Garmin 0183700 LICENSED NON-BROADCAST AERONAUTICAL TRANSMITTER User Manual 190 00303 24 01

Garmin International Inc LICENSED NON-BROADCAST AERONAUTICAL TRANSMITTER 190 00303 24 01

Users Manual

190-00303-24 January, 2012 Revision AGDR 66Transceiver Installation ManualDRAFT
Page A GDR 66 Installation ManualRevision A 190-00303-24© Copyright 2011Garmin 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 01/17/2012 Initial ReleaseDRAFT
GDR 66 Installation Manual Page i190-00303-24 Revision AINFORMATION 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) andwhich may not be exported, released, or disclosed to foreign nationals inside or outside of the United Stateswithout first obtaining an export license. The preceding statement is required to be included on any and allreproductions in whole or in part of this manual.This product, its packaging, and its components contain chemicals known to the State of California to cause cancer, birth defects, or reproductive harm. This Notice is being provided in accordance with California's Proposition 65. If you have any questions or would like additional information, please refer to our web site at www.garmin.com/prop65.CURRENT REVISION DESCRIPTIONDOCUMENT PAGINATIONWARNINGRevision Page Number(s)Section Number Description of ChangeA All All Initial releaseSection Page RangeTable of Contents i – viSection 1 1-1 – 1-8Section 2 2-1 – 2-4Section 3 3-1 – 3-4Section 4 4-1 – 4-10Appendix A A-1 – A-3Appendix B B-1 – B-3DRAFT
Page ii GDR 66 Installation ManualRevision A 190-00303-24TABLE 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 Power Requirements ........................................................................................................... 1-31.4.5 Transmitter Power Versus Aircraft Bus Voltage ................................................................ 1-31.4.6 COM Transceiver Specifications........................................................................................ 1-41.4.7 Digital Transceiver Characteristics..................................................................................... 1-41.4.8 License Requirements......................................................................................................... 1-61.5 Certification..................................................................................................................... 1-61.5.1 TSO/ETSO Compliance......................................................................................................1-71.5.2 TSO/ETSO Deviations........................................................................................................ 1-71.6 Reference Documents ..................................................................................................... 1-71.7 Aviation Limited Warranty ............................................................................................. 1-8Section 2 INSTALLATION OVERVIEW....................................................... 2-12.1 Introduction ..................................................................................................................... 2-12.2 Installation Materials....................................................................................................... 2-12.2.1 Equipment Available .......................................................................................................... 2-12.2.2 Additional Equipment Required ......................................................................................... 2-12.3 Installation Considerations.............................................................................................. 2-22.3.1 Antenna Considerations...................................................................................................... 2-22.3.2 Com Antenna Location....................................................................................................... 2-22.4 Cabling and Wiring .........................................................................................................2-32.5 Cooling Air...................................................................................................................... 2-32.6 Mounting Requirements.................................................................................................. 2-4Section 3 INSTALLATION PROCEDURE .................................................... 3-13.1 Unpacking Unit ............................................................................................................... 3-13.2 Wiring Harness Installation............................................................................................. 3-13.3 Antenna Installation ........................................................................................................ 3-23.4 Cable Installation ............................................................................................................ 3-33.5 Backshell Assembly ........................................................................................................3-43.6 Final Installation.............................................................................................................. 3-43.7 Post Installation Configuration & Checkout ................................................................... 3-43.8 Continued Airworthiness ................................................................................................ 3-4DRAFT
GDR 66 Installation Manual Page iii190-00303-24 Revision ATABLE OF CONTENTSPARAGRAPH PAGESection 4 SYSTEM INTERCONNECTS......................................................... 4-14.1 Pin Function List ............................................................................................................. 4-14.1.1 P661 (COM)........................................................................................................................ 4-14.1.2 P662 (Main) ........................................................................................................................ 4-24.2 Power Functions.............................................................................................................. 4-44.2.1 Aircraft Power..................................................................................................................... 4-44.2.2 Remote Power Off .............................................................................................................. 4-44.2.3 GDR System ID Program ................................................................................................... 