Garmin 0181200 LICENSED NON-BROADCAST AERONAUTICAL TRANSMITTER User Manual 190 01277 00

Garmin International Inc LICENSED NON-BROADCAST AERONAUTICAL TRANSMITTER 190 01277 00

User Manual

SPECIFICATIONCONTROL DRAWINGREVISIONSREV. DATE DESCRIPTION ECO NO.A12/20/12 Initial release - - -AVIATION REVIEW REQUIREDNOTES:1. DESCRIPTION: Installation Documentation - GRA 5500 Installation Manual2. 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, 3. PAGINATION: 26 double-sided letter sheets, 4 double-sided tabloid sheets, 7 single-sided tabloid sheets.4. MATERIAL: 24 pound bond. Approved equivalents allowed.5. COLOR: Black ink on white paper stock.6. BINDERY: Three-hole punch, shrink-wrap. Digital output preferred.7. FOLDS: Z-Fold tabloid sheets at end of document.8. ELECTRONIC ARTWORK: Shall conform to Garmin Archive, Filename: 190-01277-00.pdf9. This part shall comply with Garmin Banned/Restrictive Substance List, GPN 001-00211-00The following files have been archived under the above ARCHIVE FILENAME.Filename File Contents190-01277-00.pdf Portable Document Format, contains Installation Manual and Release Specificationrelease.fm FrameMaker Format, Release SpecificationManual Elements FrameMaker, Formatted Files and Figures*.* Various supporting illustrations, drawings, and artworkCONFIDENTIALThis 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 ManualChecker:Project Engineer: SIZE A Part Number: 190-01277-00 Rev AReleased By: Scale: N/A AVIATION REVIEW REQUIRED Sheet 1 of 1DRAFT
190-01277-00 December, 2012 Revision AGRA 5500Radar Altimeter Installation ManualDRAFT
GRA 5500 Installation Manual 190-01277-00Page A Rev. A© Copyright 2012Garmin Ltd. or its subsidiariesAll Rights ReservedExcept 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 StreetOlathe, KS 66062 USATelephone: 913.397.8200Aviation Panel-Mount Technical Support Line (Toll Free) 1.888.606.5482www.garmin.comGarmin (Europe) Ltd.Liberty House, Bulls Copse RoadHounsdown Business ParkSouthampton, SO40 9RB U.K.+44/ (0) 870.8501241Garmin AT, Inc.2345 Turner Rd., SESalem, OR 97302 USATelephone: 503.581.8101RECORD OF REVISIONSRevision Revision Date DescriptionA 12/20/12 Production ReleaseDRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page iINFORMATION SUBJECT TO EXPORT CONTROL LAWSThis 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 NOTESWARNINGThis 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.WARNINGWarnings 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.CAUTIONCautions are used to alert the individual that damage to equipment may result if the procedural step is not followed to the letter.NOTENotes are used to expand and explain the preceding step and provide further understanding of the reason for the particular operation.DRAFT
GRA 5500 Installation Manual 190-01277-00Page ii Rev. ACURRENT REVISION DESCRIPTIONDOCUMENT PAGINATIONRevision Page Number(s) Section Number Description of ChangeA All All Initial ReleaseSection Page RangeTable of Contents i – viIISection 1 1-1 – 1-4Section 2 2-1 – 2-14Section 3 3-1 – 3-18Section 4 4-1 – 4-6Appendix A A-1 – A-8Appendix B B-1 – B-2Appendix C C-1 – C-5DRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page iiiAviation Limited WarrantyAll 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.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. Garmin (Europe) Ltd.1200 East 151st Street Liberty House, Bulls Copse RoadOlathe, Kansas 66062, U.S.A. Hounsdown Business Park Phone:913/397.8200 Romsey, SO40 9RB, U.K.FAX:913/397.0836 Phone:44/ (0) 870.8501241 FAX:44/ (0) 870.850125DRAFT
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190-01277-00 GRA 5500 Installation ManualRev. A Page vTABLE OF CONTENTSPARAGRAPH PAGESection 1 GENERAL DESCRIPTION .............................................................1-11.1 Introduction...................................................................................................................... 1-11.2 Equipment Description ................................................................................................... 1-11.3 Interface Summary..........................................................................................................1-11.4 Technical Specifications.................................................................................................. 1-21.4.1 Environmental Qualification Form.......................................................................................1-21.4.2 Physical Characteristics........................................................................................................1-21.4.3 General Specifications..........................................................................................................1-21.4.4 Performance Specifications..................................................................................................1-31.4.5 Power Requirements.............................................................................................................1-31.5 Certification ..................................................................................................................... 1-31.5.1 TSO Compliance and Limitations........................................................................................1-41.5.2 TSO Deviations ....................................................................................................................1-41.6 Operating Instructions......................................................................................................1-41.7 Reference Documents...................................................................................................... 1-4Section 2 INSTALLATION OVERVIEW........................................................2-12.1 Introduction...................................................................................................................... 2-12.2 Installation Materials ....................................................................................................... 2-12.2.1 Available Equipment............................................................................................................2-12.2.2 Additional Equipment Required...........................................................................................2-22.2.3 Approved Radar Altimeter Antennas ...................................................................................2-22.3 Installation Considerations .............................................................................................. 2-32.3.1 Multiplex Operation (Dual and Triple Unit Installations)....................................................2-32.3.2 Installation Approval Considerations for Pressurized Aircraft ............................................2-32.3.3 Antenna Location Planning Guidance..................................................................................2-42.3.4 Antenna Installation Considerations...................................................................................2-102.4 Electrical Bonding ......................................................................................................... 2-102.5 Cabling and Wiring........................................................................................................ 2-102.5.1 Antenna Coaxial Cables (Requirements and Fabrication Guidance).................................2-112.6 Cooling Requirements ................................................................................................... 