Honeywell KTR2280 AVIATION SERVICES TRANSMITTER User Manual System Installation Manual

Honeywell International Inc. AVIATION SERVICES TRANSMITTER System Installation Manual

MANUAL

SYSTEM INSTALLATIONMANUAL (Preliminary)KTR 2280MULTI-MODEDIGITAL RADIO (MMDR)MANUAL NUMBER 006-10654-0000Revision 0 AUGUST, 2006
Honeywell - ConfidentialTHIS DOCUMENT AND ALL INFORMATION AND EXPRESSION CONTAINED HEREIN ARE THE PROPERTY OF HONEYWELL INTERNATIONAL INC., ARE PROVIDED IN CONFIDENCE, AND MAY BE USED BY PERSONS REQUIRED BY 14 CFR 21.50 TO COMPLY WITH ANY OF THE TERMS OF THESE INSTRUCTIONS. EXCEPT AS SET FORTH ABOVE, NO PERSON MAY, IN WHOLE OR IN PART, USE, DUPLICATE OR DISCLOSE THIS INFORMATION FOR ANY PURPOSE WITHOUT THE PRIOR WRITTEN PERMISSION OF HONEYWELL INTERNATIONAL INC.This document contains technical data and is subject to U.S. export regulations. These commodities, technology, or software were exported from the United States in accordance with the export administration regulations. Diversion contrary to U.S. law is prohibited.
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page MLA-1Honeywell Materials License AgreementThe documents and information contained herein ("the Materials") are the proprietary data of Honeywell International Inc. and Honeywell Intellectual Properties Inc. (collectively "Honeywell"). These Materials are provided for the exclusive use of Honeywell Service Centers; Honeywell-authorized repair facilities; operators of Honeywell aerospace products subject to an applicable product support agreement, their wholly owned-subsidiaries or a formally designated third party service provider thereunder; and direct recipients of Materials from Honeywell's Aerospace Technical Publication Distribution. The terms and conditions of this License Agreement govern your use of these Materials, except to the extent that any terms and conditions of another applicable agreement with Honeywell regarding the operation, maintenance, or repair of Honeywell aerospace products conflict with the terms and conditions of this License Agreement, in which case the terms and conditions of the other agreement will govern. However, this License Agreement will govern in the event of a conflict between its terms and conditions and those of a purchase order or acknowledgement.1. License Grant - If you are a party to an applicable product support agreement, a Honeywell Service Center agreement, or an authorized repair facility agreement, Honeywell hereby grants you a limited, non-exclusive license to use these Materials to operate, maintain, or repair Honeywell aerospace products only in accordance with that agreement.If you are a direct recipient of these Materials from Honeywell's Aerospace Technical Publication Distribution and are not a party to an agreement related to the operation, maintenance or repair of Honeywell aerospace products, Honeywell hereby grants you a limited, non-exclusive license to use these Materials to maintain or repair the subject Honeywell aerospace products only at the facility to which these Materials have been shipped ("the Licensed Facility"). Transfer of the Materials to another facility owned by you is permitted only if the original Licensed Facility retains no copies of the Materials and you provide prior written notice to Honeywell.2. Rights In Materials - Honeywell retains all rights in these Materials and in any copies thereof that are not expressly granted to you, including all rights in patents, copyrights, trademarks, and trade secrets. No license to use any Honeywell trademarks or patents is granted under this License Agreement.3. Confidentiality - You acknowledge that these Materials contain information that is confidential and proprietary to Honeywell. You agree to take all reasonable efforts to maintain the confidentiality of these Materials.4. Assignment And Transfer - This License Agreement may be assigned to a formally designated service designee to the extent allowed under an applicable product support agreement or transferred to a subsequent owner or operator of an aircraft containing the subject Honeywell aerospace products. However, the recipient of any such assignment or transfer must assume all of your obligations under this License Agreement. No assignment or transfer shall relieve any party of any obligation that such party then has hereunder.5. Copies of Materials - Unless you have the express written permission of Honeywell, you may not make or permit making of copies of the Materials. Notwithstanding the foregoing, you may make copies of only portions of the Material for your internal use. You agree to return the Materials and any copies thereof to Honeywell upon the request of Honeywell.
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page MLA-26. Term - This License Agreement is effective until terminated as set forth herein. This License Agreement will terminate immediately, without notice from Honeywell, if you fail to comply with any provision of this License Agreement or will terminate simultaneously with the termination or expiration of your applicable product support agreement, authorized repair facility agreement, or your formal designation as a third party service provider. Upon termination of this License Agreement, you will return these Materials to Honeywell without retaining any copies and will have one of your authorized officers certify that all Materials have been returned with no copies retained.7. Remedies - Honeywell reserves the right to pursue all available remedies and damages resulting from a breach of this License Agreement.8. Limitation of Liability - IN NO EVENT WILL HONEYWELL BE LIABLE FOR ANY INCIDENTAL DAMAGES, CONSEQUENTIAL DAMAGES, SPECIAL DAMAGES, INDIRECT DAMAGES, LOSS OF PROFITS, LOSS OF REVENUES, OR LOSS OF USE, EVEN IF INFORMED OF THE POSSIBILITY OF SUCH DAMAGES. TO THE EXTENT PERMITTED BY APPLICABLE LAW, THESE LIMITATIONS AND EXCLUSIONS WILL APPLY REGARDLESS OF WHETHER LIABILITY ARISES FROM BREACH OF CONTRACT, WARRANTY, TORT (INCLUDING BUT NOT LIMITED TO NEGLIGENCE), BY OPERATION OF LAW, OR OTHERWISE.9. Controlling Law - This License shall be governed and construed in accordance with the laws of the State of New York without regard to the conflicts of laws provisions thereof. This license sets forth the entire agreement between you and Honeywell and may only be modified by a writing duly executed by the duly authorized representatives of the parties.Copyright - NoticeCopyright 2006 Honeywell International Inc. All rights reserved.
n KTR 2280 Preliminary H 08/17/06REVISION HIGHLIGHTSRev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page RH-1KTR 2280 Preliminary H 08/17/06Part Number Rev Date Description006-10654-0000 0Aug/2006 Initial Release
n KTR 2280 Preliminary H 08/17/06REVISION HIGHLIGHTSRev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page RH-2Part Number Rev Date Description
n KTR 2280 Preliminary H 08/17/06TABLE OF CONTENTSRev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page TOC-1SECTION 1GENERAL INFORMATION1.1 INTRODUCTION ......................................................................................................... 1-11.2 EQUIPMENT DESCRIPTION...................................................................................... 1-11.3 TECHNICAL CHARACTERISTICS............................................................................. 1-21.3.1 KTR 2280 TECHNICAL CHARACTERISTICS ............................................................ 1-21.3.2 KA 44B ADF ANTENNA TECHNICAL CHARACTERISTICS...................................... 1-31.4 UNITS AND ACCESSORIES SUPPLIED ................................................................... 1-31.4.1 CONFIGURATIONS AVAILABLE................................................................................ 1-31.4.2 KTR 2280 INSTALLATION KIT ................................................................................... 1-31.5 ACCESSORIES REQUIRED, BUT NOT SUPPLIED.................................................. 1-51.6 LICENSING REQUIREMENTS ................................................................................... 1-61.7 CONTINUED AIRWORTHINESS INSTRUCTIONS.................................................... 1-61.7.1 EQUIPMENT ............................................................................................................... 1-61.7.2 WIRES/COAX CABLES............................................................................................... 1-71.8 ANTENNA RF EXPOSURE ........................................................................................ 1-7SECTION 2INSTALLATION2.1 GENERAL INFORMATION......................................................................................... 2-12.2 UNPACKING AND INSPECTING EQUIPMENT......................................................... 2-12.3 EQUIPMENT INSTALLATION .................................................................................... 2-12.3.1 AVIONICS COOLING REQUIREMENTS .................................................................... 2-12.3.2 EQUIPMENT LOCATION ............................................................................................ 2-12.3.2.1 MOUNTING TRAY LOCATION(S) .............................................................................. 2-22.3.2.2 ANTENNA(S)...............................................................................................................2-22.3.3 KTR 2280 MECHANICAL INSTALLATION ................................................................. 2-32.3.4 ANTENNA MECHANICAL INSTALLATION ................................................................ 2-32.3.4.1 VHF COM TRANSMITTER/RECEIVER ANTENNA .................................................... 2-32.3.4.2 NAVIGATION ANTENNAS .......................................................................................... 2-42.3.4.3 KA 44B ADF ANTENNA .............................................................................................. 2-52.3.5 ELECTRICAL INSTALLATION .................................................................................... 2-62.3.5.1 KTR 2280 INTERCONNECTION AND CABLE HARNESS FABRICATION................ 2-62.3.5.2 PRIMARY POWER AND CIRCUIT BREAKER REQUIREMENTS ............................. 2-72.3.5.3 CONNECTOR PIN FUNCTIONAL DESCRIPTIONS................................................... 2-82.3.5.4 CRIMP TOOL INFORMATION .................................................................................. 2-11
