Honeywell KTR2280A User Manual

Honeywell International Inc. 23500 West 105th Street Olathe, Kansas 66061-8425 U.S.A. CAGE: 22373 Telephone: 800-601-3099 (Toll Free U.S.A./Canada) Telephone: 602-365-3099 (International Direct) Website: www.myaerospace.com

System Installation Manual

KTR 2280A Multi-Mode Digital Radio

Part Number CAGE

069-01039-0101 22373

Legal Notice

Export Control

These items are controlled by the U.S. government and authorized for export only to the country of ultimate

destination for use by the ultimate consignee or end-user(s) herein identified. They may not be resold, transferred, or otherwise disposed of, to any other country or to any person other than the authorized ultimate consignee or end-user(s), either in their original form or after being incorporated into other items, without first

obtaining approval from the U.S. government or as otherwise authorized by U.S. law and regulations.

ECCN: 7E994.

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Proprietary Information

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COPYRIGHT BY HONEYWELL INTERNATIONAL INC. (“HONEYWELL”). ALL RIGHTS RESERVED. THIS DOCUMENT AND ALL INFORMA TION CONTAINED HEREIN ARE THE CONFIDENTIAL AND PROPRIETARY INFORMATION OF HONEYWELL AND CONTAIN HONEYWELL TRADE SECRETS. NEITHER THIS DOCUMENT NOR THE INFORMATION CONTAINED HEREIN MAY, IN WHOLE OR IN PART, BE USED, DUPLICATED, OR DISCLOSED FOR ANY PURPOSE WITHOUT PRIOR WRITTEN PERMISSION OF HONEYWELL.

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may not design or manufacture a Honeywell part or detail of a Honeywell part, to create a repair for a Honeywell part, design or manufacture any part that is similar or identical to a Honeywell part, compare a Honeywell part or design of a Honeywell part to another part design, or apply for FAA PMA or other domestic or foreign governmental approval to manufacture or repair a Honeywell part.

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Safety Advisory

WARNING: BEFORE THE MATERIALS CALLED OUT IN THIS PUBLICATION ARE USED, KNOW THE HANDLING, STORAGE AND DISPOSAL PRECAUTIONS RECOMMENDED BY THE MANUFACTURER OR SUPPLIER. FAILURE TO OBEY THE MANUFACTURERS’ OR SUPPLIERS’ RECOMMENDATIONS CAN RESULT IN PERSONAL INJUR Y OR DISEASE.

This publication describes physical and chemical processes which can make it necessary to use chemicals, solvents, paints, and other commercially available materials. The user of this publication must get the Ma terial Safety Data Sheets (OSHA Form 17 4 or equ ivalent) fro m the ma nufa cturers or supplier s of the ma teria ls to be used. The user must know the manufacturer/ supplier data and obey the procedures, recommendations, warnings and cautions set forth for the safe use, handling, storage, and disposal of the materials.

Warranty/Liability Advisory

WARNING: HONEYWELL ASSUMES NO RESPONSIBILITY FOR ANY HONEYWELL EQUIPMENT WHICH IS NOT MAINTAINED AND/OR REPAIRED IN ACCORDANCE WITH HONEYWELL'S PUBLISHED INSTRUCTIONS AND/OR HONEYWELL'S FAA/SFAR 36 REPAIR AUTHORIZATION. NEITHER DOES HONEYWELL ASSUME RESPONSIBILITY FOR SPECIAL TOOLS AND TEST EQUIPMENT F ABRICA TED BY COMPANIES OTHER THAN HONEYWELL.

WARNING: INCORRECTLY REPAIRED COMPONENTS CAN AFFECT AIRWORTHINESS OR DECREASE THE LIFE OF THE COMPONENTS. INCORRECTLY FABRICATED SPECIAL TOOLING OR TEST EQUIPMENT CAN RESULT IN DAMAGE TO THE PRODUCT COMPONENTS OR GIVE UNSA TISFACTORY RESULTS.

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Copyright - Notice

Honeywell is a registered trademark of Honeywell International Inc.

All other marks are owned by their respective companies.

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TRANSMITTAL INFORMATION

THIS IS AN INITIAL RELEASE OF KTR 2280A MULTI-MODE DIGITAL RADIO SIM PUBLICATION No. D201610000049 ISSUED FOR USE IN SUPPORT OF THE FOLLOWING:

Table TI-1 shows the applicable components.

Table TI-1. Applicable Components

Component PN Nomenclature

069-01039-0101 KTR 2280A Multi-Mode Digital Radio

Revision History

Table TI-2 shows the revision history of this SIM.

Table TI-2. Revision History

Revision Number Revision Date

0 15 May 2017

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RECORD OF REVISIONS

For each revision, write the revision number, revision date, date put in the manual, and your initials in the applicable column.

NOTE:

Revision

Number

Refer to the Revision History in the TRANSMITTAL INFORMATION section for revision data.

Revision

Date

Date Put

In Manual By

Revision

Number

Revision

Date

Date Put

In Manual By

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RECORD OF TEMPORARY REVISIONS

Instructions on each page of a temporary revision tell you where to put the pages in your manual. Remove the temporary revision pages only when discard instructions are given. For each temporary revision, put the applicable data in the record columns on this page.

Definition of Status column: A TR may be active, incorporated, or deleted. “Active” is entered by the holder of the manual. “Incorporated” means a TR has been incorporated into the manual and includes the revision number of the manual when the TR was incorporated. “Deleted” means a TR has been replaced by another TR, a TR number will not be issued, or a TR has been deleted.

Temporary

Revision

Number Status

Page

Number

Issue

Date

Date Put in

Manual By

Date

Removed

From Manual By

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LIST OF EFFECTIVE PAGES

Subheading and Page Date Subheading and Page Date

Title

T-1 15 May 2017 T-2 15 May 2017 T-3 15 May 2017 T-4 15 May 2017 T-5 15 May 2017 T-6 15 May 2017

Transmittal Information

TI-1 15 May 2017 TI-2 15 May 2017

Record of Revisions

RR-1 15 May 2017 RR-2 15 May 2017

Record of Temporary Revisions

RTR-1 15 May 2017 RTR-2 15 May 2017

List of Effective Pages

LEP-1 15 May 2017 LEP-2 15 May 2017

Table of Contents

TC-1 15 May 2017 TC-2 15 May 2017 TC-3 15 May 2017 TC-4 15 May 2017

Introduction

INTRO-1 15 May 2017 INTRO-2 15 May 2017 INTRO-3 15 May 2017 INTRO-4 15 May 2017 INTRO-5 15 May 2017 INTRO-6 15 May 2017

Section 1 - General Information

1-1 15 May 2017 1-2 15 May 2017 1-3 15 May 2017 1-4 15 May 2017 1-5 15 May 2017 1-6 15 May 2017 1-7 15 May 2017 1-8 15 May 2017

Section 2 - Installation

2-1 15 May 2017 2-2 15 May 2017 2-3 15 May 2017 2-4 15 May 2017 2-5 15 May 2017 2-6 15 May 2017 2-7 15 May 2017 2-8 15 May 2017 2-9 15 May 2017 2-10 15 May 2017 2-11 15 May 2017 2-12 15 May 2017 2-13 15 May 2017 2-14 15 May 2017 2-15 15 May 2017

2-16 15 May 2017 F 2-17 15 May 2017 F 2-18 15 May 2017

2-19 15 May 2017

2-20 15 May 2017

2-21 15 May 2017

2-22 15 May 2017 F 2-23 15 May 2017 F 2-24 15 May 2017 F 2-25 15 May 2017 F 2-26 15 May 2017 F 2-27 15 May 2017 F 2-28 15 May 2017 F 2-29 15 May 2017 F 2-30 15 May 2017 F 2-31 15 May 2017 F 2-32 15 May 2017 F 2-33 15 May 2017 F 2-34 15 May 2017 F 2-35 15 May 2017 F 2-36 15 May 2017 F 2-37 15 May 2017 F 2-38 15 May 2017 F 2-39 15 May 2017 F 2-40 15 May 2017 F 2-41 15 May 2017 F 2-42 15 May 2017 F 2-43 15 May 2017 F 2-44 15 May 2017

2-45 15 May 2017

* indicates a changed or added page. F indicates a foldout page.

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Subheading and Page Date Subheading and Page Date

2-46 15 May 2017 2-47 15 May 2017 2-48 15 May 2017 2-49 15 May 2017 2-50 15 May 2017 2-51 15 May 2017 2-52 15 May 2017

Section 3 - Operation

3-1 15 May 2017 3-2 15 May 2017 3-3 15 May 2017

3-4 15 May 2017 Appendix A - Enviro nm ent al Qualification Forms

A-1 15 May 2017 A-2 15 May 2017 A-3 15 May 2017 A-4 15 May 2017 A-5 15 May 2017 A-6 15 May 2017 A-7 15 May 2017 A-8 15 May 2017

Appendix B - Deviations

B-1 15 May 2017 B-2 15 May 2017 B-3 15 May 2017 B-4 15 May 2017

* indicates a changed or added page. F indicates a foldout page.

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(1) This publication gives maintenance instructions for the equipment shown on the Title page. (2) Standard maintenance procedures that technicians must know are not given in this manual. (3) This publication is written in agreement with the ATA Specification. (4) Warnings, cautions, and notes in this manual give the data that follows:

• A WARNING gives a condition or tells personnel what part of an operation or maintenance procedure, which if not obeyed, can cause injury or death

• A CAUTION gives a condi tion or tells personnel what part of an operation or ma intenance procedure, which if not obeyed, can cause damage to the equipment

• A NOTE g ives data, not command s. The NOTE helps personnel wh en they do the related instruction.