4-44.3 Serial Data....................................................................................................................... 4-54.3.1 RS-422 ................................................................................................................................ 4-54.3.2 RS-232 ................................................................................................................................ 4-54.3.3 ARINC 429 ......................................................................................................................... 4-64.4 Discrete I/O ..................................................................................................................... 4-74.4.1 Active Low Discrete Inputs ................................................................................................ 4-74.4.2 Key Event Out..................................................................................................................... 4-74.5 Audio............................................................................................................................... 4-84.5.1 Analog Audio...................................................................................................................... 4-84.5.2 ACARS/SELCAL............................................................................................................... 4-9Appendix A Outline and Installation Drawings............................................. A-1Appendix B Interconnect Examples.................................................................B-1DRAFT
Page iv GDR 66 Installation ManualRevision A 190-00303-24LIST OF FIGURESFIGURE PAGESection 1 GENERAL DESCRIPTION............................................................. 1-1Section 2 INSTALLATION OVERVIEW....................................................... 2-1Figure 2-1: GDR 66 Standalone Rack ..................................................................................2-4Section 3 INSTALLATION PROCEDURE .................................................... 3-1Figure 3-1 TNC Connector Installation ................................................................................ 3-3Section 4 SYSTEM INTERCONNECTS......................................................... 4-1Figure 4-1 View of J661 connector, from back of unit......................................................... 4-1Figure 4-2 View of J662 connector, from back of unit......................................................... 4-2Appendix A Outline and Installation Drawings ............................................ A-1Figure A-1 GDR 66 Outline Drawing.................................................................................. A-1Figure A-2 GDR 66 Connector/Rack Assembly Drawing.................................................. A-2Figure A-3 GDR 66 Minimum Installation/Removal Clearance ......................................... A-3Appendix B Interconnect Examples ................................................................B-1Figure B-1 GDR 66 Power and Antenna Interconnect Example ......................................... B-1Figure B-2 GDR 66 VDL Mode 2 Interconnect Example ................................................... B-2Figure B-3 GDR 66 Analog Voice Mode Interconnect Example ........................................ B-3DRAFT
GDR 66 Installation Manual Page v190-00303-24 Revision ALIST OF TABLESTABLE PAGESection 1 GENERAL DESCRIPTION .............................................................1-1Table 1-1 Physical Characteristics........................................................................................ 1-2Table 1-2 General Specifications.......................................................................................... 1-2Table 1-3 Power Requirements............................................................................................. 1-3Table 1-4 TX Power (into 50Ω load) vs Bus Voltage .......................................................... 1-3Table 1-5 Transceiver Specifications ................................................................................... 1-4Table 1-6 Digital Transceiver Characteristics ...................................................................... 1-4Table 1-7 License Requirements .......................................................................................... 1-6Table 1-8 TSO/ETSO Compliance ....................................................................................... 1-7Table 1-9 TSO/ETSO Deviations ......................................................................................... 1-7Table 1-10 Reference Documents......................................................................................... 1-7Section 2 INSTALLATION OVERVIEW........................................................2-1Table 2-1 Available Units..................................................................................................... 2-1Table 2-2 Equipment Available............................................................................................ 2-1Table 2-3 Additional Equipment Required........................................................................... 2-1Section 3 INSTALLATION PROCEDURE.....................................................3-1Table 3-1: Pin Contact Part Numbers ................................................................................... 3-1Table 3-2 Recommended Crimp Tools................................................................................. 3-2Section 4 SYSTEM INTERCONNECTS..........................................................4-1Table 4-1 P661 Connector .................................................................................................... 4-1Table 4-2 P662 Connector .................................................................................................... 4-2Table 4-3 Aircraft Power ...................................................................................................... 4-4Table 4-4 Remote Power Off................................................................................................ 4-4Table 4-5 System ID Program .............................................................................................. 4-4Table 4-6 Unit Number Configuration ................................................................................. 4-5Table 4-7 RS-422.................................................................................................................. 