Garmin 0181200 LICENSED NON-BROADCAST AERONAUTICAL TRANSMITTER User Manual 190 01277 00
Garmin International Inc LICENSED NON-BROADCAST AERONAUTICAL TRANSMITTER 190 01277 00
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| Document ID | 1885115 |
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| Document Description | User Manual |
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| Filesize | 398.78kB (4984785 bits) |
| Date Submitted | 2013-01-23 00:00:00 |
| Date Available | 2013-01-24 00:00:00 |
| Creation Date | 2012-12-20 15:19:28 |
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| Document Lastmod | 2013-01-23 14:05:32 |
| Document Title | 190-01277-00.book |
| Document Creator | FrameMaker 10.0.2 |
| Document Author: | miley |
REVISIONS
REV.
DATE
12/20/12
SPECIFICATION
CONTROL DRAWING
DESCRIPTION
ECO NO.
Initial release
---
AVIATION REVIEW REQUIRED
NOTES:
1. DESCRIPTION: Installation Documentation - GRA 5500 Installation Manual
AF
2. PAGE SIZE: Letter: Width = 8.5 inches, Height = 11 inches, Double-sided Tabloid: Height = 17.0 inches,
Width = 11 inches, Single-sided Tabloid: Width = 17.0 inches, Height = 11 inches,
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7. FOLDS: Z-Fold tabloid sheets at end of document.
8. ELECTRONIC ARTWORK: Shall conform to Garmin Archive, Filename: 190-01277-00.pdf
9. This part shall comply with Garmin Banned/Restrictive Substance List, GPN 001-00211-00
The following files have been archived under the above ARCHIVE FILENAME.
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190-01277-00.pdf
Portable Document Format, contains Installation Manual and Release
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Various supporting illustrations, drawings, and artwork
CONFIDENTIAL
This drawing and the specifications contained herein are the property of Garmin Ltd. or its
subsidiaries and may not be reproduced or used in whole or in part as the basis for
manufacture or sale of products without written permission.
Date:
Drafter:
MJM
12/20/12
GRA 5500 Installation Manual
Checker:
Project Engineer:
Released By:
SIZE A
Part Number: 190-01277-00
Rev A
Scale: N/A
AVIATION REVIEW REQUIRED
Sheet 1 of 1
GRA 5500
AF
Radar Altimeter
Installation Manual
190-01277-00
December, 2012
Revision A
© Copyright 2012
Garmin Ltd. or its subsidiaries
All Rights Reserved
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 prior written consent of Garmin. Garmin hereby grants permission to download a
single copy of this manual and of any revision to this manual onto a hard drive or other electronic
storage medium to be viewed and to print one copy of this manual or of any revision hereto,
provided that such electronic or printed copy of this manual or revision must contain the complete
text of this copyright notice and provided further that any unauthorized commercial distribution of
this manual or any revision hereto is strictly prohibited.
Garmin International, Inc.
1200 E. 151st Street
Olathe, KS 66062 USA
Telephone: 913.397.8200
Aviation Panel-Mount Technical Support Line (Toll Free) 1.888.606.5482
www.garmin.com
AF
Garmin (Europe) Ltd.
Liberty House, Bulls Copse Road
Hounsdown Business Park
Southampton, SO40 9RB U.K.
+44/ (0) 870.8501241
Garmin AT, Inc.
2345 Turner Rd., SE
Salem, OR 97302 USA
Telephone: 503.581.8101
RECORD OF REVISIONS
Revision Revision Date
12/20/12
Description
Production Release
GRA 5500 Installation Manual
Page A
190-01277-00
Rev. A
INFORMATION SUBJECT TO EXPORT CONTROL LAWS
This document may contain information which is subject to the Export Administration Regulations
("EAR") issued by the United States Department of Commerce (15 CFR, Chapter VII, Subchapter C) and
which may not be exported, released, or disclosed to foreign nationals inside or outside of the United States
without first obtaining an export license. The preceding statement is required to be included on any and all
reproductions in whole or in part of this manual.
DEFINITIONS OF WARNINGS, CAUTIONS, AND NOTES
WARNING
Warnings are used to bring to the installer’s immediate attention that not only
damage to the equipment but personal injury may occur if the instruction is
disregarded.
CAUTION
AF
Cautions are used to alert the individual that damage to equipment may
result if the procedural step is not followed to the letter.
NOTE
WARNING
Notes are used to expand and explain the preceding step and provide further
understanding of the reason for the particular operation.
This product, its packaging, and its components contain chemicals known to the State of
California to cause cancer, birth defects, or reproductive harm. This Notice is being
provided in accordance with California's Proposition 65. If you have any questions or
would like additional information, please refer to our web site at www.garmin.com/prop65.
190-01277-00
Rev. A
GRA 5500 Installation Manual
Page i
CURRENT REVISION DESCRIPTION
Revision
Page
Number(s)
All
Section
Number
All
Description of Change
Initial Release
DOCUMENT PAGINATION
Page Range
i – viII
1-1 – 1-4
2-1 – 2-14
3-1 – 3-18
4-1 – 4-6
A-1 – A-8
B-1 – B-2
C-1 – C-5
AF
Section
Table of Contents
Section 1
Section 2
Section 3
Section 4
Appendix A
Appendix B
Appendix C
GRA 5500 Installation Manual
Page ii
190-01277-00
Rev. A
Aviation Limited Warranty
All Garmin avionics products are warranted to be free from defects in materials or workmanship for: one
years from the date of purchase for new Remote-Mount and Panel-Mount products; one year from the date
of purchase for new portable products and any purchased newly-overhauled products; six months for
newly-overhauled products exchanged through a Garmin Authorized Service Center; and 90 days for
factory repaired or newly-overhauled products exchanged at Garmin in lieu of repair. Within the applicable
period, Garmin will, at its sole option, repair or replace any components that fail in normal use. Such
repairs or replacement will be made at no charge to the customer for parts or labor, provided that the
customer shall be responsible for any transportation cost. This warranty does not apply to: (i) cosmetic
damage, such as scratches, nicks and dents; (ii) consumable parts, such as batteries, unless product damage
has occurred due to a defect in materials or workmanship; (iii) damage caused by accident, abuse, misuse,
water, flood, fire, or other acts of nature or external causes; (iv) damage caused by service performed by
anyone who is not an authorized service provider of Garmin; or (v) damage to a product that has been
modified or altered without the written permission of Garmin. In addition, Garmin reserves the right to
refuse warranty claims against products or services that are obtained and/or used in contravention of the
laws of any country.
AF
THE WARRANTIES AND REMEDIES CONTAINED HEREIN ARE EXCLUSIVE AND IN LIEU OF
ALL OTHER WARRANTIES, WHETHER EXPRESS, IMPLIED OR STATUTORY, INCLUDING ANY
LIABILITY ARISING UNDER ANY WARRANTY OF MERCHANTABILITY OR FITNESS FOR A
PARTICULAR PURPOSE, STATUTORY OR OTHERWISE. THIS WARRANTY GIVES YOU
SPECIFIC LEGAL RIGHTS, WHICH MAY VARY FROM STATE TO STATE.
IN NO EVENT SHALL GARMIN BE LIABLE FOR ANY INCIDENTAL, SPECIAL, INDIRECT OR
CONSEQUENTIAL DAMAGES, WHETHER RESULTING FROM THE USE, MISUSE OR
INABILITY TO USE THE PRODUCT OR FROM DEFECTS IN THE PRODUCT. SOME STATES DO
NOT ALLOW THE EXCLUSION OF INCIDENTAL OR CONSEQUENTIAL DAMAGES, SO THE
ABOVE LIMITATIONS MAY NOT APPLY TO YOU.
Garmin retains the exclusive right to repair or replace (with a new or newly-overhauled replacement
product) the product or software or offer a full refund of the purchase price at its sole discretion. SUCH
REMEDY SHALL BE YOUR SOLE AND EXCLUSIVE REMEDY FOR ANY BREACH OF
WARRANTY.
Online Auction Purchases: Products purchased through online auctions are not eligible for warranty
coverage. Online auction confirmations are not accepted for warranty verification. To obtain warranty
service, an original or copy of the sales receipt from the original retailer is required. Garmin will not
replace missing components from any package purchased through an online auction.
International Purchases: A separate warranty may be provided by international distributors for devices
purchased outside the United States depending on the country. If applicable, this warranty is provided by
the local in-country distributor and this distributor provides local service for your device. Distributor
warranties are only valid in the area of intended distribution. Devices purchased in the United States or
Canada must be returned to the Garmin service center in the United Kingdom, the United States, Canada,
or Taiwan for service.
Garmin International, Inc.
1200 East 151st Street
Olathe, Kansas 66062, U.S.A.
Phone:913/397.8200
FAX:913/397.0836
190-01277-00
Rev. A
Garmin (Europe) Ltd.
Liberty House, Bulls Copse Road
Hounsdown Business Park
Romsey, SO40 9RB, U.K.
Phone:44/ (0) 870.8501241
FAX:44/ (0) 870.850125
GRA 5500 Installation Manual
Page iii
T
AF
This page intentionally left blank
GRA 5500 Installation Manual
Page iv
190-01277-00
Rev. A
TABLE OF CONTENTS
PARAGRAPH
PAGE
Section 1 GENERAL DESCRIPTION .............................................................1-1
1.1 Introduction...................................................................................................................... 1-1
1.2 Equipment Description ................................................................................................... 1-1
1.3 Interface Summary.......................................................................................................... 1-1
1.4 Technical Specifications .................................................................................................. 1-2
1.4.1 Environmental Qualification Form.......................................................................................1-2
1.4.2 Physical Characteristics........................................................................................................1-2
1.4.3 General Specifications..........................................................................................................1-2
1.4.4 Performance Specifications ..................................................................................................1-3
1.4.5 Power Requirements.............................................................................................................1-3
1.5 Certification ..................................................................................................................... 1-3
1.5.1 TSO Compliance and Limitations ........................................................................................1-4
1.5.2 TSO Deviations ....................................................................................................................1-4
AF
1.6 Operating Instructions...................................................................................................... 1-4
1.7 Reference Documents ...................................................................................................... 1-4
Section 2 INSTALLATION OVERVIEW........................................................2-1
2.1 Introduction...................................................................................................................... 2-1
2.2 Installation Materials ....................................................................................................... 2-1
2.2.1 Available Equipment ............................................................................................................2-1
2.2.2 Additional Equipment Required...........................................................................................2-2
2.2.3 Approved Radar Altimeter Antennas ...................................................................................2-2
2.3 Installation Considerations .............................................................................................. 2-3
2.3.1 Multiplex Operation (Dual and Triple Unit Installations)....................................................2-3
2.3.2 Installation Approval Considerations for Pressurized Aircraft ............................................2-3
2.3.3 Antenna Location Planning Guidance..................................................................................2-4
2.3.4 Antenna Installation Considerations...................................................................................2-10
2.4 Electrical Bonding ......................................................................................................... 2-10
2.5 Cabling and Wiring........................................................................................................ 2-10
2.5.1 Antenna Coaxial Cables (Requirements and Fabrication Guidance) .................................2-11
2.6 Cooling Requirements ................................................................................................... 2-14
2.7 Mounting Requirements ................................................................................................ 2-14
Section 3 INSTALLATION PROCEDURE .....................................................3-1
3.1 Unpacking Unit................................................................................................................ 3-1
3.2 Wiring Harness Installation ............................................................................................. 3-1
3.3 Backshell Assembly......................................................................................................... 3-2
3.4 Antenna Installation ......................................................................................................... 3-2
3.5 Unit Installation ............................................................................................................... 3-2
3.5.1 Installation Procedure (see Figure 3-1) ................................................................................3-2
3.5.2 Removal Procedure (see Figure 3-1) ....................................................................................3-2
3.6 Downloading and Installing the GRA 5500 Retrofit Installation Tool ........................... 3-4
3.7 Post Installation Configuration and Checkout Procedures .............................................. 3-5
190-01277-00
Rev. A
GRA 5500 Installation Manual
Page v
PARAGRAPH
PAGE
3.7.1 GRA 5500 Configuration/Checkout for Varying Installation Types ................................... 3-5
3.7.2 Using the GRA 5500 Retrofit Installation Tool................................................................... 3-6
3.7.3 Zero-Foot Calibration......................................................................................................... 3-16
3.7.4 Built-In Self-Test Functionality ......................................................................................... 3-16
3.8 Continued Airworthiness................................................................................................3-18
Section 4 SYSTEM INTERCONNECTS .........................................................4-1
4.1 Pin Function List ..............................................................................................................4-1
4.1.1 P55001.................................................................................................................................. 4-1
4.2 Power Functions ...............................................................................................................4-3
4.2.1 Aircraft Power ...................................................................................................................... 4-3
4.3 Serial Data Connections ...................................................................................................4-3
4.3.1 HSDB Over RS-422 ............................................................................................................. 4-3
4.3.2 ARINC 429 .......................................................................................................................... 4-4
4.3.3 Configuration Module .......................................................................................................... 4-4
4.3.4 USB ...................................................................................................................................... 4-5
4.4 Discrete I/O ......................................................................................................................4-5
AF
4.4.1 Active Low Discrete Inputs ................................................................................................. 4-5
4.4.2 Altitude Alert (Annunciator) Outputs .................................................................................. 4-6
Appendix A Referenced Tables ........................................................................ A-1
Appendix B Outline and Installation Drawings ............................................. B-1