n KTR 2280 Preliminary H 08/17/06TABLE OF CONTENTSRev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page TOC-22.4 POST-INSTALLATION CHECKS ............................................................................. 2-292.4.1 KTR 2280 MMDR SYSTEM CHECKOUT ................................................................. 2-292.4.1.1 INSPECTION............................................................................................................. 2-292.4.1.2 POST-INSTALLATION CHECKOUT/OPERATION................................................... 2-30SECTION 3OPERATION3.1 GENERAL ................................................................................................................... 3-13.2 RADIO TUNING WINDOW.......................................................................................... 3-13.2.1 VHF COM TUNING SUB-WINDOW ............................................................................ 3-23.2.1.1 ACTIVE FREQUENCY ................................................................................................ 3-23.2.1.2 VOLUME CONTROL INDICATION/SCALE ................................................................ 3-33.2.1.3 SOFT KEY IDENTIFIER/SOFT KEY SWAP IDENTIFIER........................................... 3-33.2.1.4 SQUELCH INHIBIT ANNUNCIATOR .......................................................................... 3-33.2.1.5 TRANSMIT/RECEIVE ANNUNCIATOR ...................................................................... 3-33.2.1.6 STANDBY FREQUENCY ............................................................................................ 3-33.2.1.7 STUCK MICROPHONE ANNUNCIATION .................................................................. 3-33.2.2 COM DETAIL WINDOW .............................................................................................. 3-43.2.3 VHF NAV TUNING SUB-WINDOW ............................................................................. 3-43.2.3.1 ACTIVE FREQUENCY ................................................................................................ 3-53.2.3.2 VOLUME CONTROL INDICATION/SCALE ................................................................ 3-53.2.3.3 SOFT KEY IDENTIFIER/SOFT KEY SWAP IDENTIFIER........................................... 3-53.2.3.4 DME ASSOCIATION/HOLD ANNUNCIATOR............................................................. 3-53.2.3.5 MORSE CODE ID ANNUNCIATOR ............................................................................ 3-53.2.3.6 STANDBY FREQUENCY/VOR BEARING .................................................................. 3-53.2.4 NAV DETAIL WINDOW ............................................................................................... 3-63.2.5 DME DETAIL WINDOW .............................................................................................. 3-63.2.6 ADF TUNING SUB-WINDOW ..................................................................................... 3-73.2.6.1 ADF FREQUENCY ...................................................................................................... 3-73.2.6.2 VOLUME CONTROL INDICATION/SCALE ................................................................ 3-73.2.6.3 SOFT KEY IDENTIFIER .............................................................................................. 3-73.2.6.4 ADF MODE.................................................................................................................. 3-73.2.7 ADF DETAIL WINDOW ............................................................................................... 3-83.3 KTR 2280 OPERATION .............................................................................................. 3-83.3.1 VHF COM CONTROLS ............................................................................................. 3-103.3.1.1 DETAIL BUTTON ...................................................................................................... 3-103.3.1.2 COM BUTTON........................................................................................................... 3-10
n KTR 2280 Preliminary H 08/17/06TABLE OF CONTENTSRev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page TOC-33.3.1.3 TUNING SELECT (SEL) CONTROL ........................................................................ 3-103.3.1.4 FREQUENCY SWAP................................................................................................. 3-103.3.2 VHF NAV CONTROLS .............................................................................................. 3-113.3.2.1 DETAIL BUTTON ...................................................................................................... 3-113.3.2.2 NAV BUTTON............................................................................................................ 3-113.3.2.3 TUNING SELECT (SEL) CONTROL ........................................................................ 3-113.3.2.4 FREQUENCY SWAP................................................................................................. 3-113.3.2.5 VOL/SQ/ID KNOB...................................................................................................... 3-123.3.2.6 NAV DETAIL WINDOW SOFT KEYS........................................................................ 3-123.3.2.7 DME DETAIL WINDOW SOFT KEYS ....................................................................... 3-123.3.3 ADF CONTROLS....................................................................................................... 3-123.3.3.1 DETAIL BUTTON ...................................................................................................... 3-123.3.3.2 ADF DETAIL WINDOW SOFT KEYS ........................................................................ 3-12APPENDIX AENVIRONMENTAL QUALIFICATION FORMS
n KTR 2280 Preliminary H 08/17/06TABLE OF CONTENTSRev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page TOC-4
n KTR 2280 Preliminary H 08/17/06LIST OF FIGURESRev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page LOF-1FIGURE 2-1 MAIN CONNECTOR - J1 ............................................................................. 2-8FIGURE 2-2 KA 44/44B PIN LOCATION DIAGRAM ...................................................... 2-10FIGURE 2-3 KTR 2280 INSTALLATION DRAWING ...................................................... 2-13FIGURE 2-4 KTR 2280 BAR CLAMP ASSEMBLY DRAWING....................................... 2-21FIGURE 2-5 KA 44B OUTLINE AND MOUNTING DRAWING (-0000)........................... 2-23FIGURE 2-6 KA 44B OUTLINE AND MOUNTING DRAWING (-0010)........................... 2-25FIGURE 2-7 KA 44B ANTENNA CABLE ASSEMBLY (-0020) ....................................... 2-27FIGURE 3-1 RADIO TUNING WINDOW .......................................................................... 3-2FIGURE 3-2 VHF COM TUNING SUB-WINDOW............................................................. 3-2FIGURE 3-3 STUCK MICROPHONE ANNUNCIATION ................................................... 3-3FIGURE 3-4 VHF COM DETAIL WINDOW ...................................................................... 3-4FIGURE 3-5 VHF NAV TUNING SUB-WINDOW.............................................................. 3-4FIGURE 3-6 VHF NAV BEARING DISPLAY .................................................................... 3-5FIGURE 3-7 VHF NAV DETAIL WINDOW ....................................................................... 3-6FIGURE 3-8 DME DETAIL WINDOW ............................................................................... 3-6FIGURE 3-9 ADF TUNING SUB-WINDOW ...................................................................... 3-7FIGURE 3-10 DUAL ADF DETAIL WINDOW ..................................................................... 3-8FIGURE 3-11 KMC 2210 PFD CONTROLLER................................................................... 3-8FIGURE 3-12 KDU 1080 DISPLAY UNIT BEZEL SOFT KEYS.......................................... 3-9FIGURE 3-13 KMC 2220 MF CONTROLLER..................................................................... 3-9
n KTR 2280 Preliminary H 08/17/06LIST OF FIGURESRev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page LOF-2
n KTR 2280 Preliminary H 08/17/06LIST OF TABLESRev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page LOT-1TABLE 1-1 KXP 2290 TECHNICAL CHARACTERISTICS............................................. 1-2TABLE 2-1 J1 PIN FUNCTION LIST ............................................................................. 2-8TABLE 2-2 ANTENNA CONNECTORS AND DESCRIPTIONS ..................................... 2-9TABLE 2-3 KA 44B PIN FUNCTION LIST .................................................................... 2-10TABLE 2-4 SIZE 22 HIGH DENSITY D-SUB CONTACT TOOLS ................................ 2-11TABLE 2-5 INSPECTION/CHECK PROCEDURE........................................................ 2-29
n KTR 2280 Preliminary H 08/17/06LIST OF TABLESRev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page LOT-2
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 1-1SECTION 1GENERAL INFORMATION1.1 INTRODUCTIONThis manual contains information relative to the physical, mechanical, and electrical characteristics of the Honeywell KTR 2280 Multi-Mode Digital Radio (MMDR). Installation and check out procedures are also included. Information relative to the maintenance, alignment, and procurement of the replacement parts may be found in the KTR 2280 Maintenance/Overhaul Manual, P/N 006-15654-XXXX. The only current KTR 2280 installation option is as a part of the APEX system. For additional information relating to the APEX system, refer to the APEX System Manual 006-10667-XXXX or applicable Engineering Bulletin (EB). This manual, the Apex System Manual, and the applicable EB define the recommended installation for the KTR 2280. Final design of the installation and airworthiness approval is incumbent upon the installer and their respective certification authority.1.2 EQUIPMENT DESCRIPTIONThe KTR 2280 APEX MMDR Transceiver is a blind, panel mount integrated transceiver containing one transmitter and four receivers. The KTR 2280 operates at a nominal voltage of 27.5 VDC. The KTR 2280 is controlled by APEX LRU's which send control information to the KTR 2280 via ARINC 429. Some outputs from the KTR 2280 are in digital formats and sent to other LRU's via ARINC 429. Other outputs are more traditional analog outputs.The transmitter is a 2280 channel, 16 Watt COM transmitter capable of 8.33 kHz channel spacing operation. The four receivers include one 200 channel NAV receiver, one 40 channel glideslope receiver, one COM receiver, and one ADF receiver. The COM receivers have 2280 channels and are capable of 8.33 kHz channel spacing. The ADF tunes frequencies from 190 kHz to 1799 kHz and 2180 kHz to 2189 kHz. The KTR 2280 has no user interface and is completely controlled by other components of the APEX system via ARINC 429. The KTR 2280 contains BIT (Built In Test) equipment so that the operational health of the unit is constantly monitored. When a critical fault is detected, the unit notifies the APEX system. The unit stores detected failures in non-volatile memory for later review. The unit also has a temperature sensor and a timer so that faults can be time stamped and temperature data can be collected and stored.