4-5Table 4-8 RS-232.................................................................................................................. 4-5Table 4-9 ARINC 429........................................................................................................... 4-6Table 4-10 Discrete Inputs.................................................................................................... 4-7Table 4-11 Key Event Out .................................................................................................... 4-7Table 4-12 Com Mic Audio.................................................................................................. 4-8Table 4-13 Com Audio Out .................................................................................................. 4-8Table 4-14 Com Mic Key ..................................................................................................... 4-8Table 4-15 Com Remote Transfer ........................................................................................ 4-9Table 4-16 SELCAL Audio and ACARS Data Out ............................................................. 4-9DRAFT
Page vi GDR 66 Installation ManualRevision A 190-00303-24DRAFT
GDR 66 Installation Manual Page 1-1190-00303-24 Revision A1 GENERAL DESCRIPTION1.1 IntroductionThis manual presents mechanical and electrical installation requirements for installing the GDR 66 as part of a Garmin Integrated Flight Deck. The GDR 66 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 GDR 66 is a remote mounted digital communications transceiver. The GDR 66 operates in the following modes in the 118.000 to 137.000 MHz VHF aviation communications band:•Analog Voice Mode (ARINC 716 Voice): Voice communications using DSB-AM modulation with 8.33 and 25 kHz channel spacing. •VDL Mode 0/A (ARINC 716 Data): ACARS using DSB-AM modulation with a 2.4 kbps data rate and 25 kHz channel spacing.•VDL Mode 2 (ARINC 750 Data): Data link using D8PSK modulation with a 31.5 kbps data rate and 25 kHz channel spacing.1.3 Interface SummaryThe GDR 66 provides the following interfaces:• 2 RS-422 inputs• 2 RS-422 outputs • 1 RS-232 input• 1 RS-232 output• 5 configurable ARINC 429 inputs• 2 configurable ARINC 429 outputs• 8 configurable active low discrete inputs• 5 active low discrete inputs: COM MIC KEY*, COM REMOTE TRANSFER*, GDR SYSTEM ID PROGRAM* 1, GDR SYSTEM ID PROGRAM* 2, GDR SYSTEM ID PROGRAM* 3• 1 active high discrete input: COM REMOTE POWER OFF• 1 active low discrete outputs: KEY EVENT OUT*• 1 analog microphone audio input• 1 analog audio output• 1 SELCAL audio/ACARS analog data output• 2 aircraft power bus inputsDRAFT
Page 1-2 GDR 66 Installation ManualRevision A 190-00303-241.4 Technical Specifications1.4.1 Environmental Qualification FormIt is the responsibility of the installing agency to obtain the latest revision of the GDR 66 Environmental Qualification Form. This form is available directly from Garmin under the following part number:GDR 66 Environmental Qualification Form, Garmin part number 005-00548-01To 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 list the physical characteristics for the GDR 66 unit, rack, and connectors. Please refer to Appendix A for additional information.1.4.3 General SpecificationsFor detailed specifications, see the Environmental Qualification Form.Table 1-1 Physical CharacteristicsCharacteristics SpecificationsWidth (w/out Rack) 2.06 inches (5.23 cm)Height (w/out Rack) 6.46 inches (16.4 cm)Depth (w/out Rack) 8.78 inches (22.3 cm)Width (with Rack) 2.06 inches (5.23 cm)Height (with Rack) 6.62 inches (16.8 cm)Depth (with Rack & Connectors) 10.1 inches (25.8 cm)Unit Weight 4.2 lbs. (1.9 kg)Rack Weight 0.36 lbs. (0.16 kg)Connector Weight 0.33 lbs. (0.15 kg)Table 1-2 General SpecificationsCharacteristics SpecificationsOperating Temperature Range -55°C to +70°C. For more details see Environmental Qualification Form.Humidity 95% non-condensingAltitude Range -1,500 ft to 55,000 ftSoftware Compliance RTCA/DO-178B Level C, EUROCAE/ED-12B Level CEnvironmental Conditions RTCA/DO-160E, EUROCAE/ED-14EDRAFT
GDR 66 Installation Manual Page 1-3190-00303-24 Revision A1.4.4 Power Requirements1.4.5 Transmitter Power Versus Aircraft Bus VoltageGDR 66 does not claim Emergency Operation as defined by RTCA DO-160E, Section 16Table 1-3 Power RequirementsCharacteristics SpecificationsInput Voltage 14/28 Vdc. See the Environmental Qualification Form for details on surge ratings and minimum/maximum operating voltages.14V Receive (AM or VDL) Maximum 3.0ATransmit (AM or VDL) Maximum 9.0A28V Receive (AM or VDL) Maximum 1.5ATransmit (AM or VDL) Maximum 8.0ATable 1-4 TX Power (into 50Ω load) vs Bus VoltageAircraft Power Bus Voltage (V) Tx Power AM Mode Tx Power VDL ModeV ≥ 22.0 V 16 W minimum20 W Typical15 W minimum20 W Typical22.0 > V ≥11.0 8 W minimum10 W Typical7.5 W minimum10 W Typical11.0 > V ≥10.25 4 W minimum5 W Typical4 W minimum5 W TypicalNOTEDRAFT
Page 1-4 GDR 66 Installation ManualRevision A 190-00303-241.4.6 COM Transceiver SpecificationsThe GDR 66 Transceiver minimally meets the requirements of DO-186B and ED-23B. Refer to Table 1-5 for detailed specifications. 1.4.7 Digital Transceiver CharacteristicsThe GDR 66 Transceiver minimally meets the requirements of DO-281A. Refer to Table 1-6 for detailed specifications.Table 1-5 Transceiver SpecificationsCharacteristics SpecificationsAudio Outputs Received Audio: 40 mW minimum into a 600Ω loadSELCAL/Data: 10.4 mW minimum into a 600Ω loadAudio Response Less than 6 dB of variation between 300 and 2500 HzGreater than 40dB rejection above 3750 HzAudio DistortionNot greater than 20.0% across the band from 300 Hz to 2500 Hz with a 90% modulated signal. No greater than 7.5% with a 30% modulated signal Receiver Dynamic Range -107 dBm to +10 dBm typicalSensitivity (S+N)/N on all channels shall be greater than 6 dB when the RF level is -107dBm modulated 30% at 1000 HzSquelch Selectable between 0 to 20 dB SNR. Squelch hysteresis is selectable up to 15 dBSpurious Response 74 dB minimum (-33 dBm signal produces no more output than desired signal producing 6 dB (S+N)/N)Multi-Carrier Operation Meets multi-carrier sensitivity, distortion, and audio output level requirements of ED-23C for Class C and Class H2 reveivers.Transmitter Power See Section 1.4.5Transmitter Duty Cycle 10% maximum, thermally limited, 30 second limit per transmissionModulation Capability The modulation shall not be less than 70% with a standard modulator signal applied to the transmitterCarrier Noise Level Shall