Appendix C Interconnect Examples ................................................................ C-1
GRA 5500 Installation Manual
Page vi
190-01277-00
Rev. A
LIST OF FIGURES
FIGURE
PAGE
Section 1 GENERAL DESCRIPTION .............................................................1-1
Section 2 INSTALLATION OVERVIEW........................................................2-1
Figure 2-1 Standard Dual and Triple End-to-End System Layouts....................................... 2-6
Figure 2-2 Compact Dual and Triple End-to-End System Layouts....................................... 2-7
Figure 2-3 Dual and Triple Side-by-Side System Layouts.................................................... 2-8
Figure 2-4 Hybrid Triple System Layout .............................................................................. 2-9
Figure 2-5 Coaxial Cable Requirements.............................................................................. 2-12
Figure 2-6 TNC Connector Installation ............................................................................... 2-12
Figure 2-7 Heat Shrink Positioning ..................................................................................... 2-13
Figure 2-8 GRA 5500 Mounting Rack ................................................................................ 2-14
Section 3 INSTALLATION PROCEDURE .....................................................3-1
AF
Figure 3-1 GRA 5500 Installation ......................................................................................... 3-3
Figure 3-2 GRA 5500 Retrofit Installation Tool (New Installation) ..................................... 3-7
Figure 3-3 GRA 5500 Retrofit Installation Tool Status Tab (Normal Operation) ................ 3-9
Figure 3-4 GRA 5500 Retrofit Installation Tool Configuration Tab................................... 3-10
Figure 3-5 GRA 5500 Retrofit Installation Tool Software Tab........................................... 3-13
Section 4 SYSTEM INTERCONNECTS..........................................................4-1
Figure 4-1 View of J55001 connector, from front of unit ..................................................... 4-1
Appendix A Referenced Tables........................................................................A-1
Appendix B Outline and Installation Drawings .............................................B-1
Figure B-1 GRA 5500 Outline Drawing................................................................................B-1
Figure B-2 GRA 5500 Connector/Rack Assembly Drawing.................................................B-2
Appendix C Interconnect Examples ................................................................C-1
Figure C-1 Garmin Integrated Flight Deck (GIFD) and non-GIFD (retrofit)
Interconnect Example ............................................................................................................C-1
Figure C-2 Garmin Integrated Flight Deck Interconnect Example .......................................C-2
Figure C-3 Non-Garmin Integrated Flight Deck (retrofit) Interconnect Example ................C-3
Figure C-4 GRA 5500 USB Dongle Cable............................................................................C-4
Figure C-5 GRA 5500 Configuration Module Interconnect Example ..................................C-5
190-01277-00
Rev. A
GRA 5500 Installation Manual
Page vii
LIST OF TABLES
TABLE
PAGE
Section 1 GENERAL DESCRIPTION .............................................................1-1
Table 1-1 Physical Characteristics......................................................................................... 1-2
Table 1-2 General Specifications........................................................................................... 1-2
Table 1-3 Performance Specifications ................................................................................... 1-3
Table 1-4 Power Requirements.............................................................................................. 1-3
Table 1-5 TSO Compliance ................................................................................................... 1-4
Table 1-6 Reference Documents............................................................................................ 1-4
Section 2 INSTALLATION OVERVIEW........................................................2-1
Table 2-1 Available Units...................................................................................................... 2-1
Table 2-2 Available Equipment ............................................................................................. 2-1
Table 2-3 Additional Equipment Required............................................................................ 2-2
Table 2-4 Approved Radar Altimeter Antennas .................................................................... 2-2
Table 2-5 System ID Discrete Inputs..................................................................................... 2-3
AF
Section 3 INSTALLATION PROCEDURE .....................................................3-1
Table 3-1 Pin Contact Part Numbers ..................................................................................... 3-1
Table 3-2 Recommended Crimp Tools.................................................................................. 3-1
Table 3-3 Recommended Insertion Tools.............................................................................. 3-1
Table 3-4 Recommended Removal Tools ............................................................................. 3-2
Table 3-5 ARINC 429 Channel 1 Settings .......................................................................... 3-11
Table 3-6 ARINC 429 Channel 2 Settings .......................................................................... 3-11
Section 4 SYSTEM INTERCONNECTS..........................................................4-1
Table 4-1 P55001 Connector ................................................................................................. 4-1
Table 4-2 Aircraft Power ....................................................................................................... 4-3
Table 4-3 HSDB Over RS-422 .............................................................................................. 4-3
Table 4-4 ARINC 429............................................................................................................ 4-4
Table 4-5 ARINC 429 Output Labels.................................................................................... 4-4
Table 4-6 Configuration Module ........................................................................................... 4-4
Table 4-7 USB Connections .................................................................................................. 4-5
Table 4-8 Active Low Discrete Inputs................................................................................... 4-5
Table 4-9 Alert Outputs ......................................................................................................... 4-6
Appendix A Referenced Tables........................................................................A-1
Table A-1 Recommended Coaxial Length ........................................................................... A-1
Table A-2 TNC Connectors .................................................................................................. A-2
Table A-3 GRA 5500 Fault Descriptions ............................................................................. A-3
Table A-4 “Various” POST (Power On Self-Test) Faults .................................................... A-7
GRA 5500 Installation Manual
Page viii
190-01277-00
Rev. A
1 GENERAL DESCRIPTION
1.1 Introduction
This manual presents mechanical and electrical installation requirements for installing the GRA 5500
Radar Altimeter as part of a Garmin Integrated Flight Deck and in retrofit/stand-alone applications. The
GRA 5500 can be integrated into a variety of airframes under an appropriate TC or STC. Each airframe
installation may vary. Use only approved (type or supplemental type) data for specific installation
instructions in a particular aircraft.
1.2
Equipment Description
1.3
Interface Summary
AF
The GRA 5500 is a digitally-based airborne low-range radar altimeter designed to calculate and provide
precise Above Ground Level (AGL) altitude information for both Garmin Integrated Flight Deck and
retrofit/stand-alone radar altimeter applications. The GRA 5500 features a standard two-antenna
architecture utilizing low-power “gated” FMCW operation, digitally-based transmitter operation,
advanced digital signal processing (DSP) based receiver altitude detection algorithms, operation from
ground to 2500 ft AGL, accuracy of +/- 1.5 ft (0 – 100 ft AGL), +/- 2 % (>100 – 2500 ft AGL), fullfeatured self-test operation (BITE) and fault logging functionality (including patent-pending automated
self-testing and fault detection of the entire internal TX, RX, and processing circuitry), a patent-pending
on-ground automated installation calibration procedure to essentially eliminate the traditional requirement
for a minimum RF antenna cable length, 14 Volt and 28 Volt operation, two configurable ARINC 429 data
outputs, two proprietary Garmin HSDB over RS-422 data interfaces, and a standard USB full-speed
interface for convenient unit configuration, calibration, diagnostics, and software updates in retrofit/standalone applications.
The GRA 5500 provides the following interfaces via circular connector:
•
•
•
•
Two “diode ORed” aircraft power inputs (for redundant power systems)
Two ARINC 429 data outputs (configurable for output data formats and data rates)
Two Garmin High-Speed Data Bus (HSDB) over RS-422 data interfaces (used in lieu of ARINC
429 data outputs in Garmin Integrated Flight Deck installations)
Two active-low annunciator outputs used for optional “altitude alert” indications (altitudes are
installation configurable)
Four active-low discrete inputs used as configuration straps in dual and triple installations and for
optional manually-initiated self-test and self-test inhibit operation in retrofit/stand-alone
applications.
One standard Universal Serial Bus (USB) full-speed interface for unit configuration, calibration,
diagnostics, and software updates in retrofit/stand-alone applications.
One Garmin configuration module interface (configuration module usage is not required in
Garmin Integrated Flight Deck installations and is optional in retrofit/stand-alone applications in
order to retain unit configuration parameters external of the installed LRU)
•
•
•
The GRA 5500 also provides RF connections from the transmitter and receiver to the respective radar
altimeter antennas via standard TNC (threaded Neill-Concelman) connectors.
See Section 4 for connection details.
190-01277-00
Rev. A
GRA 5500 Installation Manual
Page 1-1
1.4 Technical Specifications
1.4.1
Environmental Qualification Form
It is the responsibility of the installing agency to obtain the latest revision of the GRA 5500 Environmental
Qualification Form. This form is available directly from Garmin under the following part number:
GRA 5500 Environmental Qualification Form, Garmin part number 005-00616-01
To obtain a copy of this form, see the dealer/OEM portion of the Garmin web site (www.garmin.com).
1.4.2
Physical Characteristics
Table 1-1 lists the physical characteristics for the GRA 5500 unit, rack, and connectors. Refer to
Appendix B for additional information.
Table 1-1 Physical Characteristics
Characteristics
Specifications
3.99” (101.3 mm)
Unit Width (with or without mounting rack)
3.02” (76.7 mm)
Unit Depth (with mounting rack and connector)
Unit Weight (with mounting rack)
11.62” (295.2 mm)
AF
Unit Depth (with mounting rack, connector, and
configuration module)
Unit Height (with mounting rack)
12.08” (306.9 mm)
3.5 lb (1.6 kg)
Typical Mating Circular Connector Weight
0.13 lb (0.06 kg)
Typical Mating RF Connector Weight (2X)
0.07 lb (0.03 kg) (weight listed is for 2 connectors)
General Specifications
1.4.3
For detailed specifications, see the Environmental Qualification Form (Section 1.4.1).
Table 1-2 General Specifications
Characteristics
Operational Temperature Range
Altitude Range
Specifications
-55° C to +85° C
55,000 ft maximum
Software Compliance
RTCA/DO-178B Level B
Hardware Compliance
Not Applicable - The GRA 5500 does not contain
any complex or programmable logic devices.
Environmental Conditions
GRA 5500 Installation Manual
Page 1-2
RTCA/DO-160F
190-01277-00
Rev. A
1.4.4
Performance Specifications
Table 1-3 Performance Specifications
Characteristics
Specifications
± 1.5 ft (3 - 100 ft AGL)
± 2 % (> 100 - 2500 ft AGL)
Altitude Range
-20 - 2550 ft AGL
Altitude Alert Outputs Range
0 - 2500 ft AGL
Altitude Output Time Constant
0.1 second maximum
Transmitter Output
Frequency: 4.25 - 4.35 GHz "Gated" FMCW
Power: 1.0 W nominal
Horizontal Velocity
0 - 200 knots maximum
Vertical Velocity
20 ft/sec maximum (up to 100 ft AGL)
25 ft/sec maximum (above 100 ft AGL)
Pitch Angle
± 20° maximum
Roll Angle
± 20° maximum (with published altitude accuracy
limits)
± 20° to ± 30° (with ± 20 % altitude accuracy limits
throughout entire altitude range)
Power Requirements
AF
1.4.5
Altitude Accuracy
Table 1-4 Power Requirements
Characteristics
Supply Voltage
Power Consumption
Specifications
14/28 VDC. See the Environmental Qualification Form for details
on surge ratings and minimum/maximum operating voltages.
13.75 W maximum (0.5 A at 27.5 VDC, 1.0 A at 13.75 VDC)
1.5 Certification
The conditions and tests 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.
The Appliance Project Identifier (API) for the GRA 5500 is GMN-00946. Documents submitted to the
FAA and other regulatory agencies on behalf of this project will be filed under and referred to by this
number.
190-01277-00
Rev. A
GRA 5500 Installation Manual
Page 1-3
1.5.1
TSO Compliance and Limitations
When installed as a system, the GRA 5500, which must include two Garmin approved antennas (see
Section 2.2.3) installed per Section 2.3.3 of this Installation Manual and a cockpit display of altitude
information, comprise what Garmin considers to be a minimum generic GRA 5500 system installation.
The GRA 5500 lacks a display and by itself is an incomplete system and cannot completely meet the
requirements of TSO-C87a.
This article meets the minimum performance and quality control standards required by a technical standard
order (TSO). Installation of this article requires separate approval.
Table 1-5 provides a list of applicable TSOs for the GRA 5500.
Table 1-5 TSO Compliance
TSO
1.5.2
Applicable
Region List
SW Part
Numbers
006-B1447-0(_)
006-B1448-0(_)
006-B1448-B(_)
except
except
006-D3609-0(_)
except
006-B1447-00
006-B1448-00
except
006-B1448-BA
006-B1447-01
006-B1448-01 006-D3609-00
006-B1448-BB
006-B1447-02
006-B1448-02
and
and
006-D3609-01
and
and
006-B1448-BC
006-B1447-03
006-B1448-03
Airborne
Low-Range
Radio Altimeter
Applicable
LRU System
(Sensor) SW
Part Numbers
TSO-C87a
Functional
Class A
TSO Deviations
AF
Function
Applicable
Applicable
LRU System
Boot Block SW
(Main) SW Part
Part Numbers
Numbers
No TSO deviations were requested or granted for the GRA 5500.
1.6 Operating Instructions
The GRA 5500 is a remote-mount LRU with no user controls or indicators, and normal operation is
completely automated. All user interface is accomplished through a compatible display and/or interface
device. For Garmin Integrated Flight Deck installations, refer to the applicable airframe specific Pilot’s
Guide documentation for operating instructions (available at www.garmin.com). For retrofit installation
operating instructions, reference the operating instructions of the compatible display and/or interface
device. For operating instructions and characteristics for the automated and manual altitude self-test
capability of the appliance, see Section 3.7.4.1 of this document.
1.7 Reference Documents
The following publications are sources of additional information for installing the GRA 5500. Before
installing the GRA 5500, the technician should be familiar with all referenced materials, in addition to this
manual.
Table 1-6 Reference Documents
Part Number
Document
190-00313-12
Circular Connector (and Configuration Module) Installation Instructions
190-00303-00
G1000 System Installation Manual
190-00903-00
G1000 Integrated Flight Deck (LJ/VLJ) System Maintenance Manual
190-00907-00
G1000 System Maintenance Manual Standard Piston/Turboprop Aircraft
GRA 5500 Installation Manual
Page 1-4
190-01277-00
Rev. A
2 INSTALLATION OVERVIEW
2.1 Introduction
This section provides hardware equipment information for installing the GRA 5500, related hardware, and
antennas. Installation of the GRA 5500 must follow the aircraft TC or STC requirements. Cabling is
fabricated by the installing agency to fit each particular aircraft. The guidance of FAA advisory circulars
AC 43.13-1B and AC 43.13-2B, where applicable, may be found useful for making retrofit installations
that comply with FAA regulations.