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 1-21.3 TECHNICAL CHARACTERISTICS1.3.1 KTR 2280 TECHNICAL CHARACTERISTICSTABLE 1-1 KXP 2290 TECHNICAL CHARACTERISTICSSPECIFICATION CHARACTERISTICTSO COMPLIANCE COM TRANSMIT: COM RECEIVE: VOR: LOC: GS: ADF: STUCK MICROPHONE:TSO C37d, ETSO 2C37eTSO C38d, ETSO 2C38eTSO C40c, ETSO 2C40cTSO C36e, ETSO 2C36fTSO C34e, ETSO 2C34fTSO C41D, ETSO 2C41bTSO C41D, ETSO 2C41bSOFTWARE CERTIFICATION CATEGORY:RTCA/DO-178B SOFTWARE LEVEL “C”ENVIRONMENTALCATEGORIES:SEE APPENDIX APHYSICAL DIMENSIONS: SEE FIGURE 2-3 KTR 2280 INSTALLATION DRAWINGWEIGHT: SEE FIGURE 2-3 KTR 2280 INSTALLATION DRAWINGMOUNTING: BLIND, RACK MOUNT BEHIND PANELTEMPERATURE: SEE APPENDIX AALTITUDE: SEE APPENDIX ACOOLING: INTERNAL FAN & EXTERNAL RACK MOUNTED FANPOWER INPUT: 16-33 VOLTSPOWER REQUIREMENTS RECEIVE (NOMINAL): RECEIVE (MAXIMUM): TRANSMIT (NOMINAL): TRANSMIT (MAXIMUM):27.5 V @ 0.76A27.5 V @ 1.02A27.5 V @ 4.33A27.5 V @ 6.11A
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 1-31.3.2 KA 44B ADF ANTENNA TECHNICAL CHARACTERISTICS1.4 UNITS AND ACCESSORIES SUPPLIED1.4.1 CONFIGURATIONS AVAILABLEP/N 069-01037-0101 is the only version of the KTR 2280 that is currently available.1.4.2 KTR 2280 INSTALLATION KITNOTE: The following installation kit information is presented at the revision existing at the time of this publication. Future revisions to these kits may occur. Use the latest revision of the kit as provided by Honeywell.The KTR 2280 MMDR installation kit P/N 050-03721-0000 contains the following parts:PN DESCRIPTION REV-----------------------------------------------------------------------050-03721-0000 INSTALL KIT KTR 2280 B-------------------------------------------------------------------------------------------------SYMBOL PART NUMBER FIND NO DESCRIPTION UM -0000-------------------------------------------------------------------------------------------------J1 030-03296-0000 HI DENSITY SUBD44P EA 1.00J101 030-00101-0002 PANEL MOUNT PLUG EA 1.00J102 030-00101-0002 PANEL MOUNT PLUG EA 1.00J103 030-00101-0002 PANEL MOUNT PLUG EA 1.00J104 030-00101-0002 PANEL MOUNT PLUG EA 1.00J501 148-05199-0003 FAN 25X25X15MM, 4.06CFM, 55MM TEF WIRE, WITH CONN EA 1.00 001-01299-0000 INSTRUCTION FOR HARNESS ASSEMBLY PARTS RF .00J1 030-03296-0000 HI DENSITY SUBD44P EA 1.00SPECIFICATION CHARACTERISTICTSO COMPLIANCE: SEE APPENDIX AENVIRONMENTALSPECIFICATIONS:SEE APPENDIX APHYSICAL DIMENSIONS: SEE FIGURE 2-5 KA 44B OUTLINE AND MOUNTING DRAWING (-0000)/FIGURE 2-6 KA 44B OUTLINE AND MOUNTING DRAWING (-0010)WEIGHT: SEE FIGURE 2-5 KA 44B OUTLINE AND MOUNTING DRAWING (-0000)/FIGURE 2-6 KA 44B OUTLINE AND MOUNTING DRAWING (-0010)POWER REQUIREMENTS: 8.5 +/-0.5 VDC at 100mA max (supplied byKTR 2280)
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 1-4PN DESCRIPTION REV-----------------------------------------------------------------------050-03721-0000 INSTALL KIT KTR 2280 B-------------------------------------------------------------------------------------------------SYMBOL PART NUMBER FIND NO DESCRIPTION UM -0000------------------------------------------------------------------------------------------------- 030-01458-0000 CONTACT, SOCKET, SIZE 22 EA 44.00 047-11179-0002 STRAIN RELIEF CLAMP MED EA 1.00 047-11310-0004 RACK, W/FINISH EA 1.00 057-05944-0073 KTR 2280 KIT TSO LABEL EA 1.00 073-01140-0003 BACKPLATE W/HARDWARE EA 1.00 073-01141-0002 CONNECTOR HOOD SUB D 25 90 DEG W/FINISH EA 1.00 073-01142-0002 CONN HOOD COVER W/FINISH EA 1.00 076-03189-0001 SCREW 100DEG FHP 2-56 X 3/8 SPECIAL EA 5.00 088-03559-0001 FAN GUARD EA 1.00 089-05874-0014 SCR PHP 2-56X7/8 EA 4.00 089-05878-0005 SCR PHP 4-40 X 5/16 EA 1.00 089-05903-0004 SCR PHP 4-40X1/4 EA 3.00 089-06008-0004 SCR FHP 4-40X1/4 EA 2.00 089-08252-0030 WASHER EA 8.00 090-00019-0007 RING RTNR .438 EA 4.00 091-00464-0002 CABLE TIE, 5.62 INCH EA 1.00 155-03009-0001 CABLE ASSY, POWER, KTR2280 FAN EA 1.00 155-06081-0000 INSTALL DRAWING MMDR KTR 2280 RF .00 200-10452-0001 BAR CLAMP ASSEMBLY -15 EA 1.00Shield braids must be clamped to the connector backshell using bar clamp assembly P/N 200-10452-0001 which contains the following parts. See FIGURE 2-3 KTR 2280 INSTALLATION DRAWING and FIGURE 2-4 KTR 2280 BAR CLAMP ASSEMBLY DRAWING for additional information.PN DESCRIPTION REV-----------------------------------------------------------------------200-10452-0001 BAR CLAMP ASSEMBLY -15 --------------------------------------------------------------------------------------------------SYMBOL PART NUMBER FIND NO DESCRIPTION UM -0001-------------------------------------------------------------------------------------------------REF1 300-10452-0000 BAR CLAMP ASSEMBLY KMC 2220 RF .00 047-11178-0002 BACKSHELL BAR CLAMP MED EA 1.00 076-03190-0001 SCREW PHP 4-40 X 7/16 SPECIAL EA 2.00 187-01943-0002 BACKSHELL GASKET MEDIUM EA 1.00
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 1-5The KA 44B antenna installation kit P/N 050-01756-0020 contains the following parts:PN DESCRIPTION REV-----------------------------------------------------------------------050-01756-0020 INSTALL KIT 48 FT MMDR KA 44B SO-160D A-------------------------------------------------------------------------------------------------SYMBOL PART NUMBER FIND NO DESCRIPTION UM -0020------------------------------------------------------------------------------------------------- 030-00101-0000 PANEL MNT PLUG EA 1.00 057-02259-0000 ANT MTG TEMPLATE EA 1.00 057-05944-0074 KA 44B KIT TSO LABEL EA 1.00 076-01042-0001 FERRULE W/F EA 1.00 090-00019-0007 RING RTNR .438 EA 1.00 091-00031-0005 NY CA CLAMP .312 EA 1.00 200-02586-0020 ANT CBL ASSY 48FT KA 44B DO-160D EA 1.00The KA 44B antenna cable assembly P/N 200-02586-0020 contains the following parts:PN DESCRIPTION REV-----------------------------------------------------------------------200-02586-0020 ANT CBL ASSY 48FT KA 44B DO-160D E-------------------------------------------------------------------------------------------------SYMBOL PART NUMBER FIND NO DESCRIPTION UM -0020------------------------------------------------------------------------------------------------- 025-00001-0000 WIRE, HOOKUP, PTFE, 26 (7/34)AWG SPC, BLK IN 8.20 025-05120-0000 WIRE, TIN PLTD CU SHLD, 5-24 (19/36)AWG TPC COND IN 578.00 026-00029-0000 WIRE, CU, 22AWG, TINNED IN 3.00 030-01157-0011 SOCKET CRMP 20G EA 9.00 030-01171-0000 CONN SUB-D HSG 9S (FEMALE PINS) EA 1.00 030-02351-0000 HOOD/LVR ASSY ST E EA 1.00 150-00024-0010 TUBING SHRINK 10G IN 2.00 150-00049-0010 SHRINK TUBING WHT IN .75 150-00052-0010 SHRNK TUBING WHT IN 4.50 300-02586-0020 ANTENNA CABLE INTERCONNECT KA 44B DO-160D RF .00 53001150-1 50 OHM QUADRAXIAL CABLE FT 48.171.5 ACCESSORIES REQUIRED, BUT NOT SUPPLIEDA. Broadband Communications Antenna (50 ohms)B. VHF Navigation Antenna (50 ohms)C. Glideslope AntennaD. Antenna Splitter(s)E. ADF Antenna (representative type KA 44B)The KA 44B, P/N 071-1234-XX, is a low profile ADF Antenna which contains both loop and sense antennas, preamplifiers, and modulators which com-bine the antenna signals into a single RF signal which is output to the KTR 2280 via a quadaxial cable of non-critical length. The KA 44B is available in four versions. KA 44B antenna P/N 071-1234-00/03 includes a mounting plate. KA 44B P/N 071-1234-01 includes a grounding ring. KA 44B P/N 071-1234-02 has no mounting plate and has the QE adjust accessible ver-tically.
