Honeywell KMH820 Multi-Hazard Awareness unit User Manual KTA870
Honeywell International Inc. Multi-Hazard Awareness unit KTA870
Users Manual
NO TI CE UT HO IT EC TO CH AN GE SYSTEM INSTALLATION MANUAL UB KMH 880/KTA 870 NA RY -S MULTI-HAZARD AWARENESS SYSTEM/TRAFFIC ADVISORY SYSTEM PR EL IM MANUAL NUMBER 006-10609-0000 REVISION 0 OCTOBER, 2000 NO TI CE UT HO IT -S UB EC TO CH AN GE WARNING PRIOR TO THE EXPORT OF THIS DOCUMENT, REVIEW FOR EXPORT LICENSE REQUIREMENT IS NEEDED. IM NA RY COPYRIGHT NOTICE ©2000 HONEYWELL INTERNATIONAL INC. PR EL Reproduction of this publication or any portion thereof by any means without the express written permission of Honeywell International Inc. is prohibited. For further information contact the Manager, Technical Publications,Honeywell International Inc., ONE TECHNOLOGY CENTER, 23500 West 105th Street, Olathe KS 66061 Telephone: (913) 782-0400. NO TI CE UT HO IT EC TO CH AN GE SYSTEM INSTALLATION MANUAL UB KMH 880/KTA870 PR EL IM NA RY -S MULTI-HAZARD AWARENESS SYSTEM/TRAFFIC ADVISORY SYSTEM NO TI CE The binder(s) required to hold this publication(s) are available at an additional cost and may be ordered from: HO UT Honeywell One Technology Center 23500 West 105th Street Olathe, Kansas, 66061 Telephone 1-800-757-8999 IT Orders must specify part number, description, and the quantity. Use the following list to complete the order DESCRIPTION 006-03140-0001 006-03140-0002 006-03140-0003 006-03140-0004 006-03140-0005 (1) inch Binder. (1.5) inch Binder. (2) inch Binder. (3) inch Binder. (4) inch Post Binder. EC TO CH AN GE PART NUMBER IM NA RY -S UB WARNING Prior to Export of this Document, review for export license requirement is needed. COPYRIGHT NOTICE ©2000 Honeywell International Inc. PR EL Reproduction of this publication or any portion thereof by any means without the express written permission of Honeywell International Inc. is prohibited. For further information contact the Manager, Technical Publications, Honeywell International Inc., One Technology Center, 23500 West 105th Street Olathe KS 66061 Telephone: (913) 782-0400. B KMH880/KTA 870 MANUAL REVISION PART NUMBER KMH 880/KTA 870 System Install Manual 0, October, 2000 006-10609-0000 NO TI CE REVISION HISTORY AND INSTRUCTIONS HO UT Add, 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: ACTION Insert Entire Manual PR EL IM NA RY -S UB EC TO CH AN GE IT PAGE Initial Release Rev 0, October/2000 10609I00.ZIPCDL Page R- 1 B CH AN GE IT HO UT NO TI CE KMH880/KTA 870 PR EL IM NA RY -S UB EC TO THIS PAGE IS RESERVED Page R- 2 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE SECTION I GENERAL INFORMATION INTRODUCTION .................................................................................... 1.1 1.1 PURPOSE .............................................................................................. 1-1 UT 1.0 HO 1.2 APPLICABILITY OF THE SYSTEM MANUAL ....................................... 1.2.1 Equipment Applicability .......................................................................... 1-2 1-2 SYSTEM DESCRIPTION ....................................................................... Basic EGPWS System ........................................................................... Basic TAS System ................................................................................. System Components .............................................................................. System Operation .................................................................................. 1.4 TECHNICAL CHARACTERISTICS ........................................................ 1.5 1.5.1 1.5.2 1.5.3 UNIT AND ACCESSORIES SUPPLIED ................................................ TAS Processor Unit ................................................................................ Configuration Module ............................................................................. Antennas ................................................................................................ 1.6 1.6.1 1.6.2 1.6.3 INSTALLATION ACCESSORIES SUPPLIED ........................................ KMH 820/KTA 810 Installation Kit .......................................................... Antenna Installation Kits.......................................................................... Databases ............................................................................................... 1-14 1-14 1-15 1-15 1.7 1.7.1 1.7.2 1.7.3 1.7.4 ACCESSORIES REQUIRED BUT NOT SUPPLIED .............................. Temperature Probe ................................................................................ GPS Antenna Splitter .............................................................................. Miscellaneous ........................................................................................ Cable And Wire ...................................................................................... 1-16 1-16 1-16 1-17 1-17 1.8 LICENSE REQUIREMENTS .................................................................. 1-17 1.9 1.9.1 1.9.2 1.9.3 1.9.4 1.9.5 1.9.6 1.9.7 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ...................... KMH 820/KTA 810 Unit........................................................................... Annunciators/Relays ............................................................................... GPS Antenna .......................................................................................... Gps Antenna Splitter ............................................................................... Temperature Probe ................................................................................. Wire and Coax Cables ............................................................................ Terrain Data Base Updates..................................................................... 1-17 1-18 1-18 1-18 1-18 1-18 1-19 1-19 PR EL IM NA RY -S UB EC TO CH AN GE IT 1.3 1.3.1 1.3.2 1.3.3 1.3.4 Rev 0, October/2000 10609I00.ZIPCDL 1-2 1-2 1-3 1-3 1-5 1-9 1-12 1-12 1-12 1-13 TOC- i B KMH 880/KTA 870 Figure 1-1 NO TI CE LIST OF ILLUSTRATIONS KMH 880/KTA 870 System ......................................................... LIST OF TABLES EC TO CH AN GE IT HO UT KMH 880/KTA 870 Applicable Versions ...................................... KMH 880 LRUs ........................................................................... KTA 870 LRUs ............................................................................ KMH 820 w/o GPS Multi-Hazard Unit Technical Specifications .. KMH 820 w/ GPS Multi-Hazard Unit Technical Specifications..... KTA 810 Traffic Advisory Unit Technical Specifications .............. CM 805 Configuration Module Technical Specifications ............. KA 815 Traffic Antenna Technical Specifications ........................ KA 92 GPS Antenna Technical Specifications ............................ KMH 820/KTA 810 Processor Units ............................................ CM 805 Configuration Module ..................................................... KA 815/KA 92 Antennas .............................................................. GPS Cable Run Lengths ............................................................. KMH 820/KTA 810 Installation Kit .............................................. KA 815 Installation Kit ................................................................ KA 92 Installation Kit .................................................................. Data Bases................................................................................... Temperature Probe ..................................................................... GPS Antenna Splitter ................................................................... Miscellaneous Accessories ......................................................... Cable and Wire ............................................................................ -S UB Table 1-1 Table 1-2 Table 1-3 Table 1-4 Table 1-5 Table 1-6 Table 1-7 Table 1-8 Table 1-9 Table 1-10 Table 1-11 Table 1-12 Table 1-13 Table 1-14 Table 1-15 Table 1-16 Table 1-17 Table 1-18 Table 1-19 Table 1-20 Table 1-21 1-2 1-4 1-4 1-9 1-9 1-10 1-10 1-11 1-11 1-12 1-12 1-13 1-13 1-14 1-15 1-15 1-15 1-16 1-16 1-17 1-17 SECTION II INSTALLATION INTRODUCTION .................................................................................... 2.1 UNPACKING AND INSPECTING EQUIPMENT .................................... NA RY 2.0 PR EL IM 2.2 EQUIPMENT INSTALLATION ............................................................... 2.2.1 General ................................................................................................ 2.2.2 Avionics Cooling Requirements ........................................................... 2.2.3 Processor Installation ........................................................................... 2.2.3.1 Cooling Considerations ..................................................................... 2.2.3.2 Installation Considerations ................................................................ 2.2.3.3 Installation Procedure ....................................................................... 2.2.4 Configuration Module Installation.......................................................... 2.2.4.1 Cooling Considerations ..................................................................... TOC- ii 1-5 10609I00.ZIPCDL 2-1 2-1 2-1 2-1 2-2 2-2 2-2 2-2 2-4 2-9 2-9 Rev 0, October/2000 B 2-9 2-9 2-13 2-13 2-17 2-17 2-17 2-26 2-27 LIST OF ILLUSTRATIONS CH AN GE IT KMH 820/KTA 810 Installation Drawing ....................................... Configuration Module Installation Drawing................................... KA 815 Antenna Outline and Mounting Drawing ......................... KA 815 Antenna Installation Drawing........................................... KA 815 Doubler Plate Drawing..................................................... KA 92 Outline and Mounting Drawing ......................................... GPS Antenna Splitter ................................................................... Coax Cable Treatment ................................................................. Standard Coax Cable ................................................................... Bulkhead/In-Line Connection Coax Cable ................................... TNC Antenna Coax/Connector Assembly .................................... TNC Antenna Coax/Connector Assembly .................................... TO Figure 2-1 Figure 2-2 Figure 2-3 Figure 2-4 Figure 2-5 Figure 2-6 Figure 2-7 Figure 2-8 Figure 2-9 Figure 2-10 Figure 2-11 Figure 2-12 UT NO TI CE Installation Considerations ................................................................ Installation Procedure ....................................................................... Directional Antenna Installation ............................................................ KA 815 Antenna Installation Considerations ..................................... GPS Antenna Installation ..................................................................... KA 92 antenna Installation Considerations (KMH 820 EGPWS only) . Installation Procedure ....................................................................... TAS Coaxial Cable Fabrication ............................................................. GPS Coaxial Cable Fabrication ............................................................ HO 2.2.4.2 2.2.4.3 2.2.5 2.2.5.1 2.2.6 2.2.6.1 2.2.6.2 2.2.7 2.2.8 KMH 880/KTA 870 2-5 2-11 2-15 2-19 2-21 2-23 2-25 2-28 2-28 2-28 2-29 2-30 Signal Losses .............................................................................. UB Table 2-1 EC LIST OF TABLES 2-27 SECTION III -S SYSTEM PLANNING IM NA RY 3.0 INTRODUCTION ................................................................................... 3.0.1 Applicable Part Numbers Subsection Description ................................ 3.0.2 Function Subsection Description .......................................................... 3.0.3 Requirements and Limitations Subsection Description. ....................... 3.0.4 Electrical Characteristics Subsection Description. ............................... 3.0.5 Interface Subsection Description ......................................................... PR EL 3.1 GENERAL INTERCONNECT INFORMATION ...................................... 3.1.1 Power Inputs ..................................................................................... 3.1.2 Air/Ground Discrete Input ................................................................. 3.1.3 Landing Gear Discrete Input ............................................................. 3.1.4 Above/Below/Normal Input ............................................................... 3.1.5 Baro Altitude (ARINC 429) Input ....................................................... 3.1.6 Advisory Inhibit Input ........................................................................ Rev 0, October/2000 10609I00.ZIPCDL 3-1 3-1 3-1 3-1 3-1 3-1 3-5 3-5 3-5 3-6 3-6 3-7 3-7 TOC- iii B TAS Valid Output .............................................................................. Visual Annunciate Traffic (Lamp Output) .......................................... Synthesized Voice Output ................................................................ Air Temperature Input ....................................................................... GPS Input ......................................................................................... Factory Test Input ............................................................................. TAS ATE Enable Input ................................................................... TAS Built In Test Equipment (BITE) .............................................. EGPWS Self Test Input ................................................................. Display Select Input ....................................................................... Terrain Awareness Inhibit Discrete ................................................ Terrain Warning ................................................................................ Terrain Caution .................................................................................. Weather Select Output ..................................................................... EGPWS Audio On Discrete .............................................................. EGPWS Terrain Inop and Terrain Not Available Output.................... 3-7 3-8 3-8 3-9 3-9 3-10 3-10 3-10 3-11 3-12 3-12 3-12 3-12 3-12 3-13 3-13 GE IT HO UT NO TI CE 3.1.7 3.1.8 3.1.9 3.1.10 3.1.11 3.1.12 3.1.12.1 3.1.12.2 3.1.12.3 3.1.12.4 3.1.12.5 3.1.13 3.1.14 3.1.15 3.1.16 3.1.17 KMH 880/KTA 870 NA RY -S UB EC TO KMH 880/KTA 870 Interconnect Family ...................................... KMH 820/KTA 810 Pinout Diagram ............................................. KMH 820/KTA 810 System Interconnect Block Diagram ............. KMH 820/KTA 810 Power Interface ............................................ KMH 820/KTA 810 Discrete Interface ......................................... KMH 820/KTA 810 Configuration Module Interconnect ............... KMH 820/KTA 810 Attitude/Heading Interface............................. KMH 820/KTA 810 Radar/Barometric Altitude Interface ............. KMH 820/KTA 810 Antenna/Suppression Interface .................... KMH 820/KTA 810 EFS 40/50 Interface .................................... KMH 820/KTA 810 GS 362A Interface ....................................... KMH 820/KTA 810 Honeywell GS 362A Interface ....................... KMH 820/KTA 810 Collins GS 362A Interface ............................. KMH 820/KTA 810 Honeywell Primus 1000 Interface.................. KMH 820/KTA 810 Honeywell SPZ-805 Interface........................ KMH 820/KTA 810 Diagnostic/Data Recorder Interface ............. KMH 820/KTA 810 TAS ATE Interface ....................................... KMH 820/KTA 810 CP 66B Interface ........................................... KMH 820/KTA 810 KFS 578A Interface ....................................... KMH 820/KTA 810 Display Interface............................................ KMH 820/KTA 810 Processor Front Connector .......................... KMH 820/KTA 810 Front Connector Cable .................................. PR EL IM Figure 3-1 Figure 3-2 Figure 3-3 Figure 3-4 Figure 3-5 Figure 3-6 Figure 3-7 Figure 3-8 Figure 3-9 Figure 3-10 Figure 3-11 Figure 3-12 Figure 3-13 Figure 3-14 Figure 3-15 Figure 3-16 Figure 3-17 Figure 3-18 Figure 3-19 Figure 3-20 Figure 3-21 Figure 3-22 CH AN LIST OF ILLUSTRATIONS Table 3-1 TOC- iv 3-3 3-15 3-29 3-33 3-35 3-37 3-39 3-41 3-49 3-51 3-53 3-59 3-65 3-69 3-73 3-77 3-79 3-81 3-83 3-87 3-95 3-96 LIST OF TABLES KMH 820/KTA 810 Connector Pin Assignment ........................... 10609I00.ZIPCDL 3-97 Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE SECTION IV POST INSTALLATION CONFIGURATION AND CHECK OUT 4.0 INTRODUCTION .................................................................................... 4-1 4.1 LINE SELECT KEYS .............................................................................. 4-1 -S UB EC TO CH AN GE IT HO UT 4.2 CONFIGURATION PROCEDURE ......................................................... 4.2.1 Power On ............................................................................................. 4.2.2 Aircraft Configuration ........................................................................... 4.2.3 EGPWS Configuration Instructions ....................................................... 4.2.3.1 Equipment needed................................................................................ 4.2.3.2 Configuration Module Programming ..................................................... 4.2.3.3 Configuration String Format.................................................................. 4.2.3.4 RS-232 Maintenance Port (Port SMC1)................................................ 4.2.3.5 RS-232 Diagnostic Port ........................................................................ 4.2.3.6 Configuration Sequence of Events ....................................................... 4.2.3.7 Configuration Types.............................................................................. 4.2.3.8 Configuration Tables............................................................................. 4.2.3.8.1 Category 1, Aircraft/Mode Type Select ............................................... 4.2.3.8.2 Category 2, Air Data Input Select ....................................................... 4.2.3.8.3 Category 3, Position Input Select........................................................ 4.2.3.8.4 Category 4, Terrain Display Select ..................................................... 4.2.3.8.5 Category 5, Input/Output Discrete Type Select .................................. 4.2.3.8.6 Category 6, Audio Menu Select .......................................................... 4.2.3.8.7 Category 7, Audio Output Level.......................................................... 4.2.3.8.8 Category 8, Altitude Monitor Options .................................................. 4.2.3.8.9 Category 9, Terrain Display Alternate Pop Up Option ........................ 4.2.4 TAS Configuration Options .................................................................. 4.2.4.1 TAS RS-232 Maintenance Port.............................................................. 4.2.4.2 TAS RS-422 Data Recorder .................................................................. IM NA RY 4.3 GROUND TEST PROCEDURES ........................................................... 4.3.2 EGPWS Ground Test Procedures ......................................................... 4.3.3 TAS Ground Test Procedures................................................................ EL PR 4-34 LIST OF TABLES Configuration Identification........................................................... Aircraft/Mode Type Select ............................................................ Air Data Input Select .................................................................... Rev 0, October/2000 4-14 4-14 4-17 LIST OF ILLUSTRATIONS Figure 4-1 TAS Bearing Measurements............................................................ Table 4-1 Table 4-2 Table 4-3 4-1 4-1 4-1 4-1 4-1 4-2 4-2 4-3 4-3 4-4 4-4 4-5 4-6 4-6 4-7 4-8 4-9 4-9 4-9 4-10 4-10 4-11 4-13 4-14 10609I00.ZIPCDL 4-4 4-6 4-6 TOC- v B Position Input Select..................................................................... Terrain Display Select .................................................................. Input/Output DiscreteType Select ................................................ Audio Menu Select ....................................................................... Audio Output Level....................................................................... Altitude Monitor Option................................................................. Terrain Display Alternate Pop Up Option ..................................... 4-7 4-8 4-9 4-9 4-10 4-10 4-11 NO TI CE 4-4 4-5 4-6 4-7 4-8 4-9 4-10 UT Table Table Table Table Table Table Table KMH 880/KTA 870 HO SECTION V IT CERTIFICATION INTRODUCTION .................................................................................... 5-1 5.1 5.1.1 5.1.2 5.1.3 5.1.4 5.1.5 5.1.6 5.1.7 5.1.8 5.1.9 CERTIFICATION PROCEDURE ............................................................ Equipment Compatibility ........................................................................ Equipment Location ............................................................................... Federal Communication Commission Rules .......................................... TSO Category ........................................................................................ FTZ Requirement ................................................................................... FAA Requirements ................................................................................. FAA Form 337 ........................................................................................ Flight Manual Revision ........................................................................... Pilot Briefing ........................................................................................... 