Refer to Appendix B for rack drawings and dimensions.
2.2 Installation Materials
The GRA 5500 is only available as a single unit under the following part number:
Table 2-1 Available Units
Garmin P/N
GRA 5500, Unit Only (011-02537-00)
2.2.1
Available Equipment
Item
010-00946-00
AF
Each of the following accessories are provided separately from the GRA 5500 and are required for
installation.
Table 2-2 Available Equipment
Item
Sub-Assy, GRA 5500 Mounting Rack
Garmin P/N
011-02567-00
011-02573-00
Sub-Assy, Connector Kit w/Config Module & USB Pigtail,
GRA 5500 (For retrofit/stand-alone installations)*
011-02573-01
Sub-Assy, Connector Kit, GRA 5500 (For Garmin Integrated
Flight Deck installations)*
*Each GRA 5500 connector kit provides seal plugs for the circular connector. Refer to the Circular
Connector (and Configuration Module) Installation Instructions (GPN: 190-00313-12) for seal plug,
config module, and connector installation instructions.
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GRA 5500 Installation Manual
Page 2-1
2.2.2
Additional Equipment Required
The installation accessories listed in Table 2-3 are required but not provided:
Table 2-3 Additional Equipment Required
Item
Specification
Radar Altimeter Antennas (2 per installation)
See Section 2.2.3 for more information.
Antenna Coaxial Cables (2 per installation)
See Section 2.5.1 for more information.
TNC connectors (4 per installation)
See Section 2.5.1 for more information.
Circuit Breakers (1 or 2 per installation)
5 amp aircraft circuit breakers are recommended
for 28 VDC operation. Larger circuit breakers may
be required for 14 VDC operation.
2.2.3
Approved Radar Altimeter Antennas
The antennas listed in Table 2-4 are the only approved antennas for use with the GRA 5500 radar
altimeter:
AF
Table 2-4 Approved Radar Altimeter Antennas
Manufacturer Part Number
Garmin Part Number*
S67-2002
013-00378-00
S67-2002-4
013-00378-04
S67-2002-12
013-00378-12
S67-2002-13
013-00378-13
S67-2002-14
013-00378-14
S67-2002-18
013-00378-18
S67-2002-19
013-00378-19
Sensor Systems Inc.
S67-2002-29
013-00378-29
Sensor Systems Inc.
S67-2002-45
013-00378-45
Antenna Manufacturer
Sensor Systems Inc.
Sensor Systems Inc.
Sensor Systems Inc.
Sensor Systems Inc.
Sensor Systems Inc.
Sensor Systems Inc.
Sensor Systems Inc.
*Garmin encourages customers to procure the selected antenna type directly from the antenna
manufacturer. For customers who do not have a business relationship with the antenna manufacturer,
the selected antenna type may be purchased through Garmin by referencing the corresponding Garmin
Part Number.
GRA 5500 Installation Manual
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190-01277-00
Rev. A
2.3 Installation Considerations
Fabrication of a wiring harness is required. Sound mechanical and electrical methods and practices are
required for installation of the GRA 5500.
The GRA 5500 requires two antennas to be installed for each system installation. One antenna is used to
transmit the radar signal, and the other is used to simultaneously receive the reflected signal.
2.3.1
Multiplex Operation (Dual and Triple Unit Installations)
Each GRA 5500 system fulfills all TSO minimum accuracy requirements when installed with either one or
two additional GRA 5500 systems on the same aircraft. Mutual interaction is not operationally significant.
See Section 2.3.3 for guidance in planning antenna locations for multi-unit installations. The second and/
or third unit in a multi-unit installation is selected by strapping the respective discrete input(s) on each unit
per Table 2-5.
Table 2-5 System ID Discrete Inputs
RADAR ALT SYSTEM ID
PROGRAM* 2
GRA 5500 UNIT NUMBER
Open
Open
Ground
Open
AF
Open
Ground
2.3.2
RADAR ALT SYSTEM ID
PROGRAM* 1
Ground
Ground
Not Allowed
Installation Approval Considerations for Pressurized Aircraft
Cable installations (both wiring harness and coaxial antenna cables) on pressurized cabin aircraft require
FAA approved installation design and engineering substantiation data whenever such installations
incorporate alteration (penetration) of the cabin pressure vessel by connector holes and/or mounting
arrangements.
For needed engineering support pertaining to the design and approval of such pressurized aircraft
installations, it is recommended that the installer proceed according to any of the following listed
alternatives:
1. Obtain approved installation design data from the aircraft manufacturer.
2. Obtain an FAA approved STC, pertaining to and valid for the subject installation.
3. Contact the FAA Aircraft Certification Office in the appropriate Region and request identification
of FAA Designated Engineering Representatives (DERs) who are authorized to prepare and
approve the required installation engineering data.
4. Locate an appropriate consultant FAA DER from the “FAA Consultant DER Directory” at the
FAA “Designee and Delegation” web page.
5. Contact an aviation industry organization such as the Aircraft Electronics Association for
assistance.
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GRA 5500 Installation Manual
Page 2-3
2.3.3
Antenna Location Planning Guidance
NOTE
The ability of any radar altimeter system to accurately and reliably detect and process
radar altitude signals is highly dependent upon correct transmitter (TX) antenna and
receiver (RX) antenna placement on the airframe. Stated performance specifications for
the GRA 5500 can only be achieved when the system is installed in accordance with all the
guidelines stipulated in this section and with all other instructions given in this
Installation Manual.
Careful planning for optimal antenna placement is extremely critical in any radar altimeter installation
and requires a high level of attention to detail in order to achieve optimal system performance of the
GRA 5500. The following guidelines must be followed in order to achieve acceptable performance of the
system during all stages of normal operation. Failure to follow any of these guidelines will result in
degradation of system performance.
If there is any question as to whether a planned installation will meet all the guidelines given below or may
require special consideration, contact Garmin for further support.
AF
1. Location on Aircraft: Antennas must be mounted on a surface of the bottom of the aircraft near the
center point of pitch and roll rotation (this reduces the effect of momentary pitch and roll altitude
offsets/inaccuracies during approach and landing or while maneuvering the aircraft).
2. Angle of Antennas to Ground: Antennas must be mounted such that the surface of each antenna is
within +/- 6° of horizontal during level flight. If adapter plates are manufactured to ensure this
angle is met, the adapters must not recess the antenna surfaces within the skin of the aircraft. The
adapters must only extrude the antenna surfaces outside the skin of the aircraft.
3. Mounting Surface: The antennas are normally mounted on a continuous metallic surface. Nonmetallic surfaces or ones with discontinuities require special consideration. Contact Garmin for
more information or clarification if needed.
4. Minimum Height: Due to antenna spacing limits (described in following guideline 8.), the
minimum antenna height possible above ground while parked, taxiing, or at aircraft touchdown is
20 inches for any aircraft.
5. Antenna Clearance Cones: The locations chosen for both antennas must be free of aircraft
projections (landing gear, flaps, drainage vents, etc…) within a 120° cone from each antenna
downward to prevent locking onto false altitude returns. Consider all possible modes of aircraft
operation when establishing compliance with this guideline (e.g. – landing gear distances while in
transition, flap distances while fully extended, etc.).
6. Distance to Other Antennas: The radar altimeter antennas should be located no closer than 3 feet
to any other aircraft antenna.
7. Relative Location (Single System): The two radar altimeter antennas must be mounted either in a
straight, nose-to-tail longitudinal line with both antenna arrows pointing forward, or in a straight,
side-to-side, lateral line with both arrows pointing to one side of the aircraft or the other (they may
alternatively point toward each other or away from each other). The longitudinal installation is
preferred over the lateral installation to provide more roll than pitch angle coverage. Additionally,
the angle between the antenna surface planes must not exceed 6° and the antennas must not be
tipped toward each other at any angle. In a single system, either antenna may be selected as the
transmitter (TX) or receiver (RX) antenna.
GRA 5500 Installation Manual
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Rev. A
D
AF
8. Relative Antenna Spacing (Single System): The two antennas must be spaced apart a minimum
distance of 20 inches (center to center). They must be spaced a maximum distance apart of not
more than their equivalent distance to the ground while parked, taxiing, or at aircraft touchdown
(whichever is less). The absolute maximum spacing is 6 feet (regardless of touchdown, taxiing, or
parked height). For example, if the antenna distance to the ground at touchdown is 36 inches and
when parked is 30 inches, then the antenna spacing must not be more than 30 inches. Ideally, the
antennas would be spaced halfway between the given minimum and maximum constraints for the
aircraft.
9. Dual System Additional Guidance: Each individual system within a dual system installation must
first conform to the constraints of a single system. In addition, a dual system installation must
conform to an end-to-end configuration (as shown in Figure 2-1 or Figure 2-2) or a side-by-side
configuration (as shown in Figure 2-3). The end-to-end configuration requires 5 inches (center to
center) minimum spacing between systems with no limit on maximum spacing. The side-by-side
configuration requires 5 inches (center to center) minimum spacing between systems with
maximum spacing limited by the 35° angle as shown. For example, if the spacing between TX1
and RX1 is 30 inches, then the spacing between RX2 and RX1 must not be more than 30 inches
multiplied by the tangent of 35° (approximately 21 inches). The angular limit is necessary because
unwanted signal leakage between TX to RX increases rapidly as the end-to-end antenna
orientation transitions toward a pseudo side-to-side orientation (TX to TX and RX to RX antenna
spacings are not vulnerable to this leakage). It is essential that functional antenna numbering
assignments (e.g. – TX1, RX2, etc.) are used during planning and installation in order to avoid
confusion.
10. Triple System Additional Guidance: Each individual system within a triple system installation
must first conform to the constraints of a single system. In addition, a triple system installation
must conform to an end-to-end configuration (as shown in Figure 2-1 or Figure 2-2), a side-byside configuration (as shown in Figure 2-3), or a hybrid configuration (as shown in Figure 2-4).
The end-to-end configuration requires 5 inches (center to center) minimum spacing between
systems with no limit on maximum spacing. The side-by-side configuration requires 5 inches
(center to center) minimum spacing between systems with maximum spacing limited by the
overall 35° angle as shown. The hybrid configuration requires the minimum distances and
maximum angles shown. It is essential that functional antenna numbering assignments (e.g. –
TX1, RX2, etc.) are used during planning and installation in order to avoid confusion.
190-01277-00
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GRA 5500 Installation Manual
Page 2-5
Forward
T1
Forward
R1
R2
T1
AF
5” min.
T2
R1
5” min.
5” min.
R2
T3
T2
R3
Dual End-to-End System
Triple End-to-End System
Figure 2-1 Standard Dual and Triple End-to-End System Layouts
GRA 5500 Installation Manual
Page 2-6
190-01277-00
Rev. A
Forward
Forward
T1
T1
R2
AF
10”
10”
R2
5”
R3
5”
10”
R1
10”
R1
10”
T2
5”
T2
Dual End-to-End System
T3
Triple End-to-End System
Figure 2-2 Compact Dual and Triple End-to-End System Layouts
190-01277-00
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GRA 5500 Installation Manual
Page 2-7
Forward
5” min.
T1
T2
T3
35° max.
R1
35° max.
AF
5” min.
T1
T2
Forward
5” min.
R2
R1
R2
R3
Dual Side-by-Side System
Triple Side-by-Side System
Figure 2-3 Dual and Triple Side-by-Side System Layouts
GRA 5500 Installation Manual
Page 2-8
190-01277-00
Rev. A
Forward
5” min.
T1
T2
AF
35° max.
R1
R2
5” min.
35° max.
R3
T3
Figure 2-4 Hybrid Triple System Layout
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GRA 5500 Installation Manual
Page 2-9
2.3.4
Antenna Installation Considerations
The following guidelines should be observed when implementing the antenna installation:
1. Antenna and airframe surfaces should be prepared and bonded according to guidance given in
Section 2.4.
2. A visual inspection should be performed to verify that all coaxial cables are connected properly
before attempting to operate the equipment.
3. Always refer to the antenna manufacturer’s provided installation material for any additional
installation guidance specific to the antenna type being used.
2.4 Electrical Bonding
All electrical equipment, supporting brackets, racks, and antennas should be electrically bonded to the
aircraft’s main structure. Refer to SAE ARP 1870 Section 5 when surface preparation is required to
achieve electrical bond. The electrical bond should achieve direct current (DC) resistance less than or
equal to 2.5 milliohms to the local structure to where the equipment is mounted. Compliance should be
verified by inspection using a calibrated milliohm meter. An equivalent OEM procedure may also be
substituted. There may be OEM specific reasons for electrically isolating equipment or having a higher
bond resistance. These reasons should be rationalized upon installation approval. In general, Garmin
recommends that all GRA 5500 equipment be electrically bonded.
AF
2.5 Cabling and Wiring
Refer to the interconnect examples in Appendix C for wire gauge guidance. Use only wire, coaxial cable,
and installation methods that are compliant with governing aviation regulations and standards.
•
•
•
•
Any bend radius applied to a cable must not exceed the minimum bend radius specification as prescribed
by the cable manufacturer for the specific cable type. It is recommended that the bend radius applied to a
coaxial cable is minimized when in close proximity to the connector ferrule or compression housing in
order to decrease side loading of the cable at the crimp or compression area. Whenever possible, it is
recommended that no clearly visible bending exists within 1/2 inch of each coaxial cable assembly
connector ferrule or compression housing. All cables should be secured in a manner that minimizes any
potential back and forth side loading of the cable at the connector crimp or compression area. When
routing the wire and cable, the installing agency should observe the following important precautions:
Route all wiring and coaxial cables in a manner that maintains a minimal length of cable needed to
complete the required connections, while avoiding, (as much as possible) routing near noisy
environments such as power sources and circuits that carry or generate heavy current, 400 Hz
generators, trim motors, pulse transmitting equipment, or fluorescent lighting power sources.