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 1-61.6 LICENSING REQUIREMENTSThe KTR 2280 meets CFR Title 47, Part 15 and Part 2 (FCC Approvals) for all radio equipment. For non-US registered aircraft, follow applicable licensing requirements as required.The Federal Communications Commission requires that the operator of the transmitter of this equipment hold a restricted radio telephone operators permit (FCC Form 605) or higher class license. A permit may be obtained by a U.S. citizen from the nearest field office of the FCC; no examination is required. An Aircraft Station License is required for this equipment. Forms (FCC Form 605, New Aircraft Station License, or FCC Form 405A, Renewal of Aircraft Station License) can be obtained from the nearest FCC Field Office. This equipment has been type accepted by the FCC and entered on their list of type accepted equipment as Honeywell KTR 2280 and must be identified as Honeywell KTR 2280 on FCC Form 605, Aircraft Radio Station License Application.CAUTION: THE VHF TRANSMITTER IN THIS EQUIPMENT IS GUARANTEED TO MEET FEDERAL COMMUNICATIONS COMMISSION ACCEPTANCE OVER THE OPERATING TEMPERATURE RANGE ONLY WHEN A HONEYWELL CRYSTAL IS USED IN THE STABILIZED MASTER OSCILLATOR. USE OF OTHER THAN HONEYWELL CRYSTALS IS CONSIDERED AN UNAUTHORIZED MODIFICATION, AND WILL VOID THE WARRANTY.1.7 CONTINUED AIRWORTHINESS INSTRUCTIONS1.7.1 EQUIPMENTThe instructions for continued airworthiness given in the TC or STC approvals for this product supplements or supersedes the instructions for continued airworthiness in this manual.Most Honeywell products are designed and manufactured to allow "on condition maintenance". On condition maintenance is described as follows; There are no periodic service requirements necessary to maintain continued airworthiness. No maintenance is required until the equipment does not properly perform its intended function. When service is required, a complete performance test should be accomplished following any repair action. Consult the appropriate unit Maintenance/Overhaul Manual for complete performance test information.14 CFR Part 25.1529 Instructions for Continued Airworthiness is met per the following instructions:A. The removal of the equipment is on the condition of failure. There is no re-quired maintenance
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 1-71.7.2 WIRES/COAX CABLESDuring on-condition or regularly scheduled maintenance, inspect the wires and coax cables following the guidelines listed in AC 43.13-1B Chapter 11, 12 as necessary.1.8 ANTENNA RF EXPOSUREWARNING: TO MINIMIZE RF EXPOSURE TO PERSONNEL, INSTALL THE ANTENNA GENERALLY AWAY FROM AREAS WHERE PEOPLE ARE LOCATED. IN SITUATIONS WHERE A PERSON WOULD BE DIRECTLY EXPOSED TO ANTENNA RADIATION, SUCH AS IN A COMPOSITE AIRCRAFT, A MINIMUM SEPARATION OF 1.97 FT (60 CM) IS GENERALLY REQUIRED BETWEEN ANY PART OF THE ANTENNA AND ANY LOCATION WHERE A PERSON MAY BE PERMANENTLY SEATED IN THE AIRCRAFT. LESSER SEPARATION IS ACCEPTABLE IN AN AIRCRAFT WHERE METAL SKIN SHIELDS THE OCCUPANTS FROM THE ANTENNA.
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 1-8This Page Intentionally Left Blank
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-1SECTION 2INSTALLATION2.1 GENERAL INFORMATIONThis section contains general suggestions and information to consider before installation of the KXP 2290. Close adherence to these suggestions will assure optimum performance from the equipment.NOTE: The conditions and test required for the TSO/ETSO and MOPS approval of this article are minimum performance standards. It is the responsibility of those installing this article either on or with a specified type or class of aircraft to determine that the aircraft installation conditions are within the TSO/ETSO and MOPS standards. These articles must have separate approval for installation in an aircraft. Any features in this equipment outside the requirements of this applicable TSO/ETSO and MOPS must be evaluated and approved as part of the installation approval. The article may be installed only if further evaluation by the applicant confirms that the installation is acceptable and is approved by the Administrator.2.2 UNPACKING AND INSPECTING EQUIPMENTExercise extreme care when unpacking the equipment. Make a visual inspection of the unit for evidence of damage during shipment. If a claim for damage is to be made, save the shipping container to substantiate the claim. The claim should be promptly filed with the transportation company. It would be advisable to retain the container and packing material after all equipment has been removed, in the event that equipment storage or reshipment should become necessary.2.3 EQUIPMENT INSTALLATION2.3.1 AVIONICS COOLING REQUIREMENTSThe unit is cooled by a fan internal to the unit and one attached to the rear rack assembly plate, the latter being a part of the installation (see FIGURE 2-3 KTR 2280 INSTALLATION DRAWING). During installation, do not block any holes in the unit cover(s) which would restrict air flow.2.3.2 EQUIPMENT LOCATIONThe following paragraphs contain information pertaining to the initial installation of the KTR 2280 MMDR, including instructions concerning the location and mounting of the supporting antenna(s).
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-2The equipment should be installed in the aircraft in a manner consistent with acceptable workmanship and engineering practices and in accordance with the instructions set forth in this publication. To ensure that the system has been properly and safely installed in the aircraft, the installer should make a through visual inspection and conduct an overall operational check of the system on the ground prior to flight.The installation should be in accordance with standards established by the customer’s installing agency and existing conditions as to unit location and type of installation; however, the following should be considered before installing the system in order to assure a more satisfactory performance from the equipment.NOTE: The TSO identifies the minimum performance standards, tests, and other conditions applicable for issuance of design and production approval of the article. The TSO applicant is responsible for documenting all limitations and conditions suitable for installation of the article. An applicant requesting approval for installation of the article within a specific type or class of product is responsible for determining environmental and functional compatibility.Care should be exercised to avoid mounting components near equipment operating with high pulse current or high power outputs such as radar and satellite communications equipment. In general, the equipment should be installed in a location convenient for operation, inspection, and maintenance, and in an area consistent with the TSO environmental limits. Determine the mounting location for system components following the guidelines below.2.3.2.1 MOUNTING TRAY LOCATION(S)The KTR 2280 MMDR mounting tray is blind-mounted behind the APEX cockpit panel configuration.2.3.2.2 ANTENNA(S)The antenna(s) should be well removed from other antenna projections, the engine(s), and propeller(s). It should also be well removed from landing gear doors, access doors, or other openings which will break the ground plane for the antenna(s). On metal skinned aircraft, the antenna(s) should be bonded to the surface of the aircraft in a fore to aft location that provides the flattest ground plane. On composite aircraft, the antenna(s) should be a located at the center of a conductive ground plane, contoured to the shape of the aircraft, having dimensions of at least 2 feet by 2 feet. The antenna penetration should be designed such that the structural integrity of the fuselage is not compromised.The antenna(s) need to be within 5 degrees of the centerlineWhere practical, plan the antenna location(s) to keep cable lengths as short as possible and avoid sharp bends in the cable to minimize the VSWR.
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-3Avoid running other cables or wires near the antenna cable(s).On pressurized aircraft, the antenna(s) should be sealed using an approved sealant, such as RTV No. 3145 (P/N 016-01082-0000) or equivalent, around the connector and mounting hardware.The antenna mounting(s) should be sealed from the outside for moisture protection using RTV or equivalent.Mount the antenna(s) in as clean as environment as possible, away from exhaust gases and oils. The antenna(s) should be kept clean. If left dirty (oil covered), the antenna performance may be affected.2.3.3 KTR 2280 MECHANICAL INSTALLATIONThe mounting tray for the MMDR should be mounted using the dimensions specified in the outline and mounting drawing, FIGURE 2-3 KTR 2280 INSTALLATION DRAWING. Install the unit per the following:(1) Slide the MMDR into the tray until the locking rod engages the nut on the back of the rack.(2) Using an Allen wrench, turn the locking rod clockwise until it has drawn the unit into the rack and mating connectors and is tight.CAUTION: DO NOT OVERTIGHTEN THE LOCKING RODTo remove the unit, turn the securing rod counter clockwise until it disengages from the mounting tray. Then, pull the unit out of the mounting rackFor additional KXP 2290 installation information, refer to FIGURE 2-3 KTR 2280 INSTALLATION DRAWING as required2.3.4 ANTENNA MECHANICAL INSTALLATION2.3.4.1 VHF COM TRANSMITTER/RECEIVER ANTENNAThe VHF COM antenna should be mounted as far away as possible (8 feet, minimum) from other similar antennas and the vertical stabilizer. Mounting the COM antenna as far away as possible from the navigation antenna will help reduce COM to NAV interference. The COM antenna should also be mounted as far away as possible from an ELT antenna to prevent distortion of the radiated pattern and to prevent radiated broadband noise from the ELT when excited by the COM transmissions. Radiated broadband noise from an ELT is a common cause of COM-to-COM and COM-to-NAV interference. Mounting one antenna on top of the fuselage at the highest location to ensure a good radiation pattern and the other on the bottom of the fuselage offers good separation with a minimum of interaction.
