Honeywell KMH820 Multi-Hazard Awareness unit User Manual KTA870

Honeywell International Inc. Multi-Hazard Awareness unit KTA870

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PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICESYSTEM INSTALLATIONMANUALKMH 880/KTA 870MULTI-HAZARD AWARENESS SYSTEM/TRAFFIC ADVISORY SYSTEMMANUAL NUMBER 006-10609-0000REVISION 0 OCTOBER, 2000

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEWARNINGPRIOR TO THE EXPORT OF THIS DOCUMENT, REVIEW FOR EXPORT LICENSEREQUIREMENT IS NEEDED.COPYRIGHT NOTICE ©2000 HONEYWELL INTERNATIONAL INC.Reproduction of this publication or any portion thereof by any means without the express written permission of Honeywell Interna-tional Inc. is prohibited. For further information contact the Manager, Technical Publications,Honeywell International Inc., ONE TECHNOLOGY CENTER, 23500 West 105th Street, Olathe KS 66061 Tele-phone: (913) 782-0400.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEThe binder(s) required to hold this publication(s) are available at an additional cost and may be ordered from:HoneywellOne Technology Center23500 West 105th StreetOlathe, Kansas, 66061Telephone 1-800-757-8999Orders must specify part number, description, and the quantity. Use the following list to complete the orderPART NUMBER DESCRIPTION006-03140-0001 (1) inch Binder.006-03140-0002 (1.5) inch Binder.006-03140-0003 (2) inch Binder.006-03140-0004 (3) inch Binder.006-03140-0005 (4) inch Post Binder.WARNINGPrior to Export of this Document, review for export license requirement is needed.COPYRIGHT NOTICE ©2000 Honeywell International Inc.Reproduction of this publication or any portion thereof by any means without the express writtenpermission of Honeywell International Inc. is prohibited. For further information contact the Man-ager, Technical Publications, Honeywell International Inc., One Technology Center, 23500 West105th Street Olathe KS 66061 Telephone: (913) 782-0400.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page R- 1REVISION HISTORY AND INSTRUCTIONSMANUAL KMH 880/KTA 870 System Install ManualREVISION 0, October, 2000PART NUMBER 006-10609-0000Add, delete or replace pages as indicated below and retain all tabs and dividers. Insert this page immediately behind the title page as a record of revisions. This revision level of this manual consists of the following individual publications: PAGE ACTION Initial Release Insert Entire Manual

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH880/KTA 870Page R- 2 10609I00.ZIPCDL Rev 0, October/2000THIS PAGE IS RESERVED

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL TOC- iSECTION IGENERAL INFORMATION 1.0 INTRODUCTION .................................................................................... 1.11.1 PURPOSE .............................................................................................. 1-11.2 APPLICABILITY OF THE SYSTEM MANUAL ....................................... 1-21.2.1 Equipment Applicability .......................................................................... 1-21.3 SYSTEM DESCRIPTION ....................................................................... 1-21.3.1 Basic EGPWS System ........................................................................... 1-21.3.2 Basic TAS System ................................................................................. 1-31.3.3 System Components .............................................................................. 1-31.3.4 System Operation .................................................................................. 1-51.4 TECHNICAL CHARACTERISTICS ........................................................ 1-91.5 UNIT AND ACCESSORIES SUPPLIED ................................................ 1-121.5.1 TAS Processor Unit ................................................................................ 1-121.5.2 Configuration Module ............................................................................. 1-121.5.3 Antennas ................................................................................................ 1-131.6 INSTALLATION ACCESSORIES SUPPLIED ........................................ 1-141.6.1 KMH 820/KTA 810 Installation Kit .......................................................... 1-141.6.2 Antenna Installation Kits.......................................................................... 1-151.6.3 Databases............................................................................................... 1-151.7 ACCESSORIES REQUIRED BUT NOT SUPPLIED .............................. 1-161.7.1 Temperature Probe ................................................................................ 1-161.7.2 GPS Antenna Splitter.............................................................................. 1-161.7.3 Miscellaneous ........................................................................................ 1-171.7.4 Cable And Wire ...................................................................................... 1-171.8 LICENSE REQUIREMENTS .................................................................. 1-171.9 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ...................... 1-171.9.1 KMH 820/KTA 810 Unit........................................................................... 1-181.9.2 Annunciators/Relays ............................................................................... 1-181.9.3 GPS Antenna .......................................................................................... 1-181.9.4 Gps Antenna Splitter............................................................................... 1-181.9.5 Temperature Probe................................................................................. 1-181.9.6 Wire and Coax Cables ............................................................................ 1-191.9.7 Terrain Data Base Updates..................................................................... 1-19

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870TOC- ii 10609I00.ZIPCDL Rev 0, October/2000LIST OF ILLUSTRATIONSFigure 1-1 KMH 880/KTA 870 System ......................................................... 1-5LIST OF TABLESTable 1-1 KMH 880/KTA 870 Applicable Versions ...................................... 1-2Table 1-2 KMH 880 LRUs ........................................................................... 1-4Table 1-3 KTA 870 LRUs ............................................................................ 1-4Table 1-4 KMH 820 w/o GPS Multi-Hazard Unit Technical Specifications .. 1-9Table 1-5 KMH 820 w/ GPS Multi-Hazard Unit Technical Specifications..... 1-9Table 1-6 KTA 810 Traffic Advisory Unit Technical Specifications .............. 1-10Table 1-7 CM 805 Configuration Module Technical Specifications ............. 1-10Table 1-8 KA 815 Traffic Antenna Technical Specifications ........................ 1-11Table 1-9 KA 92 GPS Antenna Technical Specifications ............................ 1-11Table 1-10 KMH 820/KTA 810 Processor Units ............................................ 1-12Table 1-11 CM 805 Configuration Module ..................................................... 1-12Table 1-12 KA 815/KA 92 Antennas .............................................................. 1-13Table 1-13 GPS Cable Run Lengths ............................................................. 1-13Table 1-14 KMH 820/KTA 810 Installation Kit .............................................. 1-14Table 1-15 KA 815 Installation Kit ................................................................ 1-15Table 1-16 KA 92 Installation Kit .................................................................. 1-15Table 1-17 Data Bases................................................................................... 1-15Table 1-18 Temperature Probe ..................................................................... 1-16Table 1-19 GPS Antenna Splitter ................................................................... 1-16Table 1-20 Miscellaneous Accessories ......................................................... 1-17Table 1-21 Cable and Wire ............................................................................ 1-17SECTION II INSTALLATION2.0 INTRODUCTION .................................................................................... 2-12.1 UNPACKING AND INSPECTING EQUIPMENT .................................... 2-12.2 EQUIPMENT INSTALLATION ............................................................... 2-12.2.1 General ................................................................................................ 2-12.2.2 Avionics Cooling Requirements ........................................................... 2-22.2.3 Processor Installation ........................................................................... 2-22.2.3.1 Cooling Considerations ..................................................................... 2-22.2.3.2 Installation Considerations ................................................................ 2-22.2.3.3 Installation Procedure ....................................................................... 2-42.2.4 Configuration Module Installation.......................................................... 2-92.2.4.1 Cooling Considerations ..................................................................... 2-9

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL TOC- iii2.2.4.2 Installation Considerations ................................................................ 2-92.2.4.3 Installation Procedure ....................................................................... 2-92.2.5 Directional Antenna Installation ............................................................ 2-132.2.5.1 KA 815 Antenna Installation Considerations ..................................... 2-132.2.6 GPS Antenna Installation ..................................................................... 2-172.2.6.1 KA 92 antenna Installation Considerations (KMH 820 EGPWS only) . 2-172.2.6.2 Installation Procedure ....................................................................... 2-172.2.7 TAS Coaxial Cable Fabrication............................................................. 2-262.2.8 GPS Coaxial Cable Fabrication ............................................................ 2-27LIST OF ILLUSTRATIONSFigure 2-1 KMH 820/KTA 810 Installation Drawing....................................... 2-5Figure 2-2 Configuration Module Installation Drawing................................... 2-11Figure 2-3 KA 815 Antenna Outline and Mounting Drawing ......................... 2-15Figure 2-4 KA 815 Antenna Installation Drawing........................................... 2-19Figure 2-5 KA 815 Doubler Plate Drawing..................................................... 2-21Figure 2-6 KA 92 Outline and Mounting Drawing ......................................... 2-23Figure 2-7 GPS Antenna Splitter ................................................................... 2-25Figure 2-8 Coax Cable Treatment ................................................................. 2-28Figure 2-9 Standard Coax Cable................................................................... 2-28Figure 2-10 Bulkhead/In-Line Connection Coax Cable ................................... 2-28Figure 2-11 TNC Antenna Coax/Connector Assembly.................................... 2-29Figure 2-12 TNC Antenna Coax/Connector Assembly.................................... 2-30LIST OF TABLESTable 2-1 Signal Losses.............................................................................. 2-27SECTION IIISYSTEM PLANNING3.0 INTRODUCTION ................................................................................... 3-13.0.1 Applicable Part Numbers Subsection Description ................................ 3-13.0.2 Function Subsection Description .......................................................... 3-13.0.3 Requirements and Limitations Subsection Description. ....................... 3-13.0.4 Electrical Characteristics Subsection Description. ............................... 3-13.0.5 Interface Subsection Description ......................................................... 3-13.1 GENERAL INTERCONNECT INFORMATION ...................................... 3-53.1.1 Power Inputs ..................................................................................... 3-53.1.2 Air/Ground Discrete Input ................................................................. 3-53.1.3 Landing Gear Discrete Input ............................................................. 3-63.1.4 Above/Below/Normal Input ............................................................... 3-63.1.5 Baro Altitude (ARINC 429) Input ....................................................... 3-73.1.6 Advisory Inhibit Input ........................................................................ 3-7

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870TOC- iv 10609I00.ZIPCDL Rev 0, October/20003.1.7 TAS Valid Output .............................................................................. 3-73.1.8 Visual Annunciate Traffic (Lamp Output) .......................................... 3-83.1.9 Synthesized Voice Output ................................................................ 3-83.1.10 Air Temperature Input ....................................................................... 3-93.1.11 GPS Input ......................................................................................... 3-93.1.12 Factory Test Input ............................................................................. 3-103.1.12.1 TAS ATE Enable Input ................................................................... 3-103.1.12.2 TAS Built In Test Equipment (BITE) .............................................. 3-103.1.12.3 EGPWS Self Test Input ................................................................. 3-113.1.12.4 Display Select Input ....................................................................... 3-123.1.12.5 Terrain Awareness Inhibit Discrete ................................................ 3-123.1.13 Terrain Warning ................................................................................ 3-123.1.14 Terrain Caution.................................................................................. 3-123.1.15 Weather Select Output ..................................................................... 3-123.1.16 EGPWS Audio On Discrete .............................................................. 3-133.1.17 EGPWS Terrain Inop and Terrain Not Available Output.................... 3-13LIST OF ILLUSTRATIONSFigure 3-1 KMH 880/KTA 870 Interconnect Family ...................................... 3-3Figure 3-2 KMH 820/KTA 810 Pinout Diagram ............................................. 3-15Figure 3-3 KMH 820/KTA 810 System Interconnect Block Diagram ............. 3-29Figure 3-4 KMH 820/KTA 810 Power Interface ............................................ 3-33Figure 3-5 KMH 820/KTA 810 Discrete Interface ......................................... 3-35Figure 3-6 KMH 820/KTA 810 Configuration Module Interconnect ............... 3-37Figure 3-7 KMH 820/KTA 810 Attitude/Heading Interface............................. 3-39Figure 3-8 KMH 820/KTA 810 Radar/Barometric Altitude Interface ............. 3-41Figure 3-9 KMH 820/KTA 810 Antenna/Suppression Interface .................... 3-49Figure 3-10 KMH 820/KTA 810 EFS 40/50 Interface .................................... 3-51Figure 3-11 KMH 820/KTA 810 GS 362A Interface ....................................... 3-53Figure 3-12 KMH 820/KTA 810 Honeywell GS 362A Interface ....................... 3-59Figure 3-13 KMH 820/KTA 810 Collins GS 362A Interface ............................. 3-65Figure 3-14 KMH 820/KTA 810 Honeywell Primus 1000 Interface.................. 3-69Figure 3-15 KMH 820/KTA 810 Honeywell SPZ-805 Interface........................ 3-73Figure 3-16 KMH 820/KTA 810 Diagnostic/Data Recorder Interface ............. 3-77Figure 3-17 KMH 820/KTA 810 TAS ATE Interface ....................................... 3-79Figure 3-18 KMH 820/KTA 810 CP 66B Interface........................................... 3-81Figure 3-19 KMH 820/KTA 810 KFS 578A Interface....................................... 3-83Figure 3-20 KMH 820/KTA 810 Display Interface............................................ 3-87Figure 3-21 KMH 820/KTA 810 Processor Front Connector .......................... 3-95Figure 3-22 KMH 820/KTA 810 Front Connector Cable.................................. 3-96LIST OF TABLESTable 3-1 KMH 820/KTA 810 Connector Pin Assignment ........................... 3-97

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL TOC- vSECTION IV POST INSTALLATION CONFIGURATION AND CHECK OUT 4.0 INTRODUCTION .................................................................................... 4-14.1 LINE SELECT KEYS .............................................................................. 4-14.2 CONFIGURATION PROCEDURE ......................................................... 4-14.2.1 Power On ............................................................................................. 4-14.2.2 Aircraft Configuration ........................................................................... 4-14.2.3 EGPWS Configuration Instructions....................................................... 4-14.2.3.1 Equipment needed................................................................................ 4-14.2.3.2 Configuration Module Programming ..................................................... 4-24.2.3.3 Configuration String Format.................................................................. 4-24.2.3.4 RS-232 Maintenance Port (Port SMC1)................................................ 4-34.2.3.5 RS-232 Diagnostic Port ........................................................................ 4-34.2.3.6 Configuration Sequence of Events ....................................................... 4-44.2.3.7 Configuration Types.............................................................................. 4-44.2.3.8 Configuration Tables............................................................................. 4-54.2.3.8.1 Category 1, Aircraft/Mode Type Select............................................... 4-64.2.3.8.2 Category 2, Air Data Input Select ....................................................... 4-64.2.3.8.3 Category 3, Position Input Select........................................................ 4-74.2.3.8.4 Category 4, Terrain Display Select ..................................................... 4-84.2.3.8.5 Category 5, Input/Output Discrete Type Select .................................. 4-94.2.3.8.6 Category 6, Audio Menu Select .......................................................... 4-94.2.3.8.7 Category 7, Audio Output Level.......................................................... 4-94.2.3.8.8 Category 8, Altitude Monitor Options.................................................. 4-104.2.3.8.9 Category 9, Terrain Display Alternate Pop Up Option ........................ 4-104.2.4 TAS Configuration Options .................................................................. 4-114.2.4.1 TAS RS-232 Maintenance Port.............................................................. 4-134.2.4.2 TAS RS-422 Data Recorder .................................................................. 4-144.3 GROUND TEST PROCEDURES ........................................................... 4-144.3.2 EGPWS Ground Test Procedures ......................................................... 4-144.3.3 TAS Ground Test Procedures................................................................ 4-17LIST OF ILLUSTRATIONSFigure 4-1 TAS Bearing Measurements............................................................ 4-34LIST OF TABLESTable 4-1 Configuration Identification........................................................... 4-4Table 4-2 Aircraft/Mode Type Select............................................................ 4-6Table 4-3 Air Data Input Select .................................................................... 4-6

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870TOC- vi 10609I00.ZIPCDL Rev 0, October/2000Table 4-4 Position Input Select..................................................................... 4-7Table 4-5 Terrain Display Select .................................................................. 4-8Table 4-6 Input/Output DiscreteType Select ................................................ 4-9Table 4-7 Audio Menu Select ....................................................................... 4-9Table 4-8 Audio Output Level....................................................................... 4-10Table 4-9 Altitude Monitor Option................................................................. 4-10Table 4-10 Terrain Display Alternate Pop Up Option ..................................... 4-11SECTION V CERTIFICATION 5.0 INTRODUCTION .................................................................................... 5-15.1 CERTIFICATION PROCEDURE ............................................................ 5-15.1.1 Equipment Compatibility ........................................................................ 5-15.1.2 Equipment Location ............................................................................... 5-15.1.3 Federal Communication Commission Rules .......................................... 5-15.1.4 TSO Category ........................................................................................ 5-25.1.5 FTZ Requirement ................................................................................... 5-25.1.6 FAA Requirements ................................................................................. 5-25.1.7 FAA Form 337 ........................................................................................ 5-25.1.8 Flight Manual Revision ........................................................................... 5-25.1.9 Pilot Briefing ........................................................................................... 5-3SECTION VIOPERATION6.0 INTRODUCTION..................................................................................... 6-1LIST OF APPENDICESAPPENDIX A Mode C..................................................................................... A-1APPENDIX B STC .......................................................................................... B-1APPENDIX C Cert .......................................................................................... CERT-1APPENDIX D TASDiag................................................................................... D-1APPENDIX E TSO.......................................................................................... TSO-1

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL TOC 1-iSECTION 1 GENERAL INFORMATION 1.0 INTRODUCTION .................................................................................... 1.11.1 PURPOSE .............................................................................................. 1-11.2 APPLICABILITY OF THE SYSTEM MANUAL ....................................... 1-21.2.1 Equipment Applicability .......................................................................... 1-21.3 SYSTEM DESCRIPTION ....................................................................... 1-21.3.1 Basic EGPWS System ........................................................................... 1-21.3.2 Basic TAS System ................................................................................. 1-31.3.3 System Components .............................................................................. 1-31.3.4 System Operation .................................................................................. 1-51.4 TECHNICAL CHARACTERISTICS ........................................................ 1-91.5 UNIT AND ACCESSORIES SUPPLIED ................................................ 1-121.5.1 TAS Processor Unit ................................................................................ 1-121.5.2 Configuration Module ............................................................................. 1-121.5.3 Antennas ................................................................................................ 1-131.6 INSTALLATION ACCESSORIES SUPPLIED ........................................ 1-141.6.1 KMH 820/KTA 810 Installation Kit .......................................................... 1-141.6.2 Antenna Iinstallation Kits......................................................................... 1-151.6.3 Databases............................................................................................... 1-151.7 ACCESSORIES REQUIRED BUT NOT SUPPLIED .............................. 1-161.7.1 Temperature Probe ................................................................................ 1-161.7.2 GPS Antenna Splitter.............................................................................. 1-161.7.3 Miscellaneous ........................................................................................ 1-171.7.4 Cable And Wire ...................................................................................... 1-171.8 LICENSE REQUIREMENTS .................................................................. 1-171.9 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ...................... 1-171.9.1 KMH 820/KTA 810 Unit........................................................................... 1-181.9.2 Annunciators/Relays ............................................................................... 1-181.9.3 GPS Antenna .......................................................................................... 1-181.9.4 Gps Antenna Splitter............................................................................... 1-181.9.5 Temperature Probe................................................................................. 1-181.9.6 Wire and Coax Cables ............................................................................ 1-191.9.7 Terrain Data Base Updates..................................................................... 1-19