5-1 5-1 5-1 5-1 5-2 5-2 5-2 5-2 5-2 5-3 EC TO CH AN GE 5.0 OPERATION INTRODUCTION..................................................................................... Mode C..................................................................................... STC .......................................................................................... Cert .......................................................................................... TASDiag................................................................................... TSO .......................................................................................... A-1 B-1 CERT-1 D-1 TSO-1 PR EL IM NA APPENDIX A APPENDIX B APPENDIX C APPENDIX D APPENDIX E 6-1 LIST OF APPENDICES RY -S 6.0 UB SECTION VI TOC- vi 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE SECTION 1 GENERAL INFORMATION INTRODUCTION .................................................................................... 1.1 1.1 PURPOSE .............................................................................................. 1-1 UT 1.0 1-2 1-2 1.3 1.3.1 1.3.2 1.3.3 1.3.4 SYSTEM DESCRIPTION ....................................................................... Basic EGPWS System ........................................................................... Basic TAS System ................................................................................. System Components .............................................................................. System Operation .................................................................................. 1-2 1-2 1-3 1-3 1-5 1.4 TECHNICAL CHARACTERISTICS ........................................................ 1-9 1.5 1.5.1 1.5.2 1.5.3 UNIT AND ACCESSORIES SUPPLIED ................................................ TAS Processor Unit ................................................................................ Configuration Module ............................................................................. Antennas ................................................................................................ 1-12 1-12 1-12 1-13 1.6 1.6.1 1.6.2 1.6.3 INSTALLATION ACCESSORIES SUPPLIED ........................................ KMH 820/KTA 810 Installation Kit .......................................................... Antenna Iinstallation Kits......................................................................... Databases ............................................................................................... 1-14 1-14 1-15 1-15 1.7 1.7.1 1.7.2 1.7.3 1.7.4 ACCESSORIES REQUIRED BUT NOT SUPPLIED .............................. Temperature Probe ................................................................................ GPS Antenna Splitter .............................................................................. Miscellaneous ........................................................................................ Cable And Wire ...................................................................................... 1.8 LICENSE REQUIREMENTS .................................................................. 1.9 1.9.1 1.9.2 1.9.3 1.9.4 1.9.5 1.9.6 1.9.7 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ...................... KMH 820/KTA 810 Unit........................................................................... Annunciators/Relays ............................................................................... GPS Antenna .......................................................................................... Gps Antenna Splitter ............................................................................... Temperature Probe ................................................................................. Wire and Coax Cables ............................................................................ Terrain Data Base Updates..................................................................... PR EL IM NA RY -S UB EC TO CH AN GE IT HO 1.2 APPLICABILITY OF THE SYSTEM MANUAL ....................................... 1.2.1 Equipment Applicability .......................................................................... Rev 0, October/2000 10609I00.ZIPCDL 1-16 1-16 1-16 1-17 1-17 1-17 1-17 1-18 1-18 1-18 1-18 1-18 1-19 1-19 TOC 1-i B KMH 880/KTA 870 Figure 1-1 NO TI CE LIST OF ILLUSTRATIONS KMH 880/KTA 870 System .......................................................... LIST OF TABLES EC TO CH AN GE IT HO UT KMH 880/KTA 870 Applicable Versions ...................................... KMH 880 LRUs ........................................................................... KTA 870 LRUs ............................................................................ KMH 820 w/o GPS Multi-Hazard Unit Technical Specifications .. KMH 820 w/ GPS Multi-Hazard Unit Technical Specifications..... KTA 810 Traffic Advisory Unit Technical Specifications .............. CM 805 Configuration Module Technical Specifications ............. KA 815 Traffic Antenna Technical Specifications ........................ KA 92 GPS Antenna Technical Specifications ............................ KMH 820/KTA 810 Processor Units ............................................ CM 805 Configuration Module ..................................................... KA 815/KA 92 and Monopole Antennas ...................................... GPS Cable Run Lengths ............................................................. KMH 820/KTA 810 Installation Kit .............................................. KA 815 Installation Kit ................................................................ KA 92 Installation Kit .................................................................. Data Bases................................................................................... Temperature Probe ..................................................................... GPS Antenna Splitter ................................................................... Miscellaneous Accessories ......................................................... Cable and Wire ............................................................................ 1-2 1-4 1-4 1-9 1-9 1-10 1-10 1-11 1-11 1-12 1-12 1-13 1-13 1-14 1-15 1-15 1-15 1-16 1-16 1-17 1-17 PR EL IM NA RY -S UB Table 1-1 Table 1-2 Table 1-3 Table 1-4 Table 1-5 Table 1-6 Table 1-7 Table 1-8 Table 1-9 Table 1-10 Table 1-11 Table 1-12 Table 1-13 Table 1-14 Table 1-15 Table 1-16 Table 1-17 Table 1-18 Table 1-19 Table 1-20 Table 1-21 1-5 TOC 1-ii 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 1.0 NO TI CE SECTION 1 GENERAL INFORMATION INTRODUCTION IT HO UT This manual contains information relative to the physical, mechanical and electrical characteristics of the KMH 880/KTA 870 Multi-Hazard Awareness System. It includes the basic guidelines, considerations and recommendations for the installation 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. GE This manual assumes a familiarity with avionics installation practices, with systems on board the aircraft and access to manuals and regulations commensurate with the installation of such equipment. CH AN 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. TO The contents of this manual are for information and reference use only and must not be construed as a formal FAA approved work authorization. EC 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. 