(5) Warnings and cautions go before the applicable paragraph or step. Notes follow the

applicable paragraph or step.

SYSTEM INSTALLATION MANUAL

KTR 2280A

INTRODUCTION

B. Observance of Manual Instructions

(1) Make sure that you carefully obey all safety, quality, operation, and shop procedures for the

unit.

(2) All personnel who operate equipment and do maintenance specified in this manual must

know and obey the safety precautions.

C. Symbols

(1) The symbols and special characters are in agreement with IEEE Publication 260 and IEC

Publication 27. Special characters in text are spelled out.

(2) The signal mnemonics, unit control designators, and test designators are shown in capital

letters. (3) The signal names followed by an “*” show an active low signal. (4) The symbols in Figure INTRO-1 show ESDS and moisture sensitive devices.

Figure INTRO-1. (Sheet 1 of 1) Symbols

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D. Units of Measure

(1) Measurements, weights, temperatures, dimensions, and other values are expressed in the

USMS followed by the appropriate SI metric units in parentheses. Some standard tools or parts such as drills, taps, bolts, nuts, etc. do not have an equivalent.

E. Standard Practices Manual

(1) Not applicable.

F. Electrostatic Discharge

(1) Touch the items susceptible to electrostatic discharge in accordance with MIL-HDBK-263.

Refer to MIL-STD-1686 for definition of the standards and conditions.

2. Customer Support

A. Honeywell Aerospace Online Technical Publications Website

(1) Go to the Honeywell Online Technical Publications Website at (www.myaerospace.com).

• To download or see publications online

• To order a publication

• To tell Honeywell of a possible data error in a publication.

B. Honeywell Aerospace Contact Team

(1) If you do not have access to the Honeywell Technical Publications Website, or if you need to

speak to personnel about non-Technical Publication matters, the Honeywell Aerospace Contact Team gives 24/7 customer service to Air T ranspor t & Regional, Business & General Aviation, and Defense & Space customers around the globe.

• Telephone: 800-601-3099 (Toll Free U.S.A./Canada)

• Telephone: 602-365-3099 (International).

3. References

A. Honeywell/Vendor Publications

(1) Honeywell publications related to the content of this manual are shown in the list that follows:

• Not applicable.

B. Other Publications

(1) These publications are standard references. Check for latest version of publication.

• The United States GPO Style Manual 2000 (aavailable at http://www.gpo.gov/fdsys/pkg/GPO-STYLEMANUAL-2008/content-detail.html)

• IEEE Std 260, Standard Letter Symbols for Units of Measurement (available from the American National Standards Institute at http://www.ansi.org)

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• ASME Y14.38, Abbreviations for Use on Drawings and in Text (available from the American National Standards Institute at http://www.ansi.org)

• ANSI/IEEE Std 91, Graphic Symbols for Logic Functions (available from the American National Standards Institute at http://www.ansi.org)

• CAGE codes and manufacturers' addresses are available at https://cage.dla.mil

• IEEE 315/ANSI Y32.2, Graphic Symbols for Electrical and Electronics Diagrams (available from the American National Standards Institute at http://www.ansi.org)

• MIL-HDBK-263, Electrostatic Discharge Control Handbook for Protection of Electrical and Electronic Parts, Assemblies and Equipment (Excluding Electrically Initiated Explosive Devices) (Metric) (available from any military standards database)

• MIL-STD-1686, Electrostatic Discharge Con tr ol Pro gra m fo r Prot ec tio n of Elec tr ical an d Electronic Parts, Assemblies and Equipment (Excluding Electrically Initiated Explosive Devices) (Metric) (available from any military standards database).

4. Acronyms and Abbreviations

A. General

KTR 2280A

(1) The abbreviations are used in agreement with ASME Y14.38. (2) Acronyms and non-standard abbreviations used in this publication are as follows.

List of Acronyms and Abbreviations

Term Full Term

ACARS aircraft communications addressing and reporting system ADF automatic direction finder AM amplitude modulation ANSI American National Standards Institute ANT antenna AOA angle of attack APM airc raft personality module ARINC Aeronautical Radio, Incorporated ASME American Society of Mechanical Engineers A TA Air Transport Association ATN aeronautical telecommunication network AVLC aviation link control BFO beat frequency oscillator BIT built-in test CAGE commercial and government entity

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List of Acronyms and Abbreviations (Cont)

Term Full Term

CPDLC controller/pilot data link communications CFR Code of Federal Regulations CMC central maintenance computer CMF communications management function CMM component maintenance manual COM communication dB decibel dBm decibel (referenced to one milliwatt) DEG degree DME distance measuring equipment EB engineering bulletin ECCN export control classification number ELT emergency locator transmitter ESDS electrostatic discharge sensitive ETSO European Technical Standard Order FAA Federal Aviation Administration FCC Federal Communications Commission GMT Greenwich mean time GND ground GPO Government Printing Office GRY grey GS glidescope HIRF high intensity radiated fields Hz hertz IEC International Electrotechnical Commission IEEE Institute of Electrical and Electronics Engineers ILS instrument landing system kHz kilohertz KTR king transceiver radio LOC localizer LRU line replaceable unit mA milliampere

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List of Acronyms and Abbreviations (Cont)

Term Full Term

MHz megahertz MIC microphone MIL military MMDF multi-mode digital function MMDR multi-mode digital receiver MMDS multi-mode digital sensor MNT mount MOPS minimum operational performance standards NAV navigation NDB non-directional beacon No. number PGM program PN part number POA plain old aircraft communications addressing and reporting system PTT push-to-talk PWR power QE quadrantal error REV revision RF radio frequency RTCA Radio Technical Commission for Aeronautics RX receiver SIM system installation manual SNR signal-to-noise ratio STC supplemental type certificate TC type certificate TSO technical standard order TX transmiter UTC universal time coordinated VAC volts alternating current VDC volt direct current VHF very high frequency VOR very high frequency omnidirectional range

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List of Acronyms and Abbreviations (Cont)

Term Full Term

VSWR voltage standing wave ratio Wwatt

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SECTION 1

GENERAL INFORMATION

1.1 INTRODUCTION This manual contains information relative to the physical, mechanical, and electrical characteristics of the

Honeywell KTR 2280A MMDR. Installation and check out procedures are also included. Information relative to the maintenance, alignment, and procurement of the replacement parts may b e found in this KTR 2280 A CMM, Publication No. D201610000050. Final design of the installation an d ai rwor th iness approval is incumbent upo n the installer and their respective certification authority.

1.2 EQUIPMENT DESCRIPTION

The KTR 2280A MMDR T ransceiver is a blind panel mounted integrated transceiver containing one transmitter and six receivers. Depending on system configuration, all six receivers can be simultan eously active. The KTR 2280A will operate from a normal voltaqe of 27.5 VDC. The KTR 2280A is designed with ARINC 429 interfaces which is intended for use in the aircraft. It is also designed with RS-422 capabilities that will be used primarily for development and testing in the engineering lab. The KTR 2280A is controlled by other LRUs which will send control information to the KTR 2280A th rough ARINC 429 data. Some outputs from the KTR 2280A are in digital formats and sent to other LRUs through ARINC 429. Other outputs are more traditional analog outputs.

The six receivers and their modes of operation are as follows, The NAV receiver operates in one of three modes as dynamically controlled by the system interface. These three modes are VOR, LOC, and VDB. The GS operates in the Glideslope mode only. The ADF operates in the di rection find ing an d AM modes. There are three COM receivers. The first COM is a traditional AM mode receiver with either 25 or 8.33 kHz channel spac ing. The second AM COM receiver functions as a Guard channel receiver with either 25 or 8.33 kHz channel spacing. The third COM receiver is capable of receiving either VDL Mode 2 (D8PSK) or VDL Mode A (MSK) signals. The COM transmitter is capable of AM, VDL Mode 2, or VDL Mode A modes.

The KTR 2280A contains BIT equipment so that the operatio nal health of the unit is constantly monitored. When a critical fault is detected, the unit notifies the host 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.

1.3 TECH NIC AL CHAR A CTERISTICS

1.3.1 KTR 2280A Technical Characteristics

-

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Table 1-1 KTR 2280A Technical Characteristics

SPECIFICATION CHARACTERISTIC

TSO COMPLIANCE: COM TRANSMIT TSO-C169a, ETSO-2C169a, DO-186B, ED-23C for

transmitter Class 3 and 5

COM RECEIVE TSO-169a, ETSO-2C169a, DO-186B for receiver Classes

C, D, E, and ED-23C for receiver Classes C, D, E and H2 VOR TSO-C40c, ETSO- 2C40c, DO-196, and ED-22B LOC TSO-C36e, ETSO-2C36f, DO-195 for receiver Class B, and

ED-46B for automatic landing.