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870TOC 1-ii 10609I00.ZIPCDL Rev 0, October/2000LIST OF ILLUSTRATIONSFigure 1-1 KMH 880/KTA 870 System .......................................................... 1-5LIST OF TABLES Table 1-1 KMH 880/KTA 870 Applicable Versions ...................................... 1-2Table 1-2 KMH 880 LRUs ........................................................................... 1-4Table 1-3 KTA 870 LRUs ............................................................................ 1-4Table 1-4 KMH 820 w/o GPS Multi-Hazard Unit Technical Specifications .. 1-9Table 1-5 KMH 820 w/ GPS Multi-Hazard Unit Technical Specifications..... 1-9Table 1-6 KTA 810 Traffic Advisory Unit Technical Specifications .............. 1-10Table 1-7 CM 805 Configuration Module Technical Specifications ............. 1-10Table 1-8 KA 815 Traffic Antenna Technical Specifications ........................ 1-11Table 1-9 KA 92 GPS Antenna Technical Specifications ............................ 1-11Table 1-10 KMH 820/KTA 810 Processor Units ............................................ 1-12Table 1-11 CM 805 Configuration Module ..................................................... 1-12Table 1-12 KA 815/KA 92 and Monopole Antennas ...................................... 1-13Table 1-13 GPS Cable Run Lengths ............................................................. 1-13Table 1-14 KMH 820/KTA 810 Installation Kit .............................................. 1-14Table 1-15 KA 815 Installation Kit ................................................................ 1-15Table 1-16 KA 92 Installation Kit .................................................................. 1-15Table 1-17 Data Bases................................................................................... 1-15Table 1-18 Temperature Probe ..................................................................... 1-16Table 1-19 GPS Antenna Splitter ................................................................... 1-16Table 1-20 Miscellaneous Accessories ......................................................... 1-17Table 1-21 Cable and Wire ............................................................................ 1-17

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page1-1SECTION 1GENERAL INFORMATION1.0 INTRODUCTIONThis manual contains information relative to the physical, mechanical and electri-cal characteristics of the KMH 880/KTA 870 Multi-Hazard Awareness System. It includes the basic guidelines, considerations and recommendations for the instal-lation and ground checkout of KMH 880/KTA 870 Multi-Hazard Awareness System and associated components. It is intended to provide the detail required to assist the installer in preparation for installation and appropriate work instructions to ensure a proper installation and checkout.This manual assumes a familiarity with avionics installation practices, with sys-tems on board the aircraft and access to manuals and regulations commensurate with the installation of such equipment.The information contained herein, together with the general procedures outlined in FAA AC.43.13-1B and AC.4313- 2A should be followed carefully to ensure a safe and electrically sound system installation.The contents of this manual are for information and reference use only and must not be construed as a formal FAA approved work authorization.It is highly recommended that prior to beginning the installation of the KMH 880/KTA 870 system that this manual is carefully reviewed. Upon review the necessary configuration items and system requirements will be identified allowing a speedy installation.Operational information is contained in the KMH 880/KTA 870 Operators Manual supplied with each unit.1.1 PURPOSEThis manual will describe the detailed system requirements for the Bendix/King KMH 880 Multi-Hazard Awareness System and KTA 870 Traffic Advisory System . The KMH 880 combines TAS (Traffic Advisory System) with EGPWS (Enhanced Ground Proximity Warning System). The KTA 870 has TAS only.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Page1-2 10609I00.ZIPCDL Rev 0, October/20001.2 APPLICABILITY OF THE SYSTEM MANUAL1.2.1 Equipment ApplicabilityThis manual is applicable only to KMH 880/KTA 870 Multi-Hazard Awareness Sys-tem part numbers displayed in the table below:1.3 SYSTEM DESCRIPTION1.3.1 Basic EGPWS SystemThe KMH 880 EGPWS is a revolutionary new step in Controlled Flight Into Terrain (CFIT) protection. It is capable of producing advanced alerting for prevention of CFIT accidents. In addition to the alerting protection the system will also produce a terrain display. This display depicts relative terrain in reference to the lateral and vertical positions of the aircraft.The EGPWS is intended for Light Turbine and Piston Aircraft Operations. It has effective operational performance in providing timely alerts and operational terrain display to enhance situational awareness. This performance, coupled to the sys-tem's simplicity, practicality, small size and weight, with a minimum number of required aircraft sensors, provides a formidable safety value.NOTEThe EGPWS portion of the KMH 820 is not suitable for helicopter operation.No Radio Altimeter, Landing Gear or Flap discretes, or Glideslope receiver are necessary. This significantly lowers the installation costs.The KMH 880 is a system designed to minimize the system requirements down to a level economical to the private pilot. It is the central component in the system providing timely alerts and optional display of impending terrain incursions.The KMH 880 is a TSO C151A class B compliant system.UNIT NOMENCLATURE PART NUMBER KTA 810 Traffic Advisory Unit 066-01152-0101 KMH 820 w/o GPS Multi-hazard Awareness Unit 066-01175-0101 KMH 820 w/GPS Multi-hazard Awareness Unit 066-01175-2101Table 1-1 KMH 880/KTA 870 Applicable Versions

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page1-31.3.2 Basic TAS SystemThe Airborne TAS system is capable of surveillance of aircraft equipped with tran-sponders (i.e., Mode S and Mode C) able to reply to ATCRBS Mode C interroga-tions in their operational environments. This is a step toward determining potential collisions and displaying traffic advisory information to the pilot. The TAS system will interoperate with the U.S. National Standard Air Traffic Control Radar Beacon System (ATCRBS) and perform reliably out to a range of ten nautical miles for densities up to 0.08 aircraft per square nautical mile while complying with all ATCRBS signals-in-space requirements. The TAS equipment will not degrade either the electromagnetic or the air traffic environment.When all features are implemented the equipment has the capabilities of the Traf-fic Advisory System (TAS) defined by TSO-C147. The TAS system will provide:(1) An alert to the pilot using an audible and visual advisory of the proximity of an intruder aircraft. (2) The range to ± 0.1 nautical mile, altitude (if reported by surveilled aircraft), and relative bearing of intruder aircraft with maximum installed accuracy of ± 30° with high reliability. If the intruder aircraft is transponder equipped, within ten nautical miles, ± 10,000 feet relative altitude, and TAS is not in interference limiting, it will be reliably detected and reported.(3)Timely data that does not lag more than 2 seconds behind the actual rela-tive position as seen by the pilot during normal flight operations.(4) Probability of displaying false targets will be less than 2%. If they are dis-played, they will not persist for more than a few seconds.(5) No increase of traffic on the Secondary Surveillance Radar radio frequen-cies in a manner that degrades the ATC system.(6) Display of indications that do not encourage the pilot to maneuver without first visually acquiring the other aircraft and determining that a maneuver is required.1.3.3 System ComponentsThe KMH 880 Multi-Hazard Awareness System shall be composed of the KMH 820 (TAS/EGPWS Processor), a top mounted directional antenna (KA 815), a bot-tom mounted antenna (monopole or directional antenna which shall provide esti-mated bearing of target aircraft), a top mounted GPS antenna (KA 92), and a Configuration Module (CM 805).

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Page1-4 10609I00.ZIPCDL Rev 0, October/2000A Multifunctional Display Unit, KMD 540, shall provide control and display of traffic (via the KAC 504 Traffic Card) and control and display of EGPWS data (via the KAC 502 Adapter Card). Other displays that are compatible with ARINC 735A may be used for traffic with this system. See Figure 1-1. The KTA 870 Traffic Advisory System is similar to the KMH 880 except the KTA 810 Traffic Advisory Unit has only TAS and not EGPWS. The KTA 870 system does not use a KA 92 GPS antenna. See Table 1-2 and Table 1-3 for a complete description and part number listing for both systems.KMH 880 SYSTEM PRIMARY LRUsSystem Component LRU Manufacturer/Model DesignatorLRU Description LRU Part NumberTA S / G A E G P W SProcessorBendix/King KMH 820 Multi-Hazard Awareness Processor066-01175-0101066-01175-2101Directional Antenna Bendix/King KA 815 TAS Directional Antenna 071-01599-0100GPS Antenna Bendix/King KA 92 GPS Antenna 071-01553-0200Configuration Module Bendix/King CM 805 Configuration Module 071-00112-0100Control Panel/Display Bendix/King KMD 540 Multi-function Display 066-04035-0X01Bendix/King KAC 502 EGPWS Card 071-00158-0211Bendix/King KAC 504 Traffic Card 071-00166-0411Table 1-2 KMH 880 LRUsKTA 870 SYSTEM PRIMARY LRUsSystem Component LRU Manufacturer/Model DesignatorLRU Description LRU Part NumberTAS Processor Bendix/King KTA 810 TAS Processor 066-01152-0101Directional Antenna Bendix/King KA 815 TAS DirectionalAntenna071-01599-0100Configuration Module Bendix/King CM 805 Configuration Module 071-00112-0100Control Panel/Display Bendix/King KMD 540 Multi-function Display 066-04035-0X01Bendix/King KAC 504 Traffic Card 071-00166-0411Table 1-3 KTA 870 LRUs

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page1-5Figure 1-1 KMH 880/KTA 870 System1.3.4 System OperationA. EGPWS System1. EGPWS Modes of Operationa. TSO ModeThe EGPWS has provisions to allow the selection of alerting/warning curves which comply with the requirements of TSO C151a class B or an alternate set of warning curves which are optimized for some General Aviation operations which do not require compliance with TSO C151a-class B.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Page1-6 10609I00.ZIPCDL Rev 0, October/2000This option is programmed into the EGPWS configuration module during sys-tem installation and thus remains specific to the aircraft. Once set up, any Enhanced Ground Proximity Warning Computer installed in the aircraft will access the configuration module and provide the appropriate mode of opera-tion.NOTEAll aircraft, which are required by Federal Aviation Regulations to have Terrain Awareness and Warning System (TAWS) comply with TSO C151a-class B, must be configured with the TSO curves. Additionally, the alternate Audio Menu must be selected to meet the alert/warning aural requirements of the TSO.b. Non-TSO ModeIf this installation is intended to provide the operator with a non-required Ter-rain Awareness and Warning System to enhance safety of flight, it may be appropriate to select the Non-TSO Mode of operation. As a general rule, higher performance aircraft, especially ones flown primarily IFR and operat-ing into larger airports may find the TSO curves most appropriate. Slower performance aircraft operating primarily VFR and operating at low altitudes AGL into small airports may find the Non-TSO curves better suit their opera-tion. Any installation not required to comply with TSO C151a-class B may select either the Basic Audio menu or the Alternate Audio menu.The EGPWS may also be installed in aircraft that do not require FAA approved TAWS Systems, and may be utilized with an optional set of alerting and warning parameters that are designed especially for smaller piston aircraft and their nor-mal flight characteristics.c. GPS SensorThe KMH 880 contains an embedded GPS-XPRESS Card sensor that pro-duces validated navigational position data by continuous signal acquisition and tracking of the navigational satellite network. The GPS Sensor receives the C/A code signals transmitted by the satellite network on the L1 frequency of 1575.42 MHz. The sensor has 8 signal processing channels allowing 8 sat-ellites to be tracked simultaneously. At least 4 satellites must be in view of the antenna for the sensor to operate. The GPS Sensor uses data in the satel-lites’ navigation messages to solve for latitude, longitude, altitude, horizontal velocity, vertical velocity and current UTC.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page1-7GPS Data can also be supplied via the ARINC 743, 743A and RS 232 (KLN94) interfaces.A GPS Antenna Splitter could be used in liew of installing another antenna.B. TAS System1. TAS Modes of Operationa. Setup ModeThe system shall be configured using an external PC via the Diagnostic(RS 232) Interface. Reference the Appendices for the programming proce-dures. b. Standby ModeWhen the Standby mode is selected, the TAS Processor shall disablesurveillance and tracking operations. The Standby mode may be activated by any of the following: discrete selection, self-test, aircraft on ground (configuration option), or system failure.c. Functional Test ModeWhen the Functional Test mode is selected, the unit shall be placed into the Standby mode and the Functional Test portion of BITE shall be performed. d. TAS Operation (Traffic Advisory) ModeWhen the TAS Operation mode is selected, the TAS Processor shall perform all the surveillance functions and shall provide for the generation of traffic advisories . The information conveyed in the traffic advisories is intended to assist the flight crew in sighting nearby traffic. e. TAS ProcessorThe TAS Processor shall provide intruder surveillance and tracking, generat-ing traffic advisories for both Altitude-Reporting and Non-Altitude-Reporting intruders to display potential conflicts and advisories to the flight crew.The TAS Processor shall track intruders under surveillance and analyze range and range rate data, and altitude of the traffic to determine whether that intruder represents a threat.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Page1-8 10609I00.ZIPCDL Rev 0, October/2000The TAS Processor shall also select "proximate traffic" and "other traffic" intruders to be displayed on the basis of their altitude relative to own aircraft. The "other traffic" intruders are those that do not qualify to be TA or proximate traffic but are displayed.NOTE Optional (The TAS Processor may be controlled using discrete inputs).C. Options1. Display OptionTSO C151a-class B does not require a display for terrain data, however, if at all possible, terrain data should be displayed for the aircraft operator. The ter-rain display greatly improves situational awareness. The EGPWS supports numerous displays including traditional Radar displays as well as mode mod-ern MFD’s.Installations, which include a display, will also need to provide the EGPWS with range data via ARINC 429 format.2. Altitude Monitor OptionThe EGPWS has the ability to monitor altitude sources and provide caution-ary messages should an altitude source be suspected of being in error. This feature compares barometric altitude with GPS altitude and generates a “Check Altitude” message when an error is detected. This is a highly recom-mended option, which can alert a pilot to problems such as a stuck altimeter or plugged static port. This option requires no additional hardware and is enabled during the system installation by programming the configuration module. This feature can provide both audio and display messages.3. Outside Air Temperature (OAT) (Recommended)The EGPWS supports an OAT probe for aircraft operated in cold environ-ments. Very cold air temperatures cause an increase in the density of the air mass and can result in barometric altimeter errors, both in sensitive altime-ters/encoders and blind encoders. Aircraft normally operated in very cold cli-mates can benefit from the addition of an OAT probe interfaced to the EGPWS. If the aircraft is equipped with an Air Data Computer which outputs Digital data with Corrected Altitude on an ARINC 429 port, this can be used instead of an encoder and external OAT Probe. OAT is programmed into the configuration module during system installation.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page1-91.4 TECHNICAL CHARACTERISTICS Table 1-5 KMH 820 w/ GPS Multi-Hazard Awareness Unit Technical SpecificationKMH 820 w/o GPS MULTI-HAZARD AWARENESS UNITP/N 066-01175-0101TSO COMPLIANCE:PHYSICAL DIMENSIONS:WEIGHT: Installation KitPOWER REQUIREMENTS:See TSO Appendix ESee Figure 2-19.32 lbs.050-03361-0000Voltage Nominal: +28 Vdc Range: +22 to +30 Vdc Current Nominal: 1.3 ± 0.2 A Max Operating 1.65 ± 0.2 A Bootup: 3.3 ± 0.5 ΑPower 46 ± 2.3 WattsTable 1-4 KMH 820 w/o GPS Multi-Hazard Awareness Unit Technical SpecificationsKMH 820 w/ GPS MULTI-HAZARD AWARENESS UNITP/N 066-01175-2101TSO COMPLIANCE:PHYSICAL DIMENSIONS:WEIGHT: Installation KitPOWER REQUIREMENTS:See TSO Appendix ESee Figure 2-19.68 lbs.050-03361-0000Voltage Nominal: +28 Vdc Range: +22 to +30 VdcCurrent Nominal: 1.3 ± 0.2 A Max Operating 1.65 ± 0.2 A Bootup: 3.3 ± 0.5 ΑPower 46 ± 2.3 Watts

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Page1-10 10609I00.ZIPCDL Rev 0, October/2000KTA 810 TRAFFIC ADVISORY UNITP/N 066-01152-0101TSO COMPLIANCE:PHYSICAL DIMENSIONS:WEIGHT: Installation KitPOWER REQUIREMENTS:See TSO Appendix ESee Figure 2-18.75 lbs050-03361-0000Voltage Nominal: +28 Vdc Range: +22 to +30 VdcCurrent Nominal: 1.15 ± 0.2 A Max Operating 1.45 ± 0.2 A Bootup: 2.9 ± 0.5 ΑPower 41 ± 2.3 WattsTable 1-6 KTA 810 Traffic Advisory Unit Technical SpecificationsCM 805 CONFIGURATION MODULEP/N 071-00112-0100TSO COMPLIANCE:PHYSICAL DIMENSIONS:WEIGHT:POWER REQUIREMENTSSee TSO Appendix ESee Figure 2-20.1 lbs.5 Vdc from KMH 820/KTA 810.Table 1-7 CM 805 Configuration Module Technical Specifications

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page1-11KA 815 TRAFFIC ANTENNAP/N 071-01599-0100TSO COMPLIANCE:PHYSICAL DIMENSIONS:WEIGHT: Installation KitMOUNTING:POWER REQUIREMENTSSee TSO Appendix ESee Figure 2-30.95 lbs.050-03622-0000See Figure 2-4 and 2-5NoneTable 1-8 KA 815 Traffic Antenna Technical SpecificationsKA 92 GPS ANTENNAP/N 071-01553-0200TSO COMPLIANCE:PHYSICAL DIMENSIONS:WEIGHT: Installation KitMOUNTING:POWER REQUIREMENTSSee TSO Appendix ESee Figure 2-60.27 lbs.050-03318-0000See Figure 2-6 5v supplied by the GPS receiver.Table 1-9 KA 92 GPS Antenna Technical Specifications

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Page1-12 10609I00.ZIPCDL Rev 0, October/20001.5 UNIT AND ACCESSORIES SUPPLIED1.5.1 TAS Processor UnitThe TAS Processor will provide intruder surveillance and tracking, generating traf-fic advisories for both Altitude-Reporting and Non-Altitude-Reporting intruders to display potential conflicts and advisories to the flight crew.The TAS Processor will track intruders under surveillance and analyze range and range rate data, and altitude of the traffic to determine whether that intruder repre-sents a threat.1.5.2 Configuration ModuleThe Configuration Module contains two EEPROMs, one for the TAS Processor and one for the EGPWS.The Configuration Module will be remotely mounted in the airframe. It will be mapped with the Configuration at the installation of the system. An external PC program will be available to the installer to initialize/program the configuration module. Reference this Install Manual, Section IV for the programming proce-dures. A system failure will be annunciated if the configuration module is not pro-grammed, not compatable with the current TAS processor software or if the CRC read from the module is incorrect.SYSTEM COMPONENT MANUFACTURER/MODEL DESIGNER DESCRIPTION PA RT N U M B E R TSO COMPLIANCETA S / G A E G P W SProcessorBendix/KingKMH 820Multi-HazardAwareness Processor066-01175-0101066-01175-2101TSO C147TSO C151aTA S ProcessorBendix/King KTA 810TA SProcessor066-01152-0101TSO C147Table 1-10 KMH 820/KTA 810 Processor UnitsSYSTEMCOMPONENTMANUFACTURER/MODEL DESIGNER DESCRIPTION PART NUMBER TSO COMPLIANCEConfiguration ModuleBendix/KingCM 805Configuration Module 200-00112-0100 TSO C147TSO C151aTable 1-11 CM 805 Configuration Module