2-142.7 Mounting Requirements ................................................................................................ 2-14Section 3 INSTALLATION PROCEDURE.....................................................3-13.1 Unpacking Unit................................................................................................................ 3-13.2 Wiring Harness Installation ............................................................................................. 3-13.3 Backshell Assembly......................................................................................................... 3-23.4 Antenna Installation......................................................................................................... 3-23.5 Unit Installation ............................................................................................................... 3-23.5.1 Installation Procedure (see Figure 3-1) ................................................................................3-23.5.2 Removal Procedure (see Figure 3-1)....................................................................................3-23.6 Downloading and Installing the GRA 5500 Retrofit Installation Tool ........................... 3-43.7 Post Installation Configuration and Checkout Procedures .............................................. 3-5DRAFT
GRA 5500 Installation Manual 190-01277-00Page vi Rev. APARAGRAPH PAGE3.7.1 GRA 5500 Configuration/Checkout for Varying Installation Types...................................3-53.7.2 Using the GRA 5500 Retrofit Installation Tool...................................................................3-63.7.3 Zero-Foot Calibration.........................................................................................................3-163.7.4 Built-In Self-Test Functionality.........................................................................................3-163.8 Continued Airworthiness................................................................................................3-18Section 4 SYSTEM INTERCONNECTS .........................................................4-14.1 Pin Function List ..............................................................................................................4-14.1.1 P55001..................................................................................................................................4-14.2 Power Functions ...............................................................................................................4-34.2.1 Aircraft Power......................................................................................................................4-34.3 Serial Data Connections ...................................................................................................4-34.3.1 HSDB Over RS-422.............................................................................................................4-34.3.2 ARINC 429 ..........................................................................................................................4-44.3.3 Configuration Module..........................................................................................................4-44.3.4 USB......................................................................................................................................4-54.4 Discrete I/O ......................................................................................................................4-54.4.1 Active Low Discrete Inputs .................................................................................................4-54.4.2 Altitude Alert (Annunciator) Outputs..................................................................................4-6Appendix A Referenced Tables........................................................................A-1Appendix B Outline and Installation Drawings ............................................. B-1Appendix C Interconnect Examples ................................................................C-1DRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page viiLIST OF FIGURESFIGURE PAGESection 1 GENERAL DESCRIPTION .............................................................1-1Section 2 INSTALLATION OVERVIEW........................................................2-1Figure 2-1 Standard Dual and Triple End-to-End System Layouts....................................... 2-6Figure 2-2 Compact Dual and Triple End-to-End System Layouts....................................... 2-7Figure 2-3 Dual and Triple Side-by-Side System Layouts.................................................... 2-8Figure 2-4 Hybrid Triple System Layout .............................................................................. 2-9Figure 2-5 Coaxial Cable Requirements.............................................................................. 2-12Figure 2-6 TNC Connector Installation............................................................................... 2-12Figure 2-7 Heat Shrink Positioning ..................................................................................... 2-13Figure 2-8 GRA 5500 Mounting Rack ................................................................................ 2-14Section 3 INSTALLATION PROCEDURE.....................................................3-1Figure 3-1 GRA 5500 Installation ......................................................................................... 3-3Figure 3-2 GRA 5500 Retrofit Installation Tool (New Installation)..................................... 3-7Figure 3-3 GRA 5500 Retrofit Installation Tool Status Tab (Normal Operation) ................ 3-9Figure 3-4 GRA 5500 Retrofit Installation Tool Configuration Tab................................... 3-10Figure 3-5 GRA 5500 Retrofit Installation Tool Software Tab........................................... 3-13Section 4 SYSTEM INTERCONNECTS..........................................................4-1Figure 4-1 View of J55001 connector, from front of unit ..................................................... 4-1Appendix A Referenced Tables........................................................................A-1Appendix B Outline and Installation Drawings.............................................B-1Figure B-1 GRA 5500 Outline Drawing................................................................................B-1Figure B-2 GRA 5500 Connector/Rack Assembly Drawing.................................................B-2Appendix C Interconnect Examples................................................................C-1Figure C-1 Garmin Integrated Flight Deck (GIFD) and non-GIFD (retrofit) Interconnect Example ............................................................................................................C-1Figure C-2 Garmin Integrated Flight Deck Interconnect Example .......................................C-2Figure C-3 Non-Garmin Integrated Flight Deck (retrofit) Interconnect Example ................C-3Figure C-4 GRA 5500 USB Dongle Cable............................................................................C-4Figure C-5 GRA 5500 Configuration Module Interconnect Example ..................................C-5DRAFT