For all wiring and coaxial cables, do not exceed the specified minimum bend radius and eliminate
any potential of sharp bends that exceed the minimum bend radius (refer to preceding paragraph
for additional cable recommendations).
Ensure that all wiring and coaxial cables are properly secured while avoiding the potential of
deteriorating the integrity of the insulation and jackets because of rubbing against the aircraft
structure, other installed equipment, or excessively tight cable ties.
Prior to connecting the fabricated wiring harness to the GRA 5500, verify correct routing of
aircraft power and aircraft power ground to the assigned pins and verify that aircraft power is
available at the assigned pins after routing verification.
GRA 5500 Installation Manual
Page 2-10
190-01277-00
Rev. A
2.5.1
Antenna Coaxial Cables (Requirements and Fabrication Guidance)
The GRA 5500 requires a minimum of two coaxial cable assemblies (each coaxial cable assembly consists
of a coaxial cable and a connector properly terminating each end of the coaxial cable) assembled with the
same type of coaxial cable for connection from the radar altimeter antennas to the LRU transmitter (TX)
and receiver (RX) ports. If multiple coaxial cable assemblies must be used with adapters in order to
connect the unit ports to the antennas, all assemblies must use the same type of coaxial cable. Although
the use of adapters (both right angle and straight) may be unavoidable when addressing certain
installations, minimal use of adapters in the installation is recommended whenever possible.
NOTE
Any in-line or bulkhead penetrations must be evaluated separately from the coaxial cable
assemblies and require special consideration. It is the responsibility of the installing
agency to show airworthiness of the installed coaxial cable assemblies (whether
fabricated or purchased).
The requirements for the RF transmission lines made of coaxial cable assemblies used to connect the GRA
5500 TX and RX ports to the radar altimeter antennas are as follows (see Figure 2-5):
NOTE
AF
For the purpose of this document, an RF transmission line is defined as either a single
coaxial cable assembly used to connect a unit TX or RX port to its respective antenna port,
or a number of coaxial cable assemblies and adapters used to connect a unit TX or RX
port to its respective antenna port. It is the responsibility of the installing agency to
ensure that the RF transmission lines and associated coaxial cable assemblies meet the
following requirements in order to comply with the system installation standards.
1. The maximum total RF loss of each RF transmission line (made up of one or more cable
assemblies with adapters) must not exceed 5.0 dB at 4.3 GHz.
2. The maximum total length of each RF transmission line (made up of one or more cable assemblies
with adapters included in the length total) must not exceed 30 feet.
3. The minimum total length of each RF transmission line (made up of one or more cable assemblies
with adapters included in the length total) must not be less than 1 foot.
4. All coaxial cable assemblies making up the RF transmission line must have a Voltage Standing
Wave Ratio (VSWR) of less than 1.5:1, at each connector, at a frequency of 4.3 GHz.
5. The RF transmission line used to connect the unit to the antennas must have a total Voltage
Standing Wave Ratio (VSWR) of less than 1.5:1, at each of the two end connectors of the
assembled RF transmission lines, at a frequency of 4.3 GHz.
The VSWR of any adapter used to complete the assembly of an RF transmission line must be compliant
with the adapter’s manufacturer specification at 4.3 GHz.
190-01277-00
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GRA 5500 Installation Manual
Page 2-11
GRA 5500
RX Port
30 feet maximum length, 1 foot minimum length
5.0 dB maximum attenuation, VSWR <1.5:1
GRA 5500
TX Port
AF
30 feet maximum length, 1 foot minimum length
5.0 dB maximum attenuation, VSWR <1.5:1
Figure 2-5 Coaxial Cable Requirements
TNC male connectors are required to build the coaxial cable assemblies and are not provided with the
GRA 5500 system. Table A-1 provides guidance information concerning cable types, cable type
attenuation, and cable type lengths in agreement with the overall requirements for the coaxial cable
assemblies. The maximum coaxial cable lengths in Table A-1 are for reference only and are defined as the
end-to-end cut cable length (non-terminated cable lengths). Actual cable lengths may vary depending on
the manufacturer specifications and recommendations for the specific coaxial cable and connectors
(Table A-2) used. Table A-2 references common sources for cable and connector part numbers.
Figure 2-6 shows suggested installation instructions for typical TNC connectors.
GRA 5500 Installation Manual
Page 2-12
190-01277-00
Rev. A
T
AF
Figure 2-6 TNC Connector Installation
NOTE
It is recommended that a two inch piece of adhesive heat shrink tubing be installed over
all coaxial cable interfaces. The heat shrink tubing should overlap the connector body as
much as practical without interfering with the coupling nut (see Figure 2-7).
Connector
Body
Ferrule
Coaxial Cable
Heat shrink not to protrude past
this surface.
Figure 2-7 Heat Shrink Positioning
NOTE
It is recommended that the nominal end-to-end coaxial cable (non-terminated) length for
each assembly be recorded for the specific installation in the event that a particular
coaxial cable assembly associated with an installed set should require replacement.
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GRA 5500 Installation Manual
Page 2-13
2.6 Cooling Requirements
Dedicated cooling is not required for the GRA 5500 to meet indicated EQF categories. Thermal analysis
must be performed to verify that high temperature limits implied by the indicated EQF categories for the
GRA 5500 are not exceeded during normal operation of the aircraft. Guidance can be found in the Garmin
Integrated Avionics System Thermal Management Plan document (GPN 190-00313-50) and the Garmin
Integrated Avionics System Thermal Validation Procedure (GPN 190-00313-51).
Contact Garmin for additional cooling guidance.
2.7 Mounting Requirements
AF
The GRA 5500 mounting surface should be capable of providing a sufficient electrical bond to the aircraft
to minimize Electromagnetic Interference (EMI) and provide protection from High-Intensity Radiation
Fields (HIRF). Bonding resistance measured between the GRA 5500 mounting rack and the airframe
should measure less than 2.5 milliohms. The GRA 5500 must be mounted in the vertical position using the
GRA 5500 mounting rack. Refer to Appendix B for outline and installation drawings.
GRA 5500 MOUNTING RACK
011-02567-00
Figure 2-8 GRA 5500 Mounting Rack
GRA 5500 Installation Manual
Page 2-14
190-01277-00
Rev. A
3 INSTALLATION PROCEDURE
3.1 Unpacking Unit
Carefully unpack the equipment and make a visual inspection of the unit for evidence of damage incurred
during shipment. If the unit is damaged, notify the carrier and file a claim. To justify a claim, save the
original shipping container and all packing materials. Do not return the unit to Garmin until the carrier has
authorized the claim.
Retain the original shipping containers for storage. If the original containers are not available, a separate
cardboard container should be prepared that is large enough to accommodate sufficient packing material to
prevent movement.
3.2 Wiring Harness Installation
Allow adequate space for installation of cables and connectors. The installer shall supply and fabricate all
of the cables. All electrical connections to the GRA 5500 are made through one 55 pin circular connector
(Figure 4-1). Section 4 defines the electrical characteristics of all input and output signals. Required
connector and associated hardware are supplied with the connector kit.
See Appendix C for examples of interconnect wiring diagrams. Construct the actual harness in accordance
with aircraft manufacturer authorized interconnect standards.
AF
Contacts for the 55 pin connector must be crimped onto the individual wires of the aircraft wiring harness.
Table 3-1 through Table 3-4 list contact part numbers (for reference) and recommended tools.
Table 3-1 Pin Contact Part Numbers
Item
Part Number
Military
M39029/56-348
Pin Contacts
Manufacturer
Table 3-2 Recommended Crimp Tools
Military P/N
Contact Size/Type
Crimping Tool
Turret Die or
Positioner
22D Socket
M22520/2-01
M22520/7-01
M22520/2-07
M22520/7-05
Manufacturer
Table 3-3 Recommended Insertion Tools
Plastic Tools
Metal Tools
Angle Type
Use with
Contact
Size
MS
Part Number
Color
MS Part
Number
22D
M81969/14-01*
Green/(White)
M81969/8-01
Straight
Type
Proprietary Proprietary
Part
Part
Number
Number
Color
11-8674-24
Black
11-8794-24
*Double end insertion/removal tool.
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GRA 5500 Installation Manual
Page 3-1
Table 3-4 Recommended Removal Tools
Plastic Tools
Use with
Contact MS Part
Size
Number
22D
Color
M81969/ (Green)/
14-01*
White
Metal Tools
Angle Type
For Unwired
Contacts
Proprietary
Part Number
MS Part
Number
11-10050-07
M81969/8-02
Proprietary
Part
Number
Straight
Type
Proprietary
Part
Number
Color
11-8675-24
11/8795-24
Green/
White
*Double end insertion/removal tool.
NOTE
Non-Garmin part numbers shown are not maintained by Garmin and consequently are
subject to change without notice.
3.3 Backshell Assembly
3.4 Antenna Installation
AF
The GRA 5500 connector kit includes a circular strain relief assembly. The circular strain relief gives the
installer the ability to quickly and easily terminate shields. In non-Garmin Integrated Flight Deck (retrofit)
installations, the Garmin circular configuration module may also be attached to the strain relief (see
Figure B-2). Refer to the document Circular Connector (and Configuration Module) Installation
Instructions (190-00313-12) for circular connector installation.
Refer to Section 2.3.4 for installation instructions.
3.5 Unit Installation
For final installation and assembly, refer to the outline and installation drawings shown in Appendix B of
this manual and to the following procedures.
Installation Procedure (see Figure 3-1)
3.5.1
1. Place the unit on the mounting rack, ensuring the GRA 5500 rear feet are aligned in the mounting
rack slots.
2. Slide the GRA 5500 back until the feet are fully engaged with the mounting rack.
3. Lift the lockdown mechanism collar in place on the GRA 5500 hook and hand turn the lockdown
mechanism knob clockwise until the GRA 5500 is secure and the knob cannot reasonably be
ratcheted any tighter by hand.
3.5.2
Removal Procedure (see Figure 3-1)
1. Pull back on the lockdown mechanism and simultaneously turn counterclockwise until free.
GRA 5500 Installation Manual
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190-01277-00
Rev. A
2. Disengage the lockdown mechanism collar from the GRA 5500 hook and slide the GRA 5500
forward to remove from the mounting rack.
UNIT HOOK
ENGAGEMENT
FEET
2 PLACES
AF
FEET ENGAGEMENT
LOCATION
2 PLACES
LOCKDOWN MECHANISM COLLAR
LOCKDOWN MECHANISM KNOB
SECTION VIEW SHOWING
UNIT FEET ENGAGED INTO
MOUNTING RACK
2 PLACES
Figure 3-1 GRA 5500 Installation
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GRA 5500 Installation Manual
Page 3-3
3.6 Downloading and Installing the GRA 5500 Retrofit Installation Tool
GRA 5500 configuration, calibration, diagnostics, and software upgrades are performed (in retrofit/nonGIFD installations) using a personal computer (installed with Microsoft Windows XP or later) and the
GRA 5500 Retrofit Installation Tool, Garmin part number 006-A0451-00. This tool is also used to assist
in the diagnosis and resolution of asserts found in the GRA 5500 assert log during the installation process
and during post-installation flight operation. The tool is available for download from the Dealer Resource
Center portion of the Garmin website (www.garmin.com). See the accompanying “readme” file in the
tool’s installation directory for the latest instructions.
NOTE
A standard USB-A plug to USB-B plug commercial cable (not provided) is required to
interface between a personal computer USB-A receptacle and the GRA 5500 USB-B
receptacle installed in the wiring harness (in retrofit/non-GIFD installations). This
dongle cable is required to use the GRA 5500 Retrofit Installation Tool. Refer to
Figure C-4 for applicable interconnect drawings.
Installation
NOTE
AF
1. Once downloaded, launch the installation file from the directory in which it is stored (or use the
web browser’s download shortcuts).
2. The GRA 5500 Retrofit Installation Tool Setup Wizard will begin.
3. Click “Next” as prompted by the setup wizard, and adjust any settings (e.g. installation directory)
as needed.
4. The last screen of the setup wizard will show “Installation Complete.” Click the “Close” button to
close the setup wizard.
Depending on the computer’s security settings, Windows may prompt the installer to allow
the installation software to make changes to the computer. The installer will need access
to install hardware drivers, program files, and shortcuts. The application may be
uninstalled at any time through the Windows Control Panel.
GRA 5500 Installation Manual
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3.7 Post Installation Configuration and Checkout Procedures
The following actions must be performed after initial installation of the GRA 5500 and any time after the
equipment has been removed/disconnected and then reinstalled/reconnected:
1. GRA 5500 Configuration/Checkout for Varying Installation Types (Section 3.7.1)
2. Using the GRA 5500 Retrofit Installation Tool (Section 3.7.2) - This step is not required for GIFD
installations.
3. Zero-Foot Calibration Procedure and Initial Built-In Self-Test (Section 3.7.3 and Section 3.7.4)
3.7.1
GRA 5500 Configuration/Checkout for Varying Installation Types
Configuration instructions may differ according to the specifics of the installation. Refer to the following
subsections for specific instructions applicable to the various installation types.
3.7.1.1
FAA Approved Garmin Integrated Flight Deck GRA 5500 Installation
When installed as part of a Garmin Integrated Flight Deck via the Garmin High Speed Data Bus (HSDB
over RS-422), the GRA 5500 must have FAA approved configuration data.
AF
Configuration data is loaded to the GRA 5500 from an aircraft-specific software loader card. For basic
configuration information refer to the appropriate maintenance manual. For actual installation/checkout,
use only aircraft manufacturer approved or STC checkout procedures.
NOTE
GDU display units with SW versions prior to v15.00 do not support connection of the
GRA 5500 to the Garmin Integrated Flight Deck via the Garmin High Speed Data Bus
(HSDB over RS-422). In these installations the GRA 5500 must be connected as in a
retrofit installation. See Section 3.7.1.2 for more information.