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page1-131.5.3 AntennasFull bearing coverage will be achieved by the use of a top and bottom directional antenna system. The TAS Processor will also be capable of supporting a top directional and bottom monopole antenna configuration. In the latter configuration, only intruders being tracked via the top directional antenna will have bearing infor-mation. The antennas will be vertically polarized and cover 360 degrees in azimuth and at least -10 to +20 degrees in elevation.* This antenna has not been tested for direct effects of lightning and the installer must determine the suitability of the antenna for the specific installation.SYSTEM COMPONENTMANUFACTURER/MODEL DESIGNER DESCRIPTION PART NUMBER TSO COMPLIANCEDirectionalAntennaBendix/King KA 815TAS DirectionalAntenna071-01599-0100 TSO C147GPS Antenna Bendix/King KA 92GPS Antenna 071-01553-0200 TSO C129Omni-DirectionalAntennaDorne and Margolin L-Band Antenna DM NI50-2-2* TSO C66aTSO C74Table 1-12 KA 815/KA 92 AntennasCABLE TYPES AND PERMISSABLE GPS CABLE RUN LENGTHS(8dB allowable loss, including splitter.)CABLE TYPE CABLE RUN LENGTH(W/O Splitter)* R/G 142B/U P/N 024-00002-0000Up to 46 ft.* R/G 400/U P/N 024-00051-0060Up to 46 ft.* These cables use R/G 142/400 style connectors. Note:When using Non-KPN or Non-standard P/N cables, connectors etc., the installer has the responsibility of proving airworthiness.Table 1-13 GPS Cable Run Lengths

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Page1-14 10609I00.ZIPCDL Rev 0, October/20001.6 INSTALLATION ACCESSORIES SUPPLIED1.6.1 KMH 820/KTA 810 Installation Kit SYMBOL PART NUMBER DESCRIPTION [UOM] -0000200-09894-0000 Rack, KMH 820/ KTA 810 [EA] 1J10 D38999/26FJ35SN 128 Pin I/O Connector [EA] 1M85049/38-25N Strain Relief for 128 Pin I/O Connector [EA] 1J4,J8 030-00005-0002 TAS Antenna Ports, BNC Connectors [EA] 2J1-J3, J5-J7, J9030-00134-0000 Connector, TNC [EA] 7071-00112-0100 CM 805 Configuration Module [EA] 1 030-01171-0000 Conn Sub-D HSG 9S (Female Pins) [EA] 2010-00135-0000 Terminals [EA] 2010-00068-0026 Terminals [EA] 8150-00072-0000 Solder Sleeve [EA] 8030-01157-0011 Socket Contact [EA] 6030-01451-0000 Socket Contact 22 ga [EA] 15030-01464-0000 9 Pin Plastic Hood [EA] 2030-01428-0001 EMI Hood W/ Lock 15 Pin High Density [EA] 1030-03447-0001 High Density 15 Pin Female DSub [EA] 1155-06060-0000 KMH 820/KTA 810 Installation Drawing REFTable 1-14 KMH 820/KTA 810 Installation Kit P/N 050-03361-0000

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page1-151.6.2 Antenna Installation Kits1.6.3 DatabasesSYMBOL PART NUMBER DESCRIPTION [UOM] -0000071-01599-0100 KA 815 Antenna [EA] 1M39012/30-0101 Connector, TNC Rt Angle [EA] 4MS29513-148 KA 815 O-Ring [EA] 1MS24693-C54 Screw PHP 8-32x.875 [EA] 4155-06059-0000 KA 815 Installation Drawing REFTable 1-15 KA 815 Installation Kit P/N 050-03622-0000SYMBOL PART NUMBER DESCRIPTION [UOM] -0000030-00134-0001 Connector, TNC Rt Angle [EA] 1047-10735-0002 Antenna DBLR Complete [EA] 1089-05909-0012 Screw PHP 8-32x3/4 [EA] 4187-01831-0000 Antenna Gasket [EA] 1155-06019-0000 KA 92 INstallation Drawing REFTable 1-16 KA 92 Installation Kit P/N 050-03318-0000PART NUMBER DESCRIPTION [UOM]071- 00167-0101 America’s Database [EA]071-00167-0102 Atlantic Database [EA]071-00167-0103 Pacific Database [EA]Table 1-17 KMH 880/KTA 870 Databases

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Page1-16 10609I00.ZIPCDL Rev 0, October/20001.7 ACCESSORIES REQUIRED BUT NOT SUPPLIED 1.7.1 Temperature ProbeThe EGPWS is capable of interfacing directly to a standard 500 ohm temperature probe for aircraft operated in cold environments. Very cold air temperatures cause an increase in the density of the air mass and can result in barometric altimeter errors, both in sensitive altimeters/encoders and blind encoders. Aircraft normally operated in very cold climates can benefit from the addition of an OAT probe inter-faced to the EGPWSNOTEThe EGPWS Processor does not require a Temperature Probe input if a Digital Air Data Computer, with an OAT Label present on the bus, is available as an interface.1.7.2 GPS Antenna SplitterTo have the flexibility of using an existing KA 92 GPS Antenna, Honeywell offers a splitter that will greatly simplify the installation procedure. One of the split ports is DC blocked from the common port so that equipment voltage regulators do not conflict.SYMBOL PART NUMBER DESCRIPTION [UOM] -0001137-00042-0001 OAT Probe [EA] 1MS3106E12S-3S OAT Probe Connector [EA] 1090-01034-0001 OAT Probe Mounting Kit [EA] 1010-00068-0016 Crimp Terminal [EA] 1Table 1-18 Temperature Probe P/N 050-03610-0002SYMBOL PART NUMBER DESCRIPTION [UOM] QTY050-03610-0003 GPS Antenna Splitter Kit [EA] 1030-00134-0000 TNC Connector Straight [EA] 3030-00134-0001 TNC Connector Rt Angle [EA] 1Table 1-19 GPS Antenna Splitter P/N 071-01600-0001

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page1-171.7.3 MiscellaneousNOTE:Specification Drawing 031-00810-01 defines all of the sub-assembly partsand spacers to cover different panel thicknesses (Sheet 2). Artwork definitions for associated items are also covered (Sheet 3).1.7.4 CABLE AND WIRE1.8 LICENSE REQUIREMENTSThere are no license requirements for the KMH 880/KTA 870 Multi-Hazard/Traffic Advisory System.1.9 INSTRUCTIONS FOR CONTINUED AIRWORTHINESSFAR Part 23.1529, 25.1529, 27.1529, AND 29.1529 Instructions for Continued Airworthiness is met per the following Instructions:Design and manufacture of the equipment will provide for installation so as not to impair the airworthiness of the aircraft.SYMBOL PART NUMBER DESCRIPTION [UOM] QTY 050-03610-0000 Basic Annunciator Kit [EA] 1 050-03610-0001 Terrain Switching Kit [EA] 1Table 1-20 Miscellaneous AccessoriesSYMBOL PART NUMBER DESCRIPTION [UOM] QTYM17/158-RG400 Coaxial Cable [FT] ARMIL-W-22759/16 or Equivalent. Wire [FT] ARM17/176-00002 Shielded Wire [FT] ARMIL-C-27500 or Equivalent. Shielded Wire [FT] ARTable 1-21 Cable and Wire

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Page1-18 10609I00.ZIPCDL Rev 0, October/20001.9.1 KMH 820/KTA 810 UnitIf the unit should require maintenance, remove the unit and have it repaired by an appropriately rated Honeywell approved Instrument Service Center. If the aircraft is to fly with the KMH 820/KTA 810 removed, secure the connector(s) as neces-sary and placard the aircraft accordingly. After re-installation of the unit, accom-plish the appropriate Post Installation Checkout in Section IV.During each annual or 100 hour inspection of the aircraft, perform a Level 2 Self Test of the KMH 820/KTA 810 as defined in the Post Installation Checkout in Sec-tion IV.1.9.2 Annunciators/RelaysIf an annunciator bulb needs replacement, use a bulb with with the same type and voltage rating as originally installed. If a relay malfunctions, replace it with an air-worthy relay having the same part number. If a combination annunciator/relay unit is used, e.g. MD41-1208/1308, remove the unit and have it repaired by a factory-rated service center. If the aircraft is to fly with a relay or annunciator removed, secure the connector(s) as necessary and placard the aircraft accordingly. After re-installation of the unit, accomplish the appropriate Post Installation Checkout in Section IV.1.9.3 GPS AntennaIf the GPS Antenna should fail, replace it with an airworthy antenna having the same part number. Verify good electrical bonding surfaces before installing the antenna. Ensure that antenna radome is clean and not covered with paint. After re-installation of the antenna, accomplish the appropriate Post Installation Check-out in Section IV.1.9.4 GPS Antenna SplitterIf the GPS Antenna Splitter should fail, replace it with an airworthy antenna splitter having the same part number. The signal loss between the GPS Antenna and the GPS Receiver cannot exceed 8 dB. After re-installation of the GPS Antenna Split-ter, accomplish the appropriate Post Installation Checkout in Section IV.1.9.5 Temperature ProbeIf the KMH 820/KTA 810 Self Test indicates a failure of the temperature probe, replace the temperature probe with an airworthy temperature probe having the same part number. after installation of the temperature probe, accomplish the appropriate Post Installation Checkout in Section IV.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page1-191.9.6 Wires and 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 as neces-sary.1.9.7 Terrain Data Base UpdatesTo order database updates contact Honeywell International Inc., Navigation Ser-vices:Honeywell International Inc.Aerospace Electronic SystemsOne Technology Center23500 West 105th StreetOlathe, Kansas 66061 USAAttn: Navigation Services MS 66Phone:(800) 247-0230 within the United States or Canada (913) 712-3145 outside of the United States or CanadaFAX: (913) 712-3904e-mail:nav.database@honeywell.com

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page1-20THIS PAGE IS RESERVED

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL TOC 2-iSECTION II INSTALLATION2.0 INTRODUCTION .............................................................................. 2-12.1 UNPACKING AND INSPECTING EQUIPMENT .............................. 2-12.2 EQUIPMENT INSTALLATION .......................................................... 2-12.2.1 General ............................................................................................. 2-12.2.2 Avionics Cooling Requirements ........................................................ 2-22.2.3 Processor Installation ....................................................................... 2-22.2.3.1 Cooling Considerations ..................................................................... 2-22.2.3.2 Installation Considerations ................................................................ 2-22.2.3.3 Installation Procedure ....................................................................... 2-42.2.4 Configuration Module Installation ...................................................... 2-92.2.4.1 Cooling Considerations ..................................................................... 2-92.2.4.2 Installation Considerations ................................................................ 2-92.2.4.3 Installation Procedure ....................................................................... 2-92.2.5 DIRECTIONAL ANTENNA INSTALLATION ..................................... 2-132.2.5.1 KA 815 Antenna Installation Considerations .................................... 2-132.2.6 GPS ANTENNA INSTALLATION ..................................................... 2-172.2.6.1 KA 92 Antenna Installation Considerations (KMH 820 EGPWS only) 2-172.2.6.2 Installation Procedure ....................................................................... 2-172.2.7 TAS Coaxial Cable Fabrication.......................................................... 2-262.2.8 GPS Coaxial Cable Fabrication......................................................... 2-27LIST OF ILLUSTRATIONSFigure 2-1 KMH 820/KTA 810 Installation Drawing....................................... 2-5Figure 2-2 Configuration Module Installation Drawing................................... 2-11Figure 2-3 KA 815 Antenna Outline Drawing ................................................ 2-15Figure 2-4 KA 815 Antenna Installation Drawing........................................... 2-19Figure 2-5 KA 815 Doubler Plate Drawing..................................................... 2-21Figure 2-6 KA 92 Outline and Mounting Drawing ......................................... 2-23Figure 2-7 GPS Antenna Splitter ................................................................... 2-25Figure 2-8 Coax Cable Treatment ................................................................. 2-28Figure 2-9 Standard Coax Cable................................................................... 2-28Figure 2-10 Bulkhead/In-Line Connection Coax Cable ................................... 2-28Figure 2-11 TNC Antenna Coax/Connector Assembly.................................... 2-29Figure 2-12 TNC Antenna Coax/Connector Assembly.................................... 2-30LIST OF TABLESTable 2-1 Signal Losses............................................................................... 2-27

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870TOC 2-ii 10609I00.ZIPCDL Rev 0, October/2000THIS PAGE IS RESERVED

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 2-1SECTION II INSTALLATION2.0 INTRODUCTIONThis section contains suggestions and factors to consider before installing the KMH 880/KTA 870 System. Close adherence to these suggestions will assure satisfactory perfor-mance from the equipment.NOTEThe conditions and tests performed on the system components are mini-mum performance standards. It is the responsibility of those desiring to install the KMH 880/KTA 870 either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards. The KMH 880/KTA 870 may be installed only if further evaluation by the applicant documents an acceptable installation and is approved by the administrator.2.1 UNPACKING AND INSPECTING EQUIPMENTExercise extreme caution when unpacking equipment. Perform a visual inspection of the unit for evidence of damage incurred during shipment. If a damage claim must be filed, save the shipping container and all the packing materials to substantiate your claim. The claim should be filed as soon as possible. The shipping container and all packing mate-rial should be retained in the event that storage or re-shipment of the equipment is nec-essary.2.2 EQUIPMENT INSTALLATION2.2.1 GeneralThe following paragraphs contain information pertaining to the installation of the KMH 880/KTA 870 System, including instructions concerning location and mount-ing of the antennas.The 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 the system has been properly and safely installed in the aircraft, the installer should make a thorough visual inspection and conduct an overall operational check of the system, on the ground, prior to flight.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Page 2-2 10609I00.ZIPCDL Rev 0, October/2000CAUTIONAFTER INSTALLATION OF THE CABLING AND BEFOREINSTALLATION OF THE EQUIPMENT, A CHECK SHOULDBE MADE WITH THE AIRCRAFT PRIMARY POWER SUP-PLIED TO THE MOUNTING CONNECTOR, TO ENSURETHAT POWER IS APPLIED ONLY TO THE PINS SPECFIEDIN THE INTERWIRING DIAGRAMS IN SECTION III.The KMH 880/KTA 870 System installation will conform to standards designated by the customer, installing agency, and existing conditions as to the unit location and type of installation. However, the following suggestions should be carefully considered before installing your system.2.2.2 Avionics Cooling Requirements The most important contribution to improved reliability of all avionics equipment is to limit the maximum operating temperature of the individual unit, whether panel mounted or remote mounted. While modern circuit designs consume less total energy, the heat dissipated per unit volume (Watts/cubic inch) remains much the same due to contemporary high density packaging techniques. While each indi-vidual unit may not require forced air cooling, the combined heat generated by several units operating in a typical panel or rack, can significantly degrade the reli-ability of the equipment. Consequently, the importance of providing force air cool-ing to avionics equipment mounted in either a panel or rack, is essential to the life span of the equipment. Adequate provisions for cooling should be incorporated during the installation.2.2.3 Processor Installation2.2.3.1 Cooling ConsiderationsThe KMH 820/KTA 810 requires no external forced air cooling.2.2.3.2 Installation ConsiderationsConsideration should be given to the following items affected by the choice of installation location within the aircraft:A. Environmental ConsiderationsB. Ease of Interface to aircraft systems

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 2-3C. GPS Antenna location and coaxial cable lengthD. Ability to extract and insert new terrain/obstacle Data Bases supplied on a CompactFlash Card.If possible, install the KMH 820/KTA 810 in a dry, temperature-controlled area such as within the passenger compartment of the aircraft. Standard avionics bays are accepable as well. If possible, the KMH 820/ KTA 810 should NOT be located in close proximity to equipment which produce considerable heat. Locations, which require disassembly of the aircraft to gain access, are less desir-able.Any location that is exposed to moisture and/or temperature extremes should be avoided.Select a mounting location that allows sufficient clearance at the front of the unit for connectors and cables.Do not bundle data lines or antenna cable with any power cables.No more than 8.0dB signal loss is allowed in the GPS antenna cable run, includ-ing the antenna splitter, (if used). Refer to Note 5 on the Antenna Interface Draw-ing and Table 1-13 in Section 1 for information on cable types and lengths.Mount the unit to provide good electrical bonding to airframe ground. Lightning strike protection and RF susceptibility and emission characteristics depend on good electrical grounding of the unit and cable shield returns.Refer to Figures 2-11 and 2-12 for TNC connector assembly guidelines.NOTEThe KMH 820/KTA 810 will need to interface to the aircraft audio sys-tem, aircraft DC power, panel mounted warning lamps and switches, a source of barometric altitude (usually an encoding altimeter or blind encoder), a GPS antenna and a panel mounted display.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Page 2-4 10609I00.ZIPCDL Rev 0, October/2000If possible, clearance to the top of the KMH 820 should be provided to facilitate removal and installation of the terrain database CompactFlash card. The terrain database card is removed and installed with power NOT applied to the system. The KMH 820 may be removed from the aircraft to extract and install database cards if the mounting location does not provide enough clearance.Updating the Terrain DataBase is accomplished by:Moving the aluminum cover over the CompactFlash card out of the way.Pressing the flash card ejector button located within the unit.Removing the old flash card.Inserting the new flash card and replacing the cover.If possible, mount the KMH 820 such that the above can be accomplished without requiring disassembly of the aircraft or removal of the KMH 820.The KMH 820 drives three lamps and accepts input from two switches. The lamps should be identified as:The RED Warning lamp must be located in the pilot’s primary field of view.The EGPWS provides a single 600 ohm audio output which should be connected to a un-switched/un-muted auxiliary audio input on the aircraft’s audio control panel. The audio output power level is set by programming the configuration mod-ule.2.2.3.3 Installation ProcedureA. Slide the unit into the rack and secure it.B. Attach the harness to the front mating connector of the unit.C. Attach coax cables J1 thru J10 to the front of the unit.FUNCTION COLOR LEGENDNot Available Amber Terrain N/A or Terr N/ACaution Amber TerrainWarning Red Terrain

BBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 2-5Figure 2-1 KMH 820/KTA 810 Installation DrawingDwg. No. 300-05639-0000 R-0 (Sheet 1 of 2)PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICE

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BBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 2-7Figure 2-1 KMH 820/KTA 810 Installation DrawingDwg. No. 300-05639-0000 R0 (Sheet 2 of 2)PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICE

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PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 2-92.2.4 Configuration Module InstallationSystem configuration is defined via a Configuration Module which contains the aircraft interface and functionality definitions specific to the installed aircraft.2.2.4.1 Cooling ConsiderationsA. Make sure that the unit is installed in a location where the ambient tem-peratures are -67°F to +158°F (-55°C to +70°C).2.2.4.2 Installation ConsiderationsA. The Configuration Module must be mounted to the airframe within maxi-mum cable/harness length of 2 feet. Make sure to leave adequate space to mount the Configuration Module when installing the Processor Unit.2.2.4.3 Installation ProcedureA. Install the Configuration Module into the airframe. Refer to figure 2- 2 .B. Tighten the mounting screws to secure the Configuration Module.