GRA 5500 Installation Manual 190-01277-00Page viii Rev. ALIST OF TABLESTABLE PAGESection 1 GENERAL DESCRIPTION .............................................................1-1Table 1-1 Physical Characteristics......................................................................................... 1-2Table 1-2 General Specifications........................................................................................... 1-2Table 1-3 Performance Specifications................................................................................... 1-3Table 1-4 Power Requirements.............................................................................................. 1-3Table 1-5 TSO Compliance ................................................................................................... 1-4Table 1-6 Reference Documents............................................................................................ 1-4Section 2 INSTALLATION OVERVIEW........................................................2-1Table 2-1 Available Units...................................................................................................... 2-1Table 2-2 Available Equipment............................................................................................. 2-1Table 2-3 Additional Equipment Required............................................................................ 2-2Table 2-4 Approved Radar Altimeter Antennas.................................................................... 2-2Table 2-5 System ID Discrete Inputs..................................................................................... 2-3Section 3 INSTALLATION PROCEDURE.....................................................3-1Table 3-1 Pin Contact Part Numbers ..................................................................................... 3-1Table 3-2 Recommended Crimp Tools.................................................................................. 3-1Table 3-3 Recommended Insertion Tools.............................................................................. 3-1Table 3-4 Recommended Removal Tools ............................................................................. 3-2Table 3-5 ARINC 429 Channel 1 Settings .......................................................................... 3-11Table 3-6 ARINC 429 Channel 2 Settings .......................................................................... 3-11Section 4 SYSTEM INTERCONNECTS..........................................................4-1Table 4-1 P55001 Connector ................................................................................................. 4-1Table 4-2 Aircraft Power ....................................................................................................... 4-3Table 4-3 HSDB Over RS-422 .............................................................................................. 4-3Table 4-4 ARINC 429............................................................................................................ 4-4Table 4-5 ARINC 429 Output Labels.................................................................................... 4-4Table 4-6 Configuration Module ........................................................................................... 4-4Table 4-7 USB Connections .................................................................................................. 4-5Table 4-8 Active Low Discrete Inputs................................................................................... 4-5Table 4-9 Alert Outputs .........................................................................................................4-6Appendix A Referenced Tables........................................................................A-1Table A-1 Recommended Coaxial Length ........................................................................... A-1Table A-2 TNC Connectors.................................................................................................. A-2Table A-3 GRA 5500 Fault Descriptions ............................................................................. A-3Table A-4 “Various” POST (Power On Self-Test) Faults.................................................... A-7DRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page 1-11 GENERAL DESCRIPTION1.1 IntroductionThis 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 DescriptionThe 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), full-featured 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/stand-alone applications.1.3 Interface SummaryThe 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.DRAFT
GRA 5500 Installation Manual 190-01277-00Page 1-2 Rev. A1.4 Technical Specifications1.4.1 Environmental Qualification FormIt 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 005-00616-01To obtain a copy of this form, see the dealer/OEM portion of the Garmin web site (www.garmin.com).1.4.2 Physical CharacteristicsTable 1-1 lists the physical characteristics for the GRA 5500 unit, rack, and connectors. Refer to Appendix B for additional information.1.4.3 General SpecificationsFor detailed specifications, see the Environmental Qualification Form (Section 1.4.1).Table 1-1 Physical CharacteristicsCharacteristics SpecificationsUnit Height (with mounting rack) 3.99” (101.3 mm)Unit Width (with or without mounting rack) 3.02” (76.7 mm)Unit Depth (with mounting rack and connector) 11.62” (295.2 mm)Unit Depth (with mounting rack, connector, and configuration module) 12.08” (306.9 mm)Unit Weight (with mounting rack) 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)Table 1-2 General SpecificationsCharacteristics SpecificationsOperational Temperature Range -55° C to +85° CAltitude Range 55,000 ft maximumSoftware Compliance RTCA/DO-178B Level BHardware Compliance Not Applicable - The GRA 5500 does not contain any complex or programmable logic devices.Environmental Conditions RTCA/DO-160FDRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page 1-31.4.4 Performance Specifications1.4.5 Power Requirements1.5 CertificationThe 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.Table 1-3 Performance SpecificationsCharacteristics SpecificationsAltitude Accuracy ± 1.5 ft (3 - 100 ft AGL)± 2 % (> 100 - 2500 ft AGL)Altitude Range -20 - 2550 ft AGLAltitude Alert Outputs Range 0 - 2500 ft AGLAltitude Output Time Constant 0.1 second maximumTransmitter Output Frequency: 4.25 - 4.35 GHz "Gated" FMCWPower: 1.0 W nominalHorizontal Velocity 0 - 200 knots maximumVertical Velocity 20 ft/sec maximum (up to 100 ft AGL)25 ft/sec maximum (above 100 ft AGL)Pitch Angle ± 20° maximumRoll Angle± 20° maximum (with published altitude accuracy limits)± 20° to ± 30° (with ± 20 % altitude accuracy limits throughout entire altitude range)Table 1-4 Power RequirementsCharacteristics SpecificationsSupply Voltage 14/28 VDC. See the Environmental Qualification Form for details on surge ratings and minimum/maximum operating voltages.Power Consumption 13.75 W maximum (0.5 A at 27.5 VDC, 1.0 A at 13.75 VDC) DRAFT