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-4It is recommended that a COM be connected to the top antenna for good ground communication and that the other COM be connected to the bottom antenna to provide good airborne communications. If mounting antennas on the same side of the aircraft is unavoidable, maintain the minimum allowable separation (8 feet).The antenna should be mounted on a section of the aircraft that is horizontal during cruise flight. The base of the antenna should be well bonded to the metal aircraft skin. Remove any paint from around the mounting holes to ensure a good connection between the antenna and the skin. The metal aircraft skin at the base of the antenna should extend a minimum of twenty-four inches in every direction. This provides the ground plane required for the antenna. Any less metallized area will result in reduced communication range at some bearings around the aircraft and may increase interference to and from other systems.The COM transceiver performance depends heavily on the integrity of the electrical bonding to the airframe and also the electrical integrity of the aircraft structure. If the electrical resistance between an antenna and the aircraft or between adjacent skin panels change intermittently, noisy communications may result.Connect the antenna to the COM unit with 50 ohm coaxial cable, keeping the cable length to a minimum and avoiding sharp bends in the cable. Keep the COM antenna cable as far away from other antenna cables as possible and do not bundle several cables together.Use Dow-Corning DC-4, or equivalent, on both inside and outside of the connector and its mate as an effective barrier against moisture and to prevent corrosion.2.3.4.2 NAVIGATION ANTENNASThe NAV antenna should be well removed from other antennas, projections, engines or propellers. It should have a clear line of sight area if possible. The antenna must be mounted symmetrically with the center line of the aircraft. Avoid running other coaxial cables and wires near the NAV antenna cable.The VOR/LOC antenna with Glideslope is a two piece dipole with one part mounted on each side of the vertical stabilizer. It should be installed on the upper section of the vertical stabilizer of single finned aircraft and be at least 28 inches (measured vertically) from the horizontal stabilizer.On dual VOR/ILS installations, it is recommended that a splitter be used to divide signals from a single VOR/LOC antenna into two or more receivers. Use double shielded cables to reduce interference to the receivers.
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-52.3.4.3 KA 44B ADF ANTENNAThe antenna installation will determine, to a large extent, whether the ADF will give optimum performance (refer to FIGURE 2-5 KA 44B OUTLINE AND MOUNTING DRAWING (-0000) / FIGURE 2-6 KA 44B OUTLINE AND MOUNTING DRAWING (-0010) as required. The KA 44B antenna contains both the loop and sense antennas. The following considerations should be taken into account before selecting a location for the antenna:CAUTION: KEEP THE ANTENNA AT LEAST 4 FEET AWAY FROM DME OR TRANSPONDER ANTENNAS TO MINIMIZE L-BAND INTERFERENCE. THE ANTENNA SHOULD BE MOUNTED WELL CLEAR OF THE AIRCRAFT GENERATOR/ALTERNATOR AND WELL CLEAR OF ANY GENERATOR/ALTERNATOR CABLES.CAUTION: DO NOT ROUTE THE CABLES ALONG WITH HIGH LEVEL TRANSMITTING CABLES. DO NOT ROUTE THE CABLES WITH OR NEAR ALTERNATOR OR 400HZ CABLES. MAKE SURE THAT THE CABLES DO NOT INTERFERE WITH ANY OF THE AIRCRAFT CONTROL CABLES.• Mount the antenna on the center line of the aircraft fuselage. Failure to do so may result in excessive Q.E. error.• If the antenna is to be top mounted, select a location where shadowing from the wings, etc., is minimized.• The antenna should be well removed from any projections such as engines and propellers, as well as landing gear doors, access doors or other openings which will break the ground plane for the antenna.• Use the template included in the installation kit to mark the mounting holes on the aircraft fuselage.• Drill and/or punch the required holes.• Use a piece of fine sandpaper or emery cloth to sand the area on the fuselage skin on which the doubler plate is to be mounted.• Apply Alumiprep No. 33, P/N 016-01127-0000, to both the inside area of the fuselage and the back of the doubler plate, following the directions on the container to cleanse the metal of any residue.• Apply Alodine No. 1001, P/N 016-00128-0000, to both locations following the directions on the container. This is used to ensure good bonding and prevent oxidation.• Refer to the installation manual and mount the antenna as shown. First rivet the doubler plate in place. It is imperative that the doubler plate make a good ground plane contact with the inside of the aircraft skin.
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-62.3.5 ELECTRICAL INSTALLATION2.3.5.1 KTR 2280 INTERCONNECTION AND CABLE HARNESS FABRICATIONNOTE: The only current KTR 2280 installation option is as a part of the APEX system. For detailed interconnection information relating to a specific installation, refer to the applicable APEX system installation manual and/or engineering bulletin (EB).The KTR 2280 MMDR receives primary power from the aircraft power source. Power connections, voltage requirements, and circuit breaker requirements may be found in the APEX system installation manual and/or engineering bulletin (EB) for a specific installation.The length of the wires to parallel pins should be approximately the same length, so that the best distribution of current can be effected. Honeywell recommends that all wires, including spares, as provided with the interconnect definition information be included in the fabrication of the wiring harness. However; if full wiring is not desired, the installer should ensure that the minimum wiring requirements for the features and functions to be used have been incorporated.When cables are installed in the aircraft, they must be supported firmly enough to prevent movement and should be carefully protected against chaffing. Additional protection should also be provided in all locations where the cable may be subjected to abuse.In wire bundles, the cabling should not be tied tightly together as this tends to increase the possibility of noise pickup and similar interference. When routing cables through the aircraft the cables should cross high level rf lines at right angles.Prior to installing any equipment, make a continuity check of all wires and cables associated with the system. Then apply power and check for proper voltages at system connectors, and then remove power before completing the installation.The following guidelines are recommended:(1) The installing facility will supply and fabricate all external cables. The re-quired connectors are supplied as part of the installation kit (P/N 050-03451-0000).(2) The unit must be kept a minimum of three feet from the antenna. Addition-ally, the antenna coax cable should not be bundled with the other wiring har-nesses to the unit.(3) The length and routing of the external cables must be carefully planned be-fore attempting the actual installation. Avoid sharp bends or locating the ca-ble near aircraft control cables. The cables should be of a length to allow for a “maintenance loop”. That is, the length should be adequate to access and extend the connectors aft of the panel for future maintenance purposes. Excess cabling should be secured and stowed by tie-wrapping until such maintenance is required.
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-7(4) The cables should be supported firmly enough to prevent movement. They should be carefully protected wherever one may chafe against another or against some other object. Extra protection should be provided in all loca-tions where the cables may be subject to abuse. Shields on shielded wires should be grounded in accordance with the system interconnection informa-tion.(5) Shields should be carried through any obstruction via a thru-bulkhead con-nector. If shielding cannot be carried through by use of a bulkhead/connec-tor pin, precautions should be taken to ensure each segment of the shielded lead be grounded at only one point. A ground connection of not more than two inches in length should be used. The preceding discussion does not ap-ply to coaxial and quadraxial cable.(6) Avoid routing cabling near high noise and high power sources.2.3.5.2 PRIMARY POWER AND CIRCUIT BREAKER REQUIREMENTSThe KTR 2280 MMDR receives primary power from the aircraft power circuit breakers. Power connections, wire sizes, and circuit breaker requirements may be found in the APEX system installation manual and/or engineering bulletin (EB) for a specific installation.