be at least 45 dB (S+N)/NFrequency Stability + / - 5ppm (-55ºC to +70ºC with a 5-minute warmup at -55ºC)Demodulated Audio Distortion Less than 10% distortion when the transmitter is modulated at least 70%Sidetone 1.4 Vrms into a 600Ω loadTransmit Modulation Fidelity Shall be less than 6 dB when the audio input frequency is varied from 350 to 2500 HzMicrophone Sensitivity See Section 4.5.1.1Spurious Emissions - Global Navigation Satellite System BandHarmonic Emission products in the band extending from 1559 to 1610 Mhz shall be no greater than -60dBmTable 1-6 Digital Transceiver CharacteristicsCharacteristics SpecificationsDynamic Range +10dBm to -98dBm typicalSensitivity Uncorrected BER of no more than 0.001 at -98 dBmTransmitter Power See Section 1.4.5Transmitter Duty Cycle 20% maximum, thermally limitedModulation Capability D8PSKFrequency Stability + / - 5ppm (-55ºC to +70ºC with a 5-minute warmup at -55ºC)Transmit Symbol Constellation Error EVM of less than 6%Spurious Emissions - Global Navigation Satellite System BandHarmonic Emission products in the band extending from 1559 to 1610 Mhz shall be no greater than -60dBmDRAFT
GDR 66 Installation Manual Page 1-5190-00303-24 Revision A1.4.8 License RequirementsThe Telecommunications Act of 1996, effective February 8, 1996, provides the FCC discretion to eliminate radio station license requirements for aircraft and ships. The GDR 66 installation must comply with current transmitter licensing requirements. To find out the specific details on whether a particular installation is exempt from licensing, please visit the FCC web site http://wireless.fcc.gov/aviation.If an aircraft license is required, make application for a license on FCC form 404, Application for Aircraft Radio Station License. The FCC also has a fax-on-demand service to provide forms by fax. The GDR 66 owner accepts all responsibility for obtaining the proper licensing before using the transmitter.International transmitter license procedures vary by country. Contact the local spectrum agency for license requirements.The VHF transmitter in this equipment is guaranteed to meet federal communications commission acceptance over the operating temperature range. Modifications not expressly approved by Garmin could invalidate the license and make it unlawful to operate the equipment.1.5 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. At the time of publication, installations of this TSO approved article are only approved when installed in an aircraft as part of a Garmin Integrated Flight Deck under an appropriate TC or STC.The Appliance Project Identifier (API) for the GDR 66 is GMN-00832. Documents submitted to the FAA, EASA and other regulatory agencies on behalf of this project will be filed under and referred to by this number.Table 1-7 License RequirementsCharacteristic SpecificationTransmitter Description: Aviation-band VHF transceiver with 25 and 8.33 kHz channel spacing.Antenna Characteristics: Broad band, 50 ohm, vertically polarized.Rated Power: 20 WattsEmission Type (Voice): 6K00A3E (25 kHz Channel Spacing Mode)5K60A3E (8.33 kHz Channel Spacing Mode)Emission Type (Data): 13K0A2D (VDL Mode A, ACARS)14K0G1D (VDL Mode 2)Frequency of Operation: 118.000 – 136.975 MHz in 25 KHz AM or VDL Mode118.000 – 136.99166 MHz in 8.3 KHz AM ModeNOTEDRAFT
Page 1-6 GDR 66 Installation ManualRevision A 190-00303-241.5.1 TSO/ETSO Compliance1.5.2 TSO/ETSO Deviations1.6 Reference DocumentsThe following publications are sources of additional information for installing the GDR 66. Before installing the GDR 66, the technician should read all referenced materials along with this manual.Table 1-8 TSO/ETSO ComplianceFunction TSO/ETSO/RTCA/EUROCAE Category Applicable LRU SW Part NumbersVHF COM Transceiver from 117.975 – 137.000 MHzTSO-C169aETSO-2C37eETSO-2C38eRTCA/DO-186BEUROCAE/ED-23BTX – 3,4,5,6RX – C,E006-B1055-(_)006-B1056-(_)VDL Mode 2 Communications EquipmentTSO-C160RTCA/DO-281AEUROCAE/ED-92ATX – 7,8RX – FArchitecture – Y006-B1055-(_)006-B1056-(_)Equipment that prevents blocked channels due to unintentional transmissionsTSO-C128AETSO-2C128RTCA/DO-207EUROCAE/ED-67N/A 006-B1055-(_)006-B1056-(_)Table 1-9 TSO/ETSO DeviationsTSO/ETSO DeviationTSO-C169a1. Garmin was granted a deviation from TSO-C169a paragraph 4.a.2 to allow the unit to be perma-nently and legibly marked with a serial number and not the date of manufacture. The justification for this deviation is per FAA Memorandum “FAA Order 8150.1B, Technical Standard Order Pro-gram, Policy Clarification” which states that the date of manufacture must be used in lieu of the optional serial number when that information is critical for maintenance and/or inspections. An equivalent level of safety is provided since the date of manufacture is not critical for maintenance and/or inspections of this appliance. The appliance will be marked with a serial number.ETSO-2C37e 1. Garmin was granted a deviation from ETSO-2C37e to use DO-160E instead of DO-160D. Equivalent Level of Safety (ELOS) is provided by use of a later revision requirement document.2. Garmin was granted a deviation from ETSO-2C37e to use ED-23B amendment 3 in addition to ED-23B. ELOS is provided by use of a later revision requirement document.ETSO-2C38e1. Garmin was granted a deviation from ETSO-2C38e to use DO-160E instead of DO-160D. ELOS is provided by use of a later revision requirement document.2. Garmin was granted a deviation from ETSO-2C38e to use ED-23B amendment 3 in addition to ED23B. ELOS is provided by use of a later revision requirement document.ETSO-2C128 1. Garmin was granted a deviation from ETSO-2C128 to use DO-160E instead of DO-160D. ELOS is provided by use of a later revision requirement document.Table 1-10 Reference DocumentsPart Number Document190-00303-00 G1000 System Installation Manual190-00303-04 G1000 Line Maintenance and Configuration Manual190-00313-11 Jackscrew Backshell Installation Instructions190-00313-50 Garmin Integrated Avionics System Thermal Management Plan190-00313-51 Garmin Integrated Avionics System Thermal Validation ProcedureDRAFT