GRA 5500 Installation Manual 190-01277-00Page 1-4 Rev. A1.5.1 TSO Compliance and LimitationsWhen 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 5500.1.5.2 TSO DeviationsNo TSO deviations were requested or granted for the GRA 5500.1.6 Operating InstructionsThe 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 DocumentsThe 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 1-5 TSO ComplianceFunction TSOApplicable LRU System (Main) SW Part NumbersApplicable Boot Block SW Part NumbersApplicable LRU System (Sensor) SW Part NumbersApplicable Region List SW Part NumbersAirborneLow-RangeRadio AltimeterTSO-C87a Functional Class A006-B1447-0(_)except006-B1447-00006-B1447-01006-B1447-02and006-B1447-03006-B1448-B(_)except006-B1448-BA006-B1448-BBand006-B1448-BC006-B1448-0(_)except006-B1448-00006-B1448-01006-B1448-02and006-B1448-03006-D3609-0(_)except006-D3609-00and006-D3609-01Table 1-6 Reference DocumentsPart Number Document190-00313-12 Circular Connector (and Configuration Module) Installation Instructions190-00303-00 G1000 System Installation Manual190-00903-00 G1000 Integrated Flight Deck (LJ/VLJ) System Maintenance Manual190-00907-00 G1000 System Maintenance Manual Standard Piston/Turboprop AircraftDRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page 2-12 INSTALLATION OVERVIEW2.1 IntroductionThis 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 MaterialsThe GRA 5500 is only available as a single unit under the following part number:2.2.1 Available Equipment Each of the following accessories are provided separately from the GRA 5500 and are required for installation.Table 2-1 Available UnitsItem Garmin P/NGRA 5500, Unit Only (011-02537-00) 010-00946-00Table 2-2 Available Equipment Item Garmin P/NSub-Assy, GRA 5500 Mounting Rack 011-02567-00Sub-Assy, Connector Kit, GRA 5500 (For Garmin Integrated Flight Deck installations)* 011-02573-00 Sub-Assy, Connector Kit w/Config Module & USB Pigtail, GRA 5500 (For retrofit/stand-alone installations)* 011-02573-01*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.DRAFT
GRA 5500 Installation Manual 190-01277-00Page 2-2 Rev. A2.2.2 Additional Equipment RequiredThe installation accessories listed in Table 2-3 are required but not provided:2.2.3 Approved Radar Altimeter AntennasThe antennas listed in Table 2-4 are the only approved antennas for use with the GRA 5500 radar altimeter:Table 2-3 Additional Equipment RequiredItem SpecificationRadar 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.Table 2-4 Approved Radar Altimeter AntennasAntenna Manufacturer Manufacturer Part Number Garmin Part Number*Sensor Systems Inc. S67-2002 013-00378-00Sensor Systems Inc. S67-2002-4 013-00378-04Sensor Systems Inc. S67-2002-12 013-00378-12Sensor Systems Inc. S67-2002-13 013-00378-13Sensor Systems Inc. S67-2002-14 013-00378-14Sensor Systems Inc. S67-2002-18 013-00378-18Sensor Systems Inc. S67-2002-19 013-00378-19Sensor Systems Inc. S67-2002-29 013-00378-29Sensor Systems Inc. S67-2002-45 013-00378-45*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.DRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page 2-32.3 Installation ConsiderationsFabrication 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 2-5.2.3.2 Installation Approval Considerations for Pressurized AircraftCable 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.Table 2-5 System ID Discrete InputsRADAR ALT SYSTEM ID PROGRAM* 1 RADAR ALT SYSTEM ID PROGRAM* 2 GRA 5500 UNIT NUMBEROpen Open 1Ground Open 2Open Ground 3Ground Ground Not AllowedDRAFT
GRA 5500 Installation Manual 190-01277-00Page 2-4 Rev. A2.3.3 Antenna Location Planning GuidanceNOTEThe 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.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. Non-metallic 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.DRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page 2-58. 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-by-side 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.DRAFT
GRA 5500 Installation Manual 190-01277-00Page 2-6 Rev. AFigure 2-1 Standard Dual and Triple End-to-End System LayoutsR1R2T1T25” min.Dual End-to-End SystemT1R3R1R25” min.T2T35” min.Triple End-to-End System Forward ForwardDRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page 2-7Figure 2-2 Compact Dual and Triple End-to-End System LayoutsTriple End-to-End SystemR2T1R3R15”T2T35”5”10”10”R2R1T1T210”Dual End-to-End System10”10” Forward ForwardDRAFT
GRA 5500 Installation Manual 190-01277-00Page 2-8 Rev. AFigure 2-3 Dual and Triple Side-by-Side System LayoutsT1 T25” min.35° max.R1 R2 R3T35” min.R1 R2T1 T25” min.35° max.Dual Side-by-Side System Triple Side-by-Side System Forward ForwardDRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page 2-9Figure 2-4 Hybrid Triple System Layout5” min.35° max.R3R25” min.T3R1T1 T235° max. ForwardDRAFT
GRA 5500 Installation Manual 190-01277-00Page 2-10 Rev. A2.3.4 Antenna Installation ConsiderationsThe 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 BondingAll 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.2.5 Cabling and WiringRefer 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.DRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page 2-112.5.1 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.NOTEAny 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):NOTEFor 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.DRAFT
GRA 5500 Installation Manual 190-01277-00Page 2-12 Rev. AFigure 2-5 Coaxial Cable RequirementsTNC 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.5.0 dB maximum attenuation, VSWR <1.5:130 feet maximum length, 1 foot minimum lengthGRA 5500RX Port5.0 dB maximum attenuation, VSWR <1.5:130 feet maximum length, 1 foot minimum lengthGRA 5500TX PortDRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page 2-13Figure 2-6 TNC Connector InstallationNOTEIt 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).Figure 2-7 Heat Shrink PositioningNOTEIt 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.ConnectorBody Ferrule Coaxial CableHeat shrink not to protrude past this surface.DRAFT
GRA 5500 Installation Manual 190-01277-00Page 2-14 Rev. A2.6 Cooling RequirementsDedicated 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 RequirementsThe 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.Figure 2-8 GRA 5500 Mounting RackGRA 5500 MOUNTING RACK011-02567-00DRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page 3-13 INSTALLATION PROCEDURE3.1 Unpacking UnitCarefully 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 InstallationAllow 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.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 NumbersItem Manufacturer Part NumberPin Contacts Military M39029/56-348Table 3-2 Recommended Crimp ToolsManufacturer Contact Size/Type Crimping Tool Turret Die or PositionerMilitary P/N 22D Socket M22520/2-01M22520/7-01 M22520/2-07M22520/7-05Table 3-3 Recommended Insertion ToolsUse with Contact SizePlastic Tools Metal ToolsMSPart Number ColorAngle Type Straight Type Proprietary Part NumberColorMS Part NumberProprietary Part Number22D M81969/14-01* Green/(White) M81969/8-01 11-8674-24 11-8794-24 Black*Double end insertion/removal tool.DRAFT
GRA 5500 Installation Manual 190-01277-00Page 3-2 Rev. ANOTENon-Garmin part numbers shown are not maintained by Garmin and consequently are subject to change without notice.3.3 Backshell AssemblyThe 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.3.4 Antenna InstallationRefer to Section 2.3.4 for installation instructions.3.5 Unit InstallationFor final installation and assembly, refer to the outline and installation drawings shown in Appendix B of this manual and to the following procedures.3.5.1 Installation Procedure (see Figure 3-1)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.Table 3-4 Recommended Removal ToolsUse with Contact SizePlastic Tools Metal ToolsMS Part Number ColorFor Unwired Contacts Proprietary Part NumberAngle Type Straight Type Proprietary Part NumberColorMS Part NumberProprietary Part Number22D M81969/14-01* (Green)/White 11-10050-07 M81969/8-02 11-8675-24 11/8795-24 Green/White*Double end insertion/removal tool. DRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page 3-32. Disengage the lockdown mechanism collar from the GRA 5500 hook and slide the GRA 5500 forward to remove from the mounting rack.Figure 3-1 GRA 5500 InstallationUNIT HOOKENGAGEMENTFEET2 PLACESFEET ENGAGEMENTLOCATION2 PLACESLOCKDOWN MECHANISM COLLARLOCKDOWN MECHANISM KNOBSECTION VIEW SHOWINGUNIT FEET ENGAGED INTOMOUNTING RACK2 PLACESDRAFT