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BBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 2-11Figure 2-2 Configuration Module Installation DrawingDwg. No. 300-06161-0000 R-0 PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICE

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PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 2-132.2.5 DIRECTIONAL ANTENNA INSTALLATION2.2.5.1 KA 815 Antenna Installation ConsiderationsA. Antenna LocationNOTEThe following antenna location procedure is provided for guidance pur-poses and to outline a method of achieving certifiable system perfor-mance.The KMH 880/KTA 870 System uses a top-mounted directional antenna and either a bottom-mounted directional or an L-band omni-directional antenna. Refer to directional antenna outline drawings in Figure 2-3. Mounting the directional antenna MUST include the appropriate doubler plate.The install-ing agency is required to fabricate the doubler plate for the antenna installa-tions.NOTEThe L-band omni-directional has not been tested for the direct effects of lightning and the installer (TC or STC applicant) must determine the suitability of the antenna for the specific installation.NOTEKMH 880/KTA 870 Systems REQUIRE that the antenna installation guidelines be followed. Adherence to these guidelines will assure that crit-ical specifications are considered. Optimum bearing accuracy can be achieved by following these directions.Antenna locations should be chosen so that both antennas appear to be at the same range and bearing from the intruder.The centerline of the top and bottom-mounted TAS Antenna should be located as close as possible to the aircraft centerline. The top directional TAS Antenna should be the most forward antenna and as far forward on the constant radius portion on the fuselage as possible.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 2-15Figure 2-3 KA 815 Antenna Outline Drawing

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PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 2-172.2.6 GPS ANTENNA INSTALLATION2.2.6.1 KA 92 Antenna Installation Considerations (KMH 820 P/N 066-01175-2101 only)A. The KA 92 GPS Antenna should be mounted on top of the fuselage near the cockpit and in the centerline of the aircraft. Avoid mounting the antenna near any projections, and the tail of the aircraft, where shadows could occur. It is recommended that there be a separation of at least 3 feet between the GPS antenna and any VHF Comm, HF Comm, etc. on the aircraft. A minimum of 3 feet from any satcomm antenna should also be observed. Refer to Figure 2- 6.B. Mount the GPS antenna on the aircraft skin which is horizontal during enroute flight. Antenna baseplate must be level within + or - 5° in the longitu-dinal and lateral axes when the aircraft is in level flight.2.2.6.2 Installation ProcedureA. Make sure the antenna is well bonded to the aircraft skin.B. Make sure the antenna is sealed to the aircraft to prevent corrosion from forming between the skin of the aircraft and the antenna.C. Install the optional GPS Antenna Splitter, if aircraft is already equipped with a GPS antenna.D. Make sure the antenna cable is connected to the antenna, splitter and unit prior to system checkout.E. Perform system checkout using instructions in Section 4.3.

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BBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 2-19Figure 2-4 KA 815 Installation and Mounting DrawingDwg No. 155-06059-0000PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICE

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BBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 2-21Figure 2-5 KA 815 Doubler PlatePRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICE

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BBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 2-23Figure 2-6 KA 92 Outline and Mounting DrawingDwg. No. 155-06019-0000 R-AA PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICE

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PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 2-25Figure 2-7 GPS Antenna SplitterDwg. No. 071-01600-0001

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Page 2-26 10609I00.ZIPCDL Rev 0, October/20002.2.7 TAS Coaxial Cable FabricationThe TAS cables must have an attenuation of 2.0 ± 1.0 dB within the frequency band of 1030-1090 MHZ. To ensure proper phase matching, each of the four cables of a set must be of the same type. The lengths in each set of four must be within 2.0” of each other. Color bands on the cable ends to match the antenna color bands is suggested as an aid to hook up. Cables can be fabricated or purchased from a cable vendor.NOTEThe nominal length of each set of four cables should be recorded for the particular installation in the event a cable should require replacement. If rework is required, a cable may be cut a maximum of 6”.The following defines the characteristics of the 50 ohm coaxial cable types that can be used with the KA 815 Antenna. Connectors are also defined. All lengths are defined as end to end. Any in-line or bulkhead penetrations must be evaluated separately. It is rec-ommended that the installer purchase prefabricated cable assemblies when using in-line or bulkhead disconnects. Prefabricated cables can be purchased from Pic Wire & Cable or ECS. These vendors have expertise in providing the aviation industry reliable cable assemblies that meet the requirements for the various collision avoidance systems. It is the installing agency’s responsibility to show airworthiness of the fabricated cable assem-blies.When determining cable type and length make the following assumptions.A. Attenuation of each straight TNC male connector is 0.06 dB @ 1GHz(using a 030-00134-0000 RF Connector)B. Attenuation of each right angle TNC male connector is 0.07 dB @ 1 GHz(using a 030-00134-0001 RF Connector)C. Attenuation of each TNC female panel mount connector is 0.06 dB @ 1 GHZ (using a 030-00101-0002 RF Connector)D. Attenuation of M17/128-RG 400 Coaxial Cable is 0.13 dB/ft @ 1 GHzUsing the above information, a RG 400 cable with a right angle TNC (antenna end) and a straight TNC (KMH/KTA end) must be no longer than 22 feet long as measured from end to end. If longer length is required, then a lower loss cable with appropriate connectors must be selected. Reference the diagram below.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 2-272.2.8 GPS Coaxial Cable FabricationThe GPS Antenna Splitter allows the existing KA 91 or KA 92 GPS antenna to be interfaced to the KMH 820 EGPWS.The following criteria must be observed when using the antenna splitter:1. The length of an M17/128-RG400 coaxial cable cannot exceed 18 feet.2. The maximum allowable signal loss between the KA 91/92 antenna and the KLN series GPS receiver cannot exceed 8.0 dB. Refer to the appropriate KLN series GPS receiver Installation Manual for determination of loss.3. The maximum allowable signal loss between the KA 91/92 antenna and the KMH 820 cannot exceed 8.0 dB. Refer to the following table to determine the loss between the antenna and the KMH 820.Table 2-1 Signal LossPart Number Description Signal Lossper ItemExampleQuantityExampleSignal LossActualQuantityActual Signal Loss071-01600-001 GPS Antenna Splitter 3.4 dB 1 ea 3.4 dBM17/128-RG400 Coaxial Cable (18 ft max) 0.2dB/ft 10 ft 2.0 dB030-00134-0000 Straight TNC Connector 0.1dB 2 ea 0.2 dB030-00134-0001 Rt Angle YNC Connector 0.1dB 2 ea 0.2 dB030-00101-0002 Panel Mount Plug 0.1dB 0 0M39012/28-0504 Bulkhead TNC Connector 0.1dB 0 0M39012/29-0504 Panel TNC Connector 0.1dB 0 0TOTAL SIGNAL LOSS (8.0 dB max.) 5.8 dB

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 2-28Figure 2-8 Coax Cable TreatmentFigure 2-9 Standard RG-400 Coax CableFigure 2-10 Bulkhead/In-Line Connection RG-400 Coax Cable

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 2-29Figure 2-11 TNC Antenna Coax/Connector Assembly

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 2-30Figure 2-12 TNC Antenna Coax/Connector Assembly

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, Octobert/2000 10609I00.ZIPCDL TOC 3-iSECTION IIISYSTEM PLANNING3.0 INTRODUCTION .............................................................................. 3-13.0.1 Applicable Part Numbers Subsection Description ............................ 3-13.0.2 Function Subsection Description ...................................................... 3-13.0.3 Requirements and Limitations Subsection Description. ................... 3-13.0.4 Electrical Characteristics Subsection Description. ............................ 3-13.0.5 Interface Subsection Description ...................................................... 3-13.1 GENERAL INTERCONNECT INFORMATION ................................. 3-53.1.1 Power Inputs ..................................................................................... 3-53.1.2 Air/Ground Discrete Input ................................................................. 3-53.1.3 Landing Gear Discrete Input ............................................................. 3-63.1.4 Above/Below/ Normal Input .............................................................. 3-63.1.5 Baro Altitude (ARINC 429) Input ....................................................... 3-73.1.6 Advisory Inhibit Input ........................................................................ 3-73.1.7 TAS Valid Output .............................................................................. 3-73.1.8 Visual Annunciate Traffic (Lamp Output) .......................................... 3-83.1.9 Synthesized Voice output ................................................................. 3-83.1.10 Air Temperature Input ....................................................................... 3-93.1.11 GPS Input ......................................................................................... 3-93.1.12 Factory Test Input ............................................................................. 3-103.1.12.1 TAS ATE Enable Input ................................................................... 3-103.1.12.2 TAS Built In Test Equipment (BITE) .............................................. 3-103.1.12.3 EGPWS Self Test Input ................................................................. 3-113.1.12.4 Display Select Input ....................................................................... 3-123.1.12.5 Terrain Awareness Inhibit Discrete ................................................ 3-123.1.13 Terrain Warning ................................................................................ 3-123.1.14 Terrain Caution.................................................................................. 3-123.1.15 Weather Select Output ..................................................................... 3-123.1.16 EGPWS Audio On Discrete .............................................................. 3-133.1.17 EGPWS Terrain Inop and Terrain Not Available Output.................... 3-13LIST OF ILLUSTRATIONSFigure 3-1 KMH 880/KTA 870 Interconnect Family ...................................... 3-3Figure 3-2 KMH 820/KTA 810 Pinout Diagram ............................................. 3-15Figure 3-3 KMH 820/KTA 810 System Interconnect Block Diagram ............. 3-29Figure 3-4 KMH 820/KTA 810 Power Interface ............................................ 3-33Figure 3-5 KMH 820/KTA 810 Discrete Interface ......................................... 3-35Figure 3-6 KMH 820/KTA 810 Configuration Module Interconnect ............... 3-37Figure 3-7 KMH 820/KTA 810 Attitude/Heading Interface............................. 3-39Figure 3-8 KMH 820/KTA 810 Radar/Barometric Altitude Interface ............. 3-41

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870TOC 3-ii 10609I00.ZIPCDL Rev 0, October/2000Figure 3-9 KMH 820/KTA 810 Antenna/Suppression Interface .................... 3-49Figure 3-10 KMH 820/KTA 810 EFS 40/50 Interface .................................... 3-51Figure 3-11 KMH 820/KTA 810 GS 362A Interface ....................................... 3-53Figure 3-12 KMH 820/KTA 810 Honeywell GS 362A Interface ....................... 3-59Figure 3-13 KMH 820/KTA 810 Collins GS 362A Interface ............................. 3-65Figure 3-14 KMH 820/KTA 810 Honeywell Primus 1000 Interface.................. 3-69Figure 3-15 KMH 820/KTA 810 Honeywell SPZ-805 Interface........................ 3-73Figure 3-16 KMH 820/KTA 810 Diagnostic/Data Recorder Interface ............. 3-77Figure 3-17 KMH 820/KTA 810 TAS ATE Interface ....................................... 3-79Figure 3-18 KMH 820/KTA 810 CP 66B Interface........................................... 3-81Figure 3-19 KMH 820/KTA 810 KFS 578A Interface....................................... 3-83Figure 3-20 KMH 820/KTA 810 Display Interface............................................ 3-87Figure 3-21 KMH 820/KTA 810 Processor Front Connector .......................... 3-95Figure 3-22 KMH 820/KTA 810 Front Connector Cable.................................. 3-96LIST OF TABLESTable 3-1 KMH 820/KTA 810 Connector Pin Assignment ........................... 3-97

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 3-1SECTION IIISYSTEM PLANNING3.0 INTRODUCTIONYou will find information relative to the KMH 880/KTA 870 system requirement options available to the system planner and the electrical characteristics of the various interfaces in Section III. You will also find pin function lists and interconnect diagrams in this section.Section III contains interconnect family diagrams for the KMH 880/KTA 870 system. Refer to figure 3-3 for the KMH 880/KTA 870 system diagram. There are several intercon-nect drawings for popular equipment that interface with the KMH 880/KTA 870. The installing agency should contact Honeywell International Inc. Product Support at (800) 257-0726 for information regarding the compatibility of equipment not listed in this man-ual. Normal business hours are 8:00 A.M. to 5:00 P.M. CST, Monday through Friday.3.0.1 Applicable Part Numbers Subsection DescriptionInformation given in this section pertains only to the KMH 880/KTA 870 System using part numbers. Refer to Section 1.4.1 for complete part number descriptions.3.0.2 Function Subsection DescriptionDetailed information concerning the purpose and operation of the interface are described in this section.3.0.3 Requirements and Limitations Subsection Description.Any operational requirements or limitations relating to the interface are described in this section. Widely followed regulatory requirements may also be described here. Regionally enforced requirements vary greatly and adherence to them remains the responsibility of the installing agency.3.0.4 Electrical Characteristics Subsection Description.The electrical characteristics and format of the interface signals are described in this section. Any flavor-related differences in signal format are also described here. Overlined pin names generally indicate active low signals, although the absence of an overline does not necessarily indicate an active high signal.3.0.5 Interface Subsection DescriptionThe harness techniques for shielding and shield termination described in this manual are identical to those specified for the test harness used during HIRF and Lightning testing. Adherence to the information in this manual is essential in establishing an installation environment equivalent to the test environment used during HIRF and Lightning testing.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Page 3-2 10609I00.ZIPCDL Rev 0, October/2000Should grounding the shields, as shown in the interconnect diagrams, cause unacceptable interference due to noise sources on the aircraft, double shielded wire may be substituted for single shielded wire shown in this manual. The outer shield must be grounded at both ends to comply with HIRF and Lightning require-ments. The inner shield may then be grounded at a single end to protect against the aircraft noise source. Normally the inner shield is grounded at the source end of the signal carried by the wire. Planning to install double shielded wire for low level signals known to have a history of interference may be easier than later add-ing the double shielded wire into the aircraft harness.

B KMH 880/KTA 870Rev0, October/2000 10609I00.ZIPCDL Page 3-3Figure 3-1 KMH 880/KTA 870 Interconnect FamilyDwg. No. 155-01735-0000 (08/18/2000)PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICE

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PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 3-53.1 GENERAL INTERCONNECT INFORMATION3.1.1 Power InputsThe Processor is powered with +28 VDC and is protected by a circuit breaker (5 Ampere) in the Aircraft distribution center.A. 28 Volts Direct CurrentJ10 - 59 & 82 → Nominal: + 28 Vdc A/C Power In. Range: + 22 Vdc to + 30 Vdc. 1.3 ± 0.2 Amps @ 28 VDC typical current 1.65 ± 0.2 Amps @28 VDC Max operating 3.3 Amps @ 18 VDC maximum currentPower: 46 ± 2.3 WattsB. DC ReturnJ10 - 127 & 128These pins connect to airframe ground with 22 gauge wire minimum.NOTEThe KMH 820/KTA 810 will shut down when the power line dips below +15 VDC. The KMH 820/KTA 810 will resume normal operation (i.e. surveilling targets) on power restoration (when the power line meets +18 VDC mini-mum).3.1.2 Air/Ground Discrete InputThe Air/Ground Discrete, if used, is wired to a logic source in the aircraft that presents a standard “open” circuit while the aircraft is airborne and a standard “ground” when the aircraft is on the ground. The Air/Ground Discrete is filtered to allow takeoff and landings. The discrete will remain in the same state for 10 seconds before changing states.AIRBORNE = >100Kohms , or +18.5 to +36 VDC.ON GROUND = < 10 ohms, or 0 to +3.5 VDC.J10-4 Air_Gnd*

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Page 3-6 10609I00.ZIPCDL Rev 0, October/2000NOTEThe normal mechanical failure mode will be the “airborne” condition3.1.3 Landing Gear Discrete InputThe Landing Gear Discrete, if used, will present a standard “open” circuit when the gear is retracted and a standard ground when the gear is extended.RETRACTED = > 100Kohms to airframe DC GND or +18.5 to +36 VDC.EXTENDED = <10 ohms to airframe DC GND or 0 to +3.5 VDCJ10-3 Landing_gear*.NOTEAircraft with fixed landing gear must be equipped with a bottom monopole antenna. Furthermore, the landing gear discrete must be strapped to the retracted position.NOTEThe normal mechanical failure mode is the “retracted” condition.3.1.4 Above/Below/Normal InputThis input defines the Altitude Select for the display. Momentary (250 msec. minimum) application of a “ground” at this input will cause a transistion between the three states in a cyclical manner ; Normal- Below-Above. The default mode is “Normal”.J10-71 ABV_BEL_NORM*

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 3-73.1.5 Baro Altitude (ARINC 429) InputBaro Altitude will be input to the TAS Processor via the Baro Altitude ARINC 429 low speed input bus. This bus may also be used as an ARINC 419 low speed input bus. The ARINC 706 Air Data Computer will interface to the TAS Processor using the ARINC 429 input ports and the ARINC 575 Air Data Com-puter will interface to the TAS Processor using the ARINC 419 input ports.3.1.6 Advisory Inhibit InputThe Advisory Inhibit into the TAS Processor will cause annunciations to be inhibited when higher priority events occur (i.e., wind-shear alerts, terrain alert warnings.)NOTEThe TAS Computer Unit will inhibit certain functions which would tend to distract the pilot when faced with a potentially hazardous condition such as windshear or terrain alerts. These conditions are presumed to have a more immediate possibility and higher probability of harm than the threat of a col-lision. Thus, TAS functions such as aural announcements and aural alerts are to be inhibited by placing the TAS Computer Unit in a mode which would preclude its issuing the unwanted information.If the Advisory Inhibit has been activated, no new voice or annunciator outputs can be activated by the TAS computer unit during the deferment period. If already activated, these outputs will be discontinued within 250 milliseconds. If an advisory condition is present when the deferment is removed, it will be annunciated.ADVISORY INHIBIT = GROUNDNORMAL ADVISORY/ALERT = OPENJ10-22 ADV_INHIBIT*3.1.7 TAS Valid OutputThis output is provided as a primary indicator of valid system operation. This output is driven to the valid state during normal operation. The TAS Valid dis-crete will go invalid during power up self tests and operator commanded self tests.VALID = GROUND ( < 10 ohms to ground)INVALID = OPENJ10-25 TAS_VALID*