GS TSO-C34e, ETSO-2C34f, DO-192, and ED-47B ADF TSO-C41d, ETSO-2C41d, DO-179 for Class A, and

ED-51 STUCK MICROPHONE TSO-128a, ETSO-2C128, DO-207, and ED-67 VDB TSO-C162a and DO-253C VDL MODE 2 TRANSCEIVER TSO-C160a, DO-281B, and ED-92B for Class YF7 TSO/ETSO DEVIATIONS Refer to APPENDIX B NON-TSO FUNCTIONS

Mode A TRANSCEIVER (ACARS)

SOFTWARE QUALIFICATION DO-178B Level B HARDWARE QUALIFICATION DO-254 Level B ENVIRONMENTAL

Refer to APPENDIX A CATEGORIES

PHYSICAL DIMENSIONS Refer to Figure 2-21 KTR 2280A Installation Drawing WEIGHT Refer to Figure 2-21 KTR 2280A Installation Drawing MOUNTING Remote rack mounted TEMPERATURE Refer to APPENDIX A ALTITUDE Refer to APPENDIX A COOLING Internal fan and external rack mounted fan POWER INPUT 16 to 33 VDC (Nominal voltage 27.5 VDC) POWER REQUIREMENTS

(Note: 100% transmit is specified for short-term operation only)

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RECEIVE (NOMINAL) 19 Watt (0.7 A at 27.5 V) RECEIVE (NOMINAL) W/10% TRANSMIT 33 Watt (1.19 A at 27.5 V) RECEIVE (NOMINAL) W/100% TRANSMIT 154 Watt (5.6 A at 27.5 V) RECEIVE (MAXIMUM) 28 Watt (1.02 A at 27.5 V) RECEIVE (MAXIMUM) W/10% TRANSMIT 43 Watt (1.57 A at 27.5 V) RECEIVE (MAXIMUM) W/100% TRANSMIT 179 Watt (6.5 A at 27.5 V)

1.3.2 KA 44B Technical Characteristics

Table 1-2 KA 44B Technical Characteristics

SPECIFICATION CHARACTERISTIC

TSO COMPLIANCE Refer to APPENDIX A ENVIRONMENTAL

Refer to APPENDIX A

SPECIFICATIONS PHYSICAL DIMENSIONS Refer to Figure 2-22 and Figure 2-23 for Outline and Mounting

Drawing

WEIGHT: Refer to Figure 2-22 and Figure 2-23 for Outline and Mounting

Drawing

POWER REQUIREMENTS 8.5 ±0.5 VDC at 100 mA ma x (supplied by

KTR 2280A)

1.4 UNITS AND ACCESSORIES SUPPLIED

1.4.1 KTR 2280A Installation Kit NOTE: The following installation kit information is presented at the revision existing at the time of this

publication. Future revisions to these kits can occur. Use the latest revision of the kit as provided by Honeywell.

The KTR 2280A installation kit, PN 050-03721-0010, contains the following parts:

PN DESCRIPTION REV

------------------------------------------------------------------------------------------------------------------050-03721-0010 INSTALL KIT KTR 2280A A

--------------------------------------------------------------------------------------------------------------------------------------------------SYM-

PART NO. FIND NO. DESCRIPTION UM -QTY

BOL

--------------------------------------------------------------------------------------------------------------------------------------------------P1 030-03296-0000 HI DENSITY SUBD44P EA 1.00

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--------------------------------------------------------------------------------------------------------------------------------------------------SYM-

PART NO. FIND NO. DESCRIPTION UM -QTY

BOL

--------------------------------------------------------------------------------------------------------------------------------------------------P101 030-00101-0002 PANEL MOUNT PLUG EA 1.00 P102 030-00101-0002 PANEL MOUNT PLUG EA 1.00 P103 030-00101-0002 PANEL MOUNT PLUG EA 1.00 P104 030-00101-0002 PANEL MOUNT PLUG EA 1.00 J501 57000525-002 FAN, 25 X 25 X 10 mm, 3.5 CFM, TEFLON EA 1.00

001-01299-0000 INSTRUCTION FOR HARNESS ASSEMBLY PARTS RF .00 030-01458-0000 CONTACT, SOCKET, SIZE 22 EA 44.00 030-01466-0003 CONN, D-SUB, CONT, FEM, #22 W/ 20 AWG CRMP

EA 6.00

BARREL 047-11179-0004 STAIN RELIEF CLAMP, .220 EA 1.00 047-11310-0004 RACK, W/FINISH EA 1.00 057-05944-0085 KTR 2280A KIT TSO LABEL EA 1.00 073-01140-0003 BACKPLATE W/HARDWARE EA 1.00 073-01 141-0002 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 1.00 089-05874-0011 SCR PHP 2-56 X 11/16 EA 3.00 089-05878-0005 SCR PHP 4-40 X 5/16 EA 1.00 089-05903-0004 SCR PHP 4-40 X 1/4 EA 3.00 089-06008-0004 SCR FHP 4-40 X 1/4 E A 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 1.00 150-00128-0009 TBG HT SHRNK WHT IN 2.00 155-03009-0001 CABLE ASSY, POWER, KTR 2280A FAN EA 1.00 155-06081-0000 INSTALL DRAWING MMDR KTR 2280A RF .00 200-10452-0001 BAR CLAMP ASSEMBLY -15 EA 1.00

Shield braids must be clamped to the connector backshell using bar clamp assembly, PN 200-10452-0001, which contains the following parts. Refer to Figure 2-12 Typical Taylor Backshell Instructions and Figure 2-21 KTR 2280A Installation Drawing for additional information.

PN DESCRIPTION REV

------------------------------------------------------------------------------------------------------------------200-10452-0001 BAR CLAMP ASSEMBLY -15 -

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--------------------------------------------------------------------------------------------------------------------------------------------------SYM-

PART NO. FIND NO. DESCRIPTION UM -0001

BOL

--------------------------------------------------------------------------------------------------------------------------------------------------REF1 -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

The KA 44B antenna installation kit Honeywell PN 050-01756-0020 contains the following parts

PN DESCRIPTION REV

------------------------------------------------------------------------------------------------------------------050-01756-0020 INSTALL KIT 48 FT MMDR KA 44B DO-160D C

--------------------------------------------------------------------------------------------------------------------------------------------------SYM-

PART NO. FIND NO. DESCRIPTION UM -0020

BOL

--------------------------------------------------------------------------------------------------------------------------------------------------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 1.00 155-05334-0000 INST DWG KA44B RF 0.00 200-02586-0020 ANT CBL ASSY 48FT KA 44B DO-160D EA 1.00

The KA 44B antenna cable assembly Honeywell PN 200-02586-0020 contains the following parts

PN DESCRIPTION REV

-------------------------------------------------------------------------------------------------------------------

200-02586-0020 ANT CBL ASSY 48FT KA 44B DO-160D G

---------------------------------------------------------------------------------------------------------------------------------------------------

SYM-

PART NO. FIND NO. DESCRIPTION UM -0020

BOL

--------------------------------------------------------------------------------------------------------------------------------------------------025-00001-0000 WIRE, HOOKUP, PTFE, 26 (7/34)AWG SPC, BLK IN 3.90 025-05120-0000 WIRE, TIN PLTD CU SHLD, 5-24 (19/36)AWG TPC

IN 578.00

COND 026-00029-0000 WIRE, CU, 22AWG, TINNED IN 3.00 030-01157-0011 SOCKET CRMP 20G EA 9.00 030-01 171-0000 CONN SUB-D HSG 9S (FEMALE PINS) EA 1.00

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--------------------------------------------------------------------------------------------------------------------------------------------------SYM-

PART NO. FIND NO. DESCRIPTION UM -0020

BOL

--------------------------------------------------------------------------------------------------------------------------------------------------030-02351-0000 HOOD/L VR ASSY ST E EA 1.00 150-00024-0010 TUBING SHRINK 10G IN 2.00 150-00049-0010 SHRINK TUBING WHT IN 0.75 350-00052-0010 SHRINK TUBING WHT IN 4.5 300-02586-0020 ANTENNA CABLE INTERCONNECT KA 44B DO-160D RF .00 53001 150-1 50 OHM QUADRAXIAL CABLE FT 48.17 025-00003-0008 WIRE 22 GRY IN 4.30 710-H4TS HEAT SHRINK, 1/4, PRNTABLELABL EA 1

1.5 ACCESSORIES REQUIRED, BUT NOT SUPPLIED A. Broadband communications antenna (50 ohms)

B. V HF NA V ant en na (50 o hms ) C. Gl id esl op e a nt enn a D. An te nna s pli tt er( s) E. A DF An tenna (representative type KA 44 B) T he K A 4 4B, PN 07 1-1 23 4-00/01, is a low profile ADF Antenna which contains both loop and sense

antennas, preamplifiers, and modulators which combine the antenna sig nals into a single RF signal which is output to the KTR 2280A through a quadaxial cable of non-critical length. The KA 44B is supplied with a backing plate (Refer to Figure 2-22 KA 44B Outline and Mounting Drawing for PN 155-05334-0000 and the KA 44B, PN 155-05334-0010 is supplied with a grounding ring ( Ref to Fig-

ure 2-23 KA 44B Outline and Mounting Drawing for PN 155-05334-0010). F. C ons um abl es : ( 1) RT V No. 3 145 ( PN 01 6-0 10 82- 00 00) . ( 2) Al um ipr ep No 3 3 ( PN 01 6- 011 27 -00 00 ). ( 3) Al od ine N o 1 00 1 ( PN 01 6- 001 28 -00 00 ). ( 4) Do w Cor ni ng DC -4 or eq ui val en t.

1.6 LICENSING REQUIREMENTS The KTR 2280A meets CFR Title 47, Part 2, 15 and 87 (FCC Approvals) for all radio equipment. For non-US

registered aircraft, follow applicable licensing requirements as required. This device complies with Industry Canada’s license-exempt RSSs. Operation is subject to the following two

conditions:

• This device cannot cause inte rf er en ce : an d

• This device must accept any interference, including interference that can cause undesired operation of the device.

Le présent appareil est conforme aux CNR d'Industrie Canada applicables aux appareils radio exempts de licence. L'exploitation est autorisée aux deux conditions suivantes:

• l'appareil ne doit pas produire de brouillage, et

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• l'utilisateur de l'appareil doit accepter tout brouillage radioélectrique subi, même si le brouillage est susceptible d'en compromettre le fonctionnement.