GRA 5500 Installation Manual 190-01277-00Page 3-4 Rev. A3.6 Downloading and Installing the GRA 5500 Retrofit Installation ToolGRA 5500 configuration, calibration, diagnostics, and software upgrades are performed (in retrofit/non-GIFD 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.NOTEA 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.Installation1. 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.NOTEDepending 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.DRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page 3-53.7 Post Installation Configuration and Checkout ProceduresThe 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 TypesConfiguration 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 InstallationWhen 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.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.NOTEGDU 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.DRAFT
GRA 5500 Installation Manual 190-01277-00Page 3-6 Rev. A3.7.1.2 Non-Garmin Integrated Flight Deck (Retrofit) GRA 5500 InstallationConfiguration, calibration, diagnostics, and software upgrades are accomplished using the GRA 5500 Retrofit Installation Tool (Section 3.7.2).NOTEInstallations 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 ToolAfter 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.”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 re-install 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.DRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page 3-7When configuring a new GRA 5500 installation, the GRA 5500 Retrofit Installation Tool should look similar to Figure 3-2 (note the annunciated Calibration fault).NOTEIf 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)DRAFT
GRA 5500 Installation Manual 190-01277-00Page 3-8 Rev. A3.7.2.1 Zero-Foot Calibration ProcedureBefore the GRA 5500 is ready for normal operation, it is necessary to perform the following zero-foot calibration procedure.NOTEBefore 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.The following sections detail the primary functions of the GRA 5500 Retrofit Installation Tool.DRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page 3-9Status TabThe 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)DRAFT
GRA 5500 Installation Manual 190-01277-00Page 3-10 Rev. AConfiguration TabThe 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 TabDRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page 3-11Configuration Items• ARINC 429 Channel 1:The “ARINC 429 Channel 1” section adjusts the ARINC 429 Channel 1 settings.• ARINC 429 Channel 2:The “ARINC 429 Channel 2” section adjusts the ARINC 429 Channel 2 settings.Table 3-5 ARINC 429 Channel 1 SettingsConfiguration DescriptionEnable Channel Check to enable the channelUncheck to disable the channelEnable High Speed Check to enable high speed (100 kbps) operationUncheck to enable low speed (12.5 kbps) operationEnable Label 164 Check to enable sending label 164 (Radio Altitude, BNR format)Uncheck to disable sending label 164Enable Label 165 Check to enable sending label 165 (Radio Altitude, BCD format)Uncheck to disable sending label 165Enable Label 377 Check to enable sending label 377 (Equipment Identification)Uncheck to disable sending label 377Table 3-6 ARINC 429 Channel 2 SettingsConfiguration DescriptionEnable Channel Check to enable the channelUncheck to disable the channelEnable High Speed Check to enable high speed (100 kbps) operationUncheck to enable low speed (12.5 kbps) operationEnable Label 164 Check to enable sending label 164 (Radio Altitude, BNR format)Uncheck to disable sending label 164Enable Label 165 Check to enable sending label 165 (Radio Altitude, BCD format)Uncheck to disable sending label 165Enable Label 377 Check to enable sending label 377 (Equipment Identification)Uncheck to disable sending label 377DRAFT
GRA 5500 Installation Manual 190-01277-00Page 3-12 Rev. A• 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 HeightAltitude 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 OffsetThe “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.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).DRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page 3-13Software TabThe 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 TabDRAFT
GRA 5500 Installation Manual 190-01277-00Page 3-14 Rev. AUpdating SoftwareNOTECare 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.NOTEDue 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. NOTEIf 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.DRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page 3-155. 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.CAUTIONWhile 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.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.NOTEIf 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.DRAFT
GRA 5500 Installation Manual 190-01277-00Page 3-16 Rev. A3.7.3 Zero-Foot CalibrationAfter the GRA 5500 is configured, but before it may be put into normal flight operation, a one-time zero-foot 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: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.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.NOTEPrior 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 zero-foot calibration has not yet occurred.3.7.4 Built-In Self-Test FunctionalityThe 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.NOTEFaults 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.DRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page 3-173.7.4.1 Automated and Manually-Initiated Altitude Self-Test and Self-Test Inhibit FunctionalityThe 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: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.NOTEThe 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.DRAFT
GRA 5500 Installation Manual 190-01277-00Page 3-18 Rev. ANOTEBecause 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 AirworthinessMaintenance of the GRA 5500 is “on condition” only.NOTEIt is the installer’s responsibility to properly document any Instructions for Continued Airworthiness as may be required by the local aircraft certification authorities.DRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page 4-14 SYSTEM INTERCONNECTS4.1 Pin Function List4.1.1 P55001Figure 4-1 View of J55001 connector, from front of unitTable 4-1 P55001 ConnectorPin Pin Name I/O1AIRCRAFT POWER 2 In2POWER GROUND --3AIRCRAFT POWER 1 In4ARINC 429 OUT 2 B Out5RESERVED (DO NOT CONNECT) --6SPARE --7SPARE --8POWER GROUND --9SELF TEST SELECT* In10 ARINC 429 OUT 2 A Out11 SIGNAL GROUND --12 RESERVED (DO NOT CONNECT) --13 RADAR ALT SYSTEM ID PROGRAM* 1 In14 RADAR ALT SYSTEM ID PROGRAM* 2 In15 RESERVED (DO NOT CONNECT) --16 SPARE Out17 RADAR ALTITUDE ALERT OUT* 2 Out18 RS422 IN 2 B In19 SELF TEST INHIBIT* In20 SIGNAL GROUND --21 SIGNAL GROUND --22 SIGNAL GROUND --*Denotes Active Low (Ground to activate)DRAFT