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-82.3.5.3 CONNECTOR PIN FUNCTIONAL DESCRIPTIONSFIGURE 2-1 MAIN CONNECTOR - J1 Front ViewPin # I/O Description1 O A429 Out1 A2 O ADF Loop Enable OUT3 I TEST4 I Unit Pos PGM 15 I Unit Pos PGM 26 I COM TX Interlock* IN7 I COM MIC Key* IN8 O RS-422 RX A9 O RS-422 RX B10 I RS-422 TX A11 I RS-422 TX B12 I COM MIC GND13 N.A. Spare14 O ADF Audio LO OUT15 O ADF Audio HI OUT16 O A429 Out1 B17 O ADF MOD/0 OUT18 O A429 Out2 A19 I Unit Pos Parity20 I A429 IN1 A21 N.A. Spare22 I A429 IN2 ATABLE 2-1 J1 PIN FUNCTION LIST
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-923 I ADF ANT PWR Return24 I DC Return 125 I DC Power 2 IN26 I Emergency Channel27 I COM MIC Audio IN28 N.A. Spare29 O NAV Audio LO OUT30 O NAV Audio HI OUT31 O ADF 32 HZ/90 OUT32 O A429 Out2 B33 O MMDS FAN 5V OUT34 I A429 IN1 B35 N.A. Spare36 I A429 IN2 B37 I Pgm Pin Common38 O ADF ANT PWR OUT39 I DC Power 1 IN40 I DC Return 241 I Download42 I ON*43 O COM Audio/Sidetone LO OUT44 O COM Audio/Sidetone LO OUTConnector Pin I/O DescriptionJ101 1 I/O COM RF J102 1 I ADF RF IN J103 1 I NAV RF IN J104 1 I Glideslope RF IN TABLE 2-2 ANTENNA CONNECTORS AND DESCRIPTIONSPin # I/O DescriptionTABLE 2-1 J1 PIN FUNCTION LIST
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-10FIGURE 2-2 KA 44/44B PIN LOCATION DIAGRAMTABLE 2-3 KA 44B PIN FUNCTION LISTPIN I/O SIGNAL NAME1 I ANTENNA POWER2 I LOOP ENABLE3 O RF INPUT4 I 32Hz +/-90 DEG.5 I 32Hz 0 DEG.6 NO CONNECTION7 GROUND8 CENTER SHIELD GND9 OUTER SHIELD GND
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-112.3.5.4 CRIMP TOOL INFORMATIONThe following is a listing of crimp tools and accessories for use with the KTR 2280.* All source tools and positioners are to Mil-Spec Standard and are interchangeable.** Positioner wire gauge (AWG) refers to barrel only.*** SUPERCEDES MIL SPEC P/N M24308/18-1. ORDER FROM POSITRONICS, DANIELS, OR ASTRO BY MIL SPEC P/N.NOTE: Selections in parentheses denote optional ordering number from source.Vendor Ordering Information:Astro Tool Company21615 SW TV Hwy, Beaverton, OR 97006(503) 642-9853 * Fax: 503-591-7766 * Email: sales@astrotool.comDaniels Manufacturing Company (DMC)526 Thorpe Road, Orlando, FL 32824-8133 USATel: 407-855-6161 * Fax: 407-855-6884 * Email: dmc@dmctools.comPositronics Industries, Inc.423 N. Campbell Ave P.O. Box 8247, Springfield, MO 65801Tel: 800-641-4054 * Fax: 417-866-4115 * Email: info@connectpositronics.comTABLE 2-4 SIZE 22 HIGH DENSITY D-SUB CONTACT TOOLSSOURCE * CRIMP TOOL POSITIONER 22-30 AWG ** INSERTION/EXTRACTION TOOLHONEYWELL 005-02012-0034 Not Available Not AvailableMIL-SPEC M22520/2-01 M22520/2-06 M81969/1-04 ***DANIELS MFG. AFM8 (M22520/2-01) K41 (M22520/2-06)POSITRONICS 9507-0-0 9502-3 (K41)ASTRO (BUCHANAN) 615717 (M22520/2-01) 615722 (M22520/2-06)
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n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-13FIGURE 2-3 KTR 2280 INSTALLATION DRAWING (Dwg. 155-06081-0000 Rev. B, Sheet 1 of 4)
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n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-15FIGURE 2-3 KTR 2280 INSTALLATION DRAWING (Dwg. 155-06081-0000 Rev. B, Sheet 2 of 4)
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n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-17FIGURE 2-3 KTR 2280 INSTALLATION DRAWING (Dwg. 155-06081-0000 Rev. B, Sheet 3 of 4)
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n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-19FIGURE 2-3 KTR 2280 INSTALLATION DRAWING (Dwg. 155-06081-0000 Rev. B, Sheet 4 of 4)
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-20This Page Intentionally Left Blank
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-21FIGURE 2-4 KTR 2280 BAR CLAMP ASSEMBLY DRAWING (300-10452-0000, Rev. -)
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-22This Page Intentionally Left Blank
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-23FIGURE 2-5 KA 44B OUTLINE AND MOUNTING DRAWING (-0000) (Dwg No 155-05334-0000 R-9)
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-24This Page Intentionally Left Blank
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-25FIGURE 2-6 KA 44B OUTLINE AND MOUNTING DRAWING (-0010) (Dwg No 155-05334-0010 R-AA)
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n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-27FIGURE 2-7 KA 44B ANTENNA CABLE ASSEMBLY (-0020) (Dwg No 300-02586-0020 R-E)
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n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-292.4 POST-INSTALLATION CHECKS2.4.1 KTR 2280 MMDR SYSTEM CHECKOUT The post-installation test is used to apply power and functionally checkout the system. Successful completion of the post-installation test verifies the proper operation of the KTR 2280 MMDR.TABLE 2-5 INSPECTION/CHECK PROCEDURE is a visual inspection/check procedure that should be performed after system installation as part of a system checkout. A post-installation test per paragraph 2.4.1.2 POST-INSTALLATION CHECKOUT/OPERATION should be performed. In addition, the procedure should be used as a periodic maintenance inspection check.TABLE 2-5 INSPECTION/CHECK PROCEDURE2.4.1.1 INSPECTIONPerform the following inspection on the overall system:(1) Check that cables do not interfere with aircraft controls or other equipment.(2) Check cabling for proper routing and check security of tie-down points. In-spect and adjust cable runs to ensure that cables are not strained, kinked, or severely twisted and are not exposed to rough or sharp surfaces.EQUIPMENT INSPECTION/CHECK PROCEDUREKTR 2280 A. Inspect external surface for damage.MMDR B. Check that the unit is securely installed and that retaining mechanism is securely tightened. C. Ensure that all connections in the mounting tray are properly mounted and secure.Antennas A. Inspect external surfaces for damage. B. Check that antenna is properly mounted and mounting screws are tight. C. Ensure that antenna coaxial cable connectors are properly mated and secure.
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-302.4.1.2 POST-INSTALLATION CHECKOUT/OPERATION(1) GeneralInstallation of the MMDR system requires three stages of testing to ensure the proper operation of the MMDR. Initially, prior to the installation of the MMDR and antenna, a system interwiring check should be performed. This check verifies that the aircraft and all MMDR interconnections are correct before power is applied. After the units are installed a visual inspection of the equipment and connections is made. Finally, a ramp test is performed.(2) System Interwiring CheckTo check the aircraft and MMDR system interconnections proceed as fol-lows:(a) Check that all cables and interwiring are installed in accordance with the Interwiring and Cable Harness Fabrication instructions (para-graph 2.3.5.1 KTR 2280 INTERCONNECTION AND CABLE HAR-NESS FABRICATION).(b) Using the applicable interconnection information, check wiring for proper destination, opens, and shorts.(c) Check rf cables for insertion loss and VSWR.(3) Visual InspectionIn conjunction with system installation, perform the inspection/check proce-dure (TABLE 2-5 INSPECTION/CHECK PROCEDURE).(4) Post-Installation Test (Nav/Com Functionality)Perform a ground check of the installation prior to the flight test. Using a lo-cal frequency, confirm that the COM function can receive and transmit a modulated signal. Using a ramp tester, confirm that VOR, LOC, and GS needle deflections move in the correct direction, the To/From flag is the proper sense, and that the warning flags are functioning properly. An oper-ation performance flight test is recommended after the installation is com-pleted to insure satisfactory performance of the equipment in its normal en-vironment. Check all aircraft control movements to be sure no electrical ca-bles interfere with their operation.To check the communications transceiver, maintain an altitude of at least 1500 feet and contact a ground station facility at a range of at least fifty nau-tical miles. Contact a ground station close in. Pull the volume control knob out to defeat the automatic squelch feature and listen for any unusual elec-trical noise which would reduce the COM receiver sensitivity by increasing the squelch threshold. If possible, verify the communications capability on both the high and low end of the VHF COM band.