1.7 C ONTINUED AIRW OR THINESS INSTRUCTIONS

1.7.1 Equipment The 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. The KTR 2280A is 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 must be accomplished following any repair action. Consult the KTR 2280A CMM, Pub. No. D201610000050, for complete performance test information. All maintenance must be performed by a Honeywell approved repair center

14 CFR Part 23.1529 and 25.1529, Instructions for Continued Airworthiness is met per the following instructions: The removal of the equipment is on the con dition of failure. There is no required periodic maintenance for the

KTR 2280A. NOTE: Upon completion of maintenance or repair, the post-installation checkout procedures must be

performed. Refer to 2.4 POST-INSTALLATION CHECKS for the procedures.

1.7.2 Wires and Coaxial Cables During 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 AN TE NNA RF EXPOSURE

WARNING: 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

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SECTION 2

INSTALLATION

2.1 G ENER AL INFO RMATION This section contains general suggestions and information to consider before installation of the KTR 2280A.

Close adherence to these suggestions will assure optimum performance from the equipment. NOTE: The conditions and test required for the TSO/ETSO approval of this article are minimum performance

standards. Those installing this article, on or within a specific type or class of aircraft, are responsible for determining that the aircraft installation conditions are suitable for the TSO/ETSO article. TSO/ ETSO articles must have separate approval for installation in an aircraft. The article can be installed only if performed under article 14 CFR part 43 or the applicable airworthiness requirements.

NOTE: Per AC 23.1309-1E, the probability of total loss of navigation and communication (a Hazardous

failure) must be less than 1E-7 (Part 23 Class III or Class IV) per flight hour and only dual installation of KTR 2280A can support this probability requirement without the installation of additional navigation or communication equipment. Additionally, other installation considerations must be analyzed (e.g. electrical wiring and interconnect, power distribution, RF cabling and antennas) to determine the acceptability.

2.2 UNPACKING and INSPECTING EQUIPMENT Exercise 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 must 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 must become necessary.

2.3 EQUIPMENT INSTALLATION

2.3.1 Avionics Cooling Requirements The unit is cooled by a fan internal to the unit and an external fan attached to the rear rack assembly plate, the

latter being a part of the installation (Refer to Figure 2-21 KTR 2280A Installation Drawing ). During installa tion, do not block any holes in the unit cover(s) which would restrict air flow.

2.3.2 Equipment Location The following paragraphs contain information pertaining to the initial installation of the KTR 2280A MMDR,

including instructions concerning the location and mounting of the supporting antenna(s). The equipment must 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 make a tho rough visual inspection and conduct an overall operational check of the system on the ground prior to flight.

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The installation must 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 must 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 pr oduct is responsible for determining environmental and functional compatibility.

Care must be exercised to avoid mounting components near equipment operating with high pulse current or high rf power outputs such as radar and satellite communications equipment. In general, the equipment must be installed in a location convenient for operation, inspection, and maintenance, and in an a rea con sistent 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 2280A MMDR mounting tray can be installed in any convenient location.

2.3.2.2 Antenna(s) The antenna(s) must be well removed from other antenna projections, the engine(s), and propeller(s). It must

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 an tenna(s) must be b onded to the surfa ce of the aircraft in a fore to aft location that provides the flattest ground plane. On composite aircraft, the antenna(s) must be 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 must be designed such that the structural integrity of the fuselage is not compromised. The antenna(s) need to be withi n 5 degrees of the centerline.

Where practical, plan the antenna location(s) to ke ep cable lengths a s short as po ssible and avoi d sharp bends in the cable to minimize the VSWR. Avoid running other cables or wires near the antenna cable(s).

On pressurized aircraft, the antenna(s) must be sealed using an approved sealant, such as RTV No . 3145 (PN 016-01082-0000) or equivalent, around the connector and mounting hardware.

The antenna edge and mounting hardware recesses must 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) must be kept clean. If left dirty (oil covered), the antenna performance can be affected.

2.3.3 KTR 2280A Mechanical Installation The mounting tray for the MMDR must be mounted using the dimensions specified in the outline and mounting

drawing, Figure 2-21 (KTR 2280A Installation Drawing). Install the unit as follows:

(1) Slide the MMDR into the tray until the locking rod engages the nut on the back of the

rack.

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SYSTEM INSTALLATION MANUAL

KTR 2280A

IM PO RTA NT :Th e l ock in g ro d is lo cat ed clo se t o o ne s id e of th e KT R 2 280 A. A s t he

locking rod is tightened, use the opposite hand to press the opposite side of the KTR 2280A into the installation rack. This will ensure that the KTR 2280A is fully inserted within the mounting rack.

Th e K TR 2 28 0 A m ust u se t he i nt ern al f ans o r a p ar t of t he m oun ti ng r ack f or a ir c oo ling.

The mounting racks and other objects will be installed as per the instructions in the installations in the installation drawing to allow air flow through the chassis.

CAUTION: DO NOT OVERTIGHTEN THE LOCKING ROD.

(2) Using a 3/32 inch 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 USE BALL END ALLEN WRENCHES.

To remove the unit, turn the securing rod counter clockwise until it disengages from the mounting tray. Then, pull the unit out of the mounting rack.

The KTR 2280A can be installed in any orientation. For additional KTR 2280A installation information, refer to Figure 2-21 (KTR 2280A Installation Drawing).

2.3.4 Antenna Mechanical Installation

2.3.4.1 VHF COM Antennas The VHF COM antenna must be mounted as far away as possible (8 fee t, 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 must 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.

It is recommended that one COM transceiver be connected to the top antenna for good ground communication and that the other COM transceiver be connected to the bottom antenna to provide good airborne communications. If mounting ante nnas on the sam e side of the aircraft is unavoidable, main tain the minimum allowable separation (8 feet).

The antenna must be mounted on a section of the aircraft that is horizontal d uring cruise fligh t. The base of the antenna must 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 must 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 can increase interference to and from other systems.

The COM transceiver performance depend s heavily on the integrity of the electrical bonding to the airframe and also the electrical integrity of the aircra ft structure. If the electrical resistance between an antenna and the aircraft or between adjacent skin panels change intermittently, noisy communications can result.

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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. Prepare the cable to the BNC connector as shown in Figure 2-18 Right Angle Connector Instruction Sheet

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 NAV Antennas LIMITATIONS: If radio is used for VDB installation, the total minimum installation loss must be 5 dB in NAV

antenna RF path. Installation loss includes the antenna gain and implementation loss from antenna to MMDR.

The NAV antenna must be well removed from other antennas, projections, engines or prope llers. I t mus t hav e 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 must 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. Prepare the cable to the BNC connector as shown in Figure 2-18 Right Angle Connector Instruction Sheet

2.3.4.3 ADF Antennas The antenna installation will determine, to a large extent, whether the ADF will give optimum performance as

required. The KA 44B ADF Antenna contains both the loop and sense antennas. The following considerations must 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 MUST 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 POWER 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 can 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 must 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.

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SYSTEM INSTALLATION MANUAL

• 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 backup plate is to be mounted.

• Apply Alumiprep No. 33, PN 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, PN 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.

• Prepare the ADF RF cable as shown in Figure 2-1 thru Figur e 2-11 Quadraxial Cable Prepara tion. Note that the cable provided can be cut to length as required for the installation.

2.3.5 KTR 2280A Wiring and Cable Installation

KTR 2280A

2.3.5.1 KTR 2280A Interconnection and Cable Harness Fabrication The KTR 2280A MMDR receives primary power from the aircraft power source. A typical interface is shown in

Figure 2-24 KTR 2280A Interconnect Diagram. Aircraft specific interfaces with more details are provided in separate EB or Installation Drawings.

The length of the wires to parallel pins must be approximately the same length, so that the best dis tribution 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 must 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 pr event movement an d must be carefully protected against c hafing. Additional protection must also be provided in all locations where the cable can be subjected to chafing.

In wire bundles, the cabling must 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 must 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 required connec-

tors are supplied as part of the installation kit (Refer to 1.4.1 KTR 2280A Installation Kit).

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(2 ) Th e un it mu st b e kept a m inimum of three fee t from the antenna. Ad ditionally , the an-

tenna coax cable must not be bundled with the other wiring harnesses to the unit.

(3 ) T he l en gth a nd r outing of the external cables must be carefully planned before attempt-

ing the actual installation. Avoid sharp bends or locating the cable near aircraft contro l cables. The cables must be of a length to allow for a “maintenance loop”. That is, the length must be adequate to access and extend the connectors aft of the pan el for future maintenance purposes. Excess cablin g must be secured and stowed by tie-wrapping until such maintenance is required.

(4 ) T he c ab les m ust be supported firmly enough to prevent movement. They must be care-

fully protected wherever one can chafe against another or against some other object. Extra protection must be provided in all locations where the cables can be subject to chafe. Shields on shielded wires must be grounded in accordance with the system interconnection information.

(5 ) S hie lds m us t b e car ri ed th rou gh an y obs tr uct io n t hr oug h a t hr u-b ul khe ad co nn ect or . I f

shielding cannot be carried through by use of a bulkhead/connector pin, precautions must 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 must be used. The preceding discussion does not apply to coaxial and quadraxial cable.

(6 ) A voi d routing cables near high noise and high power sources.

Quadraxial Cable Preparation

(1 ) Re mo ve th e o ut er in stallation 0.900 inch (22.88 mm) from the end of cable, to expose

the outer layer as shown in Figure 2-1.

