......................................35 dB
Power Handling: .....................................1 Watt
Voltage:...................................................5 VDC ±10%
Current: ...................................................35 mA nominal, 40 mA max.
L1 Filter Bandwidth .........................1575 ±20 MHz (3 dB)
+110, -210 MHz (60dB)
Group Delay (3dB bandwidth)................27 ±10 nanosecond
Pass Band Ripple (3dB bandwidth) …….0.2 dB max
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General Information
1.3.7.1.2 A-34 (590-1112)
Early production runs of PN 590-1112 were marked with TSO-C129a. This antenna was re-qualified to
TSO-C144 with no changes to the antenna. P/N 590-1112 antennas marked with TSO-C129a
identification are identical to those marked with TSO-C144.
Applicable TSO: ........................................................ TSO-C144 (RTCA/DO-228 with Change No. 1)
Frequency:..................................................... 1575 MHz
Polarization: .................................................. Right Hand Circular
Axial Ratio: ................................................... 3 dB Max at bore site
Radiation Coverage:...................................... Elevation Angle
Minimum Gain
>15º
10º
5º
0º
-2.0 dBic
-3.0 dBic
-4.5 dBic
-7.5 dBic
Finish:............................................................ Polyurethane Enamel
Weight: ......................................................... 7.0 oz. (0.2 kg)
Height: .......................................................... 0.66 inches (1.76 cm)
Operating Temperature: ............................... -55°C to +85°C
Operating Altitude: ...................................... 55,000 feet (16,764m) max.
Amplifier:
Gain ........................................................ 26.5 dB ±2 dB
Noise Figure: .......................................... 2.5 dB Max
Impedance:.............................................. 50 ohms
VSWR (Dry):.......................................... < 1.5:1
VSWR (Rain): ........................................ < 2.0:1
Band Rejection: ...................................... 35 dB
Power Handling:..................................... 1 Watt
Voltage: .................................................. 5 VDC ±10%
Current:................................................... 35 mA nominal, 40 mA max.
L1 Filter Bandwidth................... ............ 1575 ±20 MHz (3 dB)
+110, -210 MHz (60dB)
Group Delay (3dB bandwidth) ............... 27 ±10 nanosecond
Pass Band Ripple (3dB bandwidth) …….0.2 dB max
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General Information
1.3.7.2
UAT Antenna
The GDL 90 requires a UHF antenna meeting the following specifications:
• Standard 50Ω vertically polarized antenna with a VSWR < 1.7:1 at 978 Mhz
•
TSO-C66, C74, C112 or C154 antennas that also meet the VSWR specification.
NOTE
Certain types of transponder antennas that utilize very thin radiator elements are only
intended for use at 1030 and 1090 MHz. These types of antennas should be evaluated on
a model-by-model basis to determine their suitability as UAT data link antennas.
CAUTION
Operating the GDL 90 with no RF terminations on the Top or Bottom UAT Antenna
ports can result in equipment damage. Always operate the GDL 90 with the Top and
Bottom UAT Antenna ports terminated with a VSWR ratio of 3.0:1 or less.
1.4 REGULATORY COMPLIANCE
1.4.1
•
•
TSO AND ADVISORY CIRCULAR REFERENCES
TSO-C154
Universal Access Transceiver (UAT) Automatic Dependent Surveillance –
Broadcast (ADS-B) Equipment Operating on the Frequency of 978 MHz.
TSO-C145A Airborne Navigation Sensors using GPS Augmented by WAAS
NOTE
Unauthorized changes or modifications to the GDL 90 may void the compliance to
required regulations and authorization for continued equipment usage.
1.4.2
TSO AUTHORIZATION
Table 1-1. TSO Authorization
Function
UAT
Transceiver
GPS/WAAS
1.4.3
TSO
TSO-C154, Class A1H, B1
Minimum Performance
Standard
RTCA/DO-282
Software
RTCA/DO-178B
TSO-C145A, Class 1
RTCA/DO-229C, Class 1
Level B
Level B,C
FCC GRANT OF EQUIPMENT AUTHORIZATION
• FCC regulations for UAT are not yet finalized. The GDL 90 meets the proposed FCC
regulations and international agency proposed regulations. Garmin AT has applied for a waiver
for UAT use in the United States during the interim until FCC regulations are adopted. Testing
was completed on the GDL 90 Universal Access Transceiver and documented in PD3621, GDL
90 UAT FCC Certification Report. The data show compliance with FAA TSO-154 and FCC
proposed rules to Parts 2 and 87 as commented in Docket No. 01-289. The data further
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General Information
demonstrate that the GDL 90 is compatible with existing FCC regulations in 47 CFR2 and 47
CFR87.
• Use of UAT for government programs, such as Capstone Phase 1 and Phase 2 in Alaska, has
been fully coordinated with NTIA, and is authorized. In December of 2000, the RTCA created
Working Group 5 of Special Committee 186, to develop and approve the Minimum Operational
Performance Standards for the UAT data link. The effort was completed in June 2002. As part
of this effort, the NTIA has granted Stage 4 spectrum certification for use of the UAT data link
using a radio frequency of 978 MHz.
1.4.4
GDL 90 STC AUTHORIZATION
Refer to the GDL 90 Product CD 140-0063-xx for data regarding GDL 90 STC authorization.
1.5 UNPACKING THE EQUIPMENT
Carefully unpack the equipment. Visually inspect the package contents for any evidence of shipping
damage. Retain all shipping containers and packaging material in case reshipment is necessary.
1.6 PACKAGE CONTENTS
As shipped from the Garmin AT factory, the GDL 90 package includes most necessary items for
installation other than supplies normally available at the installation shop, such as wire and cable ties,
circuit breakers, and required input and output equipment. The items included in the package are listed in
Table 1-2 and Table 1-3. In addition, Table 1-4 lists optional parts that may be needed for non-standard
installations.
Table 1-2. Package Contents
Part #
424-6081-1xx
430-6081-1xx-xxx
140-0063-xx
590-1104
590-0051
Qty
Description
GDL 90 Installation Kit (see Table 1-3 for detail)
GDL 90 UAT Data Link Sensor
GDL 90 Product CD
A33 GPS Antenna
UAT Blade Antenna, passive, TNC
Table 1-3. Installation Kit Contents (PN 424-6081-100)
Part #
162-0043
265-0007
240-0008
162-1574
162-1575
162-1577
162-2080
202-0002
224-0404
245-0027
310-0461-00
310-0462-00
430-6200-000
660-0014
1-10
Qty
25
50
Description
Connector, coax, RA, PNL MNT
Retainer Ring, ext,7/16 shaft
Washer, 0.446 ID 0.56 OD
Receptacle DSUB 9-pin
Receptacle DSUB 15-pin
Receptacle DSUB 37-pin
Connector, coax, RA, plug clamp, TNC
Cable tie
Screw, 4-40 x 1/4 SS flat head Phillips 82 deg.
Crimp contact, DSUB, 20 to 24 AWG wire
Cover Mounting Tray GDL 90
Mounting Tray GDL 90
Aircraft Personality Module (APM)
Cable, coax RG400 dbl shld 50-ohm (feet)
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General Information
Table 1-4. Optional Parts
Part #
310-0467-xx
500-0290-xx
560-1057-xx
Description
Capstone Phase 1 Adapter Plate
Capstone Phase 1 Adapter Cable
GDL 90 Capstone Upgrade Instructions
1.7 DEFINITIONS & ACRONYMS
ADC
AHRS
ALT
APM
EN
GPS
MFD
STC
TSO
UAT
WAAS
Air Data Computer
Attitude Heading Reference System
Altitude
Aircraft Personality Module
Engineering Notice
Global Positioning System
Multi-Function Display
Supplementary Type Certificate
Technical Standard Order
Universal Access Transceiver
Wide Area Augmentation System
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General Information
NOTES
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Installation Procedures
2 INSTALLATION
This section describes the installation of the GDL 90 including mounting, wiring, and connections. PostInstallation configuration and checkout procedures are included in Section 3.
2.1 PRE-INSTALLATION INFORMATION
Always follow acceptable avionics installation practices per FAA Advisory Circulars (AC) 43.13-1B,
43.13-2A, or later FAA approved revisions of these documents.
Follow the installation procedure in this section as it is presented for a successful installation. Read the
entire section before beginning the procedure. Prior to installation, consider the structural integrity of the
GDL 90 installation as defined in AC 43.13-2A, Chapter 1. Perform the post installation checkout before
closing the work area in case problems occur.
Complete an electrical load analysis in accordance with AC 43.13-1B, Chapter 11, on the aircraft prior to