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Page 3-8 10609I00.ZIPCDL Rev 0, October/20003.1.8 Visual Annunciate Traffic (Lamp Output)The “Visual Annuciator Traffic” output is activated whenever a traffic advisory is issued. This output will remain in the activated state for the duration of the advisory unless cancelled or inhibited.ACTIVE = GROUND ( < 10 ohms to ground), VOLTAGE 0 to +3.5 VDC.INACTIVE = OPENCurrent Capability = 200 milliamps., when activated.Voltage Capability = +36 VDC, when not activated.J10-24 VIS_ANNUN_TRAFFIC*3.1.9 Synthesized Voice outputKMH 820/KTA 810 will supply low level audio signals of up to 100 milliwatts at 1000 Hz into a 600 ohm audio distribution system. The outputs are on pins “PH_HI” and “PH_LO”.J 10-20 = PH_HI J 10-21 = PH_ LOThe power output will be adjustable based on the audio level inputs. The TAS messages available for output are as follows:1. “TAS System Test OK”2. “TAS System Test Fail”3. “Traffic, Traffic”4. “Traffic”NOTEA 1 kHz tone is available for calibration adjustments only.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 3-93.1.10 Air Temperature InputOutside Air Temperature is an optional input. This can come from a number of sources such as ARINC 429/575 Air Data or a dedicated AOT probe. EGPWS is capable of interfacing directly to a standard 500 ohm temperature probe for low temperature operations.J10-109 OAT_H, J10-110 OAT_L, J10-111 OAT_Ref.3.1.11 GPS InputGPS information is furnished in ARINC 429 and RS-232 (NEMA or RNAV) for-mats. The following Information is required from the GPS:1. Latitude/Longitude2. Ground Speed3 . Tr u e Tr a ck A n g l e4. GPS Altitude5. Indication of the quality of the navigation solution. (VFOM and HFOM prefered).Optional information to be used, if available, are:1. GPS Vertical Velocity2. Number of satelites tracked3. Results of RAIM4. Altitude aiding flagNOTEAn internal GPS xpress Card provides all the needed signals for proper operation.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Page 3-10 10609I00.ZIPCDL Rev 0, October/20003.1.12 Factory Test InputWhen active, the EGPWS will go into the Factory Test Mode. The TAS Proces-sor and the Automatic Test Equipment will interface via RS-232 and the ATE Test Pins.J10-113 GSE_PRES# (Factory Test) (Factory Only)3.1.12.1 TAS ATE Enable InputThe ATE Enable is used to enable the ATE lines for the Anechoic Chamber and the RGS stations. The TAS Automated Test Equipment will fully test the TAS system closing the loop around the TAS antenna system by emulating the functions of an intruder aircraft.3.1.12.2 TAS Built In Test Equipment (BITE)BITE enables the TAS Processor to provide internal system performance mon-itoring under normal bench conditions, under environmental extremes and dur-ing normal operation. All BITE functions are an integral part of the normal operational TAS system and do not interfere with normal TAS operations. The TAS Processor BITE function is responsible for executing the test outlined below (during cold start or functional test) to ensure that the TAS Processor and inputs from interfacing components are functional.1. Automatic System Performance Monitoring (SPM) and Functional Test The TAS Processor SPM and functional test functions will test the TAS Pro-cessor for correct operation (detection of internal faults) and test inputs provided by external system components for correct operation (detection of external faults). The SPM function and functional test are capable of detecting and initiating the appropriate response to all faults that would affect the ability of the TAS Processor to meet TAS system safety and per-formance requirements.System Performance Monitoring is performed on a continuous basis. The tests outlined below are accomplished to ensure correct operation of the TAS Processor and interfacing components during normal operation.NOTEThe purpose of the TAS Processor automatic system performance monitoring (SPM) and Self Test is to detect malfunctions that degrade or preclude TAS protection.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 3-112. Failure ProcessingAfter each functional test or monitoring cycle is complete, the failures detected are prioritized and logged in fault memory if the severity of the fault allows. The fault memory will keep the three highest priority faults per power cycle.When a fault is detected that would cause the TAS Processor to declare TAS inoperative or failed the following responses, regardless of failure cate-gory will be initiated:A. Set the ‘TAS Valid Output’ discrete to invalid.B. Inhibit ATCRBS interrogations from TAS.C. Deactivate the ‘normal’ TAS display functions.D. Cancel any TA voice message.If a fault is detected that would invoke one of the above responses, then that response will be accomplished within one second of detecting the fault.3. Failure CategoriesA. Catastrophic The severity of a catastrophic failure will preclude any software from exe-cuting.B. Fatal The severity of a fatal failure will preclude any TAS surveillance software from executing.C. Critical The severity of a critical failure will force the system to run in a failed state.D. System This type of failure is used for inputs from system sources external to the TAS Processor.3.1.12.3 EGPWS Self Test InputLevel 1 cockpit self-test will annunciate “System OK” when the system is oper-ating properly.J10-121 GND_DISC_07 (Self Test)

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Page 3-12 10609I00.ZIPCDL Rev 0, October/20003.1.12.4 Display Select InputAn input supplied by a momentarily actuated cockpit manual switch that tog-gles between activating and de-activating the Terrain Awareness Display (TAD). J10-123 GND_DISC_12 (Disp. Sel.)3.1.12.5 Terrain Awareness Inhibit DiscreteTerrain awareness will be provided via Terrain and Runway Databases. All run-ways >2000 feet are provided. The nominal terrain database resolution around the airport will be 15 arc-seconds where available. This resolution is not needed for flat areas.J10-126 GND_DISC_15 (Terrain Awareness Inhibit)3.1.13 Terrain WarningThis is a means of displaying to the flight crew that there is a critical situation involving terrain clearance and corrective action is required.J10-116 TERRAIN WARNING3.1.14 Terrain Caution This is a means of displaying to the flight crew that there is a terrain clearance situation developing that needs to be monitored.J10-117 (TERRAIN CAUTION)3.1.15 Weather Select OutputA discrete output for controlling the terrain display. It can be used either to con-trol a picture bus switching relay or connected directly to a symbol generator.J10-118 (WX/EGPWS DISPLAY SELECT)

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 3-133.1.16 EGPWS Audio On DiscreteThe Audio On Discrete goes true whenever any voice message is being annunciated. It will stay true until the voice is completed. This output can be used to inhibit other audio systems (e.g., TAS) during EGPWS audio or used to drive the audio key line input provided on some aircraft audio systems. This discrete is internally wired to the TAS advisory inhibit and is available on:J10-22 ADV_INHIBIT*3.1.17 EGPWS, Terrain Inop and Terrain not available Output The EGPWS produces one monitor output. This discrete reflects the EGPWS Inop and Terrain Inop / Terrain Not Available functions. This discrete activates with the loss of EGPWS power. The status of this discrete is also contained on an ARINC 429 output word.J10-120 (EGPWS Inop)

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BBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 3-15Figure 3-2 KMH 820/KTA 810 Pinout DiagramDwg. No. 155-01735-0001 (Sheet 1 of 7) (08/10/2000)PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICE

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PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBB KMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 3-95Figure 3-21 KMH 820/KTA 810 Processor Front Connector357172815882468384857068698677751235673242244734454457676678225633626554314313142341219405264506337745960155182638253648496173185520 76394130211691110271728295380798795969293949790988988911061051041031021011009998116115114113112111110109108107127126125124123122121120119118117128

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBB KMH 880/KTA 870Page 3-96 10609I00.ZIPCDL Rev 0, October/2000Figure 3-22 KMH 820/KTA 810 Front Connector Cable

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBB KMH 880/KTA 870Page 3-97 10609I00.ZIPCDL Rev 0, October/2000Table 3-1 KMH 820/KTA 810 Connector Pin AssignmentI/O Pin Description UnitNotesFuture Use (Do Not Wire)I1ON* PSPOWER ON=GNDI 2 FUNCTIONAL_TEST TAS TEST=GNDI 3 LANDING_GEAR* TAS EXTENDED=GNDI 4 AIR_GND* TAS ON GND=GNDI 5 DISPLAY_VALID* TAS VALID=GNDI6RADIO_ALT+ TAS ANALOGI 7 RADIO_ALT- TAS ANALOGI 8 RAD_ALT_VAL TAS ANALOGI 9 GIL_ALT_A4 BOTHI 10 GIL_ALT_A2 BOTHI 11 GIL_ALT_A1 BOTHI 12 GIL_ALT_B4 BOTHI 13 GIL_ALT_B2 BOTHI 14 GIL_ALT_B1 BOTHI 15 GIL_ALT_C4 BOTHI 16 GIL_ALT_C2 BOTHI 17 GIL_ALT_C1 BOTHI 18 GIL_ALT_D4 TASI 19 GIL_ALT_D2 TASO 20 PH_HI TAS HEADPHONEO 21 PH_LO TAS HEADPHONEI 22 ADV_INHIBIT* BOTH MUTE=GNDI 23 TAS_STANDBY* TAS STBY=GNDO 24 VIS_ANNUN_TRAFFIC* TAS TRAFFIC=GND ***O 25 TAS_VALID* TAS VALID=GND ***O 26 SPARE_DO1 TAS XO 27 SPARE_DO2 TAS XI 28 HEADING_VALID TASI 29 HEADING_H TASI 30 HEADING_C TASI 31 HEADING_X TASI 32 HEADING_Y TASI 33 HEADING_Z TASO 34 RS422_DATA+ TASO 35 RS422_DATA- TASO 36 RS422_CLK+ TASO 37 RS422_CLK- TASO 38 DIAG_RS232_TX TAS ***I 39 DIAG_RS232_RX TASO 40 DIAG_RS232_RDY TAS ***I 41 DIAG_RS232_TERMRDY TASO42ATE_A(0) TASO43ATE_A(1) TASO44ATE_A(2) TASO45ATE_D(0) TASO46ATE_D(1) TASO47ATE_D(2) TASO48ATE_D(3) TAS

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBB KMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 3-98Table 3-1 KMH 820/KTA 810 Connector Pin Assignment (Cont’)I/O Pin Description Unit NOTES Future Use (Do Not Wire)O49ATE_D(4) TASO50ATE_D(5) TASO51ATE_D(6) TASO52ATE_D(7) TASI 53 CALENB* TASO 54 CDU_429_TX_A BOTH ***O 55 CDU_429_TX_B BOTH ***I 56 RAD_ALTIM_RX_A TASI 57 RAD_ALTIM_RX_B TAS 58 n/c XI 59 AIRCRAFT POWER PSI 60 BARO_ALT_RX_A BOTHI 61 BARO_ALT_RX_B BOTHI 62 HDG_ATT_RX_A TASI 63 HDG_ATT_RX_B TASO 64 SPARE_RS232_TX TAS XI 65 SPARE_RS232_RX TAS XO 66 SPARE_RS232_RDY TAS XI 67 SPARE_RS232_TERMRDY TAS XI/O 68 SUPPRESSION TAS >18V=ACTIVE ***I 69 CNTL_RX_A TASI 70 CNTL_RX_B TASI 71 ABV_BEL_NORM TAS Above/Below/NormI 72 CONFIG_MOD_DATA_IN TASO 73 CONFIG_MOD_DATA_OUT TASO 74 CONFIG_MOD_CHIP_SEL TASO75CM_CLOCK TASO76CM_+5V TAS ***O 77 CM_GND BOTHI 78 SPARE_RX_A TAS XI 79 SPARE_RX_B TAS XO 80 SPARE_TX_A TAS XO 81 SPARE_TX_B TAS XI 82 AIRCRAFT POWER PSO 83 EGPWS RETURN EGPWSO 84 CHASSIS GROUND O 85 RS232TXD_GAMMA EGPWS XI 86 RS232RXD_GAMMA EGPWS XO 87 GPS_TXA EGPWS 232 OUT A / 422I 88 GPS_RXA EGPWS 232 IN A / 422O 89 GPS_TXB EGPWS 422I 90 GPS_RXB EGPWS 422O 91 ADC_TXA EGPWS XO 92 429TX_1B BOTH JUMPER TO TASO 93 429TX_1A BOTH JUMPER TO TASI94ADC_RXA EGPWS XI 95 429RX_1A EGPWS RANGE INPUTI 96 429RX_1B EGPWS RANGE INPUT

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBB KMH 880/KTA 870Page 3-99 10609I00.ZIPCDL Rev 0, October/2000Table 3-1 KMH 820/KTA 810 Connector Pin Assignment (Con’t)I/O Pin Description Unit NOTES Future Use (Do Not Wire)I 97 429RX_2A EGPWS GPSI 98 429RX_2B EGPWS GPSO 99 RS232TXD_MON EGPWS MONITOR PORT ***I 100 RS232RXD_MON EGPWS MONITOR PORT101 ATE_CLOCK TAS X102 n/c XO 103 ASPB_1A EGPWS PICT BUSO 104 ASPB_1B EGPWS PICT BUSO 105 SPIMOSI_CM_2 EGPWS CM DATA OUT ***I 106 SPIMISO EGPWS CM DATA INO 107 SPICLK_CM_2 EGPWS CM CLK ***O 108 SPISEL_CM#_2 EGPWS CM SEL ***I109OAT_H EGPWS AIR TEMP +I110OAT_L EGPWS AIR TEMP -O111OAT_REF EGPWSAIR TEMP REF112 n/c XI 113 GSE_PRES# BOTH FACTORY TESTO114ADC_TXB EGPWSI 115 ADC_RXB EGPWSO 116 DISC_OUT_01 EGPWS LAMP ALERTO 117 DISC_OUT_02 EGPWS WARNING ALERTO 118 DISC_OUT_03 EGPWS WX SELECTI 119 SPARE_IN_2 TASO120MON_OUT_1 EGPWS EGPWS INOPI 121 GND_DISC_07 EGPWS SELF TESTI 122 GND_DISC_08 BOTH XI 123 GND_DISC_12 EGPWS DISP SELI 124 GND_DISC_13 BOTH XI 125 GND_DISC_14 BOTH126 GND_DISC_15 EGPWS TERRAIN AWAREI 127 AIRCRAFT GROUND PSI 128 AIRCRAFT GROUND PSNotes:* indicates active ground*** indicates that this line has a transorb located on the the interconnect board

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBB KMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 3-100THIS PAGE IS RESERVED

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL TOC 4-iSECTION IV POST INSTALLATION CONFIGURATION AND CHECK OUT 4.0 INTRODUCTION .............................................................................. 4-14.1 LINE SELECT KEYS ........................................................................ 4-14.2 CONFIGURATION PROCEDURE .................................................... 4-14.2.1 Power On .......................................................................................... 4-14.2.2 Aircraft Configuration ........................................................................ 4-14.2.3 EGPWS Configuration Instructions.................................................... 4-24.2.3.1 Equipment needed............................................................................. 4-24.2.3.2 Configuration Module Programming.................................................. 4-24.2.3.3 Configuration String Format............................................................... 4-24.2.3.4 RS-232 Maintenance Port (Port SMC1) ............................................ 4-34.2.3.5 RS-232 Diagnostic Port ..................................................................... 4-44.2.3.6 Configuration Sequence of Events .................................................... 4-44.2.3.7 Configuration Types........................................................................... 4-44.2.3.8 Configuration Tables.......................................................................... 4-64.2.3.8.1 Category 1, Aircraft/Mode Type Select............................................ 4-64.2.3.8.2 Category 2, Air Data Input Select .................................................... 4-74.2.3.8.3 Category 3, Position Input Select .................................................... 4-74.2.3.8.4 Category 4, Terrain Display Select .................................................. 4-84.2.3.8.5 Category 5, Input/Output Discrete Type Select ............................... 4-94.2.3.8.6 Category 6, Audio Menu Select ....................................................... 4-104.2.3.8.7 Category 7, Audio Output Level....................................................... 4-104.2.3.8.8 Category 8, Altitude Monitor Options............................................... 4-114.2.3.8.9 Category 9, Terrain Display Alternate Pop Up Option ..................... 4-114.2.4 TAS Configuration Options................................................................ 4-124.2.4.1 TAS RS-232 Maintenance Port ......................................................... 4-154.2.4.2 TAS RS-422 Data Recorder .............................................................. 4-154.3 GROUND TEST PROCEDURES ...................................................... 4-154.3.1 Required Test Equipment.................................................................. 4-154.3.2 EGPWS Ground Test Procedures..................................................... 4-164.3.3 TAS Ground Test Procedures ........................................................... 4-18LIST OF ILLUSTRATIONSFigure 4-1 TAS Bearing Measurements............................................................ 4-34

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL TOC 4-iiLIST OF TABLESTable 4-1 Configuration Identification .............................................................. 4-5Table 4-2 Aircraft/Mode Type Select ............................................................... 4-6Table 4-3 Air Data Input Select........................................................................ 4-7Table 4-4 Position Input Select ........................................................................ 4-8Table 4-5 Terrain Display Select...................................................................... 4-9Table 4-6 Input/Output Discrete Type Select................................................... 4-9Table 4-7 Audio Menu Select........................................................................... 4-10Table 4-8 Audio Output Level .......................................................................... 4-11Table 4-9 Altitude Monitor Options .................................................................. 4-11Table 4-10 Terrain Display Alternate Pop Up Option......................................... 4-12

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 4-1SECTION IVPOST INSTALLATION CONFIGURATION AND CHECK OUT4.0 INTRODUCTIONThis Section describes the procedure for configuring and testing the KMH 880/KTA 870 System after it is installed in the aircraft.4.1 POST CONFIGURATION TESTThis Post-Installation Test verifies the proper operation of the KMH 880/KTA 870 System. These procedures are used after the units have been initially installed. Thereafter, these procedures can be used as an operational check. These tests are performed on the ground.Many of the test can be performed indoors. The scenario tests should be done in an area where the local traffic and signal multipaTH are not a factor. The bearing accuracy tests should be conducted outside away from operating aircraft. 115 VAC, 60 Hz power may be required for the test equipment.CAUTION:ADVISE THE LOCAL AIR TRAFFIC CONTROL BEFORE TESTING THE TRANSPONDERS OR THE KMH 880/KTA 870 SYSTEM WITH A SYNTHETIC ALTITUDE TO ACKNOWLEDGE POSSIBLE INTERACTION WITH OTHER TAS/TCAS-EQUIPPED AIRCRAFT.4.2 CONFIGURATION PROCEDUREThis section describes the configuration options available to be programmed into the Configuration Module of the KMH 880/KTA 870 System.4.2.1 Power OnTurn the KMH 880/KTA 870 System on.4.2.2 Aircraft ConfigurationAircraft Configuration strapping is stored in the configuration module via a personal computer executing TASDIAG software across theRS-232 port. Follow instructions for configuration programming in the TASDIAG Diagnostic, Appen-dix D of this manual.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Page 4-2 10609I00.ZIPCDL Rev 0, October/20004.2.3 EGPWS Configuration InstructionsThese instructions will detail the configuration check list, initial configuration (new configuration module) and volume output levels for the EGPWS.It describes how the EGPWS interfaces to specific aircraft configurations. It con-tains an overview of the selection categories for the different aircraft sensor interfaces. It defines how the category IDs are selected for the interface to air-craft sensors and to select EGPWS performance options. It defines the specific aircraft applications of the EGPWS.4.2.3.1 Equipment NeededA. EGPWS Installed and OperatingB. Interconnect CableC. IBM or Compatible PCD. A Copy of Honeywell WINVIEWSNOTEWinViews is an Enhanced GPWS diagnostic communications program that runs from Windows on a PC that is connected to the EGPWS. WinViews HELP, as well as many other menu items are active even though the program is fully oper-ational when communications are established with the EGPWS.4.2.3.2 Configuration Module ProgrammingThe Configuration Module Programming is completed via the RS-232 port. The application code is capable of loading the Configuration Module with new data.This programming is achieved by using the WinsViews software. In WinViews, the EGPWS will accept valid commands. To prevent inadvertent access to the Configuration Module’s EEPROM, the keyboard monitor is set up with a tiered menu. The keyboard monitor command “CFG” is used to gain access to the Configuration monitor.The command to program the memory with the Configuration String is “CUW”.This command takes a pre-configured String (defined below) containing the new memory contents and a CRC (written by the EGPWS) and writes them to the Configuration Module’s EEPROM.4.2.3.3 Configuration String FormatThe EGPWS requires a string of configuration information to be written to the configuration module memory when requested from the keyboard monitor.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 4-3Example String: = CUW 0/901000220/ (Space after cuw, category and each number if there is no separator)Where the first 0 reflects the string version, the next number is the number of categories and the remaining numbers before the second separator reflect the ID for each of the categories.String breakdown Explanations:CUW = The command to write0 = String Version/ = Separator9 = the number of categories0 = Category #1 ID = 0 (TSO-C151a Class B curve set)1 = Category #2 ID = 1 (Altitude Encoder with 500 ohm Temperature Probe)0 = Category #3 ID = 0 (GPS, Internal GPS Express RS-232)0 = Category #4 ID = 0 (Display select = ASPB)0 = Category #5 ID = 0 (I/O Discrete Type Select = Basic, Lamp format 2)0 = Category #6 ID = 0 (Audio Menu Select = Basic)2 = Category #7 ID = 2 (Audio Output Level = -12dB)2 = Category #8 ID = 2 (Altitude Monitor Option Select = Disable)0 = Category #9 ID = 0 (TA&D Alternate Pop Up = False)/ = Separator4.2.3.4 EGPWS RS-232 Maintenance Port (port: SMC1)One port is provided which meets the characteristics specified in RS232C. This bus can be used to access internal data from the EGPWS for aircraft testing. In addition to the internal data, other items such as unit configuration and flight history can also be accessed.Baud Rate 19,200Parity noneData Bits 8Stop Bits 1Maximum Recommended Cable Length 15 metersPin Assignment (Signal Mnemonic) RS-232TXD_MON J10-99 RS-232RXD_MON J10-100