Figure 2-1 (Sheet 1 of 1) Quadraxial Cable Preparation

(2) Push the braid back as far as possible as shown in Figure 2-2. This will be pulled back

up later and soldered to the connector body.

Figure 2-2 (Sheet 1 of 1) Quadraxial Cable Preparation

(3) Measure back 0.700 inch (17.78 mm) and remove the outer insulation from the middle

shield as shown in Figure 2-3.

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Figure 2-3 (Sheet 1 of 1) Quadraxial Cable Preparation

(4 ) T in th e ex pos ed shield of the middle coax. With a cutting tool, score the tinned shield

around the entire circumference as shown in Figure 2-4.

Figure 2-4 (Sheet 1 of 1) Quadraxial Cable Preparation

(5) Carefully break loose the tinned middle coax shield and slide it off. This will expose the

center coax insulation as shown in Figure 2-5.

Figure 2-5 (Sheet 1 of 1) Quadraxial Cable Preparation

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(6) Measure back 0.500 inch (12.70 mm) and remove the insulation from the center shield

as shown in Figure 2-6.

Figure 2-6 (Sheet 1 of 1) Quadraxial Cable Preparation

(7 ) T in the s hie ld fo r the c ent er co ax as s how n in Fi gur e 2-7 .

Figure 2-7 (Sheet 1 of 1) Quadraxial Cable Preparation

(8) Measure back from the end of the cable 0.30 inch (7.6 mm) and score the center shield

with a cutting tool around the full circumference as shown in Figure 2-8.

Figure 2-8 (Sheet 1 of 1) Quadraxial Cable Preparation

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(9) Carefully break the shield loose. Strip off the insulation from the center conductor as

shown in Figure 2-9.

Figure 2-9 (Sheet 1 of 1) Quadraxial Cable Preparation

(10) Install 0.25 inch (6.35 mm) length of shrink tubing over the middle shield stub to prevent

possible shorts to the outer shield as shown in Figure 10.

Figure 2-10 (Sheet 1 of 1) Quadraxial Cable Preparation

(1 1) C on nec to r A ss emb ly

• I ns tal l the f err ul e o ve r t he ce nt er sh iel d a nd so ld er.

• S li p t he ca bl e i nt o t he co nn ect or ho us ing a s s how n in Fi gur e 2-1 1.

• S ol der t he ce nte r con du cto r to th e c en ter t erm in al.

• P ul l u p the o ute r shi el d a nd so ld er to th e b ot tom s tem .

• I ns tal l shr in k tubing over the entire assembly to the bottom of the connector housing as shown in Figure 2-11.

• Install the horse shoe shaped insert for a 50 ohm impedance match.

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• Install the rear cover cap and solder to barrel lip in two places.

Figure 2-11 (Sheet 1 of 1) Connecto r As se mb ly

2.3.5.2 Taylor Backshell Instructions A. Ge ne ral I nfo rma ti on

(1 ) T ay lor Ba ck she ll s a re a pr opr ie tar y H on eyw el l d esi gn de ve lop ed to ex ped it e

cable harness fabrication while ensuring that HIRF and lightning performance goals are met. A typical backshell is shown in Figure 2-12 Typical Taylor Backshell. Figure 2-13 Backshell Assembly Exploded View provides an exploded view of the backshell. Table 2-1 KTR 2280A Backshell Hardware describes the connector type used for the KTR 2280A.

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Figure 2-12 (Sheet 1 of 1) Typical Taylor Backshell Instructions

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SYSTEM INSTALLATION MANUAL

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Table 2-1 KTR 2280A Backshell Hardware

Connector Type

44 pin right-angle custom

PN

Backshell Cover Cover

Screws

073-01141

-0002

(2 ) A pp ly Lo cti te 42 5 o r equ iv ale nt to a ll sc rew t hre ad s w he n

assembling components.

073-01142

-0002

076-03189

-0001

Bar Clamp

Assy

200-10452

-0001

Strain Relief

Clamp

047-11179

-0004

Figure 2-13 (Sheet 1 of 1) Backshell Assembly Exploded View

(B ) B ack sh ell W iri ng

(1 ) S tr i p th e ou te r j ac ket o f th e t wi ste d pa ir as s how n in F ig u re 2 -14 A sse mb ly

Details. Trim the shield braid to 1.25 in ch (31.75 mm) leng th and then comb out

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the braid. The braids from two twisted pairs can be twisted together to maintain the proper diameter for the twisted braid.

Figure 2-14 (Sheet 1 of 1) Assembly Details

(2) If installing a single twisted pair, the combed braid must be folded back on itself

and twisted to form the proper diameter bundle. Refer to Figure 2-15 Assembly Details.

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KTR 2280A

Figure 2-15 (Sheet 1 of 1) Assembly Details

(3 ) C ri mp pin s or so cke ts on to th e wir es . (4 ) I ns ert th e pins or sockets into the connector. When using oversized power and

(5 ) P la ce the b ac ksh el l o ver t he wi re bu ndl e. (6 ) A tt ach th e co n ne cto r to th e b ac ksh el l. (7 ) I ns ert t he s hie ld br ai d i nt o t he sl ot in t he ba cks he ll co ver (8 ) A tt ach th e bac ks hel l cov er to t he ba cks he ll wi th th e s cr ews p rov ide d. (9 ) D re ss th e t wis te d s hie ld s a s s how n in Fi gur e 2 -1 6 S hie ld Br aid Ro ut ing an d

ground contacts, ensure heat shrink tubing is used to cover exposed ends of contacts.

Clamping Bar Details. Do not allow twisted shields to cross over each other. Tighten the clamping bar to secure the braids and provide a reliable electrical ground.

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Figure 2-16 (Sheet 1 of 1) Shield Braid Routing and Clamping Bar Details

(11) When the clamping bar is tight, the exposed braids must be trimmed as shown

in Figure 2-16 Shield Braid Routing and Clamping Bar Details.

(12) Insert the strain relief and secure with a tie wrap as shown in Figure 2-17

Securing Strain Relief Clamp.

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Figure 2-17 (Sheet 1 of 1) Securing Strain Relief Clamp

(c ) I nst al lat ion C ons id era ti ons

(1 ) D et erm in ing W ire L eng th : T he l eng th of w ir e f ro m t he p oin t at wh ich t he sh ie ld

is split off to the terminations in the connector must be as short as possible to allow the wire to lay in the backshell without straining the wires.

(2 ) G ro und in g: T ay lor Ba cks he lls ha ve a n e xte rn al t ap pe d ho le t hat ca n b e u sed t o

attach a ground strap. This can be used at the installer's discretion.

(3) Shell Aperture: When the strain relief is tightened against the wire bundle

ensure that there are no large openings in the shell back and that the wires are held securely. A different size strain relief can be required if the wire bundle is too small. Wrapping wires in the connector throat is acceptable to bring the bundle diameter up to a size that can be properly clamped.

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Figure 2-18 (Sheet 1 of 1) Right Angle Connector Instruction Sheet

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2.3.5.3 Primary Power and Circuit Breaker Requirements The KTR 2280A MMDR receives primary power from the aircraft power circuit breakers. Power connections,

wire sizes, and circuit breaker requirements can be found in the system installation manual and/or EB for a specific installation.

2.3.5.4 Connectors

Figure 2-19 (Sheet 1 of 1) KTR 2280A Mating Connector

Front View

Table 2-2 J1 Pin Functions

Pin No.

1 O A429 Out1 A 2 O ADF Loop Enable OUT 3 I Test 4 I Unit Pos PGM 1* 5 I Unit Pos PGM 2* 6 I COM TX Interlock* IN 7 I COM MIC Key* IN 8 O RS-422 RX A 9 O RS-422 RX B 10 I RS-422 TX A 11 I RS-422 TX B 12 I COM MIC GND 13 I A429 IN3 A 14 O ADF Audio LO OUT

Pin Name Description

15 O ADF Audio HI OUT 16 O A429 Out1 B 17 O ADF MOD 0 OUT 18 O A429 Out2 A

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Pin No.

19 I Unit Pos Parity* 20 I A429 IN1 A 21 O A429 OUT3 A 22 I A429 IN2 A 23 I ADF ANT PWR Return 24 I DC Return 1 25 I DC Power 2 IN 26 I Emergency Channel* 27 I COM MIC Audio IN 28 I A429 IN3 B 29 O NAV Audio LO OUT 30 O NAV Audio HI OUT 31 O ADF MOD 90 OUT 32 O A429 Out2 B 33 O MMDS FAN 5V OUT 34 I A429 IN1 B

Pin Name Description

35 O A429 OUT3 B 36 I A429 IN2 B 37 I Pgm Pin Common 38 O ADF ANT PWR OUT 39 I DC Power 1 IN 40 I DC Return 2 41 I Download* 42 I/O VDL Interlock IN OUT* 43 O COM Audio/Sidetone LO OUT 44 O COM Audio/Sidetone HI OUT

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Table 2-3 Antenna Connector Functions

Connector Pin I/O Description

J101 1 I/O COM RF J102 1 I ADF RF IN J103 1 I NAV RF IN J104 1 I Glideslope RF IN

Note: * indicates the Pin is active GND.