starting modification to ensure aircraft has the ability to carry the GDL 90 load. Refer to Section 2.10 for
the power consumption of each GDL 90 mode of operation. Document the results of the electrical load
analysis on FAA Form 337.
The WAAS/GPS installation instructions have been prepared to meet the guidance material defined in
AC20-138A Airworthiness Approval of Global Navigation Satellite System (GNSS) Equipment.
CAUTION
Operating the GDL 90 with no RF terminations on the Top or Bottom UAT Antenna
ports can result in equipment damage. Always operate the GDL 90 with the Top and
Bottom UAT Antenna ports terminated with a VSWR ratio of 3.0:1 or less.
2.2 INSTALLATION OVERVIEW
A successful installation should start with careful planning, including determination of mounting location
for the GDL 90, cable routing, and other required modifications. Once the mounting location has been
determined, prepare the mounting tray for installation. It may be easier to complete the wiring harness
and attach the connectors to the tray upon installation.
2.3 MATERIALS NOT SUPPLIED
2.3.1
MATERIALS REQUIRED BUT NOT SUPPLIED
The GDL 90 is intended for use with standard aviation accessories. The following items are required for
the installation, but not supplied:
•
Wire (MIL-W-22759/16 or equivalent)
•
Shielded wire (MIL-C-27500 or equivalent)
•
Circuit breakers
•
Ring terminals (for grounding)
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Installation Procedures
2.4 SPECIAL TOOLS REQUIRED
Some of the connectors use crimp contacts. The tables below identify crimp tools required to ensure
consistent, reliable crimp contact connections for the rear D-sub connectors. The tables define one source
for the crimp tool. Alternate equivalent tools may be used.
Table 2-1. Crimp Tool for P/N 245-0027
Description
Insertion/Extraction tool CIET-20HD
Crimp tool
Positioner
ITT/Cannon P/N
980-200-426
995-0001-584
995-0001-604
Military number
M81969/39-01
M22520/2-01
M22520/2-08
Below is the contact for ITT/Cannon crimp tools:
ITT Cannon
Phone (714) 261-5300
1851 E. Deere Ave
FAX (714) 575-8324
Santa Ana, CA 92705-6500
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Installation Procedures
2.5 EQUIPMENT MOUNTING
2.5.1
CABLING AND WIRING
Wiring should be installed in accordance with AC 43.13-1B Chapter 11. When wire separation cannot be
achieved, the following issues should be addressed:
• The cable harness should not be located near flight control cables and controls, high electrical
capacity lines or fuel lines
• The cable harness should be located in a protected area of the aircraft
• Do not route cable near high-energy sources
Refer to the interconnection diagrams in Appendix C for the appropriate wiring. Once the cable
assemblies have been made, attach the cable connectors to the rear of the mounting tray. Route the wiring
bundle as appropriate. Use 22 to 24 AWG wire for all connections except for power. Use 20 AWG for
power/ground. Avoid sharp bends.
2.5.2
MOUNTING TRAY INSTALLATION
The GDL 90 does not require forced-air cooling; however, when mounting the GDL 90, avoid locating
the GDL 90 near sources that produce high levels of heat. The tray can be installed in a variety of
locations, such as the electronics bay, under a seat or behind the rear baggage area. Refer to Figure 2-1
and Figure 2-2 for suggested location. Leave sufficient clearance between the GDL 90 and any
obstruction. Install tray in accordance with AC 43.13-2A Chapter 2 Radio Installations. Tray should be
mounted to a surface known to have sufficient structural integrity to withstand additional inertia forces
imposed by a 6.4-pound unit. If it is necessary to build a shelf or bracket to mount the GDL 90 tray or it
is not certain that the chosen location is of sufficient structural integrity, refer to Appendix D.
Refer to Figure 2-3 for the GDL 90 tray dimensions. The tray can be mounted vertically using four 8-32
pan head screws (MS35206, AN526 or equivalent.) It can also be mounted horizontally using four 6-32
100° counter-sunk flathead screws (MS24693, AN507R or equivalent.) Install tray in accordance with
AC 43.13-2A Chapter 2 Radio Installations. Ensure that the GDL 90 chassis have a ground path to the
airframe by having at least one mounting screw in contact with the airframe. If more water-resistance is
desired, tray should be installed in the upright vertical orientation only, otherwise, tray may be mounted
in either vertical or horizontal orientation.
After the cable assemblies are made and wiring installed to the mounting tray back plate, route wiring
bundle as appropriate. Use cable ties to secure the cable assemblies and coax to the holes provided in the
side of the connector plate to provide strain relief for the cable assemblies. The cable shields should be
grounded directly to a lug mounted to one of the holes on the side of the connector plate, keeping the
ground leads to a maximum of 3 inches long.
The APM may be fastened to the back of the tray next the 37-pin connector using cable ties through any
of the four holes provided in the backplate. Refer to Figure 2-4. The APM wire length must be 4 inches
maximum.
Optional cover is provided for installations that need extra moisture protection. Install cover to aft side
of tray using 4 screws that are part of the mounting tray. Refer to Figure 2-5.
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Installation Procedures
Figure 2-1. Single Engine Aircraft GDL 90 Mounting Locations
Figure 2-2. Multi-Engine Aircraft GDL 90 Mounting Locations
2-4
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Installation Procedures
Figure 2-3. GDL 90 Mounting Tray & Dimensions
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Installation Procedures
Figure 2-4: GDL 90 Tray & Connectors
CAUTION
Operating the GDL 90 with no RF terminations on the Top or Bottom UAT Antenna
ports can result in equipment damage. Always operate the GDL 90 with the Top and
Bottom UAT Antenna ports terminated with a VSWR ratio of 3.0:1 or less.
2-6
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Installation Procedures
Figure 2-5: GDL 90 Tray & Optional Cover
2.5.3
UNIT INSERTION & REMOVAL
Position the GDL 90 in the mounting tray and slide the unit fully into the tray. Turn the DZUS fastener
on the front bottom of the GDL 90 clockwise ¼ turn to lock in the unit. If the DZUS fastener is hard to
turn or the unit does not seat fully, the unit is probably binding and the mounting tray and position of the
unit should be checked.
To remove the unit from the mounting tray, turn the DZUS fastener counter-clockwise ¼ turn then pull
the unit from the tray. No special extraction tools are required.
2.6 ANTENNA INSTALLATION AND CONNECTIONS
The GDL 90 requires three antennas (GPS antenna and two UAT antennas) for Class A1 and B1. SingleUAT-antenna installation is allowed if the aircraft meets all flight test requirements over all normal
maneuvers. Garmin AT strongly recommends two UAT antennas be used for all installations. Follow the
antenna manufacturer’s installation instructions for mounting the antennas.
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Installation Procedures
Figure 2-6. Antenna Placement
2.6.1
GPS ANTENNA
The mounting location and cable connections for the GPS antenna are very important. The antenna
should be mounted no closer than two feet from VHF comm transmitter antennas, six inches from other
antennas emitting less than 25 watts, and two feet from higher power antennas. See A-33 GPS Antenna
Installation Manual, p/n 560-0949-xx for more information. Special care should be taken to ensure that
the GPS antenna is not mounted in close proximity to antennas that may emit harmonic interference at the
L1 frequency of 1575.42 MHz. Refer to AC 20-138A Airworthiness Approval of Global Navigation
Satellite System (GNSS) Equipment for additional information and guidelines.
The connectors and RG-400 coax cable are included in the installation kit. Assembly instructions for the
connectors are included in Figure 2-7. RG-400 cable can be used as long as the length is less than 35 feet. For
longer lengths, use low-loss 50Ω coax.
Suggestion: Temporarily locate the GPS antenna with coax connected to the GDL 90 and check the GPS
performance as described in the GPS Operation and Position test in the Post Installation Checkout
Section. Once a suitable location has been verified, permanently mount the antenna.
NOTE