1.1 PURPOSE -S UB Operational information is contained in the KMH 880/KTA 870 Operators Manual supplied with each unit. PR EL IM NA RY This 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. Rev 0, October/2000 10609I00.ZIPCDL Page1-1 B APPLICABILITY OF THE SYSTEM MANUAL NO TI CE 1.2 KMH 880/KTA 870 1.2.1 Equipment Applicability This manual is applicable only to KMH 880/KTA 870 Multi-Hazard Awareness System part numbers displayed in the table below: NOMENCLATURE PART NUMBER UT UNIT 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 066-01175-2101 IT HO KTA 810 SYSTEM DESCRIPTION CH AN 1.3 GE Table 1-1 KMH 880/KTA 870 Applicable Versions 1.3.1 Basic EGPWS System EC TO The 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. NOTE RY -S UB 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 system's simplicity, practicality, small size and weight, with a minimum number of required aircraft sensors, provides a formidable safety value. NA The EGPWS portion of the KMH 820 is not suitable for helicopter operation. EL IM No Radio Altimeter, Landing Gear or Flap discretes, or Glideslope receiver are necessary. This significantly lowers the installation costs. PR 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. Page1-2 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE 1.3.2 Basic TAS System HO UT The Airborne TAS system is capable of surveillance of aircraft equipped with transponders (i.e., Mode S and Mode C) able to reply to ATCRBS Mode C interrogations 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. IT When all features are implemented the equipment has the capabilities of the Traffic Advisory System (TAS) defined by TSO-C147. GE The TAS system will provide: CH AN (1) An alert to the pilot using an audible and visual advisory of the proximity of an intruder aircraft. TO (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. EC (3)Timely data that does not lag more than 2 seconds behind the actual relative position as seen by the pilot during normal flight operations. UB (4) Probability of displaying false targets will be less than 2%. If they are displayed, they will not persist for more than a few seconds. -S (5) No increase of traffic on the Secondary Surveillance Radar radio frequencies in a manner that degrades the ATC system. NA RY (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. IM 1.3.3 System Components PR EL The KMH 880 Multi-Hazard Awareness System shall be composed of the KMH 820 (TAS/EGPWS Processor), a top mounted directional antenna (KA 815), a bottom mounted antenna (monopole or directional antenna which shall provide estimated bearing of target aircraft), a top mounted GPS antenna (KA 92), and a Configuration Module (CM 805). Rev 0, October/2000 10609I00.ZIPCDL Page1-3 B KMH 880/KTA 870 NO TI CE A 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. HO UT 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. IT KMH 880 SYSTEM PRIMARY LRUs LRU Manufacturer/ Model Designator LRU Description TAS/GA EGPWS Processor Bendix/King KMH 820 Multi-Hazard Awareness Processor Directional Antenna Bendix/King KA 815 TAS Directional Antenna 071-01599-0100 GPS Antenna Bendix/King KA 92 GPS Antenna 071-01553-0200 Configuration Module Bendix/King CM 805 Configuration Module 071-00112-0100 Control Panel/Display Bendix/King KMD 540 Multi-function Display 066-04035-0X01 TO CH AN GE System Component LRU Part Number 066-01175-0101 066-01175-2101 EGPWS Card 071-00158-0211 Bendix/King KAC 504 Traffic Card 071-00166-0411 EC Bendix/King KAC 502 UB Table 1-2 KMH 880 LRUs LRU Manufacturer/ Model Designator LRU Description LRU Part Number Bendix/King KTA 810 TAS Processor 066-01152-0101 Bendix/King KA 815 TAS Directional Antenna 071-01599-0100 Configuration Module Bendix/King CM 805 Configuration Module 071-00112-0100 Control Panel/Display Bendix/King KMD 540 Multi-function Display 066-04035-0X01 Bendix/King KAC 504 Traffic Card 071-00166-0411 NA TAS Processor RY System Component -S KTA 870 SYSTEM PRIMARY LRUs PR EL IM Directional Antenna Page1-4 Table 1-3 KTA 870 LRUs 10609I00.ZIPCDL Rev 0, October/2000 B -S UB EC TO CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 RY Figure 1-1 KMH 880/KTA 870 System NA 1.3.4 System Operation A. EGPWS System IM 1. EGPWS Modes of Operation PR EL a. TSO Mode The 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. Rev 0, October/2000 10609I00.ZIPCDL Page1-5 B KMH 880/KTA 870 NO TI CE This option is programmed into the EGPWS configuration module during system 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 operation. UT NOTE GE IT HO All 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 Mode EC TO CH AN If this installation is intended to provide the operator with a non-required Terrain 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 operating 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 operation. Any installation not required to comply with TSO C151a-class B may select either the Basic Audio menu or the Alternate Audio menu. -S UB 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 normal flight characteristics. RY c. GPS Sensor PR EL IM NA The KMH 880 contains an embedded GPS-XPRESS Card sensor that produces 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 satellites 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 satellites’ navigation messages to solve for latitude, longitude, altitude, horizontal velocity, vertical velocity and current UTC. Page1-6 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE GPS 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 System UT 1. TAS Modes of Operation HO a. Setup Mode IT The system shall be configured using an external PC via the Diagnostic (RS 232) Interface. Reference the Appendices for the programming procedures. GE b. Standby Mode CH AN When the Standby mode is selected, the TAS Processor shall disable surveillance and tracking operations. c. Functional Test Mode TO The Standby mode may be activated by any of the following: discrete selection, self-test, aircraft on ground (configuration option), or system failure. EC When 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. UB d. TAS Operation (Traffic Advisory) Mode RY -S When 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. NA e. TAS Processor IM The TAS Processor shall provide intruder surveillance and tracking, generating traffic advisories for both Altitude-Reporting and Non-Altitude-Reporting intruders to display potential conflicts and advisories to the flight crew. PR EL 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. Rev 0, October/2000 10609I00.ZIPCDL Page1-7 B KMH 880/KTA 870 NO TI CE The 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. UT NOTE HO Optional (The TAS Processor may be controlled using discrete inputs). IT C. Options 1. Display Option CH AN GE TSO 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 terrain display greatly improves situational awareness. The EGPWS supports numerous displays including traditional Radar displays as well as mode modern MFD’s. 2. Altitude Monitor Option TO Installations, which include a display, will also need to provide the EGPWS with range data via ARINC 429 format. -S UB EC The EGPWS has the ability to monitor altitude sources and provide cautionary 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 recommended 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. RY 3. Outside Air Temperature (OAT) (Recommended) PR EL IM NA The EGPWS supports an OAT 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 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. Page1-8 