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-31CAUTION: AS AN ADDED PRECAUTION BEFORE THE FLIGHT, CHECK THE ANTENNA. VSWR SHOULD BE CHECKED WITH AN IN-LINE TYPE WATTMETER INSERTED IN THE COAXIAL TRANSMISSION LINE BETWEEN THE TRANSCEIVER AND THE ANTENNA. ANY PROBLEM WITH THE ANTENNA INSTALLATION WILL MOST LIKELY BE SEEN AS A HIGH REFLECTED POWER. A VSWR OF 3:1 WILL RESULT IN A 25% LOSS IN POWER.To check the VOR/ILS system, select a VOR frequency within a forty nauti-cal mile range. Listen to the VOR audio and insure that no electrical inter-ference such as magneto noise is present. Check the tone identifier filter op-eration. Fly inbound or outbound on a selected VOR radial and check for proper LEFT-RIGHT and TO-FROM indications. Check the VOR accuracy.NOTE: VOR Ground Station scalloping may be presentTo check the localizer and glideslope functions, select an appropriate ILS frequency and fly an approach to the proper runway. Check for proper LEFT-RIGHT and UP-DOWN indications. The glideslope function will not operate for units that do not have the glideslope receiver. Check section 1 for unit part numbers that have glideslope receivers.(5) Post-Installation Test (ADF Functionality)A quick preliminary check can be made by tuning to a local AM broadcast station or a strong NDB station. Check for satisfactory audio (this should be done where clear reception is possible, preferably outside of the hanger).(a) Quadrantal Error AdjustmentsThe system has been factory adjusted to compensate for a typical airframe. Therefore, little or no compensation should be required. Nonetheless, the KTR 2280 provides software adjustment of Qua-drantal Error (the average amount of quadrantal error (QE) that ex-ists due to the shape of the airframe). The values for these align-ments are stored within the aircraft system maintenance computer and downloaded to the KTR 2280 on power up. If this download does not occur the KTR 2280 uses the last values that were loaded. In event that antenna skew and QE adjustment is required, follow the procedure outlined below.1. Set the QE adjustment to 0.2. Tune in a nearby broadcast station, NDB, or compass locator that gives a strong, clear signal free of fading. Position the air-craft on the ramp in an area that is clear of surrounding build-ings, such that the indicator points to 0 degrees (i.e., the air-craft is heading directly toward the station). Note the aircraft heading.3. Using the aircraft directional gyro or compass, turn the aircraft to the left 45 degrees. Note the indicated relative bearing and the amount of error. Continue to turn the aircraft, stopping ar each 45 degree point and noting the relative bearing error.
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 2-32The errors at the 90 degree, 180 degree, and 270 degree points should be within +/- 5 degrees.4. Using the following formulas calculate the Quadrantal Error:Bearing_45 = Bearing from KTR 2280 when aircraft is turned 45 degrees left of the beacon.Bearing_135 = Bearing from KTR 2280 when aircraft is turned 135 degrees left of the beacon.Bearing_225 = Bearing from KTR 2280 when aircraft is turned 225 degrees left of the beacon.Bearing_315 = Bearing from KTR 2280 when aircraft is turned 315 degrees left of the beacon.QE_45 = Bearing_45 - 45QE_135 = Bearing_135 - 135QE_225 = Bearing_225 - 225QE_3155 = Bearing_3155 - 315QE = Average of QE_45, QE_135, QE_225, and QE_315.(b) Operational ChecksThe following operational checks are to verify proper opera-tion of the ADF function of the KTR 2280 and can be made with the aircraft in the parking area.1. Place the ADF in the ANT mode and tune in several known stations. Verify that audio reception is satisfactory and that volume control operation is normal. Verify that the ADF indica-tor needle is parked at the 90 degree position relative to the noise of the aircraft. Place the unit in the ADF mode and verify that the needle points to the station.2. Select the BFO function to enter the BFO mode and verify that the BFO tone is present in the receiver audio (if a keyed CW station is used the tone heard will be the coded identifier).
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 3-1SECTION 3OPERATION3.1 GENERALThe radio tuning philosophy used on the display is based on an association between the tuning controls (knobs and buttons) and a graphical cursor that appears in the PFD tuning window.Normally, the cursor is a cyan box that surrounds the frequency, code, or mode being controlled. The pilot positions the cursor by pressing the display bezel soft key located adjacent to the desired data field or by pressing a window focus shortcut control key on the MF Controller (MFC). For example, if the soft key adjacent to the NAV 1 tuning field on the pilot's PFD is pressed the cyan box cursor will move to the NAV 1 standby frequency field on that display. When the MF Controller is used the 'window focus' will be on the radio window indicating control is possible through the MF Controller and the joystick is used to move the cursor to the desired field.The text is shown in the larger font size to enhance visibility while tuning. One second after the controller activity stops, the cursor reverts to the smaller font, but remains on the standby frequency field. Twenty seconds after the controller activity stops, the cursor defaults to the onside VHF COM standby frequency field as a cyan box.3.2 RADIO TUNING WINDOWThe Radio Tuning window is in the lower right hand corner of the pilot's PFD and the lower left hand corner of the copilot's PFD. The cyan box surrounding the Radio Tuning window shows that the display focus is on the radio tuning, and the MF Controller can be used to control some of the radio functions. The cyan outline on the soft key identifier indicates the radio that any inputs will affect. The Very High Frequency (VHF) Communication (COM) tuning sub-window(s) are the first line(s) of the displayed radios, then the VHF Navigation (NAV) sub-window(s) and the Automatic Direction Finder (ADF) sub-window(s).
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 3-2FIGURE 3-1 RADIO TUNING WINDOW3.2.1 VHF COM TUNING SUB-WINDOWThe Pilot and Copilot VHF COM functions and display locations are as shown in the following examples of the VHF COM tuning sub-window.FIGURE 3-2 VHF COM TUNING SUB-WINDOW3.2.1.1 ACTIVE FREQUENCYThe active COM frequency is displayed on the left side of the VHF COM tuning sub-window.
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 3-33.2.1.2 VOLUME CONTROL INDICATION/SCALEThe volume control scale and the indication of the current volume level are located at the top of the VHF COM tuning sub-window, above and between the active and standby frequencies. The volume scale is visible only when the volume knob is being rotated, and is automatically removed from the display one second after volume knob rotation ceases.3.2.1.3 SOFT KEY IDENTIFIER/SOFT KEY SWAP IDENTIFIERThis shows the function of the soft key on the PFD bezel next to the identifier. The choices are COM, COM1, or COM2. The swap identifier indicates that pressing the soft key will swap the active and standby frequencies, and is only visible when the cursor is in the COM tuning sub-window and the radio is in active/standby tuning mode.3.2.1.4 SQUELCH INHIBIT ANNUNCIATORIndicates that the Squelch Inhibit Mode is active.3.2.1.5 TRANSMIT/RECEIVE ANNUNCIATORThis annunciator indicates when the radio is transmitting (T) or receiving (R).3.2.1.6 STANDBY FREQUENCYThe Standby COM frequency is displayed to the right of the active frequency in the VHF COM tuning sub-window.3.2.1.7 STUCK MICROPHONE ANNUNCIATIONThe STUCK MIC annunciator will be shown in amber in the VHF COM sub-window between the squelch inhibit annunciation and the receive/transmit annunciator when the VHF COM detects a stuck microphone.FIGURE 3-3 STUCK MICROPHONE ANNUNCIATION
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 3-43.2.2 COM DETAIL WINDOWThe COM Detail window will be displayed when the cursor focus is on the COM tuning sub-window and the DETAIL button is pressed on either the PFD or MF Controller.FIGURE 3-4 VHF COM DETAIL WINDOWThe COM frequency spacing selections are shown in the detail window. The active modes are shown with a large font in white, and the inactive modes are shown with a smaller font in cyan.3.2.3 VHF NAV TUNING SUB-WINDOWThe Pilot and Copilot VHF NAV functions and display locations are as shown in the following examples of the VHF NAV tuning sub-window.FIGURE 3-5 VHF NAV TUNING SUB-WINDOW
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 3-53.2.3.1 ACTIVE FREQUENCYThe active NAV frequency is displayed in white on the left side of the VHF NAV tuning sub-window.3.2.3.2 VOLUME CONTROL INDICATION/SCALEThe volume control scale and the indication of the current volume level are located at the top of the VHF NAV tuning sub-window, above and between the active and standby frequencies. The volume scale is visible only when the volume knob is being rotated, and is automatically removed from the display one second after volume knob rotation ceases.3.2.3.3 SOFT KEY IDENTIFIER/SOFT KEY SWAP IDENTIFIERThis shows the function of the soft key on the PFD bezel next to the identifier. The choices are NAV, NAV1, or NAV2. The swap identifier indicates that pressing the soft key will swap the active and standby frequencies, and is only visible when the cursor is in the NAV tuning sub-window and the radio is in active/standby tuning mode.3.2.3.4 DME ASSOCIATION/HOLD ANNUNCIATORThe DME association annunciator indicates which DME is associated with the NAV radio. The choices are DME (single DME installation), DME1 or DME2 (for dual DME installations). The Hold annunciator indicates the associated DME is in Hold mode.3.2.3.5 MORSE CODE ID ANNUNCIATORThe Morse code ID annunciator indicates that the Morse code filter has been activated, allowing the crew to hear the Morse code through the audio system.3.2.3.6 STANDBY FREQUENCY/VOR BEARINGEither the standby NAV frequency or the VOR bearing is displayed in cyan to the right of the active frequency in the VHF NAV tuning sub-window. Choice of standby frequency or bearing is made on the VHF NAV detail window. The bearing display will be shown as either BRG XXX° or RAD XXX°, depending on the operator's selection.FIGURE 3-6 VHF NAV BEARING DISPLAY
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 3-63.2.4 NAV DETAIL WINDOWThe NAV detail window will be displayed when the cursor focus is on the NAV tuning sub-window and the DETAIL button is pressed on either the PFD or MF Controller.FIGURE 3-7 VHF NAV DETAIL WINDOWThe NAV mode selections (BRG, RAD and STBY) and access to the DME detail window are shown in the NAV detail window. The active modes are shown with a large font in white, and the inactive modes are shown with a smaller font in cyan.3.2.5 DME DETAIL WINDOWThe DME detail window will be displayed when the cursor focus is on the NAV tuning sub-window and the DETAIL button is pressed on either the PFD or MF Controller, when the DME button is pressed on the PFD Controller or by selecting the "Go To DME Detail" soft key on the NAV detail window.FIGURE 3-8 DME DETAIL WINDOW
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 3-7The DME association selection (NAV1, NAV2) and DME Hold mode control are shown in the DME detail window. The active modes are shown with a large font in white, and the inactive modes are shown with a smaller font in cyan.3.2.6 ADF TUNING SUB-WINDOWThe Pilot and Copilot ADF functions and display locations are as shown in the following examples of the ADF tuning sub-window.FIGURE 3-9 ADF TUNING SUB-WINDOW3.2.6.1 ADF FREQUENCYThe ADF frequency is displayed in white on the left side of the ADF tuning sub-window.3.2.6.2 VOLUME CONTROL INDICATION/SCALEThe volume control scale and the indication of the current volume level are located at the top of the ADF tuning sub-window in the middle. The volume scale is visible only when the volume knob is being rotated, and is automatically removed from the display one second after volume knob rotation ceases.3.2.6.3 SOFT KEY IDENTIFIERThis shows the function of the soft key on the PFD bezel next to the identifier. The choices are ADF, ADF1, or ADF2.3.2.6.4 ADF MODEThis shows the function of the soft key on the PFD bezel next to the identifier. The choices are ADF, ANT, or BFO.