GDR 66 Installation Manual Page 1-7190-00303-24 Revision A1.7 Aviation 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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GDR 66 Installation Manual Page 2-1190-00303-24 Revision A2 INSTALLATION OVERVIEW2.1 IntroductionThis section provides hardware equipment information for installing the GDR 66, related hardware, and antennas. Installation of the GDR 66 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 retro-fit installations that comply with FAA regulations. Refer to Appendix A for rack drawings and dimensions.2.2 Installation MaterialsThe GDR 66 is only available as a single unit under the following part number:2.2.1 Equipment AvailableEach of the following accessories are provided separately from the GDR 66 and are required for installation.2.2.2 Additional Equipment RequiredThe following installation accessories are required but not provided:* Only required for voice mode** Used for mounting unit rack to airframe Table 2-1 Available UnitsItem Garmin P/NGDR 66 Unit Only, (011-02303-00) 010-00832-00Table 2-2 Equipment AvailableItem Garmin P/NGDR 66 Standalone Install Rack 011-02477-00GDR 66 Connector Kit 011-02304-00 Table 2-3 Additional Equipment RequiredCharacteristic SpecificationCOM Antenna Shall meet TSO-C37(), C38(), and C-169(). Broad band, 50 Ω, vertically polarized with coaxial cableHeadphones* 500 Ω nominal impedance Microphone* Low impedance, carbon or dynamic, with transistorized pre-ampHardware** #10 pan head or hex head fastener (qty 4)DRAFT
Page 2-2 GDR 66 Installation ManualRevision A 190-00303-242.3 Installation ConsiderationsFabrication of a wiring harness is required. Sound mechanical and electrical methods and practices are required for installation of the GDR 66.2.3.1 Antenna ConsiderationsAntenna installations on pressurized cabin aircraft require FAA approved installation design and engineering substantiation data whenever such antenna 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 antenna installations, it is recommended that the installer proceed according to any of the following listed alternatives:1. Obtain approved antenna installation design data from the aircraft manufacturer.2. Obtain an FAA approved STC, pertaining to, and valid for the antenna 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 antenna installation engineering data.4. Obtain FAA Advisory Circular AC-183C and select (and contact) a DER from the roster of individuals listed in it.5. Contact an aviation industry organization such as the Aircraft Electronics Association for assistance.2.3.2 Com Antenna LocationThe GDR 66 COM antenna should be well removed from all projections, engines and propellers. The ground plane surface directly below the antenna should be a flat plane over as large an area as possible (18 inches square, minimum). The antenna should be mounted a minimum of three feet from any DME antennas, three feet from any GPS antennas, and as far as practical from the ELT antenna. Some ELTs have exhibited re-radiation problems generating harmonics which may interfere with other signals.In addition, the COM antenna must have at least 16 dB of isolation from other COM antennas to prevent damage to the GDR 66 COM receiver. For COM antennas mounted on the same side of the fuselage, 16 dB of isolation can be achieved by a physical separation of approximately 3 feet (0.9 meters).If simultaneous use of two or more COM transceivers is desired the COM antennas must be spaced for maximum isolation. For a two COM installation, one COM antenna should be mounted on the top of the fuselage and the other antenna should be mounted on the bottom of the fuselage. For installations with three COM’s, one COM antenna should be mounted on the top of the fuselage and the other two antennas should be mounted on the bottom of the fuselage and physically separated from each other as much as possible.The recommended minimum isolation between COM antennas for simultaneous use of two or more COM’s is 40 dB. Separating the COM antennas between the top and bottom of the fuselage typically provides 35 – 45 dB of isolation for metal skin aircraft. For COM antennas mounted on the same side of the fuselage, 40 dB of isolation can be achieved by a physical separation of approximately 60 feet (18.3 meters). Receiver sensitivity could be significantly reduced during the transmission of a co-located COM for installations with less than 40 dB of isolation between the COM antennas. For installations with less than 23 dB of isolation between COM antennas, cross modulation (bleed-through) could also be experienced during the transmission of a co-located COM. For COM antennas mounted on the same side of the fuselage, 23 dB of isolation can be achieved by a physical separation of approximately 9 feet (2.7 meters). Simultaneous COM performance varies significantly across installations and is affected by both the isolation between the COM antennas and the separation of the tuned frequencies. Each installation should be individually examined to determine the expected performance of simultaneous COM.DRAFT
GDR 66 Installation Manual Page 2-3190-00303-24 Revision A2.4 Cabling and WiringRefer to the interconnect examples in Appendix B for wire gauge guidance.The power connection can be run with three AWG #18 wires back to the breaker or can be spliced near the unit to one AWG #16 or larger wire. Special thin-wall heat shrink tubing is also provided to insulate the extended barrels inside the backshell. If using AWG #18 barrel contacts, ensure that no two contacts are mounted directly adjacent to each other. This minimizes the risk of contacts touching and shorting to adjacent pins and to ground.Ensure that routing of the wiring does not come in contact with sources of heat, RF or EMI interference. Check that there is ample space for the cabling and mating connectors. Avoid sharp bends in cabling and routing near aircraft control cables.Coaxial cable with 50Ω nominal impedance and meeting applicable aviation regulations should be used for the installation.RTCA DO-224A assumes 3dB of cable loss in its VDL Typical Uplink Power Budget. Losses greater than 3dB can reduce transceiver range.Cabling for the GDR 66 should not be routed near components or cabling which are sources of electrical noise. Route the GPS, VOR/LOC, and Glideslope antenna cables as far as possible away from all COM transceivers and antenna cables.2.5 Cooling AirDedicated cooling is not required for the GDR 66 to meet indicated EQF categories. Thermal analysis must be performed to verify that high temperature limits implied by the indicated EQF categories for the GDR 66 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.NOTEDRAFT