GRA 5500 Installation Manual 190-01277-00Page 4-2 Rev. APin Pin Name I/O23 RS422 OUT 1 B Out24 RS422 OUT 1 A Out25 RS422 IN 2 A In26 SIGNAL GROUND --27 SIGNAL GROUND --28 SIGNAL GROUND --29 SIGNAL GROUND --30 SIGNAL GROUND --31 SIGNAL GROUND --32 RADAR ALTITUDE ALERT OUT* 1 Out33 SIGNAL GROUND --34 SIGNAL GROUND --35 RS422 IN 1 B In36 SIGNAL GROUND --37 SIGNAL GROUND --38 RS422 OUT 2 A Out39 SIGNAL GROUND --40 CONFIG MODULE DATA Out41 SIGNAL GROUND --42 RS422 OUT 2 B Out43 SIGNAL GROUND Out44 USB VBUS POWER Out45 USB GROUND --46 RS422 IN 1 A In47 CONFIG MODULE CLOCK Out48 CONFIG MODULE GROUND --49 USB DATA HI I/O50 RESERVED (DO NOT CONNECT) --51 SIGNAL GROUND --52 ARINC 429 OUT 1 A Out53 CONFIG MODULE POWER Out54 USB DATA LO I/O55 ARINC 429 OUT 1 B Out*Denotes active low (ground to activate)Table 4-1 P55001 ConnectorDRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page 4-34.2 Power Functions4.2.1 Aircraft PowerThe 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.4.3 Serial Data Connections4.3.1 HSDB Over RS-422The 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 4-2 Aircraft PowerPin Name Pin I/OAIRCRAFT POWER 1 3InAIRCRAFT POWER 2 1InPOWER GROUND 2--POWER GROUND 8--Table 4-3 HSDB Over RS-422Pin Name Pin I/ORS-422 IN 1 A 46 InRS-422 IN 1 B 35 InRS-422 OUT 1 A 24 OutRS-422 OUT 1 B 23 OutRS-422 IN 2 A 25 InRS-422 IN 2 B 18 InRS-422 OUT 2 A 38 OutRS-422 OUT 2 B 42 OutDRAFT
GRA 5500 Installation Manual 190-01277-00Page 4-4 Rev. A4.3.2 ARINC 429The 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. 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):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.4.3.3 Configuration ModuleUse 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 4-4 ARINC 429Pin Name Pin I/OARINC 429 OUT 1 A 52 OutARINC 429 OUT 1 B 55 OutARINC 429 OUT 2 A 10 OutARINC 429 OUT 2 B 4OutTable 4-5 ARINC 429 Output LabelsLabel Description Output Data Rate/Period164 Radio Altitude (BNR format) 20 Hz/50 msec165 Radio Altitude (BCD format) 20 Hz/50 msec377 Equipment Identification 20 Hz/50 msecTable 4-6 Configuration ModulePin Name Pin I/OCONFIG MODULE DATA** 40 OutCONFIG MODULE CLOCK** 47 OutCONFIG MODULE GROUND** 48 --CONFIG MODULE POWER** 53 Out**Signals have ESD (Electrostatic Discharge) protection, but no lightning protection.DRAFT
190-01277-00 GRA 5500 Installation ManualRev. A Page 4-54.3.4 USBThe 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.4.4 Discrete I/O4.4.1 Active Low Discrete InputsThe 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 ohmsINACTIVE: 8 V ≤ Vin ≤ 36 V, or Rin ≥ 100k ohmsSource current is internally limited to approximately 1 mA max for a grounded input.Table 4-7 USB ConnectionsPin Name Pin I/OUSB VBUS POWER** 44 OutUSB GROUND** 45 --USB DATA HI** 49 I/OUSB DATA LO** 54 I/O**Signals have ESD (Electrostatic Discharge) protection, but no lightning protection.USB Type B Receptacle pigtail cable must be wired directly to P55001.Table 4-8 Active Low Discrete InputsPin Name Pin I/OSELF TEST SELECT* 9InRADAR ALT SYSTEM ID PROGRAM* 1 13 InRADAR ALT SYSTEM ID PROGRAM* 2 14 InSELF TEST INHIBIT* 19 In*Denotes Active Low (Ground to activate)DRAFT
GRA 5500 Installation Manual 190-01277-00Page 4-6 Rev. A4.4.2 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 manually-initiated 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 mAINACTIVE: Rout ≥ 100k ohms to ground, withstanding up to +36 VDCTable 4-9 Alert OutputsPin Name Pin I/ORADAR ALTITUDE ALERT OUT* 2 17 OutRADAR ALTITUDE ALERT OUT* 1 32 Out*Denotes Active LowDRAFT
190-01277-00 GRA 5500 Installation ManualRevision A Page A-1APPENDIX A Referenced TablesTable A-1 Recommended Coaxial LengthMin. & Max. Lengths (max. loss includes cable and connector loss combined) Max Cable Attenuation (dB/100ft) Carlisle IT Type1PIC Type2MIL-C-17 Type3RG Type4Minimum Maximum (loss of 5.0 dB)1' 0" [0.30m] 10' 0" [3.05m] 45.7 M17/128-RG400 RG-4001' 0" [0.30m] 10' 0" [3.05m] 45.6 M17/60-RG142 RG-1421' 0" [0.30m] 20' 0" [6.09m] 22.8 M17/127-RG3935RG-39351' 0" [0.30m] 14' 9" [4.49m]727.9 S882071' 0" [0.30m] 15' 3" [4.65m]731.8 3C142B1' 0" [0.30m] 15' 4" [4.76m]730.7 4321011' 0" [0.30m] 16' 7" [5.05m]727.5 S441911' 0" [0.30m] 17' 8" [5.38m]725.8 S441931' 0" [0.30m] 18' 0" [5.46m]726.4 3119011' 0" [0.30m] 18' 2" [5.54m]724.4 3520011' 0" [0.30m] 25' 6" [7.77m]718.4 3116011' 0" [0.30m] 26' 3" [7.62m]718.3 4216011' 0" [0.30m] 27' 3" [8.35m]716.3 S671631' 0" [0.30m] 29' 5" [8.96m]715.5 S331411' 0" [0.30m] 30' 0"6 [9.14m]714.7 3115011' 0" [0.30m] 30' 0"6 [9.14m] 13.0 4212011' 0" [0.30m] 30' 0"6 [9.14m] 11.8 S551221' 0" [0.30m] 30' 0"6 [9.14m] 11.8 3112011' 0" [0.30m] 30' 0"6 [9.14m] 8.3 S220891' 0" [0.30m] 30' 0"6 [9.14m] 7.8 3108011Vendor: Carlisle IT (Electronic Cable Specialists) 5300 W Franklin Drive, Franklin, WI 53132Telephone: 800.327.9473 or 414.421.5300, Fax: 414.421.5301 Website: www.carlisleit.com2Vendor: 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.com3Except for RG393, see current issue of Qualified Products List, QPL-17.4RG 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.6Antenna cable length shall not exceed 30 feet per cable.7Calculation provided by cable manufacturerDRAFT
GRA 5500 Installation Manual 190-01277-00Page A-2 Revision ATable A-2 TNC ConnectorsCable Type Connector Type Market Connector Part NumberCarlisle IT 432101 TNC Right Angle Helicopter/Fixed Wing CTR522TNC Straight Helicopter/Fixed Wing CTS522Carlisle IT 352001 TNC Right Angle Helicopter/Fixed Wing CTR3522TNC Straight Helicopter/Fixed Wing CTS3522Carlisle IT 3C142B, 311901TNC Right Angle Helicopter/Fixed Wing CTR722TNC Straight Helicopter/Fixed Wing CTS722Carlisle IT 421601, 311601, 311501TNC Right Angle Helicopter/Fixed Wing CTR922TNC Right Angle Helicopter/Fixed Wing CTS922Carlisle IT 421201, 311201TNC Right Angle Helicopter/Fixed Wing CTR122TNC Right Angle Helicopter/Fixed Wing CTS122Carlisle IT 310801 TNC Right Angle Helicopter/Fixed Wing CTR022TNC Straight Helicopter/Fixed Wing CTS022PIC S44191, S44193TNC Straight Helicopter/Fixed Wing 190108TNC Right Angle Helicopter/Fixed Wing 190109PIC S67163 TNC Straight Helicopter/Fixed Wing 190508TNC Right Angle Helicopter/Fixed Wing 190509PIC S83204, S88207 TNC Straight Helicopter/Fixed Wing 190808TNC Right Angle Helicopter/Fixed Wing 190809PIC S33141 TNC Straight Helicopter/Fixed Wing 190308TNC Right Angle Helicopter/Fixed Wing 190309PIC S55122 TNC Straight Helicopter/Fixed Wing 190608TNC Right Angle Helicopter/Fixed Wing 190609PIC S22089 TNC Straight Helicopter/Fixed Wing 190408TNC Right Angle Helicopter/Fixed Wing 190409Tyco Electronics M17/128-RG400, M17/60-RG142TNC Straight Helicopter/Fixed Wing 5225555-6TNC Right Angle Helicopter/Fixed Wing 5225554-6Tyco Electronics M17/127-RG393TNC Straight Helicopter/Fixed Wing 1-522550-3TNC Right Angle Helicopter/Fixed Wing 1-5225554-1DRAFT