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3.7.1.2
Non-Garmin Integrated Flight Deck (Retrofit) GRA 5500 Installation
Configuration, calibration, diagnostics, and software upgrades are accomplished using the GRA 5500
Retrofit Installation Tool (Section 3.7.2).
NOTE
Installations that are unable to electronically display the software part number of the GRA
5500 should affix a label on the GRA 5500 LRU marked with the software part number to
meet TSO marking requirements.
3.7.2
Using the GRA 5500 Retrofit Installation Tool
After the GRA 5500 Retrofit Installation Tool has been installed and the PC has been connected to the
GRA 5500 (as described in Section 3.6), start the GRA 5500 Retrofit Installation Tool from the provided
“Start Menu” shortcut, or launch the application from its program folder. Next, power-up the GRA 5500
by applying aircraft power.
The connection status in the lower, right-hand corner of the GRA 5500 Retrofit Installation Tool will
transition from “Not Connected,” to “Connecting,” and finally to “Connected.”
AF
If the GRA 5500 Retrofit Installation Tool does not display “Connected” in the lower-right hand corner,
check the installation and make sure the GRA 5500 has been powered-up and that the USB cable is
properly connected to the PC.
If the PC displays a “Found New Hardware” wizard, the GRA 5500 Retrofit Installation Tool was not
successfully installed. It may be necessary to cancel the “Found New Hardware” wizard and attempt to reinstall the GRA 5500 Retrofit Installation Tool. If the “Found New Hardware” wizard continues to launch
upon detecting the GRA 5500, it may be necessary to manually load the drivers. Copies of the drivers’
“.inf” files are located in the target installation directory selected during installation in Section 3.6.
Consult the PC’s operating system documentation on manually installing drivers.
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When configuring a new GRA 5500 installation, the GRA 5500 Retrofit Installation Tool should look
similar to Figure 3-2 (note the annunciated Calibration fault).
NOTE
AF
If any other faults besides a Calibration fault are indicated, it will not be possible to
perform the zero-foot calibration procedure. See Table A-3 for resolutions to specific fault
conditions before attempting to perform the zero-foot calibration procedure.
Figure 3-2 GRA 5500 Retrofit Installation Tool (New Installation)
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3.7.2.1
Zero-Foot Calibration Procedure
Before the GRA 5500 is ready for normal operation, it is necessary to perform the following zero-foot
calibration procedure.
NOTE
Before initiating the zero-foot calibration procedure, see Section 3.7.3 to ensure the GRA
5500 is physically ready to be calibrated.
The GRA 5500 Retrofit Installation Tool provides an interface button to initiate the zero-foot calibration
procedure. Clicking this button will make a series of requests to the connected GRA 5500. During the
calibration procedure, the GRA 5500 Retrofit Installation Tool will display a progress dialog. Once the
calibration procedure has completed, the progress dialog will close, and the status tab will be updated. If
the fault list does not annunciate any faults and the information displayed in the status bar area indicates “0
ft” and “Normal,” the unit has been successfully calibrated.
If a fault is indicated, see Table A-3 for resolution methods.
AF
The following sections detail the primary functions of the GRA 5500 Retrofit Installation Tool.
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Status Tab
AF
The status tab (see Figure 3-3) provides the basic fault status of the unit. During normal operation, the
status of each fault should indicate “(normal).” If the unit indicates a fault, the fault’s entry on the list will
be displayed in a bold, red font. The status will also update to show the specific failure under that fault.
See Table A-3 for a comprehensive list of possible failures.
Figure 3-3 GRA 5500 Retrofit Installation Tool Status Tab (Normal Operation)
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Configuration Tab
AF
The configuration tab (see Figure 3-4) provides an interface to change the unit’s per-airframe
configuration. The configuration tab displays the unit’s current settings. After adjusting any settings, the
“Save Configuration to Unit” button must be clicked to send the configuration values to the GRA 5500.
Clicking the button labeled “Restore Defaults to Unit” restores all settings to their default, factory state.
Figure 3-4 GRA 5500 Retrofit Installation Tool Configuration Tab
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Configuration Items
•
ARINC 429 Channel 1:
The “ARINC 429 Channel 1” section adjusts the ARINC 429 Channel 1 settings.
Table 3-5 ARINC 429 Channel 1 Settings
Configuration
Description
Check to enable the channel
Enable Channel
Uncheck to disable the channel
Check to enable high speed (100 kbps) operation
Enable High Speed
Uncheck to enable low speed (12.5 kbps) operation
Check to enable sending label 164 (Radio Altitude, BNR format)
Enable Label 164
Uncheck to disable sending label 164
Check to enable sending label 165 (Radio Altitude, BCD format)
Enable Label 165
Uncheck to disable sending label 165
Check to enable sending label 377 (Equipment Identification)
Enable Label 377
AF
•
Uncheck to disable sending label 377
ARINC 429 Channel 2:
The “ARINC 429 Channel 2” section adjusts the ARINC 429 Channel 2 settings.
Configuration
Description
Check to enable the channel
Uncheck to disable the channel
Enable Channel
Table 3-6 ARINC 429 Channel 2 Settings
Enable High Speed
Enable Label 164
Enable Label 165
Enable Label 377
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Check to enable high speed (100 kbps) operation
Uncheck to enable low speed (12.5 kbps) operation
Check to enable sending label 164 (Radio Altitude, BNR format)
Uncheck to disable sending label 164
Check to enable sending label 165 (Radio Altitude, BCD format)
Uncheck to disable sending label 165
Check to enable sending label 377 (Equipment Identification)
Uncheck to disable sending label 377
GRA 5500 Installation Manual
Page 3-11
•
Altitude Alert 1 Height:
Altitude alert heights between 0 and 2500 ft may be configured for each Altitude Alert annunciator
output. See Section 4.4.2 for more information on the functionality of the Altitude Alert
annunciator outputs.
•
Altitude Alert 2 Height
Altitude alert heights between 0 and 2500 ft may be configured for each Altitude Alert annunciator
output. See Section 4.4.2 for more information on the functionality of the Altitude Alert
annunciator outputs.
•
Manual Height Offset
The “Manual Height Offset” section configures a manual offset to all heights reported by the GRA
5500. This setting allows the GRA 5500 to report values other than “0 ft” at the zero-foot
calibration point. Setting the manual height offset to a positive value causes the GRA 5500 to
report that respective value as a “negative height” at the zero-foot calibration point (hence,
negatively offset from the calibrated height). Values are limited between 0 and +20 ft. Setting the
manual height offset to a negative value is not allowed by the GRA 5500 Retrofit Installation Tool.
AF
Configuring a manual height offset for the GRA 5500 may be useful for installations when a “0 ft”
reading is desired immediately at aircraft touchdown, instead of when the aircraft is completely at
rest on the ground (such as after the landing gear is compressed or in installations where the radar
altimeter antennas are mounted substantially forward of the main landing gear).
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Software Tab
AF
The software tab (see Figure 3-5) provides a list of currently installed software regions on the GRA 5500
as well as an interface to load new software regions to the GRA 5500.
Figure 3-5 GRA 5500 Retrofit Installation Tool Software Tab
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Updating Software
NOTE
Care should be taken when updating software in the field. While the process is designed to
be very robust and reliable, each step must be followed carefully to ensure correct
operation of the GRA 5500. Deviation from these procedures may result in a failure of the
GRA 5500 to operate correctly and may require factory servicing.
1. Depending on the method of receiving updated software region files, it may be required to extract
the files to a directory on the PC that is/will be connected to the GRA 5500. The GRA 5500
Retrofit Installation Tool will only recognize Garmin Aviation binary region files (.bin).
2. Enter the directory where these files are stored, or click the “Browse” button to locate the
directory.
3. Once the directory is selected, the GRA 5500 Retrofit Installation Tool will display a list of all
valid software region files in the directory. If no software region information is displayed in the
list, the selected directory does not contain valid software region files. Make sure the files have
been properly extracted (to .bin files), and have not been corrupted during transfer.
AF
NOTE
Due to the sensitive nature of the “Boot Block” and “Region List” software regions, the
installation tool will not list these software region files by default. If these software
regions must be updated in the field, click the “Tools” pull-down menu, select
“Preferences,” click the “Overrides” tab, check the box labeled “Allow Boot Block and
Region List updates,” and click “OK.” The available software list will now display any
valid Boot Block and Region List files.
4. Select the region(s) to upload to the unit. By default, the latest versions of all valid software
region files are selected. Single-clicking a software region will eliminate all other updates. Group
selection (CTRL+click and/or SHIFT+click) permits selecting multiple regions to upload at once.
NOTE
If there are multiple versions of the same software region in the selected directory and
more than one are selected, only the newest version will be sent to the unit.
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5. Click the “Upload Selected Software Regions” button to initiate the update procedure. This will
produce a progress dialog indicating the software update progress. Once the software update has
completed the GRA 5500 will be automatically restarted to reload the new software.
CAUTION
While the GRA 5500 provides extensive protection from corrupt and/or invalid
updates, it is important to allow the software update process to completely finish
before attempting to forcibly close the GRA 5500 Retrofit Installation Tool, shut
down Windows, power-down the PC, power-down the GRA 5500, or disconnect
the GRA 5500 from the PC. If a “Main System” or “Sensor System” software
update is accidentally corrupted in the field, the unit can still be recovered using
the GRA 5500 Retrofit Installation Tool (by repeating the software update
procedure). If a “Boot Block” or “Region List” update is accidentally corrupted in
the field, the unit must be sent to Garmin for servicing.
AF
6. Once the progress dialog has closed, check the “Current Software” section to verify that the
previously selected software regions have been successfully updated. The “Current Software”
section displays product information for each software region currently loaded on the GRA 5500.
Each region is shown with its corresponding Garmin part number and software release version.
NOTE
If the reported versions are not updated, restart the GRA 5500 by cycling aircraft power.
If the reported versions are still not updated, the software update has failed. It may be
necessary to repeat the software update procedure or return the unit to Garmin for
service.
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3.7.3
Zero-Foot Calibration
After the GRA 5500 is configured, but before it may be put into normal flight operation, a one-time zerofoot calibration procedure must be performed on the unit in order to “zero” the altitude outputs from the
unit for the individual aircraft installation. This procedure removes the altitude offsets associated with
antenna cables, antenna height above ground, etc. This procedure is accomplished via GDU display
interface in Garmin Integrated Flight Deck installations (see Section 3.7.1.1). In non-Garmin Integrated
Flight Deck (retrofit) installations this procedure is accomplished via the GRA 5500 Retrofit Installation
Tool (see Section 3.7.1.2 and Section 3.7.2). The following conditions must be met before the zero-foot
calibration procedure should be attempted:
AF
1. The entire GRA 5500 must be completely installed and mounted in the final configuration as
representative of normal flight conditions.
2. The installer must perform a visual inspection to verify that the antenna installation meets all the
guidelines of Section 2.3.3. Also, the visual inspection must verify that the antenna coaxial cables
are installed and connected properly.
3. The zero-foot calibration procedure must be performed outdoors on a hard, flat surface and away
from hangars, buildings, or other metal structures that may reflect the radar signal.
4. Dual or triple unit installations must be calibrated separately and independently. Thus, the
system(s) not presently being calibrated must be powered down (circuit breaker pulled or circular
connector wiring harness disconnected) so as to prevent interference with the unit presently being
calibrated.
NOTE
Once the calibration has successfully completed, the GRA 5500 should output “0 feet” from the altitude
outputs with no GRA 5500 faults annunciated in the GDU or Retrofit Installation Tool (depending upon
installation type). For further details on how to accomplish the zero-foot calibration procedure, see Section
3.7.2.
3.7.4
Prior to completing the zero-foot calibration procedure for the first time on an individual
GRA 5500 unit, the status of the GRA 5500 should indicate “fail” and a calibration fault
should be annunciated. This is normal operation and is used to indicate that a valid zerofoot calibration has not yet occurred.
Built-In Self-Test Functionality
The GRA 5500 contains a full-featured built-in self-test (BIST/BITE) and fault logging functionality
(including automated self-testing and fault detection of the entire internal TX and RX circuitry – see
Section 3.7.4.1 for more information) that occurs every time the unit is powered up and at periodic and
various times during unit operation. The tests in Table A-3 are run on the system and the resulting faults
are displayed and stored in the Assert Log.
NOTE
Faults can be viewed by using the GRA 5500 Retrofit Installation Tool as described in
Section 3.6 and the corresponding Assert Log may be diagnosed by using the Installation
Tool to download and diagnose the unit’s Assert Log. Alternatively, the Assert Log file
may be downloaded and send to Garmin for diagnosis.
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3.7.4.1
Automated and Manually-Initiated Altitude Self-Test and Self-Test Inhibit
Functionality
The GRA 5500 includes an advanced altitude self-test functionality which provides the ability to detect
and log faults within the entire internal transmitter and receiver circuitry and processing chain at various
internally simulated altitudes. The altitude self-test functionality is completely automated (and can be
inhibited), but it also may be run manually if desired. See below for more information applicable to both
forms of altitude self-test:
AF
Automated Altitude Self-Test
• Functionality is completely transparent to the pilot or any user of radar altitude data from the GRA
5500.
• Runs every time the unit is powered up and subsequently every 1 minute during normal unit
operation at calculated altitudes above 250 ft AGL or during “No Computed Data” conditions
(such as at actual altitudes above 2550 ft AGL, during excess pitch or roll maneuvering, or
anytime the ground reflection is poor enough to cause “No Computed Data” to appear on the
altitude outputs).
• Other than during initial unit power up, the automated altitude self-test functionality is never
initiated at calculated altitudes of 250 ft AGL or below.
• Other than during initial unit power up, the automated altitude self-test functionality can be
completely disabled (inhibited) by grounding the SELF TEST INHIBIT* active-low discrete input
(see Section 4.4.1 for more information) or by activating the “self-test inhibit” command in GIFD
installations any time (or always) during normal unit operation.