Page 2-4 GDR 66 Installation ManualRevision A 190-00303-242.6 Mounting RequirementsThe GDR 66 mounting surface should be capable of providing a sufficient electrical bond to the aircraft to minimize radiated EMI and provide protection from High-Intensity Radiation Fields (HIRF). Bonding resistance measured between the GDR 66 standalone install rack and the airframe should be less than 2.5 mlliOhms. The GDR 66 must be mounted in the vertical position using the GDR 66 standalone rack. Approximately one inch of clearance should be provided on the left side of the GDR 66 to allow for cooling of the heat sink. Refer to Appendix A for outline and installation drawings.Figure 2-1: GDR 66 Standalone RackDRAFT
GDR 66 Installation Manual Page 3-1190-00303-24 Revision A3 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 are made through 44 and 62-pin D-subminiature connectors. Section 4 defines the electrical characteristics of all input and output signals. Required connectors and associated hardware are supplied with the connector kit.See Appendix B for examples of interconnect wiring diagrams. Construct the actual harnesses in accordance with aircraft manufacturer authorized interconnect standards.Contacts for the 62 and 44 pin connectors must be crimped onto the individual wires of the aircraft wiring harness. Tables 3-1 and 3-2 list contact part numbers (for reference) and recommended crimp tools.Table 3-1: Pin Contact Part NumbersManufacturer 62 pin connector (P662), 44 pin connector (P661)18-20 AWG (Power Only)22-28 AWGGarmin P/N 336-00044-00 336-00021-00Military P/N N/A M39029/58-360AMP N/A 204370-2Positronic N/A MC8522DITT Cannon N/A 030-2042-000DRAFT
Page 3-2 GDR 66 Installation ManualRevision A 190-00303-241. Non-Garmin part numbers shown are not maintained by Garmin and consequently are subject to change without notice.2. Extracting the #18 or #20 contact requires that the expanded wire barrel be cut off from the contact. It may also be necessary to push the pin out from the face of the connector when using an extractor due to the absence of the wire. A new contact must be used when reassembling the connector.3.3 Antenna InstallationFollow the manufacturers’ instructions for installation of the COM antenna.Do not use construction grade RTV sealant or sealants containing acetic acid. These sealants may damage the electrical connections to the antenna. Use of these type sealants may void the antenna warranty.Table 3-2 Recommended Crimp ToolsManufacturer Hand Crimping Tool18-20 AWG 22-28 AWGPositioner Insertion/Extraction Tool(note 2)Positioner Insertion/Extraction ToolMilitary P/N M22520/2-01 N/A M81969/1-04 M22520/2-09 M81969/1-04Positronic 9507 9502-11 M81969/1-04 9502-4 M81969/1-04ITT Cannon 995-0001-584 N/A N/A M22520/2-09 274-7048-000AMP 601966-1 N/A 91067-1 601966-6 91067-1Daniels AFM8 K774 M81969/1-04 K42 M81969/1-04Astro 615717 N/A M81969/1-04 615725 M81969/1-04NOTECAUTIONDRAFT
GDR 66 Installation Manual Page 3-3190-00303-24 Revision A3.4 Cable Installation1. Route the coaxial cable to the rack location keeping in mind the recommendations of Section 2. Secure the cable in accordance with good aviation practice.2. Trim the coaxial cable to the desired length and install the TNC connector per the cabling instructions on Figure 3-1. If the connector is provided by the installer, follow the connector manufacturer’s instructions for cable preparation.Figure 3-1 TNC Connector InstallationDRAFT
Page 3-4 GDR 66 Installation ManualRevision A 190-00303-243.5 Backshell AssemblyThe GDR 66 connector kit includes two Garmin backshell assemblies. Garmin’s backshell gives the installer the ability to easily terminate shield grounds at the backshell housing. Refer to the Jackscrew Backshell Installation Instructions (Garmin part number 190-00313-11) for backshell assembly instructions.3.6 Final InstallationFor final installation and assembly, refer to the outline and installation drawings shown in Appendix A of this manual.3.7 Post Installation Configuration & CheckoutThe GDR 66 must be installed as part of a Garmin Integrated Flight Deck and have FAA approved configuration data. Configuration data is loaded to the GDR 66 from an aircraft-specific Garmin SW Loader Card. GDR 66 settings are predetermined for a specific aircraft. For aircraft installation/checkout, use only aircraft manufacturer approved checkout procedures.3.8 Continued AirworthinessMaintenance of the GDR 66 is “on condition” only. For regulatory periodic functional checks, refer to approved aircraft maintenance manuals or manual supplements for actual aircraft maintenance requirements.DRAFT
GDR 66 Installation Manual Page 4-1190-00303-24 Revision A4 SYSTEM INTERCONNECTS4.1 Pin Function List4.1.1 P661 (COM)Figure 4-1 View of J661 connector, from back of unitTable 4-1 P661 ConnectorPin Pin Name I/O1SPARE --2SPARE --3SPARE --4 COM MIC KEY* In5SPARE --6SPARE --7 COM MIC AUDIO IN HI In8 COM MIC AUDIO IN LO (GROUND) --9 COM 600 OHM AUDIO OUT HI Out10 COM 600 OHM AUDIO OUT LO Out11 RESERVED --12 COM REMOTE TRANSFER* In13 RESERVED --14 RESERVED --15 SIGNAL GROUND --16 COM REMOTE POWER OFF In17 SPARE --18 RESERVED --19 SPARE --20 GDR SYSTEM ID PROGRAM* 1 In21 SPARE --22 GDR SYSTEM ID PROGRAM* 2 In23 SPARE --24 GDR SYSTEM ID PROGRAM* 3 In25 SPARE --26 SIGNAL GROUND --27 SPARE --28 RESERVED --29 SIGNAL GROUND --30 SIGNAL GROUND --31 SIGNAL GROUND --32 RS-232 OUT 1 Out33 RS-232 IN 1 In34 RESERVED --35 KEY EVENT OUT* Out*Denotes Active Low (Ground to activate).1234567891011121314151617181920212223242526272829303132333435363738394041424344DRAFT
Page 4-2 GDR 66 Installation ManualRevision A 190-00303-24*Denotes Active Low (Ground to activate).4.1.2 P662 (Main)Figure 4-2 View of J662 connector, from back of unitTable 4-2 P662 ConnectorTable 4-1 P661 Connector, continued36 RESERVED --37 SPARE --38 SPARE --39 RESERVED --40 RESERVED --41 SELCAL AUDIO AND DATA OUT HI Out42 SELCAL AUDIO AND DATA OUT LO Out43 SIGNAL GROUND --44 SIGNAL GROUND --Pin Pin Name I/O1 POWER GROUND --2 RS-422 IN 1 B In3 RS-422 IN 1 A In4 RS-422 OUT 1 B Out5 RS-422 OUT 1 A Out6 RS-422 IN 2 B In7 RS-422 IN 2 A In8 RS-422 OUT 2 B Out9 RS-422 OUT 2 A Out10 DISCRETE IN* 1 In11 DISCRETE IN* 2 In12 DISCRETE IN* 3 In13 DISCRETE IN* 4 In14 DISCRETE IN* 5 In15 DISCRETE IN* 6 In16 DISCRETE IN* 7 In17 DISCRETE IN* 8 In18 ARINC 429 OUT 1 A Out19 ARINC 429 OUT 1 B Out20 ARINC 429 OUT 2 A Out21 ARINC 429 OUT 2 B Out22 SPARE --*Denotes Active Low (Ground to activate).123456789101112131415222324252627282930313233343536444647484950515253545556161718192021373839404142575859606162DRAFT