If using a GPS antenna that was already on the aircraft, or if mounting the antenna closer
than recommended distance from a comm antenna, conduct the GPS Operation and
Position test in the Post Installation Checkout. If the GDL 90 passes the test, then further
measures are not necessary.
Once the antenna mounting position has been prepared, route the coax cable from the antenna to the GDL
90. Proper selection of coax cable and assembly of connectors is critical to GPS signal performance. The
cable loss from the GPS antenna shall not be greater than 7 dB. If SatCom is installed on the aircraft, the
cable loss shall be 3 dB minimum to ensure proper interference rejection from SatCom. The coaxial
connectors and adapters, such as TNC to BNC and GPS splitter, add additional loss to the cable and
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Installation Procedures
should be considered when computing the cable loss. A typical loss of -0.2 dB can be used for each
connection. The typical cable loss for 20 feet of RG-400 coax with a connector one each end is 4 dB.
During the post-installation checkout, susceptibility to harmonics of VHF comm. transmitters will be
evaluated. If problems arise, then better isolation, or distance, may be required between the GPS and
comm antennas, or a 1575.42 MHz notch filter may be installed in series with the antenna coax of the
VHF comm transceiver to reduce or eliminate the harmonic interference. A notch filter (part #162-1059)
is available from Garmin AT.
If a VHF comm transmitter causes problems with the GPS on the selected frequencies as listed in the
post-installation checkout, the problem may be due to the ELT. This can be verified by disconnecting the
ELT antenna coax at the ELT unit. If the ELT is found to cause the problem, then contact the ELT
manufacturer or replace the ELT.
Shield 0.250
Cable
1.000
0.125
STEP 1
Insulation
-Slide shrink tube over cable.
-Strip cable as shown.
Shrink
Tube
.125
STEP 2
-Flare Outer Shield as Shown
Cap
Solder Outer Shield
to Connector
Matching Ring
Solder Center
Conductor
STEP 3
-Place cable in connector as shown placing inner
shield inside connector.
-Flatten outer shield against connector.
-Solder outer shield to connector.
-Solder center conductor
-Slide matching ring into connector and around
conductor.
-Attach cap.
Solder Cap
2 Places
STEP 4
-Solder cap into place, 2 Places.
-Shrink tube as shown.
Figure 2-7. Right Angle Coax Connector Assembly
2.6.2
UAT ANTENNAS
The UAT antenna is a standard 50Ω vertically polarized L-band antenna that operates at 978 MHz. Any
antenna meeting the requirements of TSO-C66, C74, C112 or C154 and presenting a VSWR of less than
1.7:1 at 978 Mhz is acceptable. Follow the antenna manufacturer’s installation instructions for mounting
antennas.
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Installation Procedures
The Garmin AT UAT antenna is vertical polarized, optimized for UHF operation, and designed for
installation in aircraft, including helicopters. The GDL 90 will receive signals from two antennas on top
and bottom of the fuselage. Since UAT is a line-of-sight system, the antenna must have an unobstructed
view of the target. Any “shadowing” or signal shading from the aircraft will degrade the performance.
Shadowing may be from vertical stabilizers, wings, other antennas, engines, propellers, or the fuselage
itself. Proper antenna location and installation is very important for the reception of the signals. See the
UAT Antenna Installation Instructions, P/N 560-0215, for complete details.
CAUTION
Operating the GDL 90 with no RF terminations on the Top or Bottom UAT Antenna
ports can result in equipment damage. Always operate the GDL 90 with the Top and
Bottom UAT Antenna ports terminated with a VSWR ratio of 3.0:1 or less.
2.7 ELECTRICAL CONNECTIONS
The GDL 90 installation kit includes three D-sub connectors and three coax connectors. The connector
layouts are shown in Figure 2-8. The D-sub connectors use the supplied crimp contacts as specified in
Table 2-2. Make the crimp connections with the crimp tool specified.
Table 2-2. Interface Connectors
Ref.
P1
P2
n/a
P3
P4
P5
Description
I/O
I/O
Maint. Port
GPS antenna
UAT ant (top)
UAT ant (bot)
Connector
P/N
162-1575
162-1577
162-1574
162-0043
162-0043
162-0043
Description
15 Pin D-Sub Receptacle
37 Pin D-Sub Receptacle
9 Pin D-Sub Receptacle
Coax connector, right angle
Coax connector, right angle
Coax connector, right angle
Crimp Contact
P/N
Description
245-0027 20-24 AWG socket contact
245-0027 20-24 AWG socket contact
245-0027 20-24 AWG socket contact
N/A
N/A
N/A
N/A
N/A
N/A
The following table shows the specifications for the crimp contacts. Alternate crimp contact part numbers
may be used that are equivalent to those specified in the table below.
Table 2-3. Crimp Contact Specifications
Garmin AT Part Number
Description
Color bands
ITT/Cannon P/N
Military number
2-10
245-0027
20-24 AWG crimp socket contact
Orange/Blue/Gray
031-1007-042
M39029/63-368
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Installation Procedures
2.7.1
INTERFACE CONNECTOR DEFINITION
Figure 2-8. Rear Connector Layout
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Installation Procedures
2.7.1.1
Main System Connector (P1)
The basic GDL 90 interface is handled via a standard density male 15-pin D-SUB connector located at
the rear of the unit. The pinout for the connector is defined in the following table.
Table 2-4. Main System Connector Pin-Out (P1)
Pin
10
11
12
13
14
15
I/O
-I
-O
-I
--I
--
Name
Description
Power +
Power Ground
Maint RxD
Maint TxD
Control Panel Ground
APM TxD
APM RxD
RESERVED
Power +
Power Ground
Maint Serial Ground
Control Panel RxD
Control Panel TxD
APM Ground
RESERVED
Main Aircraft Power Input (+10 to +40 VDC)
Main Aircraft Power Ground
Maintenance Port Serial Data Input
Maintenance Port Serial Data Output
Control Panel Serial Ground
APM Serial Data Output
APM Serial Data Input
RESERVED
Main Aircraft Power Input (+10 to +40 VDC)
Main Aircraft Power Ground
Maintenance Port Serial Ground
Control Panel Serial Data Input
Control Panel Serial Data Output
APM Serial Ground
RESERVED
15
View looking at rear of unit
Figure 2-9. 15-Pin Connector
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Installation Procedures
2.7.1.2
I/O Connector (P2)
The interface to external equipment is made through a standard male 37-pin D-sub connector near on the
rear of the unit. The pin-out for the connector is defined in the following table.
Table 2-5. I/O Connector Pin-Out (P2)
Pin #
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
I/O
--I
--I
-O
--I
Name
Audio Out Hi
RESERVED
RESERVED
TCAS RA Active In
Audio Inhibit Input
RESERVED
Serial Ground 7
Time Mark In +
Time Mark Out +
RS422 RxD3 +
RS422 TxD3 +
429 IN 4A
429 IN 3A
429 IN 2A
429 IN 1A / RS232 RxD7
429 OUT 4A
429 OUT 3A
429 OUT 2A
429 OUT 1A
Audio Out Lo
Suppression Output
TCAS Operational In
Air/Ground In
Serial Ground 6
UAT Fail Out
RESERVED
RESERVED
RS422 RxD3 RS422 TxD3 429 IN 4B
429 IN 3B
429 IN 2B
429 IN 1B / RS232 RxD6
429 OUT 4B
429 OUT 3B
429 OUT 2B
429 OUT 1B
Description
Low-Level Audio Out (to audio panel)
RESERVED
RESERVED
TCAS Resolution Advisory Active Discrete In (active low)
Inhibit Audio Alerts (active low)
RESERVED
RS232 signal ground
GPS 1 Pulse Per Second Input + (RS422 Level)
GPS 1 Pulse Per Second Output + (RS422 Level)
RS422 channel 3 serial data input +
RS422 channel 3 serial data output +
ARINC 429 In Channel 4A
ARINC 429 Input Channel 3A
ARINC 429 Input Channel 2A
ARINC 429 In Channel 1A / RS232 Channel 7 serial data in
ARINC 429 Output Channel 4A
ARINC 429 Output Channel 3A
ARINC 429 Output Channel 2A
ARINC 429 Output Channel 1A
Audio signal ground
Suppression Output (active high)
TCAS Operational Discrete Input (active low)
Air / Ground Discrete Input (level-configurable)
RS232 signal ground
UAT Fail Output (active low)
RESERVED
RESERVED
RS422 channel 3 serial data input RS422 channel 3 serial data output ARINC 429 Input Channel 4B
ARINC 429 Input Channel 3B
ARINC 429 Input Channel 2B
ARINC 429 In Channel 1B / RS232 Channel 6 serial data in
ARINC 429 Output Channel 4B
ARINC 429 Output Channel 3B
ARINC 429 Output Channel 2B
ARINC 429 Output Channel 1B
20
19
VIEW LOOKING AT REAR OF UNIT
37
Figure 2-10. 37-pin Connector
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Installation Procedures
2.8 FUNCTIONAL DESCRIPTIONS
2.8.1
POWER
Aircraft power is provided to the GDL 90 on the main system connector. The GDL 90 will accept input
power from 10 to 40 VDC.
P1-1