Manually Initiated Altitude Self-Test
• Performs the same physical functionality as the automated altitude self-test, but may be manually
initiated at any time during normal unit operation (including at altitudes below 250 ft AGL).
• During manually initiated altitude self-test, the status of all altitude outputs from the GRA 5500
are set to “Test” and an altitude of 40 ft is output. Unlike the automated altitude self-test, this
functionality is intentionally not transparent to the pilot or any user of radar altitude data from the
GRA 5500 in order to be useful to the pilot or crew and not provide misleading data.
• May be initiated by grounding the SELF TEST SELECT* active-low discrete input (see Section
4.4.1 for more information) or by activating the “self-test” command via GDU in GIFD
installations.
• Activation of manually initiated altitude self-test may be disabled (inhibited) by grounding the
SELF TEST INHIBIT* active-low discrete input (see Section 4.4.1 for more information) or by
activating the “self-test inhibit” command in GIFD installations any time (or always) during
normal unit operation.
NOTE
The manually initiated altitude self-test is completely optional for installation and use. It
does not provide any additional safety enhancements or fault monitoring capabilities
beyond the automated altitude self-test other than allowing the pilot or users of the GRA
5500 data to see feedback (a displayed test altitude) during any stage of GRA 5500
operation.
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NOTE
Because the automated altitude self-test functionality is always inhibited during operation
at 250 ft AGL or below (except during unit power-up), if extended flying time below 250 ft
AGL is expected (such as in certain rotorcraft operations) it is recommended to install
provisions to utilize the manually initiated altitude self-test functionality (see Section 4.4.1
for more information). Manual altitude self-test functionality may then be used (and thus
altitude sensing and processing integrity may be verified) during extended operations
below 250 ft AGL.
3.8 Continued Airworthiness
Maintenance of the GRA 5500 is “on condition” only.
NOTE
AF
It is the installer’s responsibility to properly document any Instructions for Continued
Airworthiness as may be required by the local aircraft certification authorities.
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4 SYSTEM INTERCONNECTS
4.1 Pin Function List
P55001
4.1.1
Figure 4-1 View of J55001 connector, from front of unit
Pin
AF
Table 4-1 P55001 Connector
Pin Name
AIRCRAFT POWER 2
POWER GROUND
AIRCRAFT POWER 1
ARINC 429 OUT 2 B
RESERVED (DO NOT CONNECT)
SPARE
SPARE
POWER GROUND
I/O
In
-In
Out
-----
SELF TEST SELECT*
10
ARINC 429 OUT 2 A
In
11
SIGNAL GROUND
--
12
RESERVED (DO NOT CONNECT)
--
13
RADAR ALT SYSTEM ID PROGRAM* 1
In
14
RADAR ALT SYSTEM ID PROGRAM* 2
In
15
RESERVED (DO NOT CONNECT)
--
16
SPARE
Out
17
RADAR ALTITUDE ALERT OUT* 2
Out
18
RS422 IN 2 B
In
19
SELF TEST INHIBIT*
In
20
SIGNAL GROUND
--
21
SIGNAL GROUND
--
22
SIGNAL GROUND
--
Out
*Denotes Active Low (Ground to activate)
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Table 4-1 P55001 Connector
Pin
Pin Name
I/O
23
RS422 OUT 1 B
Out
24
RS422 OUT 1 A
Out
25
RS422 IN 2 A
In
26
SIGNAL GROUND
--
27
SIGNAL GROUND
--
28
SIGNAL GROUND
--
29
SIGNAL GROUND
--
30
SIGNAL GROUND
--
31
SIGNAL GROUND
--
32
RADAR ALTITUDE ALERT OUT* 1
33
SIGNAL GROUND
34
SIGNAL GROUND
--
35
RS422 IN 1 B
In
36
SIGNAL GROUND
37
SIGNAL GROUND
38
RS422 OUT 2 A
39
SIGNAL GROUND
40
CONFIG MODULE DATA
41
SIGNAL GROUND
42
RS422 OUT 2 B
43
SIGNAL GROUND
44
USB VBUS POWER
45
USB GROUND
46
RS422 IN 1 A
47
CONFIG MODULE CLOCK
48
CONFIG MODULE GROUND
49
USB DATA HI
50
RESERVED (DO NOT CONNECT)
--
51
SIGNAL GROUND
--
52
ARINC 429 OUT 1 A
Out
53
CONFIG MODULE POWER
Out
54
USB DATA LO
I/O
55
ARINC 429 OUT 1 B
Out
Out
AF
--
--Out
-Out
-Out
Out
Out
-In
Out
-I/O
*Denotes active low (ground to activate)
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4.2 Power Functions
4.2.1
Aircraft Power
The GRA 5500 provides two aircraft power inputs which accept 14/28 VDC. AIRCRAFT POWER 1 and
AIRCRAFT POWER 2 are “diode ORed” to provide redundant aircraft power connections, such as on
aircraft with two electrical busses. For non-redundant operation, only one input need be connected.
Table 4-2 Aircraft Power
Pin Name
Pin
I/O
AIRCRAFT POWER 1
In
AIRCRAFT POWER 2
In
POWER GROUND
--
POWER GROUND
--
4.3.1
4.3 Serial Data Connections
HSDB Over RS-422
AF
The GRA 5500 provides two HSDB (High-Speed Data Bus) over RS-422 interfaces/channels. HSDB is
Garmin’s proprietary data bus for use in connecting LRUs to the Garmin Integrated Flight Deck (GIFD) in
GIFD installations. Each HSDB over RS-422 interface consists of two input lines and two output lines and
is physically compatible with EIA/TIA standards for RS-422.
In GIFD installations, GRA 5500 altitude information is outputted from this interface, and all unit
configuration (except for dual/triple unit strapping), calibration, diagnostics, and software upgrades of the
GRA 5500 occur over the HSDB over RS-422 interface. Both HSDB over RS-422 channels are identical,
and only one channel need be connected to the GIFD in order to achieve full unit functionality. However,
for redundancy or failure rate analysis reasons, both HSDB over RS-422 channels may be connected to
provide redundant information.
Table 4-3 HSDB Over RS-422
Pin Name
Pin
I/O
RS-422 IN 1 A
46
In
RS-422 IN 1 B
35
In
RS-422 OUT 1 A
24
Out
RS-422 OUT 1 B
23
Out
RS-422 IN 2 A
25
In
RS-422 IN 2 B
18
In
RS-422 OUT 2 A
38
Out
RS-422 OUT 2 B
42
Out
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4.3.2
ARINC 429
The GRA 5500 provides two independently configurable ARINC 429 output interfaces which conform to
ARINC 429 electrical specifications when loaded with up to 5 standard ARINC 429 receivers.
In non-GIFD (retrofit) installations, GRA 5500 altitude information is output from this interface. The
ARINC 429 outputs can be configured for low speed (12.5 kbps) or high speed (100 kbps) operation.
Table 4-4 ARINC 429
Pin Name
Pin
I/O
ARINC 429 OUT 1 A
52
Out
ARINC 429 OUT 1 B
55
Out
ARINC 429 OUT 2 A
10
Out
ARINC 429 OUT 2 B
Out
The ARINC 429 labels in Table 4-5 can be output from the unit and are configurable via the GRA 5500
Retrofit Installation Tool (see Section 3.7.2):
AF
Table 4-5 ARINC 429 Output Labels
Label
164
165
377
Description
Output Data Rate/Period
Radio Altitude (BNR format)
20 Hz/50 msec
Radio Altitude (BCD format)
20 Hz/50 msec
Equipment Identification
20 Hz/50 msec
4.3.3
During “No Computed Data” conditions (operation above 2550 ft AGL or insufficient return signal
conditions below 2550 ft AGL) the sign/status matrix bits of Label 164 and Label 165 are set to indicate
“No Computed Data” and the altitude bits of each label are set to indicate 4000 ft. If a unit fault is found
during normal operation, the sign/status matrix bits of Label 164 are set to indicate “Fail” and the altitude
bits are set to indicate 4000 ft. During a “Fail” state Label 165 is not transmitted.
Configuration Module
Use of a configuration module in Garmin Integrated Flight Deck (GIFD) installations is not required. For
non-GIFD (retrofit) installations, use of a configuration module is optional to retain configuration settings
outside of the individual LRU.
Table 4-6 Configuration Module
Pin Name
Pin
I/O
CONFIG MODULE DATA**
40
Out
CONFIG MODULE CLOCK**
47
Out
CONFIG MODULE GROUND**
48
--
CONFIG MODULE POWER**
53
Out
**Signals have ESD (Electrostatic Discharge) protection, but no lightning protection.
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4.3.4
USB
The GRA 5500 provides a standard Universal Serial Bus (USB) interface for unit configuration (except for
dual/triple unit strapping), calibration, diagnostics, and software upgrades in non-GIFD (retrofit)
installations. The interface is compatible with the Universal Serial Bus Version 1.1 standard for operation
as a “full-speed” device.
Table 4-7 USB Connections
Pin Name
Pin
I/O
USB VBUS POWER**
44
Out
USB GROUND**
45
--
USB DATA HI**
49
I/O
USB DATA LO**
54
I/O
4.4 Discrete I/O
Active Low Discrete Inputs
AF
4.4.1
**Signals have ESD (Electrostatic Discharge) protection, but no lightning protection.
USB Type B Receptacle pigtail cable must be wired directly to P55001.
The GRA 5500 provides four active-low discrete inputs. Two are used as configuration straps in dual and
triple installations (in both GIFD and non-GIFD/retrofit installations). Two additional inputs are provided
for optional manually-initiated self-test and self-test inhibit operation (discrete inputs used in non-GIFD/
retrofit installations only – manually-initiated self-test and self-test inhibit functionality occurs via HSDB
over RS-422 connections in GIFD installations). See Section 3.7.4.1 for more information on automated
and manually-initiated self-test capability and operation as well as self-test inhibit functionality. All
active-low discrete inputs conform to the following specifications:
ACTIVE: 0 V ≤ Vin ≤ 3.5 V, or Rin ≤ 375 ohms
INACTIVE: 8 V ≤ Vin ≤ 36 V, or Rin ≥ 100k ohms
Source current is internally limited to approximately 1 mA max for a grounded input.
Table 4-8 Active Low Discrete Inputs
Pin Name
Pin
I/O
SELF TEST SELECT*
In
RADAR ALT SYSTEM ID PROGRAM* 1
13
In
RADAR ALT SYSTEM ID PROGRAM* 2
14
In
SELF TEST INHIBIT*
19
In
*Denotes Active Low (Ground to activate)
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4.4.2
Altitude Alert (Annunciator) Outputs
The GRA 5500 provides two active-low annunciator outputs for use as “altitude alerts” or altitude trip
points to annunciate when the GRA 5500 indicates a radar altitude below the configured trip point for each
altitude alert pin. The altitude value for each altitude alert pin is configurable via the GRA 5500 Retrofit
Installation Tool (see Section 3.7.2 for further information on accomplishing configuration).
Each altitude alert pin will annunciate the active state if the altitude value output from the GRA 5500 is
less than the configured value for the respective altitude alert pin and the status of the altitude is “Normal”.
If the GRA 5500 indicates a “No Computed Data” or a “Fail” condition, both altitude alert pins will revert
to the inactive state. Both altitude alert pins will also revert to the inactive state whenever the manuallyinitiated self-test functionality is active (See Section 3.7.4.1 for more information on self-test
functionality).
ACTIVE: 0 V ≤ Vout ≤ 0.5 V, or Rout ≤ 10 ohms, sinking up to 500 mA
INACTIVE: Rout ≥ 100k ohms to ground, withstanding up to +36 VDC
RADAR ALTITUDE ALERT OUT* 2
RADAR ALTITUDE ALERT OUT* 1
Pin
I/O
17
Out
32
Out
*Denotes Active Low
AF
Pin Name
Table 4-9 Alert Outputs
GRA 5500 Installation Manual
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APPENDIX A Referenced Tables
Table A-1 Recommended Coaxial Length
Min. & Max. Lengths
(max. loss includes cable and
connector loss combined)
Max Cable
Attenuation (dB/
100ft)
Carlisle IT Type1
PIC Type2
MIL-C-17 Type3
RG Type4
Minimum
Maximum (loss of
5.0 dB)
1' 0" [0.30m]
10' 0" [3.05m]
45.7
M17/128-RG400
RG-400
1' 0" [0.30m]
10' 0" [3.05m]
45.6
M17/60-RG142
RG-142
1' 0" [0.30m]
20' 0" [6.09m]
22.8
M17/127-RG3935
RG-3935
1' 0" [0.30m]
14' 9" [4.49m]7
27.9
1' 0" [0.30m]
15' 3" [4.65m]7
31.8
3C142B
1' 0" [0.30m]
15' 4" [4.76m]7
30.7
432101
1' 0" [0.30m]
16' 7" [5.05m]7
27.5
S44191
1' 0" [0.30m]
17' 8" [5.38m]7
25.8
S44193
1' 0" [0.30m]
18' 0" [5.46m]7
26.4
311901
1' 0" [0.30m]
18' 2" [5.54m]7
24.4
352001
1' 0" [0.30m]
25' 6" [7.77m]7
18.4
311601
1' 0" [0.30m]
26' 3" [7.62m]7
18.3
421601
1' 0" [0.30m]
27' 3" [8.35m]7
16.3
1' 0" [0.30m]
29' 5" [8.96m]7
15.5
1' 0" [0.30m]
30' 0"6 [9.14m]7
14.7
1' 0" [0.30m]
30' 0"6 [9.14m]
13.0
1' 0" [0.30m]
30' 0"6 [9.14m]
11.8
1' 0" [0.30m]
30' 0"6 [9.14m]
11.8
1' 0" [0.30m]
30' 0"6 [9.14m]
1' 0" [0.30m]
30' 0"6 [9.14m]
S67163
AF
S33141
311501
421201
S55122
311201
8.3
7.8
S88207
S22089
310801
Vendor: Carlisle IT (Electronic Cable Specialists) 5300 W Franklin Drive, Franklin, WI 53132
Telephone: 800.327.9473 or 414.421.5300, Fax: 414.421.5301 Website: www.carlisleit.com
Vendor: PIC Wire and Cable N53 W24747 S Corporate Circle, Sussex, WI 53089-0330
Telephone 800.742.3191 or 262.246.0500, Fax: 262.246.0450 Website: www.picwire.com
Except for RG393, see current issue of Qualified Products List, QPL-17.