GDR 66 Installation Manual Page 4-3190-00303-24 Revision ATable 4-2 P662 Connector, continued23 SPARE --24 POWER GROUND --25 SPARE --26 POWER GROUND --27 SPARE --28 AIRCRAFT POWER 1 In29 SPARE --30 AIRCRAFT POWER 1 In31 SPARE --32 AIRCRAFT POWER 1 In33 SPARE --34 AIRCRAFT POWER 2 In35 SPARE --36 AIRCRAFT POWER 2 In37 SPARE --38 AIRCRAFT POWER 2 In39 SPARE --40 POWER GROUND --41 SPARE --42 POWER GROUND --43 POWER GROUND --44 SPARE --45 SIGNAL GROUND --46 SPARE --47 SIGNAL GROUND --48 SPARE --49 ARINC 429 IN 1 A In50 ARINC 429 IN 1 B In51 ARINC 429 IN 2 A In52 ARINC 429 IN 2 B In53 ARINC 429 IN 3 A In54 ARINC 429 IN 3 B In55 ARINC 429 IN 4 A In56 ARINC 429 IN 4 B In57 ARINC 429 IN 5 A In58 ARINC 429 IN 5 B In59 SPARE --60 SIGNAL GROUND --61 SIGNAL GROUND --62 RESERVED --DRAFT
Page 4-4 GDR 66 Installation ManualRevision A 190-00303-244.2 Power Functions4.2.1 Aircraft PowerThe GDR 66 provides two aircraft power bus inputs. Pins 28, 30, and 32 of P662 are internally connected to form AIRCRAFT POWER 1. Pins 34, 36, and 38 of P662 are internally connected to form AIRCRAFT POWER 2. AIRCRAFT POWER 1 and AIRCRAFT POWER 2 are “diode ORed” to provide power redundancy. Use of three AIRCRAFT POWER pins (either AIRCRAFT POWER 1 or AIRCRAFT POWER 2) and three POWER GROUND pins is recommended for all installations.4.2.2 Remote Power OffThe GDR 66 powers down when the COM REMOTE POWER OFF input is active. COM REMOTE POWER OFF is a non-configurable discrete input conforming to:Low: 0 VDC < Vin < 3.5 VDC, OR Rin > 100k ohms (inactive)High: 8 VDC < Vin < 36 VDC (active)4.2.3 GDR System ID ProgramThe GDR 66 determines it’s unit number based on the status of three GDR SYSTEM ID PROGRAM* non-configurable discrete inputs conforming to:Low: 0 VDC < Vin < 3.5 VDC, OR Rin < 375 ohms (active)High: 8 VDC < Vin < 36 VDC, OR Rin > 100k ohm (inactive)Table 4-3 Aircraft PowerPin Name Connector Pin I/OAIRCRAFT POWER 1 P662 28 InAIRCRAFT POWER 1 P662 30 InAIRCRAFT POWER 1 P662 32 InAIRCRAFT POWER 2 P662 34 InAIRCRAFT POWER 2 P662 36 InAIRCRAFT POWER 2 P662 38 InPOWER GROUND P662 1 --POWER GROUND P662 24 --POWER GROUND P662 26 --POWER GROUND P662 40 --POWER GROUND P662 42 --POWER GROUND P662 43 --Table 4-4 Remote Power OffPin Name Connector Pin I/OCOM REMOTE POWER OFF P661 16 InTable 4-5 System ID ProgramPin Name Connector Pin I/OGDR SYSTEM ID PROGRAM* 1 P661 20 InGDR SYSTEM ID PROGRAM* 2 P661 22 InGDR SYSTEM ID PROGRAM* 3 P661 24 InDRAFT
GDR 66 Installation Manual Page 4-5190-00303-24 Revision AThe unit number is determined by the table below:4.3 Serial Data4.3.1 RS-422The GDR 66 provides two RS-422 inputs and two RS-422 outputs conforming to TIA/EIA/ANSI-422-B. RS-422 is the only interface between the GDR 66 and the rest of the Garmin system.4.3.2 RS-232The GDR 66 provides one RS-232 input and one RS-232 output. The RS-232 output conforms to EIA Standard RS-232C with an output voltage swing of at least ± 5V when driving a standard RS-232 load. The RS-232 port is used for testing and as a back up tuning port.Table 4-6 Unit Number ConfigurationGDR SYSTEM ID PROGRAM* 1GDR SYSTEM ID PROGRAM* 2GDR SYSTEM ID PROGRAM* 3UNIT NUMBEROpen Open Open #1Ground Open Open #2Open Ground Open #3Ground Ground Open #4Open Open Ground #5Ground Open Ground #6Open Ground Ground #7Ground Ground Ground INVALID, DO NOT USETable 4-7 RS-422Pin Name Connector Pin I/ORS-422 IN 1 B P662 2 InRS-422 IN 1 A P662 3 InRS-422 OUT 1 B P662 4 OutRS-422 OUT 1 A P662 5 OutRS-422 IN 2 B P662 6 InRS-422 IN 2 A P662 7 InRS-422 OUT 2 B P662 8 OutRS-422 OUT 2 A P662 9 OutTable 4-8 RS-232Pin Name Connector Pin I/ORS-232 OUT 1 P661 32 OutRS-232 IN 1 P661 33 InDRAFT
Page 4-6 GDR 66 Installation ManualRevision A 190-00303-244.3.3 ARINC 429The GDR 66 provides five configurable ARINC 429 inputs and two configurable ARINC 429 outputs conforming to ARINC Specifications 429P1-17, 429P2-16 and 429P3-18. The ARINC 429 outputs conform to ARINC 429 specifications when loaded with up to five standard ARINC 429 receivers. The speed of the ARINC 429 outputs can be configured for low speed (14.29 kHz) or high speed (100 kHz). Table 4-9 ARINC 429Pin Name Connector Pin I/OARINC 429 IN 1 A P662 49 InARINC 429 IN 1 B P662 50 InARINC 429 IN 2 A P662 51 InARINC 429 IN 2 B P662 52 InARINC 429 IN 3 A P662 53 InARINC 429 IN 3 B P662 54 InARINC 429 IN 4 A P662 55 InARINC 429 IN 4 B P662 56 InARINC 429 IN 5 A P662 57 InARINC 429 IN 5 B P662 58 InARINC 429 OUT 1 A P662 18 OutARINC 429 OUT 1 B P662 19 OutARINC 429 OUT 2 A P662 20 OutARINC 429 OUT 2 B P662 21 OutDRAFT
GDR 66 Installation Manual Page 4-7190-00303-24 Revision A4.4 Discrete I/O4.4.1 Active Low Discrete InputsThe GDR 66 provides 8 configurable discrete inputs conforming to:Low: 0 VDC < Vin < 3.5 VDC, OR Rin < 375 ohms (active)High: 8 VDC < Vin < 36 VDC, OR Rin > 100k ohm (inactive)4.4.2 Key Event OutThe GDR 66 provides one output to signal when the GDR 66 is transmitting, regardless of what mode the radio is in. KEY EVENT OUT* can be used as needed to decrease the sensitivity of other COM receivers on the aircraft when the GDR 66 is transmitting. KEY EVENT OUT* is a non-configurable discrete output conforming to:Active: 0 VDC < Vout < 1.0 VDC with < 20 mA sink current; sink current must be externally limited to 20 mA max.Inactive: Open circuit, can be pulled up to an externally sourced Vout in the range 3.3 VDC < Vout < 36 VDC; leakage current is typically <10 uA to ground.Table 4-10 Discrete InputsPin Name Connector Pin I/ODISCRETE IN* 1 P662 10 InDISCRETE IN* 2 P662 11 InDISCRETE IN* 3 P662 12 InDISCRETE IN* 4 P662 13 InDISCRETE IN* 5 P662 14 InDISCRETE IN* 6 P662 15 InDISCRETE IN* 7 P662 16 InDISCRETE IN* 8 P662 17 InTable 4-11 Key Event OutPin Name Connector Pin I/OKEY EVENT OUT* P661 35 OutDRAFT
Page 4-8 GDR 66 Installation ManualRevision A 190-00303-244.5 AudioWhen the GDR 66 is in analog voice mode (ARINC 716 Voice), audio from the microphone and audio to the headset can be transferred to/from the GDR 66 as analog audio or digital audio. If analog audio is used, the COM MIC KEY* discrete input must be used. If digital audio is used all of this information is transferred in the digital audio stream.4.5.1 Analog Audio4.5.1.1 Com Mic AudioThe GDR 66 provides one microphone audio input. COM MIC AUDIO has a 150 ohm AC input impedance and supplies the microphone with a 12 V bias through 400Ω +/− 20%. COM MIC AUDIO is set in the factory for 250 mVrms to modulate the transmitter at 90% nominally. The microphone gain is adjustable during installation to increase the sensitivity to 20 mVrms or decrease the sensitivity to 2.5 Vrms.4.5.1.2 Com Audio OutThe GDR 66 provides one audio output that is intended to drive a headset or an audio panel. The rated output is 4.90 Vrms into a 600 ohm load (40 mWavg). A volume control is available during flight to reduce the output by at least 40 dB to 49 mVrms. COM 600 OHM AUDIO OUT is the summation of the COM receiver audio and COM sidetone audio.4.5.1.3 Com Mic KeyThe GDR 66 transmits the audio from the microphone (COM MIC AUDIO IN) when the COM MIC KEY* input is active. The COM MIC KEY* should be connected to the microphones PTT output. COM MIC KEY* is a non-configurable discrete input conforming to:Low: 0 VDC < Vin < 3.5 VDC, OR Rin < 375 ohms (active)High: 8 VDC < Vin < 36 VDC, OR Rin > 100k ohm (inactive)Table 4-12 Com Mic AudioPin Name Connector Pin I/OCOM MIC AUDIO IN HI P661 7 InCOM MIC AUDIO IN LO (GROUND) P661 8 --Table 4-13 Com Audio OutPin Name Connector Pin I/OCOM 600 OHM AUDIO OUT HI P661 9 OutCOM 600 OHM AUDIO OUT LO P661 10 OutTable 4-14 Com Mic KeyPin Name Connector Pin I/OCOM MIC KEY* P661 4 InDRAFT