190-01277-00 GRA 5500 Installation ManualRevision A Page A-3Table 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 DescriptionsFault Type Fault Name Description Cause ResolutionConfiguration N/A Unit does not bootGRA HW Revision ID invalid for SW version Update software to correct version for hardwareGRA Unit ID invalid (Both discrete inputs grounded) Check Unit ID strapping and set to a valid IDHardware failure Return unit to Garmin for serviceCalibrationZero-Foot LockAverage frequency of zero-foot signal is larger/smaller than allowable frequenciesImproper antenna connectionsCheck 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 airCalibrate 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.POST (Power On Self-Test)PLL RegisterAfter programming, read-back of the PLL register values does not match what was sent from the CPUInternal communication error Cycle power to unit. If fault persists, return unit to Garmin for service.RF Self-TestThe self-test signal is not within the acceptable frequency range Improper antenna connections Check antenna installation and all cable connectionsInternal failure Download the assert log and send to Garmin for diagnosis. If fault persists, return unit to Garmin for service.Sensor Boot Sensor processor software not successfully loadedInternal communication error Cycle power to unit. If fault persists, return unit to Garmin for service.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)Cycle power to unit. If fault persists, return unit to Garmin for service.(continued on next page)DRAFT
GRA 5500 Installation Manual 190-01277-00Page A-4 Revision AFault Type Fault Name Description Cause ResolutionDigital HWClock Generator I2CClock Generator is read to determine correct frequency output. Internal communication error Cycle power to unit. If fault persists, return unit to Garmin for service.Main Temp Sensor I2C Temperature Sensor is read to determine correct operation.CRF Temp Sensor I2CADC (Voltage Monitor)ADC did not respond to sampling conversion command within 20usInternal 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.Flash-to-RAM Code Failed to validate code sections in memoryCode corrupted in flash memory Cycle power to unit. If fault persists, return unit to Garmin for service.Code corrupted during transfer from flash to RAMSensor Code CRC Sensor processor code failed validity checkCode corrupted during transfer from flash to main processorCycle power to unit. If fault persists, return unit to Garmin for service.Code corrupted during transfer from main to sensor processorCycle power to unit. If fault persists, return unit to Garmin for service.Sensor StatusSensor CPU fails to respond to Main CPU or packet information is not correct from sensorSensor processor failure Cycle power to unit. If fault persists, return unit to Garmin for service.Internal communication errorSensor Watchdog Sensor processor reset signal triggered by sensor watchdogSensor processor failure Cycle power to unit. If fault persists, return unit to Garmin for service.Internal communication error(continued on next page)Table A-3 GRA 5500 Fault DescriptionsDRAFT
190-01277-00 GRA 5500 Installation ManualRevision A Page A-5Fault Type Fault Name Description Cause ResolutionElectrical+12.5V Monitor +12.5 V power rail outputs improper voltageAircraft 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 power rail outputs improper voltageAircraft 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.+8V RF Monitor +8 V RF power rail outputs improper voltageAircraft 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.-6V RF Monitor -6 V RF power rail outputs improper voltageAircraft 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.+5.75V RF Monitor +5.75 V RF power rail outputs improper voltageAircraft 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.+5.75V Monitor +5.75 V power rail outputs improper voltageAircraft 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.+3.3V Monitor +3.3 V power rail outputs improper voltageAircraft 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.+1.9V Monitor +1.9 V power rail outputs improper voltageAircraft 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.Current Monitor Improper current on +8 V power railAircraft 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 RF Monitor +12.5 V RF power rail outputs improper voltageAircraft 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.+80V Backup Monitor +80 V backup power rail outputs improper voltageAircraft 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.Suspended 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.Radio HWDDSFailure to program DDS or read back correct register information from the DDSInternal 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.Auto RF Self-TestThe self-test signal is not within the acceptable frequency rangeImproper antenna connections Check antenna installation and all cable connections.Internal failure If fault persists, download the assert log and send to Garmin for diagnosis.Main RF Self-TestThe self-test signal is not within the acceptable frequency rangeImproper 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.(continued on next page)Table A-3 GRA 5500 Fault DescriptionsDRAFT
GRA 5500 Installation Manual 190-01277-00Page A-6 Revision AFault Type Fault Name Description Cause ResolutionTemperatureMain TempMain board temperature greater than 100° C or less than -60° CInstalled unit location is too hot/cold Return unit to qualified temperature range as specified in Environmental Qualification Form (EQF). If fault persists, return unit to Garmin for service.Internal failureRF TempRF board temperature greater than 100° C or less than -60° CInstalled unit location is too hot/cold Return unit to qualified temperature range as specified in Environmental Qualification Form (EQF). If fault persists, return unit to Garmin for service.Internal failureTable A-3 GRA 5500 Fault DescriptionsDRAFT
190-01277-00 GRA 5500 Installation ManualRevision A Page A-7Table 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) FaultsPOST Fault Description Cause ResolutionADC Monitor 0ADC used to monitor internal unit voltages fails self-testInternal voltage monitor failure Return unit to Garmin for service.ADC Monitor 1ADC used to monitor internal unit voltages fails self-testInternal voltage monitor failure Return unit to Garmin for service.ADC Monitor 2ADC used to monitor internal unit voltages fails self-testInternal voltage monitor failure Return unit to Garmin for service.+12.5V RF Monitor+12.5 V RF power rail outputs improper voltageAircraft 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 power rail outputs improper voltageAircraft power input voltage out of range Check aircraft power supply. Cycle power to unit.Internal power supply failureDownload the assert log and send to Garmin for diagnosis. If fault persists, return unit to Garmin for service.-12.5V Monitor -12.5 V power rail outputs improper voltageAircraft power input voltage out of range Check aircraft power supply. Cycle power to unit.Internal power supply failureDownload the assert log and send to Garmin for diagnosis. If fault persists, return unit to Garmin for service.+8V RF Monitor +8 V RF power rail outputs improper voltageAircraft power input voltage out of range Check aircraft power supply. Cycle power to unit.Internal power supply failureDownload the assert log and send to Garmin for diagnosis. If fault persists, return unit to Garmin for service.-6V RF Monitor -6 V RF power rail outputs improper voltageAircraft power input voltage out of range Check aircraft power supply. Cycle power to unit.Internal power supply failureDownload the assert log and send to Garmin for diagnosis. If fault persists, return unit to Garmin for service.+5.75V RF Monitor+5.75 V RF power rail outputs improper voltageAircraft power input voltage out of range Check aircraft power supply. Cycle power to unit.Internal power supply failureDownload the assert log and send to Garmin for diagnosis. If fault persists, return unit to Garmin for service.