P1-9
P1-2
P1-10
Power +
Power +
Power Ground
Power Ground
Refer to Appendix C for recommended power connections.
CAUTION
Operating the GDL 90 with no RF terminations on the Top or Bottom UAT Antenna
ports can result in equipment damage. Always operate the GDL 90 with the Top and
Bottom UAT Antenna ports terminated with a VSWR ratio of 3.0:1 or less.
2.8.2
MICRO AIRCRAFT PERSONALITY MODULE (µAPM)
The GDL 90 stores installation-specific configuration information in an aircraft personality module
located on the rear of the mounting tray. This eliminates the need to set up the configuration again if a
new GDL 90 is installed. Since APM contains no lightning protection, the wire length from APM to
GDL 90 must be limited to 4 inches maximum.
P1-6
P1-7
P1-14
APM TxD
APM RxD
APM Gnd
Refer to Appendix C for interconnect information.
2.8.3
STATUS LEDS
The GDL 90 uses 6 LEDs mounted on the front of its enclosure to communicate system status and
conditions of various internal functions. The descriptions of the LEDs, with power applied to the unit,
are as follows:
Name
Tx
Rx
Maint
2-14
Description
UAT Transmit – normally LED blinks at once a second
ON = UAT data is being transmitted
OFF = No UAT transmission
UAT Receive
ON = UAT data is being received
OFF = No UAT reception
Maintenance
ON = GDL 90 needs maintenance check at the earliest convenience
OFF = No maintenance issue
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Installation Procedures
Ext
GPS
Status
2.8.4
External connections
ON = One or more external systems have disconnected or failed
OFF = No external system failure
GPS Status
Flashing = GDL 90 is acquiring GPS position
Steady ON = GPS position has been acquired
OFF = system failure
GDL 90 System Status
ON = GDL 90 has failed. Perform troubleshooting procedure and
maintenance check.
OFF = GDL 90 is functioning satisfactorily.
DISCRETE OUTPUT
Discrete outputs can be used to drive annunciator lamps or provide status information to other equipment.
Unless otherwise indicated, they are active low (i.e. grounded when active, and open otherwise) and open
collector output capable of sinking up to 400 mA.
2.8.4.1
P2-25
UAT Fail / GPS Status Output
UAT Fail Out
The UAT Fail Out (P2-25) is used to indicate the status of the GDL 90 or status of its internal GPS
engine. The function of this discrete output can be configured via the APM setup (refer to Section 3.0.)
Using the APM initialization, the UAT Fail Out can be configured to behave as follows:
As UAT Fail Indicator
The UAT Fail Out will be grounded when the GDL 90 has detected a
system failure. This output will be open otherwise.
As GPS Status Indicator
The UAT Fail Out will be grounded when the GDL 90 has acquired
valid GPS position. The UAT Fail Out will flash (i.e. alternate between
being open and grounded) at a 1 Hz rate when the GDL 90 is searching
but has not acquired a position. The UAT Fail Out will be open if the
GDL 90 has detected a system failure.
2.8.4.2
P2-21
Transponder Suppression Output
Suppression Out
The Suppression Out is used to indicate to on-board transponder that the GDL 90 is transmitting and
therefore inhibit the transponder from transmitting. The Suppression Output is an active signal and will
be active high when on-board transponder should be suppressed and grounded when transponder is free
to transmit.
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Installation Procedures
2.8.5
DISCRETE INPUTS
The discrete inputs can be used to provide additional status information from aircraft systems or
equipment. All of these inputs are active low (i.e. grounded when active, and open otherwise). Each
input presents a load of greater than 100 kΩ.
2.8.5.1
Air/Ground Discrete Input
P2-23
Air/Ground In
The Air/Ground In is used to provide the aircraft air/ground status. The function of this discrete input
can be configured via the APM setup (refer to Section 3.0). Using the APM setup, the Air/Ground In can
be configured in one of the following options:
•
An air/ground switch is not installed.
•
A ‘ground’ at the Air/Ground In indicates that the aircraft is on the ground, and an ‘open’
indicates that the aircraft is in the air.
•
A ‘ground’ at the Air/Ground In indicates that the aircraft is in the air, and an ‘open’ indicates
that the aircraft is on the ground.
NOTE
The air/ground status provided by the Air/Ground In may be overridden by other system
inputs, such as ground speed and radio altitude (if available).
2.8.5.2
P2-5
Audio Inhibit In
Audio Inhibit In (not used)
The Audio Inhibit In is used to inhibit the GDL 90 audio messages. A ground on this input causes GDL
90 audio messages not to be played; if this input is open GDL 90 audio messages will be played.
NOTE
Audio output and Audio Inhibit input is provisioned for future versions and
currently not used.
2.8.5.3
P2-22
TCAS Operational Discrete Input
TCAS Operational In
The TCAS Operational In is used to provide operational mode information of an on-board TCAS system.
A ground on this input indicates that the TCAS system is installed and operational. An open on this input
indicates that the TCAS is not installed or operational.
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2.8.5.4
TCAS Resolution Advisory Active Discrete Input
P2-4
TCAS RA Active In
The TCAS RA Active In is used to provide the existence of any resolution advisories that the on-board
TCAS may be generating. A ground on this input indicates that a TCAS resolution advisory is currently
active. An open on this input indicates that there are currently no active TCAS resolution advisories.
2.8.6
SERIAL INTERFACES
2.8.6.1
RS232 / RS422
The GDL 90 provides two bi-directional RS232 serial interfaces, up to two receive-only RS232 serial
interfaces, and one bi-directional RS422 serial interface for making optional connections. The serial port
can be used for connecting to:
• MX20 Multi-function Display
• External UAT control panel
• Altitude Encoder
• Transponder
• Maintenance PC
P1-3
P1-4
P1-11
RS232 RxD1 (Maintenance PC only)
RS232 TxD1 (Maintenance PC only)
Serial Ground 1
P2-15
P2-7
429 IN 1A / RS232 RxD7
Serial Ground 7
P1-12
P1-13
P1-5
RS232 RxD2
RS232 TxD2
Serial Ground 2
P2-33
P2-24
429 IN 1B / RS232 RxD6
Serial Ground 6
P2-10
P2-28
P2-11
P2-29
RS422 RxD3 +
RS422 RxD3 –
RS422 TxD3 +
RS422 TxD3 –
NOTE
In order for a serial port to function correctly, the baud rate of the Rx and Tx channels on
a given RS232 or RS422 port must be the same. This must be considered when assigning
serial ports to interfacing equipment.
NOTE
The two receive-only serial ports (RxD4 and RxD5) are shared with ARINC 429 input 1.
If the ARINC 429 input is used, RxD4 and RxD5 cannot be used.
The GDL 90 can communicate with maintenance PC using RS232 RxD1 and TxD1. This interface is
used to program the APM and get additional system status information on the system.
The GDL 90 can receive altitude data from an altitude encoder using RS232 RxD2.
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Installation Procedures
2.8.6.2
ARINC 429
The GDL 90 provides up to four ARINC 429 inputs. Each of these may be configured for low-speed or
high-speed operation.
P2-15
P2-33
P2-14
P2-32
P2-13
P2-31
P2-12
P2-30
429 IN 1A
429 IN 1B
429 IN 2A
429 IN 2B
429 IN 3A
429 IN 3B
429 IN 4A / RS232 RxD6
429 IN 4B / RS232 RxD7
NOTE
ARINC 429 inputs are provisioned for future versions and not currently used.
2.8.7
AUDIO
The GDL 90 provides an audio output for aural advisory messages. A discrete input is also provided to
allow these audio messages to be inhibited by higher priority systems.
NOTE
Audio input and output are provisioned for future versions and not currently used.
2.8.8
SUPPRESSION OUTPUT
P2-21
Suppression Out
The Suppression Out is intended to suppress other L-band equipment (such as a transponder) when the
UAT transmits. It provides a high signal (Vin – 1.5V) whenever the UAT is transmitting, and an low
signal otherwise.
NOTE
Certain transponders emit spurious replies in response to some UAT transmissions.
Consequently, it is recommended that the GDL 90 suppression output be connected to
the suppression input on these transponders (if available.)
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Installation Procedures
2.9 WEIGHT AND BALANCE
Weight and balance computation is required after the installation of the GDL 90. Follow the guidelines as
established in AC 43.13-1B, Chapter 10, Section 2. Make appropriate entries in the equipment list
indicating items added, removed, or relocated along with the date accomplished. Include your name and