10609I00.ZIPCDL Rev 0, October/2000 B TECHNICAL CHARACTERISTICS NO TI CE 1.4 KMH 880/KTA 870 KMH 820 w/o GPS MULTI-HAZARD AWARENESS UNIT P/N 066-01175-0101 See TSO Appendix E PHYSICAL DIMENSIONS: See Figure 2-1 WEIGHT: 9.32 lbs. HO IT 050-03361-0000 POWER REQUIREMENTS: Voltage +28 Vdc +22 to +30 Vdc Nominal: 1.3 ± 0.2 A Max Operating 1.65 ± 0.2 A Bootup: 3.3 ± 0.5 Α CH AN Current Nominal: Range: GE Installation Kit UT TSO COMPLIANCE: Power 46 ± 2.3 Watts EC TO Table 1-4 KMH 820 w/o GPS Multi-Hazard Awareness Unit Technical Specifications TSO COMPLIANCE: -S PHYSICAL DIMENSIONS: UB KMH 820 w/ GPS MULTI-HAZARD AWARENESS UNIT P/N 066-01175-2101 See Figure 2-1 050-03361-0000 POWER REQUIREMENTS: Voltage Nominal: Range: Current Nominal: 1.3 ± 0.2 A Max Operating 1.65 ± 0.2 A Bootup: 3.3 ± 0.5 Α Power 46 ± 2.3 Watts PR EL Installation Kit NA 9.68 lbs. IM RY WEIGHT: See TSO Appendix E +28 Vdc +22 to +30 Vdc Table 1-5 KMH 820 w/ GPS Multi-Hazard Awareness Unit Technical Specification Rev 0, October/2000 10609I00.ZIPCDL Page1-9 B NO TI CE KMH 880/KTA 870 KTA 810 TRAFFIC ADVISORY UNIT P/N 066-01152-0101 See TSO Appendix E PHYSICAL DIMENSIONS: See Figure 2-1 WEIGHT: 8.75 lbs Nominal: Range: +28 Vdc +22 to +30 Vdc Current Nominal: 1.15 ± 0.2 A Max Operating 1.45 ± 0.2 A Bootup: 2.9 ± 0.5 Α GE Voltage CH AN POWER REQUIREMENTS: IT 050-03361-0000 HO Installation Kit UT TSO COMPLIANCE: Power 41 ± 2.3 Watts EC TO Table 1-6 KTA 810 Traffic Advisory Unit Technical Specifications TSO COMPLIANCE: -S PHYSICAL DIMENSIONS: UB CM 805 CONFIGURATION MODULE P/N 071-00112-0100 NA RY WEIGHT: POWER REQUIREMENTS See TSO Appendix E See Figure 2-2 0.1 lbs. 5 Vdc from KMH 820/KTA 810. PR EL IM Table 1-7 CM 805 Configuration Module Technical Specifications Page1-10 10609I00.ZIPCDL Rev 0, October/2000 B NO TI CE KMH 880/KTA 870 KA 815 TRAFFIC ANTENNA P/N 071-01599-0100 See TSO Appendix E PHYSICAL DIMENSIONS: See Figure 2-3 WEIGHT: 0.95 lbs. IT 050-03622-0000 HO Installation Kit UT TSO COMPLIANCE: See Figure 2-4 and 2-5 POWER REQUIREMENTS None GE MOUNTING: TO CH AN Table 1-8 KA 815 Traffic Antenna Technical Specifications EC KA 92 GPS ANTENNA P/N 071-01553-0200 PHYSICAL DIMENSIONS: See TSO Appendix E See Figure 2-6 0.27 lbs. Installation Kit 050-03318-0000 RY -S WEIGHT: UB TSO COMPLIANCE: See Figure 2-6 NA MOUNTING: 5v supplied by the GPS receiver. IM POWER REQUIREMENTS PR EL Table 1-9 KA 92 GPS Antenna Technical Specifications Rev 0, October/2000 10609I00.ZIPCDL Page1-11 B UNIT AND ACCESSORIES SUPPLIED NO TI CE 1.5 KMH 880/KTA 870 1.5.1 TAS Processor Unit The TAS Processor will provide intruder surveillance and tracking, generating traffic advisories for both Altitude-Reporting and Non-Altitude-Reporting intruders to display potential conflicts and advisories to the flight crew. SYSTEM COMPONENT DESCRIPTION PART NUMBER GE MANUFACTURER/ MODEL DESIGNER IT HO UT 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 represents a threat. Bendix/King KMH 820 Multi-Hazard Awareness Processor TAS Processor Bendix/King KTA 810 TAS Processor CH AN TAS/GA EGPWS Processor TSO COMPLIANCE 066-011750101 066-011752101 TSO C147 TSO C151a 066-011520101 TSO C147 EC TO Table 1-10 KMH 820/KTA 810 Processor Units UB 1.5.2 Configuration Module The Configuration Module contains two EEPROMs, one for the TAS Processor and one for the EGPWS. IM NA RY -S 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 procedures. A system failure will be annunciated if the configuration module is not programmed, not compatable with the current TAS processor software or if the CRC read from the module is incorrect. EL SYSTEM COMPONENT PR Configuration Module Page1-12 MANUFACTURER/ MODEL DESIGNER Bendix/King CM 805 DESCRIPTION PART NUMBER Configuration Module 200-00112-0100 TSO COMPLIANCE TSO C147 TSO C151a Table 1-11 CM 805 Configuration Module 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE 1.5.3 Antennas Full 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 information. MANUFACTURER/ MODEL DESIGNER DESCRIPTION PART NUMBER IT SYSTEM COMPONENT HO UT The antennas will be vertically polarized and cover 360 degrees in azimuth and at least -10 to +20 degrees in elevation. TSO COMPLIANCE Bendix/King KA 815 TAS Directional Antenna 071-01599-0100 TSO C147 GPS Antenna Bendix/King KA 92 GPS Antenna 071-01553-0200 TSO C129 Omni-Directional Antenna Dorne and Margolin L-Band Antenna DM NI50-2-2* TSO C66a TSO C74 CH AN GE Directional Antenna Table 1-12 KA 815/KA 92 Antennas EC TO * 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. UB CABLE TYPES AND PERMISSABLE GPS CABLE RUN LENGTHS (8dB allowable loss, including splitter.) CABLE RUN LENGTH (W/O Splitter) Up to 46 ft. RY * R/G 142B/U P/N 024-00002-0000 -S CABLE TYPE Up to 46 ft. NA * R/G 400/U P/N 024-00051-0060 IM * These cables use R/G 142/400 style connectors. Table 1-13 GPS Cable Run Lengths PR EL Note: When using Non-KPN or Non-standard P/N cables, connectors etc., the installer has the responsibility of proving airworthiness. Rev 0, October/2000 10609I00.ZIPCDL Page1-13 B INSTALLATION ACCESSORIES SUPPLIED NO TI CE 1.6 KMH 880/KTA 870 1.6.1 KMH 820/KTA 810 Installation Kit SYMBOL PART NUMBER DESCRIPTION [UOM] -0000 [EA] [EA] [EA] [EA] [EA] [EA] Rack, KMH 820/ KTA 810 D38999/26FJ35SN 128 Pin I/O Connector M85049/38-25N Strain Relief for 128 Pin I/O Connector J4,J8 030-00005-0002 TAS Antenna Ports, BNC Connectors J1-J3, J5-J7, J9 030-00134-0000 Connector, TNC 071-00112-0100 CM 805 Configuration Module 030-01171-0000 Conn Sub-D HSG 9S (Female Pins) [EA] 010-00135-0000 Terminals [EA] 010-00068-0026 Terminals [EA] 150-00072-0000 Solder Sleeve [EA] 030-01157-0011 Socket Contact [EA] 030-01451-0000 Socket Contact 22 ga [EA] 15 030-01464-0000 9 Pin Plastic Hood [EA] 030-01428-0001 EMI Hood W/ Lock 15 Pin High Density [EA] High Density 15 Pin Female DSub [EA] KMH 820/KTA 810 Installation Drawing REF HO IT GE UB 030-03447-0001 155-06060-0000 CH AN TO EC J10 UT 200-09894-0000 PR EL IM NA RY -S Table 1-14 KMH 820/KTA 810 Installation Kit P/N 050-03361-0000 Page1-14 10609I00.ZIPCDL Rev 0, October/2000 B PART NUMBER DESCRIPTION [UOM] -0000 071-01599-0100 KA 815 Antenna [EA] M39012/30-0101 Connector, TNC Rt Angle [EA] MS29513-148 KA 815 O-Ring [EA] MS24693-C54 Screw PHP 8-32x.875 [EA] 155-06059-0000 KA 815 Installation Drawing REF UT SYMBOL NO TI CE Antenna Installation Kits HO 1.6.2 KMH 880/KTA 870 DESCRIPTION CH AN PART NUMBER [UOM] -0000 Connector, TNC Rt Angle [EA] 047-10735-0002 Antenna DBLR Complete [EA] 089-05909-0012 Screw PHP 8-32x3/4 [EA] 187-01831-0000 Antenna Gasket [EA] 155-06019-0000 KA 92 INstallation Drawing REF TO 030-00134-0001 EC SYMBOL GE IT Table 1-15 KA 815 Installation Kit P/N 050-03622-0000 UB Table 1-16 KA 92 Installation Kit P/N 050-03318-0000 -S 1.6.3 Databases 071- 00167-0101 NA 071-00167-0102 071-00167-0103 [UOM] America’s Database [EA] Atlantic Database [EA] Pacific Database [EA] Table 1-17 KMH 880/KTA 870 Databases PR EL IM DESCRIPTION RY PART NUMBER Rev 0, October/2000 10609I00.ZIPCDL Page1-15 B ACCESSORIES REQUIRED BUT NOT SUPPLIED NO TI CE 1.7 KMH 880/KTA 870 DESCRIPTION OAT Probe MS3106E12S-3S OAT Probe Connector 090-01034-0001 010-00068-0016 -0001 [EA] [EA] OAT Probe Mounting Kit [EA] Crimp Terminal [EA] CH AN 137-00042-0001 [UOM] IT PART NUMBER GE SYMBOL HO UT 1.7.1 Temperature Probe The 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 interfaced to the EGPWS Table 1-18 Temperature Probe P/N 050-03610-0002 NOTE TO The 