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 3-83.2.7 ADF DETAIL WINDOWThe ADF detail window will be displayed when the cursor focus is on the ADF tuning sub-window and the DETAIL button is pressed on either the PFD or MF Controller.FIGURE 3-10 DUAL ADF DETAIL WINDOWThe ADF mode selection(s) (ADF, ANT or BFO) are shown in the ADF detail window. The active modes are shown with a large font in white, and the inactive modes are shown with a smaller font in cyan.3.3 KTR 2280 OPERATIONThe VHF COM, VHF NAV, and ADF can be operated using the Display Bezel Soft Keys, the PFD Controller, or the MF Controller.FIGURE 3-11 KMC 2210 PFD CONTROLLER
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 3-9FIGURE 3-12 KDU 1080 DISPLAY UNIT BEZEL SOFT KEYSFIGURE 3-13 KMC 2220 MF CONTROLLER
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 3-103.3.1 VHF COM CONTROLS3.3.1.1 DETAIL BUTTONThe DETAIL button on either the PFD or MF Controller activates a secondary window related to the currently active window providing additional details or controls related to the item. A subsequent selection of the DETAIL button removes the secondary window and displays the primary window for the item. Selection of modes from the MFC is accomplished using the SEL outer knob.3.3.1.2 COM BUTTONThe COM button on either the MF Controller transfers window focus to the pilot's Radio Tuning window and sets the cursor focus to the NAV 1 sub-window, permitting direct keyboard data entry.3.3.1.3 TUNING SELECT (SEL) CONTROLThe Tuning Select Control consists of two concentric knurled knobs. The outer knob typically controls coarse tuning and the inner knob controls fine tuning. The frequency can also be entered using the MFC numeric keypad, followed by the Enter (ENT) key.3.3.1.4 FREQUENCY SWAPThe Frequency Swap function exchanges the active and standby frequency. The active frequency becomes the standby frequency, and the standby frequency becomes the active frequency. The swap function can be accomplished using the following:3.3.1.4.1 SOFT KEYThe function is available when the double-headed arrow is shown in the soft key identifier window. Depressing the soft key initiates the frequency swap. 3.3.1.4.2 SEL/FREQ SWAP KNOBDepressing the inner knob on the PFD Controller initiates the frequency swap for the radio that has the cursor focus.3.3.1.4.3 FREQ SWAP BUTTONDepressing the button on the MF Controller initiates the frequency swap for the radio that has the cursor focus.Soft keys are also selectable from the MFC using the Joystick control followed by the ENT key.
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 3-113.3.2 VHF NAV CONTROLS3.3.2.1 DETAIL BUTTONThe DETAIL button on either the PFD or MF Controller activates a secondary window related to the currently active window providing additional details or controls related to the item. A subsequent selection of the DETAIL button removes the secondary window and displays the primary window for the item. Selection of modes from the MFC is accomplished using the SEL outer knob.3.3.2.2 NAV BUTTONThe NAV button on the MF Controller transfers window focus to the pilot's Radio Tuning window and sets the cursor focus to the NAV 1 sub-window, permitting direct keyboard data entry.3.3.2.3 TUNING SELECT (SEL) CONTROLThe Tuning Select Control consists of two concentric knurled knobs. The outer knob typically controls coarse tuning and the inner knob controls fine tuning.3.3.2.4 FREQUENCY SWAPThe Frequency Swap function exchanges the active and standby frequency. The active frequency becomes the standby frequency, and the standby frequency becomes the active frequency. The swap function can be accomplished using the following:3.3.2.4.1 SOFT KEYThe function is available when the double-headed arrow is shown in the soft key identifier window. Depressing the soft key initiates the frequency swap. If the VOR bearing has been selected for display, the swap arrow is not shown, but a blind transfer can be done.3.3.2.4.2 SEL/FREQ SWAP KNOBDepressing the inner knob on the PFD Controller initiates the frequency swap for the radio that has the cursor focus.3.3.2.4.3 FREQ SWAP BUTTONDepressing the button on the MF Controller initiates the frequency swap for the radio that has the cursor focus.Soft keys are also selectable from the MFC using the Joystick control followed by the ENT key.
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page 3-123.3.2.5 VOL/SQ/ID KNOBPushing the volume knob on the PFD Controller will toggle selection of the Morse code ID filter.3.3.2.6 NAV DETAIL WINDOW SOFT KEYSThe soft keys control the NAV mode {BRG (bearing displayed, direct NAV tuning), RAD (radial displayed, direct NAV tuning) or STBY (standby frequency displayed, active/standby NAV tuning)} and allow access to the DME detail window.3.3.2.7 DME DETAIL WINDOW SOFT KEYSThe soft keys control the DME association with each NAV and toggle the DME hold mode.3.3.3 ADF CONTROLS3.3.3.1 DETAIL BUTTONThe DETAIL button on either the PFD or MF Controller activates a secondary window related to the currently active window providing additional details or controls related to the item. A subsequent selection of the DETAIL button removes the secondary window and displays the primary window for the item. Selection of modes from the MFC is accomplished using the SEL outer knob.3.3.3.2 ADF DETAIL WINDOW SOFT KEYSThe soft keys control the ADF mode (ADF, ANT, or BFO). Pressing the FREQ SWAP button on the PFD or MF Controller while on the ADF detail page also changes the ADF modes.
n KTR 2280 Preliminary H 08/17/06Rev. 0, Aug/2006 ©Honeywell International Inc. Do not print without express permission of Honeywell Page A-1APPENDIX AENVIRONMENTAL QUALIFICATION FORMSINCLUDINGSUPPLEMENTAL ENVIRONMENTAL PERFORMANCE INFORMATION
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KA 44B ENVIRONMENTAL PERFORMANCEThe KA 44B ADF Antenna (071-1234-XX) is certified to TSO C41c with RTCA DO-160A environmentals per B2D2/A/LJY/XXXXXX/ABABA.Recent "not-for-certification-credit" testing has been performed on this antenna to determine expected performance in selected DO-160D environmental conditions.DO-160D Section 20 (RF Susceptibility) Tests A KA 44B production test sample was subjected to Category TT fields as defined in the test environment called out in RTCA DO-160D Section 20 (Change No. 1). This unit was tested in conjunction with the KTR 2280 Multi-Mode Digital Radio. All conducted and radiated susceptibility performance requirements were passed except for radiated susceptibility in the band of interference frequencies between 277 MHz and 339 MHz. Within this band the KA 44B could not tolerate interference levels greater than 0.8 V/m (for acceptable audio signal-to-noise) or greater than 1.1 V/m (for acceptable bearing error).A KA 44B production test sample was subjected to the 100 V/M (and greater) HIRF levels expected for aircraft system level certification. This test was done in a manner consistent with aircraft system level HIRF certification testing. No permanent damage was noted during the HIRF exposure and the unit returned immediately to normal operation after the HIRF event terminated.DO-160D Section 22 (Lightning Induced Transient Susceptibility) Tests A KA 44B production test sample was subjected to Category A3J33 as defined and in the test environment called out in RTCA DO-160D Section 22 (Change No. 3). The KA 44B passed all requirements.DO-160D Section 23 (Lightning Direct Effects) Tests A KA 44B production test sample was subjected to Category 2A as defined in the test environment called out in RTCA DO-160D Section 23. The KA 44B passed all requirements.Other DO-160D based test data has been collected and is available on request from Honeywell.
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