certificate number in the aircraft records. Table 2-6 identifies the weight of the new GDL 90 equipment
and Figure 2-9 shows the center of gravity.
Table 2-6. Unit Weights
Item
GDL 90 only
GDL 90 mounting tray
GDL 90 mounting tray with optional cover
Micro APM
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Weight
5.2 lbs
1.0 lbs
1.2 lbs
0.1 lbs
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Installation Procedures
Figure 2-11. GDL 90 Center of Gravity
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Installation Procedures
2.10 ELECTRICAL LOAD ANALYSIS
An electrical load analysis should be completed on each aircraft prior to installation in accordance with
AC 43.13-1B, Chapter 11. Use the following values for computation:
Table 2-7. Unit Power Loads
GDL 90 Input
GDL 90 Main Power
14 VDC
Typical
Max
1.5 A
3.00
28 VDC
Typical
Max
750mA
1.5
NOTE
Circuits should be protected in accordance with guidelines in AC 43.13-1B, chapter 11,
Section 2, Paragraph 429.
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3 LIMITATIONS
3.1 OPERATION
The installation of a GDL 90 into an aircraft does not alter the operational approvals previously granted
to that aircraft. Additional operation approvals may require FAA evaluation of all the systems installed
in a particular aircraft and is outside the scope of the GDL 90 STC.
3.2 INSTALLATION
The conditions and test required for TSO approval of this article are minimum performance standards. It
is the responsibility of those installing this article either on or within a specific type or class of aircraft to
determine that the aircraft installation conditions are within the TSO standards. TSO articles must have
separate approval for installation in an aircraft. The article may be installed only if performed under 14
CFR Part 43 or the applicable airworthiness requirements.
If the aircraft with a GDL 90 installed operates outside the state of Alaska, the system must be configured
to disallow the Capstone squawk code features. This is done by configuring the APM to disable
Capstone feature (Section 4.2.1.2). In addition, if installed, the MX20 should also be configured to
inhibit the entering of squawk code (The transponder should be the only source to enter squawk code.)
The TCAS interface is not currently approved for installation or use. The micro APM shall be configured
with TCAS not installed.
3.2.1
GPS ANTENNA
The GDL 90 is only compatible with the Garmin AT A-33 (590-1104) or A-34 (590-1112) antennas, or
those with equivalent specifications. Refer to section 1.3.7.1 for specifications.
Testing has demonstrated GDL 90 compatibility with SatCom installation in the aircraft, if cable loss is
as specified Section 2.6.1.
3.2.2
UAT ANTENNA
The GDL 90 requires at least one UHF antenna meeting the following specifications:
• Standard 50Ω vertically polarized antenna with a VSWR < 1.7:1 at 978 Mhz
•
TSO-C66, C74, C112 or C154 antennas that also meet the VSWR specification
CAUTION
Operating the GDL 90 with no RF terminations on the Top or Bottom UAT Antenna
ports can result in equipment damage. Always operate the GDL 90 with the Top and
Bottom UAT Antenna ports terminated with a VSWR ratio of 3.0:1 or less.
3.2.3
ANTENNA INSTALLATION – GENERAL
Antenna installation in the pressure vessel of pressurized aircraft is beyond the scope of the GDL 90
STC. Additional manufacturer's data may be necessary and FAA approval may be required to cover the
installation of any antenna in the pressure vessel of a pressurized aircraft.
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3.2.4
EQUIPMENT INTERFACED TO THE GDL 90
Any aircraft systems, other than those shown in this installation manual, that interface to the GDL 90 are
outside the scope of this manual and may require further evaluation and/or certification approval.
All equipment interfaced to the GDL 90 must be previously or concurrently approved.
3.2.5
PRESERVATION OF PREVIOUS SYSTEMS
It is the installer’s responsibility to preserve the essential characteristic of the aircraft being modified by
this manual to be in accordance with the aircraft manufacturer’s original design. This includes the
preservation of multiple power buses, which reduce the probability of interrupting power to essential
instruments and avionics.
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4 POST INSTALLATION CONFIGURATION & CHECKOUT
PROCEDURES
Once the GDL 90 unit has been installed, configure the unit for the particular installation and then
complete the checkout procedures herein to verify proper operation for continued airworthiness. The
steps that are not applicable to a particular installation may be skipped. A checkout log sheet, included on
page 4-10, is to be filled out during the checkout procedure. The completed checkout log sheet should be
maintained with the aircraft permanent records.
CAUTION
Operating the GDL 90 with no RF terminations on the Top or Bottom UAT Antenna
ports can result in equipment damage. Always operate the GDL 90 with the Top and
Bottom UAT Antenna ports terminated with a VSWR ratio of 3.0:1 or less.
4.1 MOUNTING AND WIRING CHECK
Verify that all cables are properly secured and shields are connected as the install drawings indicate.
Installation may require that you check the movement of the aircraft controls to verify that there is no
interference.
4.2 EQUIPMENT SETUP AND CONFIGURATION
Prior to system operation, the GDL 90 must be configured for the particular installation. The system
setup and checkout functions are accessed through the Maintenance mode of the GDL 90, which is
accessible by connecting a PC or terminal to the GDL 90 serial maintenance port (P1-3 and 4, RS232
RxD1 and TxD1, 38400 baud rate, 8-bit data, 1 stop bit, no parity, no flow control) and using commands
as described in the following sections.
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4.2.1
MAINTENANCE MODE
The GDL 90 maintenance port, operating at 38400 baud rate, 8-bit data, 1 stop bit, no parity, no flow
control, allows maintenance personnel to perform the following functions:
• Program/view GDL 90 APM settings
• View GDL 90 system status
• View the status of the GDL 90 external inputs
• View status of GPS/WAAS Engine
• View version numbers
• Reset the GDL 90
Available commands are summarized in Table 4-1. Commands are not case-sensitive (some characters in
commands described in this section are capitalized to improve readability). Within a command, fields
and parameters are separated by spaces.
Command
Parameters
Description
Help
APMinit
APMread
Discrete
External
GPSstatus
PlayAudio
Reset
RxMsg
Service
Version
none
none
none
none
none
P1
none
none
P1
none
none
Display list of available commands
Start the APM initialization routine
Display APM settings
View discrete inputs & outputs
View status of connected external systems
Monitor GPS status
Test audio output
Reset unit
View number of good messages in 1 second
View service information
View software versions
Table 4-1. Maintenance Mode Commands
4.2.1.1
Help
This command causes the GDL 90 to display a list of available commands and their brief descriptions,
which are listed in Table 4-1.
4.2.1.2
APMinit Command
This command starts the micro APM initialization procedure, which leads the user step by step in setting
up the aircraft personality module (APM). The user can quit the initialization procedure at any time;
however the APM will not be programmed if the procedure is prematurely terminated. The new settings
will not take effect until the GDL 90 is restarted or reset.
The procedure guides the user step-by-step in entering data that will be stored in the APM. The required
settings and formats are listed in the following sections.
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Settings
Format
Description
Aircraft Category
integer (int)
Code for aircraft category, from 0 to 18
0 = No aircraft type information
1 = Light (ICAO) < 15 500 lbs
2 = Small - 15 500 to 75 000 lbs
3 = Large - 75 000 to 300 000 lbs
4 = High Vortex Large (e.g., aircraft such as B757)
5 = Heavy (ICAO) - > 300 000 lbs
6 = Highly Maneuverable > 5G acceleration and high speed
7 = Rotorcraft
8 = (Unassigned)
9 = Glider/sailplane
10 = Lighter than air
11 = Parachutist/sky diver
12 = Ultra light/hang glider/paraglider
13 = (Unassigned)
14 = Unmanned aerial vehicle
15 = Space/transatmospheric vehicle
16 = (Unassigned)
17 = Surface vehicle — emergency vehicle
18 = Surface vehicle — service vehicle
Aircraft Length & Width
 