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. EC 1.7.2 GPS Antenna Splitter PART NUMBER RY SYMBOL -S UB To 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. DESCRIPTION [UOM] QTY GPS Antenna Splitter Kit [EA] 030-00134-0000 TNC Connector Straight [EA] 030-00134-0001 TNC Connector Rt Angle [EA] IM NA 050-03610-0003 PR EL Table 1-19 GPS Antenna Splitter P/N 071-01600-0001 Page1-16 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 SYMBOL PART NUMBER DESCRIPTION [UOM] QTY 050-03610-0000 Basic Annunciator Kit [EA] 050-03610-0001 Terrain Switching Kit [EA] HO UT Table 1-20 Miscellaneous Accessories NO TI CE 1.7.3 Miscellaneous IT NOTE: CABLE AND WIRE SYMBOL CH AN 1.7.4 GE Specification Drawing 031-00810-01 defines all of the sub-assembly parts and spacers to cover different panel thicknesses (Sheet 2). Artwork definitions for associated items are also covered (Sheet 3). PART NUMBER DESCRIPTION Coaxial Cable TO M17/158-RG400 [UOM] QTY [FT] AR Wire [FT] AR M17/176-00002 Shielded Wire [FT] AR Shielded Wire [FT] AR EC MIL-W-22759/16 or Equivalent. MIL-C-27500 or Equivalent. LICENSE REQUIREMENTS -S 1.8 UB Table 1-21 Cable and Wire 1.9 NA RY There are no license requirements for the KMH 880/KTA 870 Multi-Hazard/Traffic Advisory System. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS EL IM FAR Part 23.1529, 25.1529, 27.1529, AND 29.1529 Instructions for Continued Airworthiness is met per the following Instructions: PR Design and manufacture of the equipment will provide for installation so as not to impair the airworthiness of the aircraft. Rev 0, October/2000 10609I00.ZIPCDL Page1-17 B KMH 880/KTA 870 NO TI CE 1.9.1 KMH 820/KTA 810 Unit If 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 necessary and placard the aircraft accordingly. After re-installation of the unit, accomplish the appropriate Post Installation Checkout in Section IV. IT HO UT 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 Section IV. 1.9.2 Annunciators/Relays TO CH AN GE If 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 airworthy 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 factoryrated 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 Antenna UB EC If 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 Checkout in Section IV. -S 1.9.4 GPS Antenna Splitter NA RY If 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 Splitter, accomplish the appropriate Post Installation Checkout in Section IV. IM 1.9.5 Temperature Probe PR EL If 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. Page1-18 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE 1.9.6 Wires and Coax Cables During ON-condition or regularly scheduled maintenance, inspect the wires and coax cables following the guidelines listed in AC 43.13-1B Chapter 11 as necessary. 1.9.7 Terrain Data Base Updates HO UT To order database updates contact Honeywell International Inc., Navigation Services: CH AN GE IT Honeywell International Inc. Aerospace Electronic Systems One Technology Center 23500 West 105th Street Olathe, Kansas 66061 USA Attn: Navigation Services MS 66 Phone:(800) 247-0230 within the United States or Canada (913) 712-3145 outside of the United States or Canada FAX: (913) 712-3904 PR EL IM NA RY -S UB EC TO e-mail:nav.database@honeywell.com Rev 0, October/2000 10609I00.ZIPCDL Page1-19 B CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA RY -S UB EC TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL Page1-20 B KMH 880/KTA 870 NO TI CE SECTION II INSTALLATION INTRODUCTION .............................................................................. 2-1 2.1 UNPACKING AND INSPECTING EQUIPMENT .............................. 2-1 2.2 2.2.1 2.2.2 2.2.3 2.2.3.1 2.2.3.2 2.2.3.3 2.2.4 2.2.4.1 2.2.4.2 2.2.4.3 2.2.5 2.2.5.1 2.2.6 2.2.6.1 2.2.6.2 2.2.7 2.2.8 EQUIPMENT INSTALLATION .......................................................... General ............................................................................................. Avionics Cooling Requirements ........................................................ Processor Installation ....................................................................... Cooling Considerations ..................................................................... Installation Considerations ................................................................ Installation Procedure ....................................................................... Configuration Module Installation ...................................................... Cooling Considerations ..................................................................... Installation Considerations ................................................................ Installation Procedure ....................................................................... DIRECTIONAL ANTENNA INSTALLATION ..................................... KA 815 Antenna Installation Considerations .................................... GPS ANTENNA INSTALLATION ..................................................... KA 92 Antenna Installation Considerations (KMH 820 EGPWS only) Installation Procedure ....................................................................... TAS Coaxial Cable Fabrication.......................................................... GPS Coaxial Cable Fabrication ......................................................... 2-1 2-1 2-2 2-2 2-2 2-2 2-4 2-9 2-9 2-9 2-9 2-13 2-13 2-17 2-17 2-17 2-26 2-27 EC TO CH AN GE IT HO UT 2.0 LIST OF ILLUSTRATIONS NA RY -S UB KMH 820/KTA 810 Installation Drawing ....................................... Configuration Module Installation Drawing................................... KA 815 Antenna Outline Drawing ................................................ KA 815 Antenna Installation Drawing........................................... KA 815 Doubler Plate Drawing..................................................... KA 92 Outline and Mounting Drawing ......................................... GPS Antenna Splitter ................................................................... Coax Cable Treatment ................................................................. Standard Coax Cable ................................................................... Bulkhead/In-Line Connection Coax Cable ................................... TNC Antenna Coax/Connector Assembly .................................... TNC Antenna Coax/Connector Assembly .................................... PR EL IM Figure 2-1 Figure 2-2 Figure 2-3 Figure 2-4 Figure 2-5 Figure 2-6 Figure 2-7 Figure 2-8 Figure 2-9 Figure 2-10 Figure 2-11 Figure 2-12 Table 2-1 LIST OF TABLES Signal Losses ............................................................................... Rev 0, October/2000 2-5 2-11 2-15 2-19 2-21 2-23 2-25 2-28 2-28 2-28 2-29 2-30 10609I00.ZIPCDL 2-27 TOC 2-i B TO CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA RY -S UB EC THIS PAGE IS RESERVED TOC 2-ii 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 SECTION II 2.0 NO TI CE INSTALLATION INTRODUCTION UT This section contains suggestions and factors to consider before installing the KMH 880/ KTA 870 System. Close adherence to these suggestions will assure satisfactory performance from the equipment. HO NOTE 2.1 CH AN GE IT The conditions and tests performed on the system components are minimum 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. UNPACKING AND INSPECTING EQUIPMENT 2.2 UB EC TO Exercise 