Figure 2-20 (Sheet 1 of 1) KA 44B Mating Connector Front View

(Part of Antenna Cable Assembly, PN 200-02586-0020)

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Table 2-4 KA 44B Pin Functions

PIN I/O SIGNAL NAME

1 I ANTENNA POWER 2 I LOOP ENABLE 3 O RF INPUT 4 I ADF MOD 90 Out 5 I ADF MOD 0 Out 6 NO CONNECTION 7 GROUND 8 INNER SHIELD 9 MIDDLE/OUTER SHIELD

2.3.5.5 Crimp Tool Information

Table 2-5 Crimp Tools and Accessories

Crimp Tool Honeywell PN 005-02012-0021, Positronic 9507 or

equivalent

Positioner Positronic 9502-3 or equivalent Insertion/Extraction Tool Positronic 4811-2-0-0 or equivalent

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Figure 2-21 (Sheet 1 of 4) KTR 2280A Installation Drawing

(Dwg No 155-06081-0000 Rev N)

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Figure 2-21 (Sheet 2 of 4) KTR 2280A Installation Drawing

(Dwg No 155-06081-0000 Rev N)

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Figure 2-21 (Sheet 3 of 4) KTR 2280A Installation Drawing

(Dwg No 155-06081-0000 Rev N)

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Figure 2-21 (Sheet 4 of 4) KTR 2280A Installation Drawing

(Dwg No 155-06081-0000 Rev N)

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Figure 2-22 (Sheet 1 of 1) KA 44B Outline and Mounting Drawing

(Dwg No 155-05334-0000 Rev AC)

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Figure 2-23 (Sheet 1 of 1) KA 44B Outline and Mounting Drawing

(Dwg No 155-05334-0010 Rev AD)

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Figure 2-24 (Sheet 1 of 5) KTR 2280A Interconnect Diagram

(Dwg No 155-01835-0000 Rev -)

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Figure 2-24 (Sheet 2 of 5) KTR 2280A Interconnect Diagram

(Dwg No 155-01835-0000 Rev -)

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Figure 2-24 (Sheet 3 of 5) KTR 2280A Interconnect Diagram

(Dwg No 155-01835-0000 Rev -)

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Blank Page

Figure 2-24 (Sheet 4 of 5) KTR 2280A Interconnect Diagram

(Dwg No 155-01835-0000 Rev -)

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Figure 2-24 (Sheet 5 of 5) KTR 2280A Interconnect Diagram

(Dwg No 155-01835-0000 Rev -)

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2.4 POST-INSTALLATION CHECK S

2.4.1 KTR 2280A MMDR Post-Installation Inspection and Ground Test

2.4.1.1 INSPECTION Table 2-6 Inspection/Check Procedure is a visual inspection/check procedure that must be performed after

system installation as part of a system checkout. A post-installation test per paragraph must be performed. In addition, the procedure must be used as a periodic maintenance inspection ch eck.

2.4.1.2 Ground Tests

Table 2-6 Inspection/Check Procedure

EQUIPMENT INSPECTION/CHECK PROCEDURE KTR 2280A

MMDR

Antennas A. Inspect external surfaces for dama ge.

(1) Perform the following inspections on the overall system:

(a ) Che ck th at ca bl es do no t i nt erf er e w it h a ir cra ft co nt rol s or ot her eq ui pme nt . (b) Check cabling for proper routing and check security of tie-down points. Inspect and adjust cable

runs to ensure that cables are not strained, kinked, or severely twisted and are not exposed to rough or sharp surfaces.

(2) System Interwiring Check

To check the aircraft and MMDR system interconnections proceed as follows:

A. Inspect external surface for damage. 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.

B. Check that antenna is properly mounted and mounting screws are tight.

C. Ensure that antenna coaxial cable connectors are properly mated and secure.

(a ) Ch ec k t ha t a ll ca bl es and interwiring are installed in accordance with the interwiring and cable

harness fabrication instructions (refer to paragraph 2.3.5.1 KTR 2280A Interconn ection and Cable Harness Fabrication).

(b ) Us in g th e ap pli ca ble interconnection information, check wiring for proper destinations, opens

and shorts.

(c ) C hec k RF ca ble s f or in se rti on lo ss an d VSW R.

(3) Visual Inspection

In conjunction with system installation, perform the inspection/check procedure. Refer to Table 2-6 Inspection/Check Procedure.

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2.4.1.2 Ground Tests

(1 ) P ost -I nst al lat io n T es t ( NA V/C OM Fu nc tio na lit y)

Pe rfo rm a g rou nd c hec k of t he in st all at ion b ef ore t he f li ght t es t . U sin g a lo ca l fr eq uency, confirm

that the COM function can receive and transmit a modulated si gnal. Using a ramp tester, confirm that VOR, LOC, and GS needle deflections move in the correct direction, the To/F rom flag is the proper sense, and that the warning flags are functioning properly. Check all aircraft control movements to be sure no electrical cables interfere with their operation.

CAUTION: AS AN ADDED PRECAUTION BEFORE ANY FLIGHT TESTS, CHECK THE ANTENNA.

VSWR MUST 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.

NOTE: Installed system transmitter power may show considerably less that the manufacturer’s rating of

16 W (minimum). There are several reasons for this:

1. It i s n o t u nc omm on f or a n i nst al lat io n to h av e up t o a s mu ch a s 1 dB o f R F tr an smi ss ion line cable loss. This would reduce a 16 W transmitter output to 12.7 W.

2. RF power meter test equipment that has an accuracy of ± 0.3 dB would cause power reading variations as high as ± 1 W.

3. Th e e ffe ct of antenna VSWR in a given installation will affect the output power. The VSWR is a function of the antenna design itself, aircraft skin properties and proximate metallic features of the airframe, and the size of the metallic surface the antenna is bonded to. Note that the committees that wrote the Minimum Operation Performance Standards to which the VHF COM system is TSO’d are aw are of this characteristic. They have established that transmitter power for a 16 W (minimum) transmitter must not drop below 8.0 W into a 2:1 VSWR and 6.4 W into a 3:1 VSWR (Refer to RTCADO-186B and Eurocae ED-23C).

(2 ) P os t-I ns tal lat io n T es t ( AD F F un cti on ali ty )

A qu ic k pr eli min ar y ch eck can b e ma de b y tu nin g to a loc al A M br oad ca st st at ion or a strong

NDB station. Check for satisfactory audio (this must be done where clear reception is possible, preferably outside of the hangar).

(a ) Qu ad ran ta l E rr or Ad jus tm ent s T he s ys t em h as b ee n fa ct ory a dj ust ed t o c om pe n sa te f or a t ypi ca l ai rfr am e. T he ref or e,

little or no compensation must be required. Nonetheless, the KTR 2280A provides software adjustment of Quadrantal Error (the average amount of quadrantal error (QE) that exists due to the shape of the airframe). The values for these alignments are stored within the aircraft system maintenance computer and downloaded to the KTR 2280A on power up. If this download does not occur the KTR 2280A uses the last values that were loaded.

T he KA 44B A DF ant en na, li ke m os t m ode rn AD F a nt enn as , c an hav e inh ere nt er ro rs

at the quadrantal (45°, 135°, 225° and 315°) bearings re lative to the antenna’s boresite. The following procedure details the process for setting a KTR 2280A configuration parameter to allow the radio to automatically compensate for these inherent errors. It is very important that this procedure be followed exactly as stated to ensure these quadrantal bearings are properly compensated.

T his pr oc edu re ca n b e c ar rie d out at an y loc at ion , h ow eve r car e m us t b e e xe rci se d t o

ensure that the chosen location is magnetically “clean”. Usually an airfield’s compass

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rose location is a good choice since magnetically “clean” is one of the criteria for establishing compass rose location.

NOTE: Ensure that QE = 0 is the value being fed or the last value that was fed to the KTR

2280A before performing this procedure.

1. Po int th e n ose of the aircraft directly at the emitter (NDB or AM broadcast radio station) being used for this purpose. Confirm this orientation by verifying the ADF indicator’s bearing pointer is pointing directly to the lubber line (aircraft nose reference).

2. Re cor d th e magnetic heading of the aircraft using the aircraft directional gyro or magnetic compass.

3. Us ing th e a ir cra ft ’s dir ec tio na l g yro or ma gn eti c c om pas s as a g ui de, ro ta te the ai rc raf t 45° to the left such that the aircraft magnetic head ing is now 45° less that the value found in Step 2.

4. Re cor d t he num be r of de gre es by w hi ch t he AD F be ar ing ha s mo ve d re la tiv e t o th e ADF indicator’s lubber line. (This number must be a positive number and must be approximately 45°.) Log this number as Bearing_45.

5. Us ing th e a ir cra ft ’s dir ec tio na l g yro or ma gn eti c c om pas s as a g ui de, ro ta te the ai rc raf t another 45° to the left so that the aircraft magnetic heading is now 90° less than the value found in Step 2.

6. Record the number of degrees by which the ADF bearing indication has moved relative to the ADF indicator’s lubber line. (This number must be a positive number and must be approximately 90°.)

7. Co nf ir m th at th e val ue in S tep 6 i s wit hin ± 5° of 90°. If not, the aircra ft ha s a m agn etic anomaly that precludes the ability to calculate an acceptable QE adjustment The QE alignment process must terminate at this point and not resume until any air craft related anomalies have been corrected. (Note: Problems with this step could also be due to the airfield location where the QE alignment procedure is being performed if that location is not magnetically “clean”.)

8. Us ing th e a ir cra ft ’s dir ec tio na l g yro or ma gn eti c c om pas s as a g ui de, ro ta te the ai rc raf t another 45° to the left so that the magnetic heading is now 135° less than the value found in Step 2.

9. Record the number of degrees by which the ADF bearing indication has moved relative to the ADF indicator’s lubber line. (This number must be a positive number and must be approximately 135°.) Log this number as Bearing_135.

10 . Usi ng t he a ir cra ft ’s directional gyro or ma gnetic compa ss as a guide, ro tate the aircra ft

another 45° to the left so that the aircraft magnetic heading is now 180° less than the value found in Step 2.