ICAO Address
Aircraft Call Sign
xxxxxxxx
xxxxxxxx
Anonymous Mode
Multi-Function Display
Altitude Filter Settings
 
Transmit Only
CAPSTONE feature
GDL 90 Installation Manual
 
1 to 300 feet
Eight octal digits
Eight characters defining aircraft call sign. Valid characters are AZ, 0-9, and trailing space.
Enter # if call sign is not available.
1=available, 0=not available
When in anonymous mode, the GDL 90 doesn’t send out aircraft
ICAO address.
0 = not installed
1 = MX20
 
10 to 254 hundreds of feet (Zero= No
filtering)
GDL 90 will not make available targets that are at altitudes higher
than the aircraft’s altitude +  OR lower than aircraft’s
altitude - 
Ex: if (50 20) was entered and aircraft is currently at 6000’, the
GDL 90 will only provide for display any targets that are between
4000’ (6000-2000) and 11000’ (6000+5000).
Enter zero if no filtering is desired.
1 =Tx-only
0 =Tx/Rx
Indicates whether the installed GDL 90 is a transceiver or just a
transmitter.
0 =disabled
1 =enabled
Enable/disable Capstone Squawk Code features. Refer to Section
3.2 for more explanation of this setting.
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Settings
Format
Description
UAT Failure Annunciator
usage
Air/Ground Indication
TCAS installation
Altitude source
Control Panel source
UAT Antenna mode
DC-grounded UAT
antenna
Aircraft GPS Antenna
Length & Width Offset
 
GPS Antenna Delay
integer
Top UAT Antenna Delay
integer
Bottom UAT Antenna
Delay
integer
ARINC 429 ADC port
setup
x y
0 =as UAT Fail Indicator
1 =as GPS Valid indicator
The GDL 90’s UAT Fail discrete output that can be set to function
in 2 different ways. Refer to Section 2.8.4.1for more details.
1 =airborne open 2 =on-ground open 0 =not available
If GDL 90 is connected to the aircraft’s air/ground switch, enter the
orientation of the switch.
0 = TCAS not installed
1 = TCAS installed without interface (to GDL 90)
2 = TCAS installed with interface (to GDL 90)
The TCAS interface is not currently approved for installation or
use. “0” must be entered for TCAS not installed. See Section 3.2.
0 =none
1 =RxD Port 2 2 =via MFD
3 =via an ARINC-429 device 4 =RxD Port 6 5 =RxD Port7
Indicates how GDL 90 obtains altitude information.
0 =none 1 =via MFD 2 =dedicated control panel
Indicates how GDL 90 obtains user input information.
0 = dual 1 = top
2 = bottom
Indicates whether the GDL 90 is connected to 1 or 2 antennas.
N = no
Y = yes
Indicates whether the installed UAT antenna(s) can be tested by the
GDL 90’s grounding the antenna(s).
 
0 to 200 feet
Length offset = distance from aircraft nose to GPS antenna
Width offset = distance from aircraft center line to GPS antenna
0 to 65534 in nanoseconds
It’s recommended that zero be entered for most installations where
antenna cable is not excessively long.
0 to 65534 in nanoseconds
It’s recommended that zero be entered for most installations where
antenna cable is not excessively long.
0 to 65534 in nanoseconds
It’s recommended that zero be entered for most installations where
antenna cable is not excessively long.
x: 1 = port 1 2 = port 2 3 = port 3 0=not installed
y: L = Low speed
H = High speed
ARINC 429 AHRS port
setup
Air/Ground Audio
Volume
4-4
x y
 
Indicates how ADC interfaces to the GDL 90.
Ex: (1 L) indicates ADC is connected through port 1 and it’s a
low-speed ARINC 429.
x: 1 = port 1 2 = port 2 3 = port 3 0=not installed
y: L = Low speed
H = High speed
Indicates how AHRS interfaces to the GDL 90.
Ex: (2 H) indicates AHRS is connected through port 2 and it’s a
high-speed ARINC 429.
 
0 to 31
Indicates audio volume when aircraft is in the air and on ground.
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Settings
Format
Air/Ground Threshold
Speed
integer
Description
Zero is the minimum and 31 is the maximum setting.
30 to 100 kts.
Applicable only for light aircraft (category 1), if air/ground switch
is not connected, this threshold speed is used to determine
air/ground status of aircraft. It is recommended that this be set to
75% of stall speed.
If zero is entered and air/ground switch is not connected, the
aircraft is assumed airborne.
Table 4-2. Data Items for APM initialization
NOTE
The APM initialization procedure contains some settings that are reserved for future
upgrade and are not currently operational.
4.2.1.3
APMread Command
The APMread command displays the current APM settings. An example of APM settings is shown
below:
>apmread
Field Name
Option
-----------------------------------------------------Product ID
139-0362-010
Emitter Category
light
Participant Address
77777775
Anonymous Mode
Available
Altitude Filter Settings
Above 0 - Below 0
Display
Installed
Receiver Mode
Tx/Rx
CALL SIGN
ALASKA11
CAPSTONE
Disabled
FAIL Annunciator
UAT fail light
AIR/GROUND Indication
Airborne Open
Takeoff Ground Speed
70 kts
TCAS
Not installed
Altitude Source
RxD Port 2 with baud rate 38400
Control Panel Source
via MFD
Antenna Mode
Dual
DC-Grounded UAT Antenna No
GPS Delay
0 ns
Top Antenna Delay
0 ns
Bottom Antenna Delay
0 ns
A429 Port 4
ADC - High Speed
AHRS
Not installed
Audio Air Volume
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Audio Ground Volume
Aircraft Length
Aircraft Width
Antenna Length Offset
Antenna Width Offset
4.2.1.4
25 feet
20 feet
0 feet
0 feet
Discrete Command
The Discrete command displays the states of the GDL 90 discrete inputs and outputs.
>discrete
4.2.1.5
External Command
The External command displays status of the connections to external systems. This is intended for
checking system wiring and status of external systems.
>external
4.2.1.6
GPSstatus Command
The GPSstatus command displays the current status and data from the internal GPS Engine. Response
includes GPS 3D fix, tracked satellites, current latitude, current longitude and UTC time.
>gpsstatus P1
P1
Once / On
/ Off
4.2.1.7
Description
ONCE = output the current GPS status once
ON = output GPS status once per second
OFF = stop outputting GPS status
Playaudio Command
The Playaudio command causes the GDL 90 to output 1 kHz tone for a second. This is intended for
testing the audio connections in the aircraft.
>playaudio
4.2.1.8
Reset Command
The Reset command causes the GDL 90 to reset itself.
4.2.1.9
Rxmsg Command
The Rxmsg command displays the number of good messages received in last one second.
>rxmsg P1
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P1
on / off
4.2.1.10
Description
ON – display the number of good message received in last second
OFF – turn off the display of the number of good messages
Service Command
The Service command causes service information to be returned. It is useful for troubleshooting system
failure or malfunction.
>service
4.2.1.11
Version Command
The Version command displays version numbers of the Application software, Main I/O Board FPGA, Rx
Logic FPGA, PLD, Micro APM software, Radio-controller software and GPS Engine software.
>version
4.2.2
MX20 SETUP
If the GDL 90 is used in conjunction with a Garmin MX20 Multi-function Display, the MX20 should be
configured accordingly. For instructions, refer to the MX20 User Guide (Part No. 560-1026-06 or later
FAA-approved revision), which is included in the GDL 90 Product CD.
4.3 EQUIPMENT OPERATIONAL/FUNCTIONAL TEST
4.3.1
SYSTEM CHECKOUT – GROUND CHECKS
The GDL 90 executes a self test at power-up to verify the unit operation as well as other internal
functions. Failures and system status are recorded and communicated via 6 LEDs in the front of the unit.
Verify that the unit does not display a failure indication when turned on.
The GDL 90 must be properly configured prior to performing system checkouts. When configured
correctly, the GDL 90 will annunciate failures that are detected with interfacing systems when it is first
turned on. Any annunciated failures should be corrected prior to proceeding with the ground checks
4.3.1.1
GPS Navigation Checkout
Following configuration of the APM, the aircraft should be moved to a location with an unobstructed
view of the available GPS satellites. A computer must be connected to the maintenance port to verify
position and signal strength information.
Check the GPS operation as follows:
1. Connect a computer to the 9-pin maintenance port connector (Refer to Section 4.2.)
2. Turn on the GDL90 and allow the unit to acquire a position. Verify that the GPS LED on the front
of the GDL 90 stops blinking and remains steadily lit within 20 minutes of power-on, indicating
unit has acquired a 3-D fix. All other avionics should be turned off for this part of the test.
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3. Check the position using the GPSstatus command. The displayed lat/lon should agree with a known
reference position.
4. Turn on other avionics one at a time and verify that the GPS LED remains steady on.
5. Check for VHF comm transmitter interference.
NOTE
The interference check must be completed on all IFR installations.
a)
b)
c)
Tune the Com 1 radio to 121.125 MHz. Listen on the frequency to ensure it is not in use,
and then transmit for 30 seconds.
While transmitting, observe the ‘GPS’ LED. Verify that the GPS LED remains steady on. If
not, additional isolation measures will have to be taken.
Repeat steps a) and b) for additional frequencies as follows.
121.150 MHz
131.225 MHz
121.175 MHz
131.250 MHz
121.185 MHz [1]
131.275 MHz
121.190 MHz [1]
130.285 MHz [1]
121.200 MHz
131.290 MHz [1]
121.225 MHz
131.300 MHz
121.250 MHz
131.325 MHz
131.200 MHz
131.350 MHz
[1] frequency is only applicable to VHF radios with 8.33 kHz channel spacing
d)
e)
f)
g)
Repeat for each com transmitter installed in the aircraft.
If aircraft is TCAS-equipped, turn on the TCAS system and verify that GPS LED remains
steady on.
If aircraft is SATCOM-equipped, use the SATCOM system and verify that GPS LED remains
steady on.
If the GDL 90 is susceptible to VHF Com transmitter interference, then better isolation (or greater
separation) may be required between the GPS and VHF (or other offending system) antennas.
With some com transmitters, a 1575.42 MHz notch filter (such as Garmin AT P/N 162-1059) may
be required in series with the VHF Com antenna coax at the rear of the com unit. ELT’s may reradiate harmonics of the VHF Com signal into the GPS band. A 1575.42 MHz notch filter on the
ELT will solve this.
NOTE
Older VHF Com transmitters may emit higher levels of harmonic interference.
4.3.1.2
Interface Checkout
This section describes checks that can be carried out to verify that systems interfacing to the CNX80 are
communicating properly.
4.3.1.2.1 Air Data Computer and Altitude Encoder
Verify that the Ext LED on the front of the GDL 90 is not illuminated.
4.3.1.2.2 MX20 Display Checkout
Refer to the MX20 installation manual (P/N 560-1025-08 or later FAA approved revision) for the
following checks.
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With the MX20 in Installer mode, select the FUNC pages and verify that all functions are
enabled except for lightning.
Go to the DATA pages and configure the MX20 as follows:
UAT Traffic Data Link Source
Port 4
Wait at least 30 seconds (until red message no longer appears at the bottom of the screen) and
then recycle power to the MX20. Wait another 30 seconds and verify that the TRAF warning
does not appear.
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Table 4-3. GDL 90 Post-Installation Checkout Log
GDL 90 Post-Installation Checkout Log
Date: ___/___/___
By: _____________
430-6081-1_____-______ HW Mod ____
Serial # ___________
SW Mod ____
SETUP ITEMS:
Serial Interface Configuration (RX/TX):
Reserved for maintenance PC
(Port 1)
______________/_____________
(Port 2)
MX20 MFD interface
(Port 3)
______________/_____________
(Rx Port 6)
______________/_____________
(Rx Port 7)
ANNUNCIATOR OUTPUTS CHECKOUT:
UAT Fail Annunciator:

 UAT Fail; 
 GPS Indicator
Suppression Out: 
 connected to transponder
GPS NAVIGATION CHECKOUT

 Position checked

 Signal reception checked
ARINC 429 Input Configuration:
_____________ 
 Hi 
 Low (Channel 1 In)
_____________ 
 Hi 
 Low (Channel 2 In)
_____________ 
 Hi 
 Low (Channel 3 In)
_____________ 
 Hi 
 Low (Channel 4 In)
DISCRETE INPUTS CHECKOUT:

 [
 N/A] Air / Ground Switch

 Interference from other avionics checked

 VHF com interference checked
INTERFACE CHECKOUT

 [
 N/A] Transponder

 [
 N/A] Altitude Encoder

 [
 N/A] MX20 Display
FLIGHT CHECKS:
FINAL SYSTEM CHECK:
COMMENTS:
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5 TROUBLESHOOTING
This section provides information to assist troubleshooting if problems occur after completing the
installation. Use Table 5-1 and flowcharts in Appendix B to assist in troubleshooting. A PC connected to
the GDL 90 Maintenance port is essential in troubleshooting. In addition, devices connected to the GDL
90, such as a control panel / transponder or MX20 can be useful for determining whether the GDL 90 is
functioning properly or if there are problems with the installation.
5.1 TROUBLESHOOTING PROCEDURE
Table 5-1. Troubleshooting Guide
Problem
Possible Cause
Solution
No LED activity
1.
No power to unit.
1.
Verify that power and ground leads are
correct and power is getting to unit.
No targets are
displayed on your
MX20 MFD.
1.
No targets are transmitting
ADSB.
No targets are within line-ofsight range.
Antennas and cables are not
connected.
MX20 is not connected.
Transmit malfunction.
1.
Verify that other targets are transmitting
ADSB.
Verify that other targets are within line-ofsight range.
Verify that antennas and cables are connected
properly.
Verify Ext LED is not lit.
Verify that Tx LED on the GDL 90 blinks at
lease once per second.
2.
3.
4.
Your aircraft is not
1.
displayed on other
aircraft MFD.
Tx LED is not on
1.
(flashing at 1 Hz rate).
2.
3.
4.
1.
Unit is not transmitting UAT
messages.
1.
Verify antennas and cables are properly
connected.
Verify antennas and cables are properly
connected and that other UAT-equipped
aircraft is transmitting.
Use the Service command in Maintenance
mode to verify system condition. Consult
dealer or factory technician for recommended
action.
Use the External command in Maintenance
mode to determine which system(s) or
connection(s) has failed. Verify wiring,
connector and health status of the failed
system(s).
Use the Service command in Maintenance
mode to verify system condition. If the
Status LED is also lit, return unit to Factory
for repair.
Return unit to Factory for repair. Refer to
Section 5.2 for procedure to follow.
Rx LED is not on.
1.
Unit is not receiving UAT
messages.
1.
Maint LED is on.
1.
Maintenance check may be
needed.
1.
Ext LED is on.
1.
External system(s) or
connections to those systems
have failed.
1.
GPS LED is not on.
1.
System or GPS failure
1.
Status LED is on.
1.
System malfunction or failure
1.
GDL 90 Installation Manual
560-1049-00 Rev B
5-1
Limitations
5.2 CONTACTING THE FACTORY FOR ASSISTANCE
If the GDL 90 unit fails to operate despite troubleshooting efforts, contact Garmin AT Technical Support
for assistance.
Garmin AT, Inc.
2345 Turner Rd. SE
Salem, Oregon 97302
USA
Phone: 503.581.8101 or 800.525.6726 (ext. 3991)
http://www.garmin.com
Be prepared to offer the following information about the installation:
5-2
•
Installation configuration (list of any accessories)
•
Model number, part number with mod levels, and serial number
•
Software Versions
•
Description of problem
•
Efforts made to isolate the problem
560-1049-00 Rev B
GDL 90 Installation Manual
Periodic Maintenance
6 PERIODIC MAINTENANCE
This section contains information on periodic calibration and maintenance required for continued
airworthiness.
6.1 EQUIPMENT CALIBRATION
No scheduled servicing tasks or internal manual adjustments are required on the GDL 90.
6.2 CLEANING
The GDL 90 does not require regular cleaning.
6.3 BATTERY REPLACEMENT
The GDL 90 includes an internal battery that will last about 10 years. The battery is used for internal
RAM memory and GPS system information. Regular planned replacement is not necessary. The GDL 90
Maint. LED will be lit when replacement is required. To verify that the battery needs replacing, use the
“Service” command in Maintenance Mode. Once low battery is confirmed, the battery should be
replaced within 1 to 2 months.
If the battery is not replaced and becomes totally discharged, the GDL 90 will remain fully operational,
but the GPS signal acquisition time will be increased. There is no loss of function or accuracy of the
GDL 90 with a discharged battery.
The battery is not user-replaceable. To replace the battery, contact the Garmin AT repair station.
GDL 90 Installation Manual
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6-1
Periodic Maintenance
NOTES
6-2
560-1049-00 Rev B
GDL 90 Installation Manual
Appendix A - Certification Data
APPENDIX A - CERTIFICATION DATA
A.1 GDL 90 ENVIRONMENTAL QUALIFICATION
The GDL 90 has been tested to the following environmental categories per procedures defined in RTCA/DO-160D.
Tests were conducted in February to April 2004 using the original 1997 revision of DO-160D and the specification
defined in PD3536.
Environmental Qualification Form
Nomenclature: GDL 90
Part No.:
430-6081-1xx-xxx
TSO No.:
C145a, C154
Environment
Temperature and Altitude
Section
Category
F1 & A1
Temperature Variation
Humidity
Operational Shocks and Crash
Safety
Vibration
Explosion Proofness
Waterproofness
Fluids Susceptibility
Sand and Dust
Fungus Resistance
Salt Spray
Magnetic Effect
Power Input
Voltage Spike
Audio Frequency Conducted
Susceptibility - Power Inputs
Induced Signal Susceptibility
Radio Frequency Susceptibility
(Radiated and Conducted)
B5R
10
11
12
13
14
15
16
17
18
S(M & B)
A&B
19
20
UV-
Emission of Radio Frequency
Energy
Lightning Induced Transient
Susceptibility
Lightning Direct Effects
Icing
Electrostatic Discharge (ESD)
21
22
A3XX
23
24
25
[1]
Manufacturer:
Garmin AT
2345 Turner Road SE
Salem, Oregon 97302
Comment
Operating temp ........ –20°C to +55°C
Short time hi temp ....
to +70°C
Ground survival temp –55°C to +85°C
Altitude .................... 55,000 feet
Decompression
55,000 feet
Overpressure
Loss of cooling test -- not required
No external cooling required provided internal fans
are unobstructed and operating
Minimum 5°C per minute
Severe humidity environment.
meets operational and crash safety shock tests 20
Gs at 11 ms.
Standard vibration. Meets without shock mounts.
not applicable, no test required
not applicable, no test required
not applicable, no test required
not applicable, no test required
not applicable, no test required
not applicable, no test required
< 0.3 meter
for 28 and 14 volt systems
Equipment tested to Category U (Conducted)
Equipment tested to Category V (Radiated)
No Pulse tests performed.
Equipment tested to pin test waveform set A, level
3. No cable bundle test required.
not applicable, no test required
not applicable, no test required