RG types are obsolete and are shown for reference only; replaced by M17 type numbers.
5RG393
is listed only for the purpose of re-using existing RG393 cable for retrofits.
Antenna cable length shall not exceed 30 feet per cable.
7Calculation
provided by cable manufacturer
190-01277-00
Revision A
GRA 5500 Installation Manual
Page A-1
Cable Type
Connector Type
Market
Connector Part Number
TNC Right Angle
Helicopter/Fixed Wing
CTR522
TNC Straight
Helicopter/Fixed Wing
CTS522
TNC Right Angle
Helicopter/Fixed Wing
CTR3522
TNC Straight
Helicopter/Fixed Wing
CTS3522
TNC Right Angle
Helicopter/Fixed Wing
CTR722
TNC Straight
Helicopter/Fixed Wing
CTS722
TNC Right Angle
Helicopter/Fixed Wing
CTR922
TNC Right Angle
Helicopter/Fixed Wing
CTS922
TNC Right Angle
Helicopter/Fixed Wing
CTR122
TNC Right Angle
Helicopter/Fixed Wing
CTS122
TNC Right Angle
Helicopter/Fixed Wing
CTR022
TNC Straight
Helicopter/Fixed Wing
CTS022
TNC Straight
Helicopter/Fixed Wing
190108
TNC Right Angle
Helicopter/Fixed Wing
190109
TNC Straight
Helicopter/Fixed Wing
190508
TNC Right Angle
Helicopter/Fixed Wing
190509
TNC Straight
Helicopter/Fixed Wing
190808
TNC Right Angle
Helicopter/Fixed Wing
190809
TNC Straight
Helicopter/Fixed Wing
190308
TNC Right Angle
Helicopter/Fixed Wing
190309
TNC Straight
Helicopter/Fixed Wing
190608
TNC Right Angle
Helicopter/Fixed Wing
190609
AF
Table A-2 TNC Connectors
Helicopter/Fixed Wing
190408
Helicopter/Fixed Wing
190409
Helicopter/Fixed Wing
5225555-6
Helicopter/Fixed Wing
5225554-6
TNC Straight
Helicopter/Fixed Wing
1-522550-3
TNC Right Angle
Helicopter/Fixed Wing
1-5225554-1
Carlisle IT 432101
Carlisle IT 352001
Carlisle IT 3C142B,
311901
Carlisle IT 421601,
311601, 311501
Carlisle IT 421201,
311201
Carlisle IT 310801
PIC S44191,
S44193
PIC S67163
PIC S83204,
S88207
PIC S33141
PIC S55122
TNC Straight
PIC S22089
TNC Right Angle
TNC Straight
Tyco Electronics
M17/128-RG400,
M17/60-RG142
TNC Right Angle
Tyco Electronics
M17/127-RG393
GRA 5500 Installation Manual
Page A-2
190-01277-00
Revision A
Table A-3 identifies the various unit faults that can be encountered during normal operation of the GRA 5500. Use Table A-3 as a reference to
determine the proper actions to take after a fault has been identified.
Table A-3 GRA 5500 Fault Descriptions
Fault Type
N/A
Zero-Foot Lock
Calibration
Unit does not boot
Average frequency of
zero-foot signal is
larger/smaller than
allowable
frequencies
Cause
Resolution
GRA HW Revision ID
invalid for SW version
Update software to correct version for hardware
GRA Unit ID invalid
(Both discrete inputs
grounded)
Check Unit ID strapping and set to a valid ID
Hardware failure
Return unit to Garmin for service
Improper antenna
connections
Check antenna installation and all cable
connections and retry calibration. Note there are no
assert log entries for this fault.
Antenna cables are
too long or calibration
completed while
aircraft is in air
Calibrate unit while on ground. Note there are no
assert log entries for this fault.
Zero-Foot Cal
Zero-foot point not
set
Calibration not
complete
Calibrate the unit. Note there are no assert log
entries for this fault.
PLL Register
After programming,
read-back of the PLL
register values does
not match what was
sent from the CPU
Internal
communication error
Cycle power to unit. If fault persists, return unit to
Garmin for service.
Improper antenna
connections
Check antenna installation and all cable
connections
RF Self-Test
The self-test signal is
not within the
acceptable frequency
range
Internal failure
Download the assert log and send to Garmin for
diagnosis. If fault persists, return unit to Garmin for
service.
POST (Power On
Self-Test)
Description
Sensor Boot
Sensor processor
software not
successfully loaded
Internal
communication error
Various
(see Table A-4)
Numerous tests
identified in this table
are run during Power
On Self-Test (POST).
Failure of these tests
is identified as a
POST fault during
power up and also
identified by the fault
name in the fault log.
Various
(see Table A-4)
AF
Configuration
Fault Name
Cycle power to unit. If fault persists, return unit to
Garmin for service.
Cycle power to unit. If fault persists, return unit to
Garmin for service.
(continued on next page)
190-01277-00
Revision A
GRA 5500 Installation Manual
Page A-3
Table A-3 GRA 5500 Fault Descriptions
Fault Type
Fault Name
Clock Generator I2C
Description
Clock Generator is
read to determine
correct frequency
output.
Cause
Resolution
Internal
communication error
Cycle power to unit. If fault persists, return unit to
Garmin for service.
ADC (Voltage Monitor)
ADC did not respond
to sampling
conversion command
within 20us
Internal
communication error
Cycle power to unit. If fault persists, return unit to
Garmin for service.
ADC Monitor 0
ADC used to monitor
internal unit voltages
fails self-test
ADC failure
Cycle power to unit. If fault persists, return unit to
Garmin for service.
ADC Monitor 1
ADC used to monitor
internal unit voltages
fails self-test
ADC failure
Cycle power to unit. If fault persists, return unit to
Garmin for service.
ADC Monitor 2
ADC used to monitor
internal unit voltages
fails self-test
ADC failure
Cycle power to unit. If fault persists, return unit to
Garmin for service.
Clock Generator
Register
Clock generator
programming failure
Clock generator failure
Cycle power to unit. If fault persists, return unit to
Garmin for service.
DDR
Memory integrity test
Memory failure
Cycle power to unit. If fault persists, return unit to
Garmin for service.
Main Temp Sensor
I2C
CRF Temp Sensor I2C
Temperature Sensor
is read to determine
correct operation.
Digital HW
Sensor Code CRC
Sensor processor
code failed validity
check
Sensor CPU fails to
respond to Main CPU
or packet information
is not correct from
sensor
Sensor Status
Sensor processor
reset signal triggered
by sensor watchdog
Sensor Watchdog
GRA 5500 Installation Manual
Page A-4
Code corrupted during
transfer from flash to
RAM
Cycle power to unit. If fault persists, return unit to
Garmin for service.
Failed to validate
code sections in
memory
Code corrupted during
transfer from flash to
main processor
Cycle power to unit. If fault persists, return unit to
Garmin for service.
Code corrupted during
transfer from main to
sensor processor
Cycle power to unit. If fault persists, return unit to
Garmin for service.
AF
Flash-to-RAM Code
Code corrupted in
flash memory
Sensor processor
failure
Internal
communication error
Sensor processor
failure
Internal
communication error
Cycle power to unit. If fault persists, return unit to
Garmin for service.
Cycle power to unit. If fault persists, return unit to
Garmin for service.
(continued on next page)
190-01277-00
Revision A
Table A-3 GRA 5500 Fault Descriptions
Fault Name
+12.5 V power rail
outputs improper
voltage
+12.5V Monitor
-12.5 V power rail
outputs improper
voltage
-12.5V Monitor
+8 V RF power rail
outputs improper
voltage
+8V RF Monitor
-6 V RF power rail
outputs improper
voltage
-6V RF Monitor
+5.75V RF Monitor
Electrical
Description
+5.75 V RF power
rail outputs improper
voltage
+5.75 V power rail
outputs improper
voltage
+5.75V Monitor
+3.3 V power rail
outputs improper
voltage
+3.3V Monitor
+1.9V Monitor
Improper current on
+8 V power rail
+12.5 V RF power
rail outputs improper
voltage
Current Monitor
+80V Backup Monitor
Suspended
+80 V backup power
rail outputs improper
voltage
+12.5V RF Monitor
Resolution
Aircraft power input
voltage out of range
Check aircraft power supply. Cycle power to unit.
Internal power supply
failure
If fault persists, download the assert log and send to
Garmin for diagnosis.
Aircraft power input
voltage out of range
Check aircraft power supply. Cycle power to unit.
Internal power supply
failure
If fault persists, download the assert log and send to
Garmin for diagnosis.
Aircraft power input
voltage out of range
Check aircraft power supply. Cycle power to unit.
Internal power supply
failure
If fault persists, download the assert log and send to
Garmin for diagnosis.
Aircraft power input
voltage out of range
Check aircraft power supply. Cycle power to unit.
Internal power supply
failure
If fault persists, download the assert log and send to
Garmin for diagnosis.
Aircraft power input
voltage out of range
Check aircraft power supply. Cycle power to unit.
Internal power supply
failure
If fault persists, download the assert log and send to
Garmin for diagnosis.
Aircraft power input
voltage out of range
Check aircraft power supply. Cycle power to unit.
Internal power supply
failure
If fault persists, download the assert log and send to
Garmin for diagnosis.
Aircraft power input
voltage out of range
Check aircraft power supply. Cycle power to unit.
Internal power supply
failure
If fault persists, download the assert log and send to
Garmin for diagnosis.
Aircraft power input
voltage out of range
Check aircraft power supply. Cycle power to unit.
AF
+1.9 V power rail
outputs improper
voltage
Cause
Fault Type
Internal power supply
failure
If fault persists, download the assert log and send to
Garmin for diagnosis.
Aircraft power input
voltage out of range
Check aircraft power supply. Cycle power to unit.
Internal power supply
failure
If fault persists, download the assert log and send to
Garmin for diagnosis.
Aircraft power input
out of range
Check aircraft power supply. Cycle power to unit.
Internal power supply
failure
If fault persists, download the assert log and send to
Garmin for diagnosis.
Aircraft power input
voltage out of range
Check aircraft power supply. Cycle power to unit.
Internal power supply
failure
If fault persists, download the assert log and send to
Garmin for diagnosis.
Power Fail
Aircraft power lost for
greater than 220 ms
Aircraft power failure
Return power to unit. Note there are no assert log
entries for this fault.
DDS
Failure to program
DDS or read back
correct register
information from the
DDS
Internal
communication error
Cycle power to unit. If fault persists, return unit to
Garmin for service.
TX PLL Lock
The TX PLL is not
locked while the unit
is transmitting.
Internal failure
If fault persists, download the assert log and send to
Garmin for diagnosis.
LO PLL Lock
The LO PLL is not
locked while the unit
is transmitting
Internal failure
If fault persists, download the assert log and send to
Garmin for diagnosis.
Improper antenna
connections
Check antenna installation and all cable
connections.
Auto RF Self-Test
The self-test signal is
not within the
acceptable frequency
range
Internal failure
If fault persists, download the assert log and send to
Garmin for diagnosis.
Improper antenna
connections
Check antenna installation and all cable
connections.
Internal failure
Download the assert log and send to Garmin for
diagnosis. If fault persists, return unit to Garmin for
service.
Radio HW
Main RF Self-Test
The self-test signal is
not within the
acceptable frequency
range
(continued on next page)
190-01277-00
Revision A
GRA 5500 Installation Manual
Page A-5
Table A-3 GRA 5500 Fault Descriptions
Fault Type
Fault Name
Main Temp
Description
Cause
Main board
temperature greater
than 100° C or less
than -60° C
Installed unit location
is too hot/cold
RF board
temperature greater
than 100° C or less
than -60° C
Installed unit location
is too hot/cold
Internal failure
Resolution
Return unit to qualified temperature range as
specified in Environmental Qualification Form
(EQF). If fault persists, return unit to Garmin for
service.
Temperature
Internal failure
AF
RF Temp
Return unit to qualified temperature range as
specified in Environmental Qualification Form
(EQF). If fault persists, return unit to Garmin for
service.
GRA 5500 Installation Manual
Page A-6
190-01277-00
Revision A
Table A-4 identifies the various unit faults that can be encountered during the initial Power On Self-Test (POST) of the GRA 5500. Use
Table A-4 as a reference to determine the proper actions after a fault has been identified.
Table A-4 “Various” POST (Power On Self-Test) Faults
POST Fault
Description
Cause
Resolution
Internal voltage monitor
failure
Return unit to Garmin for service.
ADC Monitor 1
ADC used to monitor
internal unit voltages fails
self-test
Internal voltage monitor
failure
Return unit to Garmin for service.
ADC Monitor 2
ADC used to monitor
internal unit voltages fails
self-test
Internal voltage monitor
failure
Return unit to Garmin for service.
Aircraft power input
voltage out of range
Check aircraft power supply. Cycle power to unit.
Internal power supply
failure
If fault persists, download the assert log and send to Garmin for diagnosis.
Aircraft power input
voltage out of range
Check aircraft power supply. Cycle power to unit.
Internal power supply
failure
Download the assert log and send to Garmin for diagnosis. If fault persists,
return unit to Garmin for service.
Aircraft power input
voltage out of range
Check aircraft power supply. Cycle power to unit.