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Page 4-4 10609I00.ZIPCDL Rev 0, October/20004.2.3.5 Configuration Sequence of Events (Application)A. Turn the KMH 880 system power on.B. Bring up the WINVIEWS program. Type Ctrl Z.C. At the WINVIEWS prompt type “CFG”. Press the ENTER key.D. Type in the pre-configured STRING using the command “CUW”. Press theENTER key.E. After loading this string in the WINVIEWS, the cursor will flash waiting for an answer “Y” or “N”.F. Ty p e “Y”.NOTE At this point the EGPWS will reboot itself.G. When, the system comes back up type Ctrl “Z” then type “PS” (Present Status).H. Check the Status information displayed. Confirm that your configuration input write is accurate.4.2.3.6 Configuration Types (Categories)The selection of the basic interfaces to the EGPWS can be found in the following catego-ries.Aircraft/Mode Type Category 1Air Data Type Category 2Position Type Category 3Terrain Display Type Category 4I/O Discretes Types Category 5Audio Menu Type Category 6Audio Output Level Type Category 7Altitude Monitor Options Type Category 8Terrain Display Alternate Pop up Option Category 94.2.3.7 Configuration Identification Selection (ID)The method to select the Configuration Identification (ID) for each Category Type on a given aircraft installation is with the information in this document and the following table.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 4-5This table provides the procedure to determine the Configuration ID selection required for any given aircraft installation.STEP(CATEGORY)SIGNALSELECTION INSTRUCTION IDENT. NO. 1Selects:a) Aircraft Typeb) Mode TypeUsing Table 4-2 and any sub-tables contained within, locate the Air-craft/Mode type.Record the Ident (ID No.) on the space available on Ident column of this table._____ ID # 2Selects:a) Air Data SourceUsing Table 4-3 and any sub-tablescontained within, locate the desiredAir Data signal type.Record the Ident (ID No.) on the space available on Ident column of this table_____ ID # 3Selects:a) Position SourceUsing Table 4-4 and any sub-tablescontained within, locate the desiredPosition Signal type.Record the Ident (ID No.) on the space available on Identcolumn of this table._____ ID # 4Selects:a) Display ConfigurationUsing Table 4-5 and any sub-tablescontained within, locate the desiredDisplay indicator type/range bus type.Record the Ident (ID No.) on the spaceavailable on Identcolumn of this table._____ ID # 5Selects:a) Input discrete Functionsb) Output Discrete Functions.Using Table 4-6 and any sub-tablescontained within, locate the desiredI/O Discrete type.Record the Ident (ID No.) on the spaceavailable on Ident column of this table._____ ID # 6Selects:a) Audio MenuUsing Table 4-7 and any sub-tablescontained within, locate the desiredAudio Menu typeRecord the Ident (ID No.) on the spaceavailable on Identcolumn of this table._____ ID # 7Selects:a) Audio Output LevelUsing Table 4-8 and any sub-tablescontained within, locate the desiredVolume typeRecord the Ident (ID No.) on the spaceavailable on Identcolumn of this table._____ ID #

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Page 4-6 10609I00.ZIPCDL Rev 0, October/2000Table 4-1 Configuration Identification4.2.3.8 Configuration TablesThe Category columns define a category (or group) of functions or input devices that are selected through ID Numbers. The Category Number identifies the subsection where the details are defined. For example Air Data, Category 2, is identified in Table 4-3 and Posi-tion Input Source, Category 3, is defined in Table 4-4.4.2.3.8.1 Category 1, Aircraft/Mode Type SelectThe following table provides identification of the basic mode types and associated parameters.In this category only the following parameters are to be defined:• Basic mode alert and warning thresholdsTable 4-2 Aircraft / Mode Type Select 8Selects:a) Altitude Monitor Display Disableb) Altitude Monitor Call out Disablec) Altitude Monitor DisableUsing Table 4-9 and any sub-tablescontained within, select the desiredTrue or False Condition for AltitudeMonitor Display Disable, AltitudeMonitor Callout Disable, and Alti-tude Monitor Disable.Record the Ident (ID No.) on the spaceavailable on Identcolumn of this table. _____ ID # 9 Selects:a) TA&D alternatePop UpUsing Table 4-10 and any sub-tables contained within, select the desired True or False condition forTA&D Alternate Pop Up.Record the Ident (ID No.) on the space available on Ident column of this table._____ ID # ID Aircraft/Mode Type Description EffectivityApp. Cfg. 0 0 TSO-C151a Class B curve set -001 -001 1 1 Non-TSO curve set #1 -001 -001STEP(CATEGORY)SIGNALSELECTION INSTRUCTION IDENT. NO.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 4-7NOTEWhen selecting ID 0; Category 6, (Audio Menu Select) must select ID #1 (Alter-nate) in order to be in compliance with TSO-C151a.4.2.3.8.2 Category 2, Air Data Input SelectThe following table provides identification of the Air Data source type. In this category only the following parameters are to be defined:• Gillham/Gray coded altitude or uncorrected altitude in ARINC 429 format. Temperature, Outside Air or Static Air in analog or ARINC 429 format.Table 4-3 Air Data Input Select4.2.3.8.3 Category 3, Position Input SelectThe following table provides identification of the Position Source Signal. In this category, only the following POSITION signals are to be defined:• Altitude • Sensor Status• Date • Track angle• Ground Speed • Universal Time Correlation• Horizontal Figure of Merit (HFOM) • Vertical Figure of Merit (VFOM)• Horizontal Integrity Limit • Vertical Velocity• Latitude Position • N/S Velocity• Longitude Position • E/W Velocity ID AIR DATA TYPE DESCRIPTION EFFECTIVITYApp. Cfg. 0 0 Altitude Encoder (9 wire Gillham/Gray coded altitude) -001 -001 1 1 Altitude Encoder (9 wire Gillham/Gray coded altitude)with 500 ohm OAT Temperature Probe-001 -001 2 2 Digital - ARINC 429 (Required Labels are 203 and 213)-001 -001 3 3 Digital - ARINC 429 (with Corrected Altitude)(Required Labels are 203,204,212,and 213)-001 -001

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Page 4-8 10609I00.ZIPCDL Rev 0, October/2000Table 4-4 Position Input SelectNOTE 1The GPS Altitude Reference MSL or WGS-84 must be properly applied for the appropriate GPS Position Type. At the time of release of this document, all GPS sources except the Universal UNS-1 GPS are of the MSL type. The Universal UNS-1 GPS (GPS-1000 engine in the UNS-1B+,-1C, -1D, -1k,and -1M) sources are of WGS-84 type.NOTE 2This configuration is only applicable to Honeywell Qualification Test Lab. When this configuration is enabled on a 066-01175-2101 (EGPWS with internal GPS) a software internal GPS monitor is activated for testing.4.2.3.8.4 Category 4, Terrain Display SelectThe following table has an identification number (ID) associated with each Terrain Display configuration. Each of the ID rows has a group number for the Display configuration, the Input Control and the output 429 bus. The TA&D Pop Up Disable function is defined by a Boolean. See Table 4-10. ID POSITION INPUT TYPE DESCRIPTION GPS ALTITUDE REFERENCE EFFECTIVITYApp. Cfg. 0 0 GPS, Internal GPS-PXPRESS RS-232 MSL -001 -001 1 1 GPS, External RS-232 (GPS-PXPRESS format) MSL -001 -001 2 2 GPS, ARINC 429 low speed, 743A format MSL -001 -001 3 3 GPS, ARINC 429 low speed, 743 format MSL -001 -001 4 4 GPS, ARINC 429 low speed, 743 format(GPS Altitude referenced to WGS-84) WGS-84 -001 -001

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 4-9In this category the following signals are configured by the ID number:Table 4-5 Terrain Display Select4.2.3.8.5 Category 5, Input/Output Discrete Type SelectThe following table provides identification of the Input/Output Discrete Type.Table 4-6 Input/Output Discrete Type Select SIGNAL NAME SIGNAL TYPE DEFINED BYTerrain Display Bus ASPB or ARINC Display configuration GroupRange Bus ARINC 429 Display Input Control GroupTA&D Alternate Pop Up Boolean Defined directly in Table 4-10 ID DISPLAYCONFIG.GROUPDISPLAY INPUTCONTROL GROUP (NOTE 1)OUTPUT429 BUS GROUPAPPLICATION NOTES EFFECTIVITYApp. Cfg. 0 0 0 0 ASPB -001 -001 1 None None 0 No Display -001 -001 2 1 1 0 Bendix IN 182A, IN 812A-001 -001 3 2 1 0 BendixIN 842A, IN 862A-001 -001 4 3 2 0 Bendix RDR 4A/B PPI(with blue waters modification)-001 -001 ID Input/Output Discrete Type Description EffectivityApp. Cfg. 0 0 Basic input/output discretes (Lamp Format: Type 2) -001 -001

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Page 4-10 10609I00.ZIPCDL Rev 0, October/2000NOTEIf a single cockpit lamp is desired for Terrain Cautions and Warnings, J10-116 and J10-117 can be diode or’ed together to drive one lamp.4.2.3.8.6 Category 6, Audio Menu SelectThe following table provides identification of the Voice Menu type.Table 4-7 Audio Menu SelectNOTEIf Category 1 selected ID #0 (TSO-C151a Class B curve set) Category 6 ID #1 (Alternate) must be selected to be in compliance with the TSO.4.2.3.8.7 Category 7, Audio Output LevelThe following provides identification of the Audio Output Level type. Each entry in the ID column corresponds to a particular nominal alert output level selection (max,-6dB, -12 dB, -18dB AND -24Db). The Nominal “Max” Output is 100 mW/rms for the 600 ohm out-put. The output power level will be the nominal maximum output 100mW reduced by the selected volume type. ID AUDIO MENU TYPE DESCRIPTION EFFECTIVITYApp. Cfg. 0 0 Basic -001 -001 1 1 Alternate -001 -001

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 4-11Table 4-8 Audio Output level4.2.3.8.8 Category 8, Altitude Monitor OptionsThe following table provides identification of the Altitude Monitor Options. Each entry in the ID column corresponds to a particular combination of Altitude Monitor Display Dis-able, Altitude Monitor Callout Disable and Altitude Monitor Disable.NOTE: TRUE = DisableTable 4-9 Altitude Monitor Options4.2.3.8.9 Category 9, Terrain Display Alternate Pop Up OptionThe following table provides identification of the Terrain Display Alternate Pop Up Option. TA&D Alternate Pop Up = False allows automatic Pop Up On Caution or Warnings. ID VOLUME TYPE EFFECTIVITYApp. Cfg. 0 Max (600 ohm ≈ 100mW) -001 -001 1 -6 dB -001 -001 2 -12dB -001 -001 3 -18dB -001 -001 4 -24dB -001 -001255 -14db for ΚΜΗ 880/ΚΤΑ 870 configuration -001 -001 ID ALTITUDE MON-ITOR DISABLEALTITUDE MONITOR CALLOUTDISABLEALTITUDE MONITORDISPLAY DISABLEEFFECTIVITYApp. Cfg. 0 False False False -001 -001 1 False False True -001 -001 2 False True False -001 -001 3 False True True -001 -001 4 True True True -001 -001

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Page 4-12 10609I00.ZIPCDL Rev 0, October/2000TA&D Alternate Pop Up = True disables the automatic Pop Up feature.Table 4-10 Terrain Display Alternate Pop Up Option4.2.4 TAS Configuration OptionsThe TAS Processor will acquire the following hardware strap information from the configuration module.NOTEFormat is as follows: Configuration Option; Configuration Option Description.A. Display Intruder Limit; 3 (Minimum) Display Intruder Limit 30 (Maximum), incremented by 1.The Display Intruder Limit Program is used to limit the number of intruders displayed in the aircraft. The Display Intruder Limit will be configured to a value between 3 (minimum FAA requirement) and 30 (max. intruder limit).NOTEThe TAS Processor will transmit a maximum of 30 intruders to the traffic display.B. Heading Type; Synchro Data or ARINC 429 DataThe Heading Type Program will indicate the type of heading source (either ARINC 429 or Synchro) that interfaces to the TAS. C. Attitude Type; Not Installed or ARINC 429 Data. ARINC 429 magnetic heading (BCD or Binary), pitch angle and roll are input to the TAS Processor via the Attitude/Magnetic Heading ARINC 429 high speed input bus. ID TA&D ALTERNATE POP UP DISABLE EFFECTIVITY 0 False -001 -001 1 True -001 -001

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 4-13D. Radio Altimeter Type; Not Installed, ARINC 429, Bendix/King Analog, Sperry Analog, Collins Analog or ARINC 552A.The Radio Altimeter Source Port will input to the TAS Processor. The input impedance into this port is 55 Kohms. The port has an associated Radio Altitude Valid flag input to the TAS Processor.Radio Altimeter Valid input will be 20 to 30 VDC during proper altimeter operation (if present). Any failure of the altimeter causes the flag signal to become an open circuit. The analog radio altimeter input (if present) will be considered failed if the altitude is within a valid range (-20 to 2500 feet) and the valid pin is in the invalid state.The Radio Altimeter Type Program will indicate which type of radio altime-ter input is used.NOTEDue to tolerances in the TAS Processor analog I/O hardware, the accuracy for the 0 - 100 foot range may be ± 10 feet.E. On Ground Display Mode; TAS in Standby Mode On-Ground or TAS in TA Only Mode On-Ground.The On Ground Display Mode will indicate to the processor whether the system will go to Standby Mode when on the ground or that the system will go to TA Mode (with aurals and voice inhibited due to altitude defined by TAS logic) when the aircraft is on the ground.F. Baro Altimeter Type; Gillham, ARINC 575, ARINC 706.The Barometric Altimeter Type program will indicate the type of barometric altimeter source [either Gillham/Gray Code, ARINC 575 (ARINC 419) or ARINC 706 (ARINC 429)] that interfaces to the TAS Processor.G. Controller Type; ARINC 735 Protocol, or Discrete Control.The Controller Type will determine the type of control data, either the Con-trol Panel to the TAS Processor via the CNTL HD RX (ARINC 429) input bus or via Discrete Control switches.H. Ground Headphone Volume; 1.25, 2.5, 5, 10, 20, 40, 80, 100 mw.The on ground headphone level will be configurable to the above levels.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Page 4-14 10609I00.ZIPCDL Rev 0, October/2000I. Airborne Headphone Volume; 1.25, 2.5, 5, 10, 20, 40, 80, 100 mw.The airborne headphone level will be configurable to the above levels.J. Airborne Functional Test; Inhibited or Allowed.When the Airborne Functional Test is inhibited, the TAS Processor will inhibit Functional Test while in the air.When the Airborne Functional Test is allowed, the TAS Processor will allow Functional Test in the air.K. ATE Output; Enabled or Disabled.The ATE Output will be used to enable the ATE lines for the Anechoic Chamber and the RGS stations.L. Intruder File ProtocolARINC 735a or Honeywell Business and Commuter Aviation Systems (BCAS) protocol.M. Display Valid Input Usage: Used or Ignored.If “Used“ is selected, TAS will use the Display Valid Input for BITE pur-poses. If “Ignored” is selected, TAS will ignore the Display Valid Input for BITE purposes.N. RS-422 Output Drivers: enabled or disabledWhen the TAS processor is configured to have the Data Recorder RS-422 Drivers enabled, the RS-422 output bus shall be active. When the RS-422 Drivers are disabled the output bus shall be inactive. This should be set to “disable” for aircraft installations.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 4-154.2.4.1 TAS RS-232 Maintenance PortOne port is provided which meets the characteristics specified in RS232C. This bus can be used to access internal data from the TAS for aircraft testing. In addi-tion to the internal data, other items such as unit configuration and flight history can also be accessed.Baud Rate 38,400Parity noneData Bits 8Stop Bits 1Maximum Recommended Cable Length 15 MetersPin Assignment (Signal Mnemonic)DIAG_RS232_TX J10-38DIAG_RS232_RX J10-39DIAG_RS232_RDY J10-40DIAG_RS232_TERMRDY J10-414.2.4.2 TAS RS-422 Data RecorderOne port is provided which meets the characteristics specified in EIA RS-422A. This bus can be used as a data recording vehicle. It need not be wired unless requested by Honeywell personnel.Maximum Recommended Cable Length 15 FeetPin Assignment (Signal Mnemonic)RS422_DATA+ J10-34RS422_DATA- J10-35RS422_CLK+ J10-36RS422_CLK- J10-374.3 GROUND TEST PROCEDURES4.3.1 Required Testing Equipment• Personal Computer with Diagnostic Program (WinViews for the EGPWS ground tests and TASDIAG for TAS ground tests. (See Appendix D).• TCAS Ramp Test Set; TCAS 201, or equivalent.• Transponder Ramp Test Set.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Page 4-16 10609I00.ZIPCDL Rev 0, October/2000• Pitot-Static Test Set.• Radio Altimeter Test Set, or equivalent.• Volt-Ohmmeter (DVM) (optional).• 429 Bus reader (optional).4.3.2 EGPWS Ground Test Procedures (066-01175-x101 only).This Ground Test Procedure is designed to minimize potential equipment dam-age and verify proper operation of the Honeywell EGPWS as installed in the air-craft. A. Review your aircraft installation drawings against the manufacturer’s data sheets and verify that all necessary connections are included on your draw-ings and that the pin numbers are in agreement.B. With all units disconnected and aircraft power off, do a point to point wiring check using an ohm meter to verify proper wiring interconnect.C. With all units disconnected, apply aircraft DC power and verify that power is supplied to the power input pins.D. Remove power from the aircraft and connect all units.E. Connect a PC to the RS-232 communications port of the EGPWS unit.F. Power up the PC, start “WinViews” and select connect.G. Power up the avionics in the aircraft. You should note the “Not Available” light ON and you should see INITIALIZATION messages coming from the EGPWS on your PC. When the messages quit (could be as long as 3 min-utes for the first application of power) press Control ‘Z’ on your keyboard. The PC display should show a ‘>’.H. Type ‘PS’ and the ‘return’ key on your PC. You should receive several lines of status messages from the EGPWS. One of the messages should be ‘Configuration Module not initialized’. Instructions for programming the con-figuration module are contained in section 4.2.3.2 of this document. Go to section 4.2.3.2 at this time and after configuration has been completed, return to item I below.I. With your PC communicating with the EGPWS, select ‘file’ at the top of the WinViews screen. Select ‘Load Command File’ and then select the file named Gagnddtst.cmd. (This file was supplied on your WinsViews Disk).