11. Record the number of degrees by which the ADF bearing indication has moved relative to the ADF indicator’s lubber line. (This number must be a positive number and must be approximately 180°.)

12 . Con fi rm t he v al ue r ec ord ed i n S tep 11 i s w ith in ± 5° of 180°. If not, the aircraft has a

magnetic anomaly the precludes the ability to calculate an acceptable QE adjustment. The QE alignment process must terminate at this point and not resume until the aircraft related anomalies have been corrected. (Note: Problems with this step could also be due to the airfield location where the QE alignment proce dure is being performed if that location is not magnetically “clean”.)

13 . Usi ng t he a ir cra ft ’s directional gyro or ma gnetic compa ss as a guide, ro tate the aircra ft

another 45° to the left so the aircraft magnetic heading is now 225° less than the value found in Step 2.

14. Record the number of degrees by which the ADF bearing indication has moved relative to the ADF indicator’s lubber line.

(T his num be r mu st be a po sit iv e nu mbe r a nd m us t be ap pro xi mat el y 22 5°.) Log this

number as Bearing_225.

15 . Usi ng t he a ir cra ft ’s directional gyro or ma gnetic compa ss as a guide, ro tate the aircra ft

another 45° to the left so that the aircraft magnetic heading is now 270° less than the value found in Step 2.

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16. Record the number of degrees by which the ADF bearing indicator has moved relative the ADF indicator’s lubber line (This number must be a positive number and must be approximately 270°.)

17 . Co nf irm the val ue r ec or de d in S te p 16 i s wi th in ± 5 ° of 270°. If not, the aircraft has a

magnetic anomaly that precludes the ability to calculate an acceptable QE adjustment. The QE alignment process must terminate at this point and not resume until the aircraft related magnetic anomalies have been corrected. (Note: Problems with this step could also be due to the airfield location where the QE alignment procedure is being performed if that location is not magnetically “clean”.)

18 . Us in g t he air cr aft ’s directional gyro or magnetic compass as a guide, rotate the aircraft

19. Record the number of degrees by which the ADF bearing indicator has moved relative

20 . Us in g t he fo ll owi ng fo rm ula s, ca lcu la te th e Q E off se t: QE_45 = 45 - Bearing_45 (This could be a negative number if Bearing_45 is > 45) QE_135 = Bearing_135 - 135 (This could be a negative number if Bearing_135 is <

QE_225 = 225 - Bearing_225 (This could be a negative number if Bearing_225 is > QE_315 = Bearing_315 - 315 (This could be a negative number if Bearing_315 is < QE = (( QE _45 ) + ( QE _13 5) + (Q E _2 25 ) + ( QE _3 15 )) / ( 4)

21. Enter the value calculated in Step 20 into the KTR 2280A Parameter table per 2.5 KTR

22. Recheck the relative bearings abd readjust the QE compensation as necessary to split

(b ) Op er ati on al Ch eck s

The following operational checks are to verify proper operation of the

ADF function of the KTR 2280A and can be made with the aircraft in the parking area.

1. P la ce th e A DF in the ANT mode and tune in several known stations. Verify that audio

2. S el ect t he B FO f un cti on t o e nt er th e B FO mo de a nd v er ify t ha t th e B FO t on e is p re s en t

another 45° to the left so that the aircraft magnetic heading is now 315° less than the value found in Step 2.

to the ADF indicator’s lubber line. (This number must be a positive number and must be approximately 315°.) Log this number as Bearing_31 5.

135)

225)

315)

2280A INSTALLATION PARAMETER MODIFICATIONS. the error at the quadrantal points (45°, 135°, 225° and 315°) to obtain the lowest pos-

sible error.

reception is satisfactory and that volume control operation is normal. Verify that the ADF indicator needle is parked at the 90 degree position rel ative to the noise of the aircraft. Place the unit in the ADF mode and verify that the needle points to the station.

in the receiver audio (if a keyed CW station is used the tone heard will be the coded identifier).

2.4.2 KTR 2280A Post-Installation Flight Tests

2.4.2.1 COM TRANSCEIVER FLIGHT TEST To check the COM transceiver, maintain altitude of at least 1500 feet and contact a ground station

facility at a range of at least fifty nautical miles. Contact a ground station close in. Disable the automatic squelch and listen for any unusual electrical 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. Ensure that the COM mode selector is capable of individually selecting all three modes (one mode at a time).

2.4.2.2 NAV RECEIVER FLIGHT TEST To check the VOR/ILS system, select a VOR frequency within a forty nautical mile range. Listen to the

VOR audio and ensure that no electrical interference such as magneto noise is present. Check the tone

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identifier filter operation. Fly inbound and 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 present. To check the localizer and glideslope functions, select an appropriate ILS frequency an d fly an approach

to the proper runway. Check for proper LEFT-RIGHT and UP-DOWN indications.

2.4.2.3 ADF RECEIVER FLIGHT TEST Confirm that bearing indications to several local NDB facilities appear reasonable. Listen to the ADF

audio and ensure that no unusual electrical interference is present.

2.5 KTR 2280A INSTALLA TION PARAMETER MODIFICATIONS

The KTR 2280A has several parameters that can be adjusted during installation in order to conform the unit to a given installation. Parameter modifications must only be performed by a qualified avionics technician. Table 2-7 Unit Parameters, lists the KTR 2280A adjustments accessible by the technician to facilitate the unit installation.

NOTE: KTR 2280A units sent to the factory for repair will be returned to service with their factory defaults

reset as shown in Table 2-7 Unit Parameters.

The method for setting these parameters is a function of the specific installed system and the user interface used for personality module settings. Refer to the appropriate STC Installation Manual for specific instructions. The KTR 2280A responds to installed system personality module settings through high speed ARINC 429 labels 300, 301, 302, and 303. These labels occur periodically at a 1 Hz rate.

T

Parameter

Table 2-7 Unit Parameters

MMDR Factory

Default

Minimum

Setting

Maximum

Setting

Resolution

COM Carrier Squelch (-dBm) 88 85 100 1 COM Emergency Freq. (MHz) 121.500 118.000 136.990 *

COM Emergency Volume (dB) COM Sidetone Level (dB)

1

20 0 72 1

52 0 72 1 COM Squelch (SNR dB) 12 3 20 1 COM Microphone Gain

2

21 0 31 ** QE Offset (degrees) 0 -20 +20 0.1

* 8.33 kHz channel spacing ** Each resolution increment is equivalent to 1.5 dB. Total range is -31.5 dB to 15.0 dB

NOTE: 1: This setting represents attenuation (in dB) relative to ra te d au d io ou tp ut level. NOTE: 2: This setting is a relative number only. Each numeric value represents a change of 1.5 dB.

Nominal setting, which represents the level provided by typical microphones, is the default

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numeric value of 21. This control provides amp lification (for unusually weak microphones) of up to 15 dB (setting of 31) or attentuation (for extra sensitive microphones) of up to 31.5 dB (setting of 0) relative to the default.

2.6 ARINC 429 INTERFACE The KTR 2280A has three high speed ARINC 429 transmitters and three high speed ARINC 429 r eceivers. All

labels are transmitted on both transmit channels. The same data is transmitted over both channels

Table 2-8 ARINC 429 Output Labels

Function Label Parameter Interval (ms)

NAV 034 VOR/ILS Frequency 200

053 VOR/ILS Standby (Preset) Frequency 200 173 Localizer Deviation 100 174 Glideslope Deviation 100 222 VOR Bearing 100 242 VOR/ILS Station Ident (Characters 1-2) 200 244 VOR/ILS Station Ident (Characters 3-4) 200 265 VOR/ILS Volume 200

COM 030 VHF COM Frequency 200

047 VHF Aux/Guard COM Frequency 200 052 VHF COM Standby (Preset) Frequency 200 263 VHF Aux/Guard COM Frequency 200 266 VHF COM Volume 200 267 VHF COM Status 200

ADF 032 ADF Frequency 200

162 ADF Bearing 100 262 ADF Volume 200

CMC 350 Member System Status 1000

352 MMDF System Fault Report 1000 377 Member System Identification 1000

VDL 172 System Address Label (SAL) 1000

270 VDR Status Word 1000

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Function Label Parameter Interval (ms)

VDL 304 Williamsburg BOP Burst

377 VDR Equipment ID 1000

VDB 033 Landing Mode/Frequency 200

045 Message Block Start Burst 046 Message Block Data Burst

* MMDR hardware fault (BIT 19 in Label 352) is set when the unit detects a hardware fault and/or

malfunction of the hardware that can result in incorrect data.

Table 2-9 ARINC 429 Input Labels

Function Label Parameter Interval (ms)

NAV 034 Set VOR/ILS Frequency 200

053 Set VOR/ILS Standby (Preset) Frequency 200 265 Set VOR/ILS Volume 200

COM 030 Set VHF COM Frequency 200

047 Set VHF Aux/Guard COM Frequency 200 052 Set VHF/COM Standby (Preset) Freq ue n cy 200 263 Set VHF Aux/Guard COM Volume 200 266 Set VHF COM Volume 200

ADF 032 Set ADF Frequency 200

262 Set ADF Volume 200

CLOCK 150 GMT (UTC) 1000

260 Date 1000 FLIGHT 151 Flight Leg 1000 APM 300 MMDR Configuration Options #1 1000

301 MMDR Configuration Options #2 1000

302 MMDR Configuration Options #3 1000

303 MMDR Configuration Options #4 1000

304 MMDR Configuration Options #5 1000

305 MMDR Configuration Options #6 1000

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Function Label Parameter Interval (ms)

CMC 227 CMC Command and Control 1000 VDB 033 Landing Mode/Frequency 200 VDL 172 System Address label 1000

214 Aircraft ICAO Address #1 1000

216 Aircraft ICAO Address #2 1000

251 Williamsburg BOP VDR #1 Burst

252 Williamsburg BOP VDR #2 Burst

253 Williamsburg BOP VDR #3 Burst

270 Apex CMU Status Word 1 1000

276 Apex CMU Status Word 2 1000

276 VDR Mode Command 500

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SECTION 3

OPERATION

3.1 GENERAL The KTR 2280A is a remote mounted radio. As such, the user interface is defined by controllers and displays

unique to the particular system configuration. Refer to the appropriate pilot’s guide or flight manual supplement for complete operating instructions.