Internal power supply
failure
Download the assert log and send to Garmin for diagnosis. If fault persists,
return unit to Garmin for service.
Aircraft power input
voltage out of range
Check aircraft power supply. Cycle power to unit.
Internal power supply
failure
Download the assert log and send to Garmin for diagnosis. If fault persists,
return unit to Garmin for service.
+8V RF Monitor
-6V RF Monitor
+5.75V RF
Monitor
+5.75V Monitor
+3.3V Monitor
+1.9V Monitor
+80V Backup
Monitor
Main Temp
RF Temp
190-01277-00
Revision A
-12.5 V power rail outputs
improper voltage
+8 V RF power rail outputs
improper voltage
-6 V RF power rail outputs
improper voltage
+5.75 V RF power rail
outputs improper voltage
AF
-12.5V Monitor
+12.5 V power rail outputs
improper voltage
Aircraft power input
voltage out of range
Check aircraft power supply. Cycle power to unit.
Internal power supply
failure
Download the assert log and send to Garmin for diagnosis. If fault persists,
return unit to Garmin for service.
Aircraft power input
voltage out of range
Check aircraft power supply. Cycle power to unit.
Internal power supply
failure
Download the assert log and send to Garmin for diagnosis. If fault persists,
return unit to Garmin for service.
Aircraft power input
voltage out of range
Check aircraft power supply. Cycle power to unit.
Internal power supply
failure
Download the assert log and send to Garmin for diagnosis. If fault persists,
return unit to Garmin for service.
Aircraft power input
voltage out of range
Check aircraft power supply. Cycle power to unit.
Internal power supply
failure
Download the assert log and send to Garmin for diagnosis. If fault persists,
return unit to Garmin for service.
Aircraft power input
voltage out of range
Check aircraft power supply. Cycle power to unit.
Internal power supply
failure
Download the assert log and send to Garmin for diagnosis. If fault persists,
return unit to Garmin for service.
Aircraft power input
voltage out of range
Check aircraft power supply. Cycle power to unit.
Internal power supply
failure
If fault persists, download the assert log and send to Garmin for diagnosis.
+12.5V Monitor
+12.5 V RF power rail
outputs improper voltage
+5.75 V power rail outputs
improper voltage
+12.5V RF
Monitor
+3.3 V power rail outputs
improper voltage
+1.9 V power rail outputs
improper voltage
+80 V backup power rail
outputs improper voltage
Main board temperature
greater than 100° C or less
than -60° C
RF board temperature
greater than 100° C or less
than -60° C
ADC Monitor 0
ADC used to monitor
internal unit voltages fails
self-test
Installed unit location is
too hot/cold
Internal failure
Installed unit location is
too hot/cold
Internal failure
Return unit to qualified temperature range as specified in Environmental
Qualification Form (EQF). If fault persists, return unit to Garmin for
service.
Return unit to qualified temperature range as specified in Environmental
Qualification Form (EQF). If fault persists, return unit to Garmin for
service.
GRA 5500 Installation Manual
Page A-7
T
AF
This page intentionally left blank
GRA 5500 Installation Manual
Page A-8
190-01277-00
Revision A
APPENDIX B Outline and Installation Drawings
3.02 76.7
TNC CONNECTOR
2X
.20 5.1
AF
3.99 101.3
3.00 76.2
2.2 56
4.9 125
7.88 200.2
.61 15.5
10.40 264.2
11.62 295.2 (NO CONFIGURATION MODULE)
12.08 306.9 (WITH CONFIGURATION MODULE)
4X .210±.003 5.33±0.08
SEE NOTE 3
2X 2.150±.005 54.61±0.13
1.5 38
2X .425 10.80
NOTES:
1.
2.
3.
DIMENSIONS: INCHES[mm].
DIMENSIONS ARE SHOWN FOR REFERENCE ONLY.
MOUNTING HOLES FOR #10 PAN HEAD OR HEX HEAD FASTENERS.
2X .630 16.00
2X 7.000±.005 177.80±0.13
Figure B-1 GRA 5500 Outline Drawing
190-01277-00
Revision A
GRA 5500 Installation Manual
Page B-1
APPENDIX B Outline and Installation Drawings
MINIMUM REQUIRED INSTALLATION AND REMOVAL CLEARANCE
WITH LOCKDOWN OVERHANGING MOUNTING SHELF
4.18 106.2
330-00727-01
(MILITARY P/N
D38999/26ME35SA)
HARNESS CONNECTOR P55001
GRA 5500 UNIT
011-02537-00
330-90007-01
(MILITARY P/N
M85049/38S17N)
011-02582-00
AF
SOME PARTS NOT SHOWN; REFER TO
190-00313-12 FOR ADDITIONAL PARTS LISTS
MINIMUM REQUIRED INSTALLATION AND REMOVAL CLEARANCE
WITH LOCKDOWN NOT OVERHANGING MOUNTING SHELF
4.76 120.8
GRA 5500 CONNECTOR KIT
011-02573-01 SHOWN
(INCL. CONFIG. MODULE)
CIRCULAR CONN SHELL SIZE 17
MOUNTING SHELF
GRA 5500 MOUNTING RACK
011-02567-00
MOUNTING SHELF
Figure B-2 GRA 5500 Connector/Rack Assembly Drawing
190-01277-00
Revision A
GRA 5500 Installation Manual
Page B-2
APPENDIX C Interconnect Examples
GRA 5500
RADAR ALTIMETER
AIRCRAFT POWER 1
P55001
GRA 5500
5A
TO 14/28 VDC AIRCRAFT POWER
(OR GREATER)
GRA 5500
AIRCRAFT POWER 2
5A
TO 14/28 VDC AIRCRAFT POWER
(OR GREATER)
RADAR ALT SYSTEM ID PROGR AM* 1
RADAR ALT SYSTEM ID PROGR AM* 2
13
14
TX ANTENNA
TX
RX ANTENNA
RX
NOTES:
FOR MULTI-UNIT INSTALLATION, CONNECT PINS AS SPECIFIED IN SECTION 2.3.1 OF THIS INSTALLATION MANUAL.
FOR SINGLE UNIT INSTALLATION, LEAVE BOTH PINS UNCONNECTED.
TX ANTENNA
RX ANTENNA
AF
POWER GROUND
POWER GROUND
1. THIS INTERCONNECT EXAMPLE DRAWING APPLIES TO BOTH GIFD (GARMIN INTEGRATED FLIGHT DECK)
AND NON-GIFD (RETROFIT) INSTALLATIONS.
2. UNLESS OTHERWISE NOTED, ALL STRANDED WIRE MUST CONFORM TO MIL-W-22759/16 OR EQUIVALENT.
3. UNLESS OTHERWISE NOTED, ALL SHIELDED WIRE MUST CONFORM TO MIL-C-27500 OR EQUIVALENT.
4. UNLESS OTHERWISE NOTED, ALL WIRES ARE 22 GAUGE MINIMUM.
5. SYMBOL DESIGNATIONS
AIRCRAFT GROUND
TWISTED SHIELDED PAIR
GARMIN (SHIELD BLOCK) GROUND
AND CIRCULAR CONNECTOR SHIELD GROUND
WIRE SPLICE CONNECTION
TWISTED SHIELDED 4 CONDUCTOR
COAXIAL CABLE
Figure C-1 Garmin Integrated Flight Deck (GIFD) and non-GIFD (retrofit) Interconnect Example
190-01277-00
Revision A
GRA 5500 Installation Manual
Page C-1
APPENDIX C Interconnect Examples
THIS INTERCONNECT EXAMPLE DRAWING APPLIES ONLY TO GARMIN INTEGRATED FLIGHT DECK (GIFD) INSTALLATIONS.
P412
GSD 41
DATA CONCENTRATOR
46
35
24
23
10
MAIN2 RS-485/RS-422 4 A
MAIN2 RS-485/RS-422 4 B
MAIN2 RS-485/RS-422 5 A
MAIN2 RS-485/RS-422 5 B
RS422 IN 1 A
RS422 IN 1 B
RS422 OUT 1 A
RS422 OUT 1 B
P55001
AF
GRA 5500
RADAR ALTIMETER
GRA 5500
RADAR ALTIMETER
RS422 IN 2 A
RS422 IN 2 B
RS422 OUT 2 A
RS422 OUT 2 B
AND/OR
P55001
25
18
38
42
P603
36
37
27
28
GIA 63
INTEGRATED AVIONICS UNIT
RS-485 5 A/RS-422 OUT A
RS-485 5 B/RS-422 OUT B
RS-485 3 A/RS-422 IN A
RS-485 3 B/RS-422 IN B
Figure C-2 Garmin Integrated Flight Deck Interconnect Example
190-01277-00
Revision A
GRA 5500 Installation Manual
Page C-2
APPENDIX C Interconnect Examples
THIS INTERCONNECT EXAMPLE DRAWING APPLIES ONLY TO NON-GARMIN INTEGRATED FLIGHT DECK (RETROFIT) INSTALLATIONS.
GRA 5500
RADAR ALTIMETER
ARINC 429 OUT 1 A
ARINC 429 OUT 1 B
P55001
DISPLAY UNIT AND/OR
OTHER ARINC 429 RECEIVERS
ARINC 429 IN A
ARINC 429 IN B
52
55
RADAR ALTITUDE ALERT OUT* 1
RADAR ALTITUDE ALERT OUT* 2
32
17
OPTIONAL CONNECTIONS, SEE SECTION 4.4.2 FOR INFORMATION ON FUNCTIONALITY OF ALTITUDE ALERT OUTPUTS
SIGNAL GROUND
43
CONFIG MODULE GROUND
CONFIG MODULE POWER
CONFIG MODULE DATA
CONFIG MODULE CLOCK
48
53
40
47
SELF TEST SELECT*
SELF TEST INHIBIT*
19
28 AWG
28 AWG
RED
GRN
WHT
BLK
SHELL
BLK
RED
YELLOW
WHT
VBUS
D+
DGND
SEE NOTE 3
AF
44
49
54
45
USB VBUS POWER
USB DATA HI
USB DATA LO
USB GROUND
USB TYPE B
RECEPTACLE
SHIELD (DRAIN)
CONFIG MODULE
GND
VCC
DATA
CLOCK
SEE NOTE 2
OPTIONAL CONNECTIONS, SEE SECTIONS 3.7.4.1 AND 4.4.1 FOR INFORMATION ON FUNCTIONALITY OF MANUALLY
INTIATED ALTITUDE SELF-TEST AND SELF-TEST INHIBIT.
SEE NOTE 1
NOTES
1. EXTERNAL ACTIVE LOW DISCRETE OUTPUTS/ANNUNCIATORS FROM OTHER APPLIANCES MAY BE USED AS INPUTS FOR PINS 9 AND 19 INSTEAD OF SWITCHES.
2. CONFIGURATION MODULE USE IS OPTONAL. SEE SECTION 4.3.3 FOR MORE INFORMATION.
3. USB TYPE B RECEPTACLE PIGTAIL MUST BE WIRED DIRECTLY TO P55001. USB EXTENSION CABLES MUST BE DISCONNECTED FROM THE PIGTAIL WHILE IN FLIGHT.
Figure C-3 Non-Garmin Integrated Flight Deck (retrofit) Interconnect Example
190-01277-00
Revision A
GRA 5500 Installation Manual
Page C-3
APPENDIX C Interconnect Examples
GRA 5500
RADAR ALTIMETER
USB TYPE B
RECEPTACLE
44
49
54
45
SIGNAL GROUND
43
NOTES:
28 AWG
28 AWG
RED
GRN
WHT
BLK
AF
USB VBUS POWER
USB DATA HI
USB DATA LO
USB GROUND
P55001
PIN 2
PIN 1
PIN 3
PIN 4
VBUS
D+
DGND
SHIELD (DRAIN)
1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED.
2. USB TYPE B RECEPTACLE PIGTAIL (P/N 011-01782-00) MUST BE WIRED DIRECTLY TO P55001.
ALL USB EXTENSION CABLES MUST BE DISCONNECTED DURING FLIGHT.
3. TRIM ALL EXPOSED INDIVIDUAL 24 AWG AND 28 AWG WIRES AND THE TINNED 28 AWG DRAIN
WIRE BACK TO THE OUTER BLACK INSULATION.
4. REMOVE THE OUTER BLACK INSULATION SO THAT THE INDIVIDUAL WIRES ARE EXPOSED
FOR A LENGTH OF 1.25 INCHES.
5. AS THE DRAIN WIRE IS UN-INSULATED, A TEFLON SLEEVE (18 AWG OR HIGHER) IS REQUIRED
OVER THE EXPOSED AREA BACK TO THE OUTER INSULATION OF THE CABLE. THE DRAIN
WIRE IS CONNECTED TO THE METALLLIC AREA AROUND THE USB RECEPTACLE.
6. CRIMP PINS ON TO THE INDIVIDUAL WIRES AND THE DRAIN WIRE USING BEST SHOP PRACTICES.
Figure C-4 GRA 5500 USB Dongle Cable
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GRA 5500 Installation Manual
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GRA 5500
RADAR ALTIMETER
P55001
NOTE:
48
53
40
47
BLK
RED
YELLOW
WHT
AF
CONFIG MODULE GROUND
CONFIG MODULE POWER
CONFIG MODULE DATA
CONFIG MODULE CLOCK
APPENDIX C Interconnect Examples
CONFIGURATION
MODULE
GROUND
VCC
DATA
CLOCK
USE OF A CONFIGURATION MODULE IN GARMIN INTEGRATED FLIGHT DECK (GIFD) INSTALLATIONS IS NOT REQUIRED.
FOR NON-GIFD (RETROFIT) INSTALLATIONS, USE OF A CONFIGURATION MODULE IS OPTIONAL TO RETAIN CONFIGURATION
SETTINGS OUTSIDE OF THE INDIVIDUAL LRU.
Figure C-5 GRA 5500 Configuration Module Interconnect Example
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