GDR 66 Installation Manual Page 4-9190-00303-24 Revision A4.5.1.4 Com Remote TransferThe GDR 66 provides one COM REMOTE TRANSFER* input which allows the COM Emergency State to be entered or exited. When the GDR 66 enters Emergency State, it automatically switches to AM COM mode and tunes to the emergency channel, 121.500 MHz. When in Emergency State, the GDR 66 ignores inputs from the front panel controls for COM selections and cannot be used for digital data link.The COM REMOTE TRANSFER* input controls Emergency State via one of two modes: “Hold-to-Acitvate” mode and “On/Off” mode. A GDR 66 aircraft configuration parameter selects the mode as well as the activation time for Hold-to-Acitvate mode. In Hold-to-Acivate mode, the Emergency State is entered when the COM REMOTE TRANSFER* input is held active for the configured time, and is exited immediately when the COM REMOTE TRANSFER* input becomes active after having been inactive. In On/Off mode, COM REMOTE TRANSFER* acts as an on/off switch for Emergency State, which is entered immediately when COM REMOTE TRANSFER* becomes active, and is exited immediately when COM REMOTE TRANSFER* becomes inactive.Low: 0 VDC < Vin < 3.5 VDC, OR Rin < 375 ohms (active)High: 8 VDC < Vin < 36 VDC, OR Rin > 100k ohm (inactive)4.5.2 ACARS/SELCAL4.5.2.1 SELCAL Audio and ACARS Data OutThe GDR 66 provides one SELCAL audio/ACARS data output that can either be used for SELCAL or VDL Mode 0 (ARINC 716 Data). The rated output is 2.45 Vrms into a 600 ohm load (10 mWavg). The gain is adjustable during installation to decrease the output by at least 40 dB to 24.5 mVrms. A gain setting of -7.0 dB (1.2 Vrms minimum) is recommended. Refer to EQF for certification considerations for this output. Table 4-15 Com Remote TransferPin Name Connector Pin I/OCOM REMOTE TRANSFER* P661 12 InTable 4-16 SELCAL Audio and ACARS Data OutPin Name Connector Pin I/OSELCAL AUDIO AND DATA OUT HI P661 41 OutSELCAL AUDIO AND DATA OUT LO P661 42 OutDRAFT
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GDR 66 Installation Manual Page A-1190-00303-24 Revision AAPPENDIX A Outline and Installation DrawingsFigure A-1 GDR 66 Outline Drawing.8 20CG81CG3.21174.6CGP662P661COM(TNC CONNECTOR)NOTES:DIMENSIONS: INCHES[mm]1.DIMENSIONS ARE SHOWN FOR REFERENCE ONLY2.MOUNTING HOLES FOR #10 PAN HEAD OR HEX HEAD FASTENERS (4 PLACES)3.SEE NOTE 3±.005±0.25±0.13±.010 177.82X7.002X5.331.2652.3.21010.22.06±.010.4032.0±0.254X2X2X .85 21.610.14 257.66.62 168.18.17 207.5DRAFT
GDR 66 Installation Manual Page A-2190-00303-24 Revision AAPPENDIX A Outline and Installation DrawingsFigure A-2 GDR 66 Connector/Rack Assembly Drawing011-02477-00330-00776-442.GDR 66 UNIT011-02303-00GDR66 RACK011-02304-00011-01855-02011-01855-03330-00776-62NOTE 1CONNECTOR KITNOTES:GASKETS ARE PART OF 330-00776-44 AND 330-00776-62. INSTALL GASKETS OVER PINS.1.REFER TO 190-00313-11 FOR ADDITIONAL PARTS LISTS.NOTE 2DRAFT
GDR 66 Installation Manual Page A-3190-00303-24 Revision AAPPENDIX A Outline and Installation DrawingsFigure A-3 GDR 66 Minimum Installation/Removal ClearanceMINIMUM RECOMMENDED INSTALLATION AND REMOVAL CLEARANCEWITH LOCKDOWN NOT OVERHANGING MOUNTING SHELFMOUNTING SHELF1.00 25.4MINIMUM RECOMMENDED INSTALLATION AND REMOVAL CLEARANCEWITH LOCKDOWN OVERHANGING MOUNTING SHELFMOUNTING SHELF.30 7.6DRAFT
GDR 66 Installation Manual Page B-1190-00303-24 Revision AAPPENDIX B Interconnect ExamplesFigure B-1 GDR 66 Power and Antenna Interconnect Example7. GIA 63W -00 AND -01 UNITS CANNOT BE USED WITH THE GDR 66.TO MINIMIZE VHF DIGITAL TRANSMISSION INTERFERENCE (ACARS/CPDLC) WITH RECEPTION OF VHF VOICE COMMUNICATION, IT IS RECOMMEDED THAT GIA 63W -40 UNITS SHOULD BE USED IN ALL INSTALLATIONS USINGA GDR 66.2830321GDR 66 DIGITAL RADIO GDR 6610AP662AIRCRAFT POWER 1 TO 14/28 VDC AIRCRAFT POWER2426AIRCRAFT POWER 1AIRCRAFT POWER 1POWER GROUNDPOWER GROUNDPOWER GROUNDCOM ANTENNA J1SEE NOTE 7GDR SYSTEM ID PROGRAM* 1GDR SYSTEM ID PROGRAM* 2GDR SYSTEM ID PROGRAM* 3P6612422202830321GDR 66 DIGITAL RADIO GDR 6610AP662AIRCRAFT POWER 1 TO 14/28 VDC AIRCRAFT POWER2426AIRCRAFT POWER 1AIRCRAFT POWER 1POWER GROUNDPOWER GROUNDPOWER GROUNDCOM ANTENNA J1GDR SYSTEM ID PROGRAM* 1GDR SYSTEM ID PROGRAM* 2GDR SYSTEM ID PROGRAM* 3P661242220 N/CN/CN/C18 AWG18 AWG18 AWG18 AWG18 AWG18 AWG16 AWG16 AWGDRAFT
GDR 66 Installation Manual Page B-2190-00303-24 Revision AAPPENDIX B Interconnect ExamplesFigure B-2 GDR 66 VDL Mode 2 Interconnect Example5432GDR 66 DIGITAL RADIO P662RS 422 OUT 1A RS 422 OUT 1B RS 422 IN 1A RS 422 IN 1B No. 1 GSD 41DATA CONCENTRATOR1P4122625 MAIN2 RS-485/RS-422 13AMAIN2 RS-485/RS-422 13B2728MAIN2 RS-485/RS-422 14AMAIN2 RS-485/RS-422 14BNo. 2 GSD 41DATA CONCENTRATOR2P41265MAIN2 RS-485/RS-422 3AMAIN2 RS-485/RS-422 3B78MAIN2 RS-485/RS-422 4AMAIN2 RS-485/RS-422 4B9876RS 422 OUT 2A RS 422 OUT 2B RS 422 IN 2A RS 422 IN 2B No. 1 GIA 63W1P60111 TRANSMIT INTERLOCK*No. 2 GIA 63W2P60111 TRANSMIT INTERLOCK*P66135KEY EVENT OUT* SEE NOTE 6 DRAFT
GDR 66 Installation Manual Page B-3190-00303-24 Revision AAPPENDIX B Interconnect ExamplesFigure B-3 GDR 66 Analog Voice Mode Interconnect Example478GDR 66 DIGITAL RADIO P661COM MIC KEY* COM MIC AUDIO IN HI COM MIC AUDIO IN LO No. 1 GMA 36AUDIO PROCESSOR1P34713233TRANSCEIVER 2 MIC KEY* OUTTRANSCEIVER 2 MIC AUDIO OUT HI13TRANSCEIVER 2 AUDIO LONo. 1 GIA 63W1P60111TRANSMIT INTERLOCK*No. 2 GIA 63W2P60111TRANSMIT INTERLOCK*35KEY EVENT OUT* SEE NOTE 6 910COM 600 OHM AUDIO OUT HI COM 600 OHM AUDIO OUT LO 12TRANSCEIVER 2 AUDIO IN HI4142SELCAL AUDIO AND DATA OUT HI SELCAL AUDIO AND DATA OUT LO 3152RECEIVER 4 AUDIO IN HIRECEIVER 4 AUDIO IN LO DRAFT

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