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 4-17J. Now press function key F6 on your keyboard.K. Set the aircraft’s altimeter to 29.92 IN Hg and note the altitude displayed on the altimeter. Now look at the PC screen and locate the item named Gill-ham Alt ft. and verify that the altitude shown agrees with the aircraft altime-ter, ± 100 feet. If it does not, troubleshoot the encoding altimeter / wiring.L. Provide a source of GPS signals to the GPS antenna. This can be accom-plished by using a GPS repeater inside a hanger, or by taking the aircraft outside where it has a clear view of the sky.M. Press function key F6 to return to the command mode of WinsViews. Type in GPS followed by the ‘Return’ key to view the status of the GPS receiver. Typing control ‘R’ on the keyboard will re-issue the last command sent and allow you to continue to monitor GPS status. Once the GPS has acquired satellites, the status message “Not Navigating” will change to “Navigation with possible data collection”. The Not Available Lamp should turn off and if a display is being used, a North UP terrain view should be shown on the display.N. Press the ‘Self Test’ switch and verify that the unit lights all lamps, produces audio and the display, if installed, shows a test pattern. The EGPWS self test function will identify any problems with the interfaces or with the EGPWS computer. Troubleshoot any problem reported during the self test.O. Connect a pitot-static test set to the aircraft static system. Operation of the pitot-static test set should be performed only by persons trained in its use. Additionally, if the aircraft static system was opened or modified to add an encoder, the static system must be tested and approved by a licensed mechanic or authorized repairman. Improper use of the pitot-static test set can result in damage to altimeters, vertical speed indicators, etc.P. Start with the pitot-static test set at current field elevation. Set the reference altimeter in the test set for 29.92 IN. Hg.Q. On the PC, select the Data display mode (F6). With the system receiving GPS signals and no faults reported, you should now verify that the system has correctly identified your closest airport. Look at the following items on the PC display:CrwyApt (the letter/number identifier of the closest airport Only public airports with runways 2000 feet or longer)CRwyDist nm The distance in nm to the reference point of the airport.Verify that the displayed information agrees with your geographic location.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Page 4-18 10609I00.ZIPCDL Rev 0, October/2000R. Set the pitot-stat test set to -1000 feet, exercise caution to avoid excessive pressure changes to the static system of the aircraft. Verify that the PC dis-play shows the item named Gillham Alt ft. at -1000 feet ± 100 feet.S. Set up the pitot-static test set to allow an ascent to 30,000 feet, or to the maximum altitude of the lowest rated device attached to the static system. If, for example, the aircraft uses a blind encoder rated to 25,000 feet; the altitude to climb to would be 25,000 feet.You must verify that all equipment connected to the static system can safely be driven to your test altitude. If you go above 30,750 feet, the Gillham Alti-tude displayed on your PC will start going backwards. This is normal because the EGPWS does not use Gillham Code line D4. At altitudes above 18,000 feet, the EGPWS uses GPS altitude for calculations.T. Start an ascent at 3,000 feet per minute while monitoring the item named Gillham Alt ft. At approximately a 2-second rate the displayed altitude should increase by 100 feet. Make absolutely certain that the altitude always increases; never goes backwards and never skips a 100 foot incre-ment. You can record this test using the data collection feature of Win-Views. This will allow you to look through the data after the test using a text editor. This test verifies that the barometric altitude source is working correctly and that the wiring is correct. Troubleshoot anomalies discovered during this test.U. Return the static test set and aircraft static system to the local ambient pressure.V. If installed, press the Terrain Inhibit switch and verify that the item named TerrDis switches between true and false on your PC’s display.W. This completes the Ground Test of the EGPWS.4.3.3 (TAS) Ground Test ProcedureInstallation of the TAS System requires three stages of testing to ensure the proper oper-ation of the TAS System components. Initially, before installation of the TAS processor and display units, a system interwiring check is performed. This check verifies that the aircraft and all TAS System interconnections are correct, before power is applied. After the units are installed, a visual inspection of the equipment and connections is made. The Post-installation test is used to apply power and functionally check out the system. Successful completion of the post-installation test verifies the proper operation of the KMH/KTA Traffic Advisory System.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 4-19A. To check the aircraft system interconnections, perform the following:Check that all cables and interwiring are installed according to the Interwir-ing and Cable Fabrication instructions. (paragraph 2.2.7 and 2.2.8)Check that the following functions are properly strapped to reflect the air-craft system configuration. (paragraph 4.2.3.6)•Aircraft/Mode Type•Air Data Type•Position Type•Terrain Display type•I/O Discretes Type•Audio Menu Type•Audio Output Level Type•Altitude Monitor Options Type•Terrain Display Alternate Pop UP OptionUsing the interconnect diagrams (Figures 3-1 through Figure 3-23), check wiring for proper destinations, opens and shorts.Check RF Cable for electrical length matching, insertion loss and VSWR. (See paragraph 2.2.7 and 2.2.8)Check the transponder and DME interface.NOTEThe only required interface between the KMH/KTA TAS and the transponder is the suppression line. Some installations may use a common control for the tran-sponder and the TAS. In these cases, the TAS control comes from the transpon-der control unit.B. In conjunction with the system installation, perform a visual inspection.C. Perform the Pretest Setup to set the initial conditions to check the operation and self-test features of the system. The following steps apply and check the TAS System input power, configure the operational controls, and verify that the system is ready for testing. It is assumed that the person perform-ing these tests has a working knowledge of the KMH/KTA TAS System and the Graphics Unit and is qualified to perform these tests on the aircraft.Ensure that all aircraft systems are secure and safe. Confirm that 28Vdc and 26Vac 400 Hz power sources are operational; i.e., check power bus meter.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Page 4-20 10609I00.ZIPCDL Rev 0, October/2000Check that the aircraft 5Vac or Vdc or 28 Vdc panel background lighting power source and dimmer control is operational by adjusting the cockpit dimmer switch for proper cockpit panel background illumination.Check that the Transponder, TAS, and Radar Systems are OFF. If applica-ble, the selected encoding altitude source should be #1. If applicable, the ADC (Air Data Computer) source should be set to normal.Operate the appropriate aircraft circuit breakers to apply power to the TAS Processor, Traffic Advisory displays and all other aircraft equipment con-nected to the TAS Processor subsystem. Check that the circuit breakers remain closed (pushed in).Allow enough time for equipment warm-up. Equipment in the TAS system require one minute for equipment warm-up. External sensors may require more than one minute warm-up time.On the TAS control panel, Place the SBY switch to SBY mode. Place the ABOVE/NORM/BELOW switch so as to indicate “NORM”. Place the Range so the 5 nautical mile (nmi) range has been selected. The following should be visible on the traffic display screen:• No “TAS” flag annunciation.• “TAS STBY”.• If installed, the TA/VSI vertical speed needle should indicate 0 fpm.Check that the brightness of the traffic display can be controlled by the appropriate control. Brightness of the traffic display may be controlled by the aircraft dimmer switch or by the BRT control on the display unit.On the TAS Control Unit, select the ON position. The following conditions should exist:• The traffic display should indicate “TA ” or “TA ONLY”.• No faults or fail annunciations are present on the traffic display.• Traffic may be displayed on the traffic display depending on the TAS strapping configuration and whether traffic exists in the area. • Non-threat Traffic, displayed as an open white diamond. • Proximity Intruder Traffic, displayed as a filled white diamond. • Traffic Advisory (TA) traffic, displayed as a yellow circle.D. Perform the Self-test by initiating the TAS System Self-test on the TAS Con-trol Panel. The following events should occur during the test period:On the traffic display, a test pattern will be displayed that allows verification of each type of intruder symbol that can be displayed. During the self-test,

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 4-21the word “TEST” is displayed on the display. The following symbols are dis-played:• Traffic Advisory (yellow circle) will appear at 9 o’clock, range of 2 miles, 200 feet below and climbing.• Proximity traffic (solid white diamond) will appear at 1 o’clock, range 3.6 miles, 1000 feet below and descending.• Non-threat traffic (open white diamond) will appear at 11 o’clock, range of 3.6 miles, flying level 1000 feet above.At the conclusion of a successful self-test, a synthesized voice announces, “TAS System Test OK”. Should a failure be detected during self-test, the audio message says, “TAS System Test Fail”.E. Perform the Ground Test.Ground tests are necessary to meet the requirements of DRAFT AC 20 ZZ. While the tests are organized in a sequential fashion, they may be com-pleted in a random order to accommodate other conditions. The person performing these tests should be familiar with the TAS equipment, the air-craft installation and the supporting test equipment.NOTEIn the following test results space “_____”, enter “P” for Passed, “F” for Failed and/or fill in the results or comments. If the section does not apply, write N/A.1. Perform the TAS Power Checks Verify aircraft power to TAS Pull the 5 amp TAS Processor circuit breaker. Verify that the “TA S ” flag appears on the traffic display. Reset the circuit breaker. Verify that the flag clears. Pass/Fail _____. Pull the 1 amp TAS Control circuit breaker. Verify that the “TA S ” flag appears on the traffic display. Reset the circuit breaker. verify that the flag clears.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Page 4-22 10609I00.ZIPCDL Rev 0, October/2000 Pass/Fail _____NOTEThe following three steps should only be performed when the configuration mod-ule is set to use the Display Valid input. Pull the Traffic Display circuit breaker.NOTEThe above circuit breaker should be for the unit providing a valid to the TAS Pro-cessor at pin 5. Verify that the appropriate flag appears INVALID. Reset the circuit breaker. Verify that the flag clears. Pass/Fail _____ Disable the 26Vac 400 Hz source used as a reference for the Hg and Alt inputs. Verify that the “TA S ” flag appears on the traffic display. Reset the circuit breaker. Verify that the flag clears. Pass/Fail _____2. On the TAS Control Panel exercise all the TAS control functions and observe for correct operation. Test the ON/OFF and STB/ON functions as follows: Set the PWR switch to the OFF condition. (If applicable) Reset the PWR switch to the ON condition. (If applicable) Set the SBY switch to the ON mode. On the traffic display screen, check that “TA ” or “TA ONLY” annuncia-tion is displayed.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 4-23 Pass/Fail _____ Test the ABOVE/NORMAL/BELOW function as follows: On the TAS Control Panel, set the ABOVE/NORMAL/BELOW to ABOVE. On the traffic display screen, “ABOVE” should be annunciated. Traffic between 2700 feet below and 8700 feet above can be displayed. Select BELOW. The screen should annunciate “BELOW” in place of the “ABOVE” annunciation. Traffic between 8700 feet below and 2700 feet above can be displayed. Set the switch to NORMAL. The screen area that annunciated “ABOVE” or “BELOW” should be blank. Traffic between 2700 feet above and 2700 feet below can be displayed. Traffic Display _____ On the traffic display, check the TAS ranges to observe the range annunciations and range rings.NOTEThere are two configurations for the KMH 820/KTA 810, 3-5-10-15 and 5-10-20-40. Not all ranges are available in every configuration.NOTEThe 2 nm range ring is visible on all TAS RANGE selections less than 20 nm. Set TAS RANGE switch to 3 nautical miles. The following properly scaled range rings should be visible: 2 and 3 nautical mile range rings. ______ Set TAS RANGE switch to 5 nautical miles. The following properly scaled range rings should be visible: 2 and 5 nautical mile range rings. ______ Set TAS RANGE switch to 10 nautical miles. The following properly scaled range rings should be visible:

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Page 4-24 10609I00.ZIPCDL Rev 0, October/2000 2 and 10 nautical mile range rings. ______ Set TAS RANGE switch to 15 nautical miles. The following properly scaled range rings should be visible: 2 and 15 nautical mile range rings. ______ Set TAS RANGE switch to 20 nautical miles. The following properly scaled range rings should be visible: 5, 10, and 20 nautical mile range rings. ______ Set TAS RANGE switch to 40 nautical miles. The following properly scaled range rings should be visible:NOTEOn the traffic display unit, an outer ring represents maximum nautical (nm) dis-play scaling as selected on the RANGE switch. If applicable, test the FL (Flight Level) function as follows: Press the FL switch. Observe that the traffic display indicates “FL” in the upper left hand corner. It will be FL --- (flagged) on most displays unless encoding altitude source is higher than 18,000 feet. Pass/Fail _____ If applicable (-0901 and -1001 versions of the CP 66B with a Honeywell Multi-Functional Display), check that the display modes can be selected properly via the MAN_AUTO discrete as follows: Via the separate Man/Auto switch, ground MAN_ AUTO, CP 66B J1 pin 23, and verify that when TCAS is not selected on the Multi-Functional Display, it only displays TAS information when a TA is in effect. Via the separate Man/Auto switch, open MAN_AUTO, CP 66B J1 pin 23, and verify that TAS information is displayed on the Multi-Functional Display only when TAS has been selected on it regardless of whether there is a TA in effect.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 4-25 Pass/Fail _____3. If applicable, check that the traffic modes (T/WX) can be selected on the color radar indicator as follows: Set the T/WX switch to indicate “WX” (Weather Only). Observe that the traffic display (radar indicator) annunciates “TA AU TO ”, but unless TA traffic is present only the radar picture is displayed. Set the T/WX switch to “T/WX” (TAS and Weather). Observe that the traffic display annunciates “TA ” or “TA O N LY ” and shows both traffic and weather if the radar is ON. Select “TCAS” (TAS ONLY) with the T/WX switch. Observe that the traffic display annunciates “TA ” or “TA O N LY ” and shows TAS traffic but no weather is displayed. Pass/Fail ______4. Confirm the Sensor Input to TAS by using a diagnostic computer program. Additionally, the fault source can be viewed on the radar indicator or by reading the LED fault code on the processor. Verify the heading source interface to the TAS Processor. Confirm the heading source and measure the inputs at the KMH/KTA Processor. Refer to the drawings for the proper pin assignments. The TAS and heading system should be operating normally for the following test. Connect the Diagnostic Computer to the KMH/KTA through the RS-232 port. Run the TASDIAG Input Data program and observe the following on the Diagnostic Computer. Monitor the heading source in the cockpit. Observe the Mag. Heading readout on the computer. The computer readout should agree to within a few degrees with the cockpit heading display. Record a heading other than North (0.0°) _________. The Heading Status on the computer should indicate VALID. The heading type should indicate Synchro or ARINC 429. Flag the heading source by pulling the circuit breaker.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Page 4-26 10609I00.ZIPCDL Rev 0, October/2000 Verify that the Heading Status goes INVALID. Verify that the “TA S ” flag appears on the traffic display. Reset the circuit breaker. Verify that the TAS flag clears. Pass/Fail ______5. Verify that the encoding altitude is properly interfaced to the TAS Processor. Confirm that the encoding altitude of the transponder and TAS agree.CAUTIONPRECAUTIONS MUST BE TAKEN TO INSURE THAT THE ALTITUDE TEST OF THE TRANSPONDER DOES NOT INTERFERE WITH OTHER TCAS/TAS EQUIPPED AIRCRAFT. SHIELDING THE TRANSPONDER AND TAS ANTEN-NAS IS THE BEST WAY TO PREVENT INTERFERENCE WITH OTHER AIR-CRAFT. The TAS, transponder and encoding altitude source(s) should be operating normally for the following test. Connect the Diagnostic Computer to the KMH/KTA through the RS-232 port. Run the TAS-DIAG Input Data program and observe the following on the Diagnostic Computer. Monitor the altitude source in the cockpit. Set the baro to 29.92”. Observe the Enc. Altitude readout. The computer readout should agree to within 50 feet of the cockpit altimeter. The Enc. Alt. Status in the computer should indicate VALID. Confirm the following Encoding Altitudes at the altimeter, Diagnostic Computer and transponder:Altitude at 2,000 feet, the computer screen indicates ______feet.Transponder indicates ______ feet.Altitude at 7,800 feet, the computer screen indicates ______ feet.Transponder indicates ______ feet.Altitude at 19,000 feet, the computer screen indicates ______ feet.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 4-27Transponder indicates ______ feet.Altitude at 31,800 feet, the computer screen indicates ______ feet.Transponder indicates ______ feet.NOTEThe above test step checks both logic states for all Gillham lines. Other tests may be adequate for some installations.Flag the encoding altitude source by pulling the circuit breaker.Verify that the Enc. Alt. Status goes INVALID.Verify that the ”TAS” flag appears on the traffic display.Reset the circuit breaker. Verify that the “TA S ” flag clears.Enc. Altitude Source #1 Pass/Fail ______.If applicable, select the other encoding source and repeat the abovesteps.Enc. Altitude Source #2 Pass/Fail ______.If applicable, verify the attitude interface to the TAS Processor. Confirmthe pitch and roll attitude source and measure the inputs at the KMH/KTA Processor.The TAS and attitude should be operating normally for the followingtest. Connect the Diagnostic Computer to the KMH/KTA through theRS-232 port. Run the TASDIAG Input Data program and observe the following on the computer screen.Monitor the attitude source in the cockpit. Observe the Pitch and Rollattitude readouts. The computer screen readouts should agree towithin a few degrees of the cockpit heading display. Record a pitch androll attitude other than (0.0°) ______. Is it consistent with the aircraft’sattitude?The Pitch and Roll Status on the computer should indicate VALID.Flag the attitude source by pulling the circuit breaker.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Page 4-28 10609I00.ZIPCDL Rev 0, October/2000Verify that the Pitch and Roll Status goes INVALID.Verify that the “TAS” flag appears on the traffic display.Reset the circuit breaker. Verify that the “TA S ” flag clears.Pass/Fail ______.6. If applicable, verify that the Radio Altimeter is properly interfaced to theTAS Processor. Confirm the radio altitude configuration straps and measure the input at the KMH/KTA Processor.The TAS and radio altitude source(s) should be operating normally forthe following test. Connect the Diagnostic Computer to the TAS through the RS-232 port. Run the TASDIAG Input Data program and observe the following on the computer.Monitor the radio altitude source in the cockpit. Observe the RadioAltitude readout. The computer readout should agree with the cockpit radio altimeter indicator. If the computer display is too erratic, measurethe voltage with an alternative test.The Rad. Alt. Status on the computer should indicate VALIDUsing the radio altimeter self-test, confirm the following:With Radio Altitude source at 0 feet (on Ground), the computer indicates ______feet.When Radio altitude self-test (40-50’) is pressed, the computer indicates ______ feet.Do these readings agree with the cockpit display? Yes/NoAn alternate method can be by using a Radio Altimeter tester. Confirm the following:When the Radio altitude is at 0 feet, the Diagnostic Computer indicates ______ feet.When the Radio altitude is at 1,000 feet, the Diagnostic Computerindicates ______ feet.When the Radio altitude is at 2,000 feet, the Diagnostic Computerindicates ______ feet.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 4-29When the Radio altitude is at 2,500 feet, the Diagnostic Computer indicates ______ feet.Flag the Rad. Altitude source by pulling the circuit breaker.Verify that the Rad. Alt. Status goes INVALID.Verify that the “TAS” flag appears on the traffic display.Reset the circuit breaker. Verify that the “TA S ” flag clears.Rad. Altitude Source #1 Pass/Fail ______.7. Check that the configurationmodule and logic discretes are correct. Refer to supporting drawings and documentation if necessary to confirm the following items.The TAS and related aircraft system should be operating normally for the following test. Connect the Diagnostic Computer to the KMH/KTA through the RS-232 port. Run the TASDIAG Input Data program andobserve the following on the Diagnostic Computer.Disable the WOW logic and check that the air/ground (J10-4) mode changes from “ON-GROUND” (GND) to “AIRBORNE” (OPEN).Pass/Fail ______.Disable the landing gear logic and check that the gear position (J10-3)changes from “EXTENDED (GND) to “RETRACTED (OPEN).Pass/Fail ______.If applicable, confirm that ADVISORY INHIBIT (J10-22) changes from “INHIBITED” (GND) to NOT-INHIBITED (OPEN). when testing theGPWS.Top Antenna elements (J1-J4) indicate ______ ______ ______ _____.The HEX value of the antenna elements should indicate between:J1: BF H and CC H.J2: D4 H and DF H.J3: E5 H and ED H.J4: 6C H and 93 H.Bottom Antenna elements (J1-J4) indicate _____ _____ _____ _____.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Page 4-30 10609I00.ZIPCDL Rev 0, October/2000The HEX value of the bottom directional antenna elements shouldindicate as described above. The value of the monopole antenna elements (J2-J4) should indicate between 00 H and 93 H. antenna, Do all items Pass/Fail ______?8. Perform the Ramp test. This test requires the use of a TCAS Ramp Tester. Specific instructions for operating the ramp tester are contained in the applicable operator’s manual. Using the TCAS Ramp Tester exercise the TAS with the various intruder aircraft scenarios. Monitor the displays and aural messages to verify that system response iscorrect.Evaluate proper operation of the TAS system by observing trafficadvisories, proximity traffic and “other” traffic. Confirm that the voice announcement is correct and occurs at the proper time. At this time it will be necessary to have the appropriate systems operational.WARNINGPRECAUTIONS MUST BE TAKEN TO INSURE THAT THIS TEST DOES NOT INTERFERE WITH OTHER TCAS/TAS EQUIPPED AIRCRAFT.Apply static pressure to the airplane using the pitot-static tester. Increase the altitude to 20,000 feet. NOTEThe TAS and Transponder controls should be in Standby until the test altitude is set. Apply a radio altitude signal to the aircraft using the radio altimeter test set or equivalent. Increase the radio altitude to 2,000 feet or greater.Disable the WOW logic and put the aircraft systems into the “AIRBORNE” mode. For retractable gear aircraft, the landing gear logic should remain in the “EXTENDED” or DOWN position.Put the TAS and transponder control panels in the ON position. Select #1 Transponder.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 4-31Using TASDIAG, enable the “Ramp Tester Mode under the “File” drop down menu.NOTEOnce “Ramp Tester Mode” is entered, power must be cycled on the KMH/KTA before any flightSet up the TCAS Ramp Test Set.Using the TCAS Ramp test set, create a scenario to simulate an approaching Mode C transponder equipped aircraft beginning at 10 NM, at an altitude of 20,500 feet, at a closure rate of +450 KTS and an altitude rate of 0 FPM. An alternate scenario may be required for some test sets.Initiate the intruder test on the TCAS Ramp Tester.Verify that the intruder symbol corresponds to the scenario in bearing, distance and relative altitude. Confirm that the audio announcement agrees with the scenario.The intruder symbol will begin as an open white diamond with relative altitude tag of + 05. The bearing should be from the direction of the test antenna. The intruder will become proximity traffic at 5 NM; The white diamond will be filled. Finally, the intruder becomes a TA (traffic advisory) and the symbol will change to a yellow circle.“TRAFFIC, TRAFFIC” voice announcement should occur around 3.75 NM.Traffic Display ______, Taffic Announcement ______.While simulating a pressure altitude of more than 18,000 feet, MSL, press the “FL” (Flight Level) switch on the TCAS Control Panel. Verify the proper operation of the flight level mode on the traffic displays.Traffic Display ______.9. If installed, verify that the GPWS and Windshear warnings and TAS voice alerts are compatible. Also verify that the GPWS and Windshear warnings have been prioritized over the TAS voice alerts.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Page 4-32 10609I00.ZIPCDL Rev 0, October/2000Another test to check the Advisory Inhibit Inputs can be performed with the Diagnostic Computer.Initiate the TAS self-test.As soon as the “TAS SYSTEM TEST OK” message begins, press the GPWS Test switch or simulate a GPWS advisory. TAS audio is interrupted.Pass/Fail ______.Initiate the TAS self-test.As soon as the “TAS SYSTEM TEST OK” message begins, press the Wind Shear test switch or simulate a Wind Shear advisory. Verify the TAS audio is interrupted.Pass/Fail ______.10. TAS Bearing Accuracy is required for STC Approval.Evaluate the performance of the directional antenna for 360° coverage at 30° intervals.NOTEWhenever checking the TAS bearing accuracy, the test antenna must be within line-of-sight of the directional antenna under test. The accuracy to the top direc-tional antenna should be checked while the test antenna is 50 to 75 feet distant, and the landing gear logic is “DOWN”. When measuring the accuracy of the bot-tom antenna, the test antenna should not be within line-of sight of the top direc-tional antenna. Either use the fuselage to block the top directional antenna and position the test antenna 8 to 12 feet from the bottom antenna or shield the top antenna with echosorb or equivalent. The landing gear logic must simulate “RETRACTED” (UP) whenever checking the bearing accuracy to the bottom antenna. TAs will appear as “No Bearing” targets when the gear position logic is “EXTENDED” (DOWN) because the bottom antenna is in omni directional mode.To insure proper antenna selection, the relative altitude difference between the simulated intruder and own aircraft altitude should be + 6,000 feet (or greater) when checking the top antenna. The test antenna should be ele-vated slightly above the height of the top directional antenna.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 4-33When checking the bottom antenna bearing accuracy, the relative altitude difference between the simulated intruder and own aircraft altitude should be -6,000 feet (or more). The test antenna should be below the mounting plane of the bottom directional antenna.Position the aircraft outside on a heading of north away from hangers and other aircraft.Static pressure to the aircraft using the static tester is not required unless local conditions make it necessary.Apply a radio altitude signal to the aircraft using the Radio Altimeter Test Set or equivalent. Increase the radio altimeter to 1,000 feet or greater.Disable the WOW logic to put the aircraft systems in the “AIRBORNE” modeSet up the TCAS Ramp Tester on headings listed in the following Figure.On each heading in a CW direction initiate an intruder test scenario on the TCAS Ramp Tester and measure the relative bearing to the intruder from the traffic display.Whenever testing the bottom directional antenna, set the landing gear logic to “RETRACTED” (GEAR UP). Repeat the above steps for the bottom antenna.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Page 4-34 10609I00.ZIPCDL Rev 0, October/2000Figure 4-1 TAS Bearing MeasurementsNOTEBearing Error equals the heading to TCAS Ramp Tester less the relative bearing of intruder. Relative bearing to the intruder should be a positive number mea-sured clockwise from north on the traffic display unit.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 4-35NOTEThe largest acceptable TAS bearing error is +/- 30° except between 135° and 225° (aft of the wings) where the error may be 45°.11. Perform the Power and Frequency tests shown in the TAS Operator’sGuide.12. Perform Electromagnetic Interference (EMI) / Radio Frequency Interference (RFI) required for STC. Determine if there is any mutual interference with any other aircraft system.Pass/Fail ______.13. Determine that the system suppression is active.14. Conduct a flight test of TAS (Required for STC) according to the requirements of FAA Advisory Circular AC 20-ZZ, titled “Airworthiness Approval and Operational Use of Active Traffic Advisory System (TAS)”.