The paragraphs below provide an overview of the controls and displays that are typically available in systems that provide full KTR 2280A functionality.

3.1.1 VHF COM Controls and Displays A. Frequency Selectors: An active frequency (channel) and a standby frequency (channel)

selector. A “swap” or “flip-flop” button may be available for swapping the active and standby frequencies. The KTR 2280A responds to high speed ARINC 429 labels 030 and 052 for the active and standby selections respectively. These labels appear only when a frequency (channel) change is made.

B. Volume Control: A rotational knob or up/down pushbutton to adjust the volume of the COM

audio output. The KTR 2280A responds to high speed ARINC 429 label 266 for the COM volume control setting. This label appears only when a volume change is made.

C. RX/TX Annunciators: Some display means indicate when the radio is transmitting (TX

Annunciator) and when the radio is receiving (RX Annunciator). This is keyed by the squelch status. The KTR 2280A outputs the RX status and TX status on the high speed ARINC 429 label 267, having a 5 Hz update rate.

D. Squelch Disable Control: Normally a pushbutton that cycles between Squelch Disable and

Squelch Enable. The RX annunciator will be displayed during Squelch Disable. The KTR 2280A responds to high speed ARINC 429 label 266 for COM squelch disable (override). This label appears only when a status change is made.

E. Stuck Microp ho n e Annu nc iator: Some display means to indicate when the Pus h-to -T a lk (PTT )

button has been held down beyond the 30 seco nd transmitter time-out per iod. The KTR 2280A outputs the stuck microphone alert on high speed ARINC 429 label 267, having a 5 Hz update rate.

F. Emergency COM Control: Some means to channel the KTR 2280A transmitter and receiver to

a pre-defined emergency frequency (ch an nel) in the event of display and/or control failure. Pin 26 on main connector J1 (Refer to Figure 2-24 KTR 2280A Interconnect Diagram) is the discrete control for this function. Grounding this normally open pin places the unit into Emergency COM Mode.

G. AUX COM channel and volume controls are typically not available. These parameters can be

adjusted through APM settings.

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3.1.2 VHF NAV Controls and Displays A. Frequency Selectors: An active frequency (channel) and a standby frequency (channel)

selector. A “swap” or “flip-flop” button may be available for swapping the active and standby frequencies. The KTR 2280A responds to high speed ARINC 429 labels 034 and 053 for the active and standby selections respectively. These labels appear only when a frequency (channel) change is made.

B. Volume Control: A rotational knob or up/down pushbutton to adjust the volume of the NAV

audio output. The KTR 2280A responds to high speed ARINC 429 label 265 for the volume control setting. This label appears only when a volume change is made.

C. Ident Tone Control: A means to defeat the Ident Tone notch filter in the NAV audio so the 1020

Hz Ident Tone can be heard. The KTR 2280A respon ds to high speed ARINC 4 29 label 265 for

ident filter control. This label only occurs when a status change is made. D. The NAV Station Ident is Output on Label 242 and 244. E. KTR 2280A responds to high speed ARINC 429 label 033 for VDB mode selection. This label

only occurs when a mode change is made.

KTR 2280A

3.1.3 ADF Controls and Displays A. Frequency Selectors: An active frequency (channel) and a standby frequency (channel)

selector. A “swap” or “flip-flop” button may be available for swapping the active and standby frequencies. The KTR 2280A responds to high speed ARINC 429 label 032 for frequency selection. This label only occurs when a frequency (channel) change is made.

B. Volume Control: A rotational knob or up/down pushbutton to adjust the volume of the ADF audio

output. The KTR 2280A responds to high speed ARINC 429 label 262 for volume setting. This label only occurs when a change is made.

C. Mode Control: A means to select the following ADF operating modes:

ADF Mode - The normal ADF operating mode. ANT Mode - The mode in which ADF bearing information is defeated and receiver sensitivity

and bandwidth are optimized for audio recep tio n only. BFO Mode - The mode required in order to use first generation NDB facilities that used on/off carrier keying for identification.

The KTR 2280A responds to high speed ARINC 429 label 032 for mode selection. This label only occurs when a change is made.

3.1.4 VDL Mode A and VDL Mode 2 A. VDL Mode A

Mode A allows the KTR 2280A to exchange downlink and uplink POA data messages with a CMF through a transmit/receive pair of 100 Kbps ARINC 429 digital interfaces.

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The downlink message data bits transferred to the KTR 2280A modulate the RF carrier at a rate of 2,400 bps using the DSB-AM MSK modulation scheme.

The KTR 2280A also controls when to access the channel to transmit data. The data link channel selection is still controlled by the CMF , but channel selection messages are exchanged through the same high-speed ARINC 429 interface used to exchange AOA messages which simplifies wiring.

BVDL Mode 2

VDL Mode 2 is the term used to describe a suite of air /ground protocols that increase s the data rate of the air/ground link to 31,500 bps.

VDL Mode 2 allows the transition from character-oriented ACARS protocols for end-to-end delivery of messages to one that uses bit-o rient ed ATN protocols using the same VHF ground and aircraft radios. The KTR 2280A Mode 2 capability supports the transmission and reception of standard ACARS messages using a protocol referred to as AOA.

The KTR 2280A Mode 2 capability also supports the transmission and reception of bit-oriented

ATN application messages such as CPDLC. The set of VDL Mode 2 protocols consist of the physical layer protocol, channel access protocol, data link service and management protocol, and Mode 2 network access protocol. The physical layer protocol includes the modulation, data rate, and forward error correction techniques used to transmit data over the air/ground link.

The channel access protocol is the method that allows multiple aircraft to communicate with the ground stations on the same frequency. The data link service and management protocol includes procedures to establish, maintain and hand-off an air/ground link, and ensure error-free delivery of messages . The network access protocol is the interface between users and the Mode 2 air/ground link service providers. As in Mode A, only the physical layer and channel access protocols are performed by the KTR 2280A while the data link service and management, and the network access protocols are performed by the CMF.

The VDL Mode 2 physical layer protocol employs a bit transmission rate of 31,500 bps over the

air/ground link on a single 25-kHz channel. The increased utilization of the 25-kHz channel is achieved by use of a bandwidth modulation scheme known as D8PSK. A D8PSK transmitter transmits a carrier whose phase is modulat ed by the data. The phase can be 0, 45, 90, 135, 180, 225, 270, or 315 degrees. The rate at which the carrier p hase is changed is the modulation rate.

The phase difference or D8PSK symbol between successive phase changes can be equal to 0, 45, 90, 135, 180, 225, 270, or 315 degrees. Since there are eight possible phase differences, each phase change (D8PSK symbol) represents three bits of information: 000, 001, 011, 010, 110, 111, 101, or 100.

For example, if the phase changes at a 10.5-kHz rate, the bit transm ission rate is equal to 31.5 Kbps. The VDL Mode 2 D8PSK modulator uses the bits in the message, three at a time, to select the carrier phase change at a rate of 10 ,500 D 8PSK sym bols e ach seco nd. A 10 .5-k Hz D8PSK phase modulation rate corresponds to a D8PSK bit transmission rate of 31.5 Kbps.

The VDL Mode 2 channel access protocol is CSMA modifi ed to let all terminals to hav e equal chances to access the channel when multiple terminals have data to transmit. The ability to

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optimize the CSMA protocol is included in the VDL Mode 2 channel access protocol specification.

As in Mode A, the Mode 2 data link channel selection is controlled by the CMF through the same high-speed ARINC 429 interface used to exchange downlink and uplink AOA or ATN messages. The CMF also dynamically controls the switching between Mode A and Mode 2 operation subject to available coverage. Since the VDL Mode 2 data rate and modulation scheme differ from those used in Mode A, separate VHF frequencies and ground-based VHF equipment must be used to give POA and AOA/ATN service coverage. As a result, the availability of high-speed AOA service depends on the availability of ground stations.

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APPENDIX A

KTR 2280A MMDR TRANSCEIVER

ENVIRONMENTAL QUALIFICATION FORMS

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KA 44B ENVIRONMENTAL PERFORMANCE

The KA 44B ADF Antenna (Honeywell PN 071-1234-00) 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 Categor y TT fields as de fined in th e 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 dur ing th e HIRF e xposur e a nd the unit r etur ned

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 ou t 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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APPENDIX B

DEVIATIONS

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Honeywell KTR2280A User Manual

Specifications and Main Features

Frequently Asked Questions

User Manual

TRANSMITTAL INFORMATION

RECORD OF REVISIONS

RECORD OF TEMPORARY REVISIONS

LIST OF EFFECTIVE PAGES

TABLE OF CONTENTS

1. How to Use This Manual

INTRODUCTION

2. Customer Support

3. References

4. Acronyms and Abbreviations

SECTION 1

GENERAL INFORMATION

SECTION 2

INSTALLATION

SECTION 3

OPERATION

APPENDIX A

APPENDIX B