[1] The GDL 90 passes Category V (Radiated) for all TSO functions except temporary degraded receiver
sensitivity at one frequency in the 2 to 3 GHz band.
GDL 90 Installation Manual
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A-1
Appendix A - Certification Data
A.2 MICRO APM ENVIRONMENTAL QUALIFICATION
The Micro APM has been tested with the GDL 90 to the following environmental categories per procedures defined
in RTCA/DO-160D. Tests were conducted in February to April 2004 using the original 1997 revision of DO-160D
and the specification defined in PD3536.
Environmental Qualification Form
Nomenclature: Micro APM
Part No.:
430-6200-xxx
TSO No.:
C154
Manufacturer:
Garmin AT
2345 Turner Road SE
Salem, Oregon 97302
Comment
Operating temp ........ –20°C to +55°C
Short time hi temp ....
to +70°C
Ground survival temp –55°C to +85°C
Altitude .................... 55,000 feet
Decompression
55,000 feet
Overpressure
Loss of cooling test -- not required
Environment
Temperature and Altitude
Section
Category
F1 & A1
Temperature Variation
Humidity
Operational Shocks and Crash
Safety
Vibration
Explosion Proofness
Waterproofness
Fluids Susceptibility
Sand and Dust
Fungus Resistance
Salt Spray
Magnetic Effect
Power Input
Voltage Spike
Audio Frequency Conducted
Susceptibility - Power Inputs
Induced Signal Susceptibility
Radio Frequency Susceptibility
(Radiated and Conducted)
B5R
10
11
12
13
14
15
16
17
18
S(M & B)
A&B
[1]
[1]
[1]
19
20
UV-
Emission of Radio Frequency
Energy
Lightning Induced Transient
Susceptibility
Lightning Direct Effects
Icing
Electrostatic Discharge (ESD)
21
[2]
22
XXXX
[2]
23
24
25
Minimum 5°C per minute
Severe humidity environment.
meets operational and crash safety shock tests 20
Gs at 11 ms.
Standard vibration. Meets without shock mounts.
not applicable, no test required
not applicable, no test required
not applicable, no test required
not applicable, no test required
not applicable, no test required
not applicable, no test required
< 0.3 meter
for 28 and 14 volt systems
Equipment tested to Category U (Conducted)
Equipment tested to Category V (Radiated)
No Pulse tests performed.
not applicable, no test required
not applicable, no test required
not applicable, no test required
[1] APM powered by GDL 90. APM not directly exposed to this condition.
[2] Maximum APM wire length 4 inches.
A-2
560-1049-00 Rev B
GDL 90 Installation Manual
Appendix B - Serial Interface Specifications
APPENDIX B - TROUBLESHOOTING FLOWCHARTS
GDL 90 Installation Manual
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B-1
Appendix B - Serial Interface Specifications
B-2
560-1049-00 Rev B
GDL 90 Installation Manual
Appendix B - Serial Interface Specifications
GDL 90 Installation Manual
560-1049-00 Rev B
B-3
Appendix B - Serial Interface Specifications
B-4
560-1049-00 Rev B
GDL 90 Installation Manual
Appendix C - Interconnect Diagrams
APPENDIX C - INTERCONNECT DIAGRAMS
GDL 90 Installation Manual
560-1049-00 Rev B
C-1
Appendix C - Interconnect Diagrams
NOTES
C-2
560-1049-00 Rev B
GDL 90 Installation Manual
GDL 90 Installation Manual
560-1049-00 Rev B
Figure C-1. Interconnect Diagram for installation w/ MX20 MFD
Appendix C – Interconnect Diagrams
C-3
C-4
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This page intentionally left blank.
GDL 90 Installation Manual
Appendix D – Construction and Validation of Structures
APPENDIX D - CONSTRUCTION & VALIDATION OF
STRUCTURES
This appendix includes information necessary for testing load-carrying capabilities of equipment
mounting structures, such as shelves, mounting plates and mounting brackets, used to mount the GDL 90
mounting tray.
Baggage compartments and cabins or cockpit floors are good mounting platforms providing the floor
attachments meet the strength requirements. If support racks, brackets or shelves need to be fabricated,
they should be fabricated and attached to the aircraft structure in accordance with the methods outlined in
AC 43.13-2A Chapter 2. After the structure is installed, it should be tested as outlined in AC43.13-2A
Chapter 1 to verify that it is capable of supporting the required loads.
The GDL 90 installation must be capable of withstanding the Ultimate Load Factors listed in Table D-1
for at least 3 seconds in each direction specified without damage or permanent deformation. Note that
these required loads differ somewhat from those normally required for equipment installations.
Since the combined weight of the GDL 90 and its equipment mounting rack is 6.4 lbs, the static loads
which must be applied (Load Factor x 6.4 lbs.) will be the following:
Direction of Force
Load Factor
Static Test Load
(Load Factor x GDL 90 weight)
Downward
Upward
Sideward
Forward
6.6 g
6.0 g
4.5 g
18.0 g
(6.6 x 6.4) = 42.24 lbs
(6.0 x 6.4) = 38.4 lbs
(4.5 x 6.4) = 28.8 lbs
(18.0 x 6.4) = 115.2 lbs
Table D-1. Static Test Load
One method of determining the static load capability is as follows:
1. Mark and drill the holes where the GDL 90 equipment rack will be mounted.
2. Install four 8-32 machine screws (MS35206, AN526 or equivalent) in the four holes which
will be used to mount the GDL 90 equipment rack using washers, nuts and nutplates to mount the
equipment rack to the mounting surface. Note: some means of locking fastener must be used, ie.
lock nuts & lock washers.
2. For testing downward loading, place shot bags or other suitable weights totaling 42.24 pounds
within the footprint outlined by the four screw holes (assuming the mounting surface is
horizontal) or use a calibrated force gauge at the location of the center of gravity when the unit is
mounted.
3. Verify there is no damage or permanent deformation of the structure after 3 seconds.
GDL 90 Installation Manual
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D-1
Appendix D – Construction and Validation of Structures
5. Fasten a 36 inch loop of suitable material such as fishing line, braided wire, or other similar
material having a breaking strength of at least 150 lbs, diagonally between two of the screws.
Then fasten another loop diagonally between the other two screws, adjusting the length of the
loop so it exactly matches the first.
6. Hook a calibrated force gauge through both loops and apply a sustained pull for at least 3
seconds in each of the other three directions (upward, sideward and forward) at the above
calculated forces (i.e. 38.4 lb upward, 28.8 lb sideward and 115.2 lb forward).
7. Examine the support structure carefully. If there has been damage or permanent deformation,
the structure is not suitable and must be replaced with one which is strong enough to withstand
the test loads. Examine all aircraft stringers, bulkheads and skin surfaces, which may have direct
or indirect contact with the fabricated shelf. If it is determined that no damage or permanent
deformation has occurred, the structure is of sufficient strength and the GDL 90 equipment rack
may be permanently mounted on it.
Figure D-2. Upward Static Load Test
Figure D-3. Forward Static Load Test
D-2
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GDL 90 Installation Manual


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