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PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL TOC 5-iSECTION V CERTIFICATION 5.0 INTRODUCTION ................................................................................. 5-15.1 CERTIFICATION PROCEDURE ......................................................... 5-15.1.1 Equipment Compatibility ...................................................................... 5-15.1.2 Equipment Location ............................................................................. 5-15.1.3 Federal Communication Commission Rules ....................................... 5-25.1.4 TSO Category ..................................................................................... 5-25.1.5 FTZ Requirement ................................................................................ 5-25.1.6 FAA Requirements .............................................................................. 5-25.1.7 FAA Form 337 ..................................................................................... 5-35.1.8 Flight Manual Revision ........................................................................ 5-35.1.9 Pilot Briefing ........................................................................................ 5-3

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PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 5-1SECTION VCERTIFICATION5.0 INTRODUCTIONThis section outlines the procedures required to obtain IFR certification for the KMH 880/KTA 870 System. Recommended flight test procedures are also included.5.1 CERTIFICATION PROCEDURE5.1.1 Equipment CompatibilityCareful consideration must be paid to the electrical characteristics of existing equipment or possible additions that will be interfaced with the KMH 880/KTA 870 System, in order to ensure system compatibility. Section III of this manual provides system planning guidelines, and defines the electrical characteristics of the KMH 880/KTA 870 System. The installing agency should contact Honey-well International Inc. Product Support at (800) 257-0726, for information regarding the compatibility of equipment not listed in Section III. Normal busi-ness hours are 8:00 AM to 5:00 PM Central Time, Monday through Friday.The TAS system may operate in conjunction with, and in close proximity to, a transponder. The functions of the system will not in any way degrade the per-formance of the transponder beyond its specified limits.All of the TAS requirements stated in this document will be met when the TAS equipment is operating in conjunction with a compatible operating transponder, except when the transponder is active. The active state of the transponder is defined as the greater of the time interval between (a) the leading edge of the first transmitted pulse of the transponder reply minus 10 microseconds and the trailing edge of the last transmitted pulse of that reply plus 10 microseconds, or (b) the time interval during which a mutual suppression occurs.5.1.2 Equipment LocationThe KMH 880/KTA 870 System and associated indicators, annunciators and switches should be clearly visible and within easy reach of the pilot. Refer to Section II of this manual for complete installation information.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Page 5-2 10609I00.ZIPCDL Rev 0, October/20005.1.3 Federal Communication Commission RulesThe equipment will comply with all applicable rules of the Federal Communica-tion Commission.5.1.4 TSO CategoryAll aircraft, which are required by Federal Aviation Regulations to have a Ter-rain Awareness and Warning System complying with TSO C151a Class B, must be configured with the TSO curves. Additionally, the Alternate Audio Menu must be selected to meet the alert/warning aural requirements of the TSO.5.1.5 FTZ RequirementThe KMH 880/KTA 870 system is compliant to FTZ document 17 TR 2010.5.1.6 FAA RequirementsThe installing agency should contact a local FAA Inspector (GADO, FSDO, ACDO, MIDO, or ACO) who will determine whether the installation may be approved by submitting FAA Form 337or whether a Supplemental Type Certifi-cate (STC) will be required. If FAA Form 337 is determined to be sufficient, the installing agency should determine the acceptability of the procedures defined within this manual. If the FAA Inspector determines that an STC is required, the installing agency will need to contact the nearest Aircraft Certification Office (ACO) to obtain acceptable procedures.The FAA Central Region Aircraft Certification Office, Wichita, Kansas, has on file an approved report regarding the KMH 880/KTA 870 System. This report contains the bench test data and DO-160D environmental test data required to demonstrate the KMH 880/KTA 870 System’s compliance.5.1.7 FAA Form 337FAA Form 337 (if applicable) must be completed and submitted to the FAA. A sample checklist is provided in the Certification Appendix of this manual.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 5-35.1.8 Flight Manual RevisionA Flight Manual Supplement is usually required for approval. A sample supple-ment is provided in the Flight Manual Supplement Appendix of this manual. The sample is to be used as a guide to acceptable content and format, and not intended to apply to all installations. It is the responsibility of the installing agency to prepare an appropriate Flight Manual Supplement, and obtain FAA approval.5.1.9 Pilot BriefingThe installing agency should carefully review the Flight Manual Supplement and the KMH 880/KTA 870 System Operator’s Manual, P/N 006-18265-0000, with the owner/operator of the aircraft.

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PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL TOC 6-iSECTION VIOPERATION6.0 INTRODUCTION..................................................................................... 6-1

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PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page 6-1SECTION VIOPERATION6.0 INTRODUCTIONRefer to Section IV, of this manual, for the operating instructions for the post installation checkout. Refer to the KMH 880/KTA 870 System Operator’s Manual P/N 006-18265-0000, for complete operating instructions.

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PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page A-1APPENDIX AAntenna Surveillance Range

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PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page STC-1APPENDIX BSTC Appendix

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Page STC-2 10609I00.ZIPCDL Rev 0, October/2000Information to be added, if required.

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page CERT-1APPENDIX CCERTIFICATION APPENDIXSAMPLE CERTIFICATION CHECKLIST

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PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL Page CERT-3SAMPLE CERTIFICATION CHECKLISTAIRCRAFT MAKE: _______________________________AIRCRAFT MODEL: _______________________________AIRCRAFT SERIAL NUMBER: _______________________________AIRCRAFT REGISTRATION NUMBER: _______________________________DATE WORK COMPLETED: _______________________________A. Installed the KMH 880/KTA 870 System in accordance with Unit Installation Manual number 006-10609-000_, Revision ____, dated __________, and has been flight tested in accordance with AC20-ZZ (draft), to verify proper operation and accuracy for a follow-on IFR approval. Original IFR approval was accomplished by STC ____________, Master Drawing List number _________, specifications of TSO-C147 and TSO-C151a.B. Ground and flight tests were conducted and determined that the KMH 880/KTA 870 System does not interfere with normal operation of other equipment installed in the aircraft, and the KMH 880/KTA 870 System equipment is not a source of objection-able electromagnetic interference. Proper operation and accuracy were verified, and the unit functions properly and safely in accordance with the manufacturer’s specifica-tions.C. The unit was mounted in rack location for avionics provided by the manufacturer and is sufficient to ensure the restraint of the equipment when subjected to emergency landing loads.D. Installed an FAA Approved Flight Manual Supplement in the aircraft manual and a Operator’s Manual, part number 006-18265-0000, Revision _____, dated ________, in the aircraft. Weight, balance and equipment list changes have been made in the aircraft flight manual.

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PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL D-1APPENDIX DDIAGNOSTIC APPENDIX

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PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL D-3DIAGNOSTIC APPENDICESTASDIAG-TAS Processor Field Diagnotic Program User InstructionsWARNING: DO NOT USE THE “TASDIAG PROCESSOR FIELD DIAGNOSTIC PROGRAM” WHILE AIRBORNE. THE PROGRAM IS USED ONLY WHILE THE AIR-CRAFT IS ON THE GROUND. THE SYSTEM IS DEGRADED TO PERFORM MAINTE-NANCE FUNCTIONS AND IS NOT AIRWORTHY WHILE RUNNING THE DIAGNOSTIC SOFTWARE.NOTEThe diagnostic tests are performed with KMH 880/KTA 870 installed in the aircraft.

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PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870D-5 10609I00.ZIPCDL Rev 0, October/2000____________________________________________________________________Honeywell International Inc. P/N 700-01055-0000TAS Diag for Windows User Manual Revision-Page 1 of 18

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870D-6 10609I00.ZIPCDL Rev 0, October/2000THIS PAGE IS RESERVED____________________________________________________________________Honeywell International Inc. P/N 700-01055-0000TAS Diag for Windows User Manual Revision-Page 2 of 18

PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870D-7 10609I00.ZIPCDL Rev 0, October/2000Table of Contents1. Introduction.........................................................................................................42. Computer Requirements ....................................................................................43. Installing the TAS Diag Program.........................................................................44. Starting TAS Diag ...............................................................................................5 4.1 TAS Diag. Demonstration Mode ................................................................65. Inspecting Current Processor I/O Data...............................................................6 5.1 Snapshot View...........................................................................................65.2 Continous View .........................................................................................76. Inspecting TAS Unit’s Internal Diagnostic and Log Data....................................77. Configuration Module Options ...........................................................................77.1 View Strap Data.........................................................................................77.2 Modify Strap Data......................................................................................87.3 Save to Text File ........................................................................................97.4 Save to Binary File ....................................................................................97.5 Copy from Binary File................................................................................97.6 Initialize Config Module .............................................................................108. Intruder Data ......................................................................................................108.1 Overwrite View ..........................................................................................128.2 Capture View .............................................................................................129. Viewing Cable Calibration Data..........................................................................1210.Viewing Current System Status..........................................................................1311.TAS S/W Info ......................................................................................................1412 Ramp Tester Mode .............................................................................................1413 Suggestions and Hints........................................................................................1413.1 TAS Diag Doesn’t Communicate with TAS Unit .......................................14____________________________________________________________________Honeywell International Inc. P/N 700-01055-0000TAS Diag for Windows User Manual Revision-Page 3 of 18

$PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870Rev 0, October/2000 10609I00.ZIPCDL D-81. IntroductionThe TAS Processor Field Diagnostics Program (TAS Diag) provides an interface to the KMH 820/KTA 810 (TAS Processor Unit). The following information may be retrieved from the TAS Unit via TAS Diag:- I/O data (straps, attitude, altitude, etc.),-TAS’s internal Diagnostic and Log File,- Configuration module straps,- Currently tracked intruder data (range, altitude, bearing, etc.),- Cable calibration data,- Current system status (fault LED reading and description).TAS Diag for Windows has four different diagnostic windows:•Main Diagnostic Window•IO Continuous Window•Intruder Data Window•System Status WindowAll data may be written to a user-specified file by clicking Save from the File menu. The active (selected) window will be saved.A TAS Diag demonstration mode, in which no RS-232 communications are present, is available for familiarizing the user with the program. Select Demo Mode from the File menu.This document is an operations manual for TAS Diag, providing tips and techniques enabling TAS Diag to be a useful tool in installation and/or troubleshooting KMH 820/KTA 810 TAS P{rocessors.The following Part Numbers identify the TAS Diag program and documentation:700-01055-0000 User Manual (this documentation)731-30007-0000 CD-ROM containing TAS Diag for Windows and User Manual____________________________________________________________________Honeywell International Inc. P/N 700-01055-0000TAS Diag for Windows User Manual Revision-Page 4 of 18$

$PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICEBBBBKMH 880/KTA 870D-9 10609I00.ZIPCDL Rev 0, October/20002. Computer RequirementsThe TAS Diag program requires a personal computer with a CD_ROM running Microsoft Windows 95, Windows 98, or Windows NT 4.0 or above WINDOWS 2000???. The user should be familiar with running Windows programs.3. Installing the TAS Diag Program1. Insert the TAS Diag CD into your CD-ROM drive.2. Select the “Start” button then “Run”.3. In the Command Line Box, type the letter of the drive that contains the TAS Diag CD, acolon, a backslash, and the word setup. For example, Type: d:\setup4. Click the OK button.5. Follow the instructions that appear on the screen.If Setup prompts you to replace some of the system files with newer ver-sions: •Select OK, then Yes when prompted to restart Windows.•After Windows restarts, repeat steps 1 through 5.A Program Group called “TAS Diag” should have been created.4. Starting TAS DiagThe TAS Diag program may be started at any time. If the TAS unit is currently pow-ered on, TAS Diag will automatically establish communications. If the TAS unit is not currently powered on, TAS Diag will continuously attempt to establish communica-tions until communication is established or the Cancel button is pressed. Once com-munications are established and the TAS unit has completed initialization, TAS Diag will accept user input.NOTEIf the TAS unit is powered on but communications are not being established, ensure that the computer’s COM port is connected to the TAS unit’s RS-232 diagnostics port. If the computer has more than one COM port, determine which one is con-nected and check TAS Diag COM port propertiesThe TAS Diag program is started by selecting the “TAS Diag for Windows” icon in the “Start-Programs-TAS Diag’ group.____________________________________________________________________Honeywell International Inc. P/N 700-01055-0000TAS Diag for Windows User Manual Revision- Page 5 of 18$

Honeywell KMH820 Multi-Hazard Awareness unit User Manual KTA870

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