+5.75V Monitor +5.75 V power rail outputs improper voltageAircraft power input voltage out of range Check aircraft power supply. Cycle power to unit.Internal power supply failureDownload the assert log and send to Garmin for diagnosis. If fault persists, return unit to Garmin for service.+3.3V Monitor +3.3 V power rail outputs improper voltageAircraft power input voltage out of range Check aircraft power supply. Cycle power to unit.Internal power supply failureDownload the assert log and send to Garmin for diagnosis. If fault persists, return unit to Garmin for service.+1.9V Monitor +1.9 V power rail outputs improper voltageAircraft power input voltage out of range Check aircraft power supply. Cycle power to unit.Internal power supply failureDownload the assert log and send to Garmin for diagnosis. If fault persists, return unit to Garmin for service.+80V Backup Monitor +80 V backup power rail outputs improper voltageAircraft 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.Main TempMain board temperature greater than 100° C or less than -60° CInstalled unit location is too hot/cold Return unit to qualified temperature range as specified in Environmental Qualification Form (EQF). If fault persists, return unit to Garmin for service.Internal failureRF TempRF board temperature greater than 100° C or less than -60° CInstalled unit location is too hot/cold Return unit to qualified temperature range as specified in Environmental Qualification Form (EQF). If fault persists, return unit to Garmin for service.Internal failureDRAFT
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190-01277-00 GRA 5500 Installation ManualRevision A Page B-1APPENDIX B Outline and Installation DrawingsFigure B-1 GRA 5500 Outline Drawing3.00 76.23.02 76.73.99101.3TNC CONNECTOR2X7.88200.211.62 (NO CONFIGURATION MODULE)295.2.20 5.1.6115.510.40 264.212.08 306.9 (WITH CONFIGURATION MODULE)2.2564.91252X 7.000±.005177.80±0.132X 2.150±.00554.61±0.132X .42510.802X .63016.004X .210±.003 5.33±0.08SEE NOTE 31.538NOTES:DIMENSIONS: INCHES[mm].1.DIMENSIONS ARE SHOWN FOR REFERENCE ONLY.2.MOUNTING HOLES FOR #10 PAN HEAD OR HEX HEAD FASTENERS.3.DRAFT
190-01277-00 GRA 5500 Installation ManualRevision A Page B-2APPENDIX B Outline and Installation DrawingsFigure B-2 GRA 5500 Connector/Rack Assembly DrawingGRA 5500 UNIT011-02537-00GRA 5500 MOUNTING RACK011-02567-00GRA 5500 CONNECTOR KIT011-02573-01 SHOWN(INCL. CONFIG. MODULE)CIRCULAR CONN SHELL SIZE 17SOME PARTS NOT SHOWN; REFER TO190-00313-12 FOR ADDITIONAL PARTS LISTS330-00727-01(MILITARY P/ND38999/26ME35SA)HARNESS CONNECTOR P55001330-90007-01(MILITARY P/NM85049/38S17N)011-02582-004.18106.2MINIMUM REQUIRED INSTALLATION AND REMOVAL CLEARANCEWITH LOCKDOWN OVERHANGING MOUNTING SHELFMOUNTING SHELF4.76120.8MINIMUM REQUIRED INSTALLATION AND REMOVAL CLEARANCEWITH LOCKDOWN NOT OVERHANGING MOUNTING SHELFMOUNTING SHELFDRAFT
190-01277-00 GRA 5500 Installation ManualRevision A Page C-1APPENDIX C Interconnect ExamplesFigure C-1 Garmin Integrated Flight Deck (GIFD) and non-GIFD (retrofit) Interconnect ExampleGRA 5500RADAR ALTIMETERTO 14/28 VDC AIRCRAFT POWERGR A 5500 5A(OR GREATER)P55001AIR CR AFT POWE R 1 3TO 14/28 VDC AIRCRAFT POWERAIR CR AFT POWE R 2 1POWER GROUND 8POWER GROUND 2GRGRNOTES: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 DESIGNATIONSSTWISTED SHIELDED PAIRTWISTED SHIELDED 4 CONDUCTORAIRCRAFT GROUNDGARMIN (SHIELD BLOCK) GROUNDAND CIRCULAR CONNECTOR SHIELD GROUNDWIRE SPLICE CONNECTIONCOAXIAL CABLETX ANTENNARX ANTENNATXRX5A(OR GREATER)RADAR ALT SYSTEM ID PRO AM* 1 13RADAR ALT SYSTEM ID PRO AM* 2 14 }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.GR A 5500 TX ANTENNARX ANTENNA1. THIS INTERCONNECT EXAMPLE DRAWING APPLIES TO BOTH GIFD (GARMIN INTEGRATED FLIGHT DECK)AND NON-GIFD (RETROFIT) INSTALLATIONS.DRAFT
190-01277-00 GRA 5500 Installation ManualRevision A Page C-2APPENDIX C Interconnect ExamplesFigure C-2 Garmin Integrated Flight Deck Interconnect ExampleGRA 5500RADAR ALTIMETER P5500146RS422 IN 1 A35RS422 IN 1 B24RS422 OUT 1 A23RS422 OUT 1 BGSD 41DATA CONCENTRATORP412SS91078MAIN2 RS-485/RS-422 4 AMAIN2 RS-485/RS-422 4 BMAIN2 RS-485/RS-422 5 AMAIN2 RS-485/RS-422 5 B25RS422 IN 2 A18RS422 IN 2 B38RS422 OUT 2 A42RS422 OUT 2 BGIA 63INTEGRATED AVIONICS UNITP603SS27283637RS-485 5 A/RS-422 OUT ARS-485 5 B/RS-422 OUT BRS-485 3 A/RS-422 IN ARS-485 3 B/RS-422 IN BGRA 5500RADAR ALTIMETER P55001AND/ORTHIS INTERCONNECT EXAMPLE DRAWING APPLIES ONLY TO GARMIN INTEGRATED FLIGHT DECK (GIFD) INSTALLATIONS.DRAFT
190-01277-00 GRA 5500 Installation ManualRevision A Page C-3APPENDIX C Interconnect ExamplesFigure C-3 Non-Garmin Integrated Flight Deck (retrofit) Interconnect ExampleGRA 5500RADAR ALTIMETERP5500152ARINC 429 OUT 1 A55ARINC 429 OUT 1 BDISPLAY UNIT AND/OR OTHER ARINC 429 RECEIVERSSSARINC 429 IN AARINC 429 IN BTHIS INTERCONNECT EXAMPLE DRAWING APPLIES ONLY TO NON-GARMIN INTEGRATED FLIGHT DECK (RETROFIT) INSTALLATIONS.32RADAR ALTITUDE ALERT OUT* 117RADAR ALTITUDE ALERT OUT* 2}OPTIONAL CONNECTIONS, SEE SECTION 4.4.2 FOR INFORMATION ON FUNCTIONALITY OF ALTITUDE ALERT OUTPUTSNOTES1. 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.9SELF TEST SELECT*19SELF TEST INHIBIT*OPTIONAL CONNECTIONS, SEE SECTIONS 3.7.4.1 AND 4.4.1 FOR INFORMATION ON FUNCTIONALITY OF MANUALLYINTIATED ALTITUDE SELF-TEST AND SELF-TEST INHIBIT.}SEE NOTE 1CONF IG MODULE GR OUND 48CONFIG MODULE POWER 53CONF IG MODULE DATA 40CONFIG MODULE CLOCK 47YELLOWREDBLKWHT1GND4VCC3DATA2CLOCKSEE NOTE 2CONFIG MODULEUSB DATA HIUSB VBUS POWERUSB DATA LOUSB GROUND44495445SIGNAL GROUND 43USB TYPE BRECEPTACLEVBUSD+D-GND1324SHIELD (DRAIN)REDGRNWHTBLK28 AWG28 AWG SEE NOTE 3SHELLDRAFT
190-01277-00 GRA 5500 Installation ManualRevision A Page C-4APPENDIX C Interconnect ExamplesFigure C-4 GRA 5500 USB Dongle CableGRA 5500RADAR ALTIMETER USB TYPE BRECEPTACLENOTES:1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 4. REMOVE THE OUTER BLACK INSULATION SO THAT THE INDIVIDUAL WIRES ARE EXPOSED FOR A LENGTH OF 1.25 INCHES. 6. CRIMP PINS ON TO THE INDIVIDUAL WIRES AND THE DRAIN WIRE USING BEST SHOP PRACTICES.USB DATA HIUSB VBUS POWERUSB DATA LOUSB GROUND44495445VBUSD+D-GND1324SHIELD (DRAIN)REDGRNWHTBLK28 AWG28 AWG5SIGNAL GROUND 433. TRIM ALL EXPOSED INDIVIDUAL 24 AWG AND 28 AWG WIRES AND THE TINNED 28 AWG DRAIN WIRE BACK TO THE OUTER BLACK INSULATION. 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. 2 2. 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. PIN 3PIN 1PIN 2PIN 4P55001DRAFT
190-01277-00 GRA 5500 Installation ManualRevision A Page C-5APPENDIX C Interconnect ExamplesFigure C-5 GRA 5500 Configuration Module Interconnect Example GRA 5500GRA 5500RADAR ALTIMETERRADAR ALTIMETER4848535340404747NOTE: USE OF A CONFIGURATION MODULE IN GARMIN INTEGRATED FLIGHT DECK (GIFD) INSTALLATIONS IS NOT REQUIRED. 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 FOR NON-GIFD (RETROFIT) INSTALLATIONS, USE OF A CONFIGURATION MODULE IS OPTIONAL TO RETAIN CONFIGURATION SETTINGS OUTSIDE OF THE INDIVIDUAL LRU. SETTINGS OUTSIDE OF THE INDIVIDUAL LRU. P55001P55001CONFIGURATIONCONFIGURATIONMODULEMODULECONFIG MODULE GROUNDCONFIG MODULE GROUNDCONFIG MODULE POWERCONFIG MODULE POWERCONFIG MODULE DATACONFIG MODULE DATACONFIG MODULE CLOCKCONFIG MODULE CLOCKGROUNDGROUNDVCCVCCDATADATACLOCKCLOCK1432BLKBLKREDREDYELLOWYELLOWWHTWHTDRAFT

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