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 material should be retained in the event that storage or re-shipment of the equipment is necessary. EQUIPMENT INSTALLATION -S 2.2.1 General NA RY The following paragraphs contain information pertaining to the installation of the KMH 880/KTA 870 System, including instructions concerning location and mounting of the antennas. PR EL IM 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. Rev 0, October/2000 10609I00.ZIPCDL Page 2-1 B NO TI CE KMH 880/KTA 870 CAUTION IT HO UT AFTER INSTALLATION OF THE CABLING AND BEFORE INSTALLATION OF THE EQUIPMENT, A CHECK SHOULD BE MADE WITH THE AIRCRAFT PRIMARY POWER SUPPLIED TO THE MOUNTING CONNECTOR, TO ENSURE THAT POWER IS APPLIED ONLY TO THE PINS SPECFIED IN THE INTERWIRING DIAGRAMS IN SECTION III. 2.2.2 Avionics Cooling Requirements CH AN GE 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. -S UB EC TO 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 individual 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 reliability of the equipment. Consequently, the importance of providing force air cooling 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. RY 2.2.3 Processor Installation Cooling Considerations The KMH 820/KTA 810 requires no external forced air cooling. 2.2.3.2 Installation Considerations IM NA 2.2.3.1 PR EL Consideration should be given to the following items affected by the choice of installation location within the aircraft: Page 2-2 A. Environmental Considerations B. Ease of Interface to aircraft systems 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE C. GPS Antenna location and coaxial cable length D. Ability to extract and insert new terrain/obstacle Data Bases supplied on a CompactFlash Card. UT 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. HO If possible, the KMH 820/ KTA 810 should NOT be located in close proximity to equipment which produce considerable heat. IT Locations, which require disassembly of the aircraft to gain access, are less desirable. CH AN GE 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. TO Do not bundle data lines or antenna cable with any power cables. EC No more than 8.0dB signal loss is allowed in the GPS antenna cable run, including the antenna splitter, (if used). Refer to Note 5 on the Antenna Interface Drawing and Table 1-13 in Section 1 for information on cable types and lengths. -S UB 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. RY Refer to Figures 2-11 and 2-12 for TNC connector assembly guidelines. PR EL IM NA NOTE The KMH 820/KTA 810 will need to interface to the aircraft audio system, 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. Rev 0, October/2000 10609I00.ZIPCDL Page 2-3 B KMH 880/KTA 870 NO TI CE If 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. UT Updating the Terrain DataBase is accomplished by: HO Moving the aluminum cover over the CompactFlash card out of the way. IT Pressing the flash card ejector button located within the unit. Removing the old flash card. GE Inserting the new flash card and replacing the cover. CH AN 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. COLOR LEGEND Amber Terrain N/A or Terr N/A Amber Terrain Warning Red Terrain -S UB Not Available Caution EC FUNCTION TO The KMH 820 drives three lamps and accepts input from two switches. The lamps should be identified as: RY The RED Warning lamp must be located in the pilot’s primary field of view. Installation Procedure PR EL 2.2.3.3 IM NA 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 module. Page 2-4 A. 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. 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 2-1 KMH 820/KTA 810 Installation Drawing Dwg. No. 300-05639-0000 R-0 (Sheet 1 of 2) Rev 0, October/2000 10609I00.ZIPCDL Page 2-5 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 2-6 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 2-1 KMH 820/KTA 810 Installation Drawing Dwg. No. 300-05639-0000 R0 (Sheet 2 of 2) Rev 0, October/2000 10609I00.ZIPCDL Page 2-7 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 2-8 10609I00.ZIPCDL Rev 0, October/2000 B Configuration Module Installation NO TI CE 2.2.4 KMH 880/KTA 870 System 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 Considerations Installation Considerations HO 2.2.4.2 UT A. Make sure that the unit is installed in a location where the ambient temperatures are -67°F to +158°F (-55°C to +70°C). 2.2.4.3 IT A. The Configuration Module must be mounted to the airframe within maximum cable/harness length of 2 feet. Make sure to leave adequate space to mount the Configuration Module when installing the Processor Unit. Installation Procedure PR EL IM NA RY -S UB EC TO CH AN GE A. Install the Configuration Module into the airframe. Refer to figure 2- 2 . B. Tighten the mounting screws to secure the Configuration Module. Rev 0, October/2000 10609I00.ZIPCDL Page 2-9 B CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA RY -S UB EC TO THIS PAGE IS RESERVED Page 2-10 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 2-2 Configuration Module Installation Drawing Dwg. No. 300-06161-0000 R-0 Rev 0, October/2000 10609I00.ZIPCDL Page 2-11 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 2-12 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 2.2.5.1 NO TI CE 2.2.5 DIRECTIONAL ANTENNA INSTALLATION KA 815 Antenna Installation Considerations A. Antenna Location UT NOTE IT HO The following antenna location procedure is provided for guidance purposes and to outline a method of achieving certifiable system performance. CH AN GE 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 installing agency is required to fabricate the doubler plate for the antenna installations. TO NOTE UB EC The 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. NOTE RY -S KMH 880/KTA 870 Systems REQUIRE that the antenna installation guidelines be followed. Adherence to these guidelines will assure that critical specifications are considered. Optimum bearing accuracy can be achieved by following these directions. PR EL IM NA 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. Rev 0, October/2000 10609I00.ZIPCDL Page 2-13 B KMH 880/KTA 870 IT HO UT NO TI CE Obstructions and ground plane discontinuities, such as door hatches, cowlings and unriveted airframe skin overlaps must be 18 inches from the nearest edge of the TAS Antenna. Other antennas, particularly high profile and Lband transponder antennas, cannot be located in front of or within 30 inches (edge to edge) of the top mounted TAS directional antenna. This will ensure a minimum of 20 dB of isolation at 1090 MHz, while minimizing far-field path distortion in the forward quadrants. B. Mount the antenna on the aircraft skin which is horizontal during enroute flight. Antenna baseplate must be level within + or - 5° in longitudinal and lateral axes when the aircraft is in level flight. See Figure 2-4. C. The antenna must be mounted on a nearly flat surface such that the antenna contacts the bare metal skin all around the perimeter without gaps when normal mounting screw torque is applied. GE NOTE PR EL IM NA RY -S UB EC TO CH AN Aircraft with fixed landing gear must be equipped with a bottom monopole antenna. Furthermore, the landing gear discrete must be strapped to the retracted position. The bearing from a bottom directional is invalidated when landing gear is extended, so it would always be invalidated on a fixed-gear aircraft. (Therefore, there would be no use for a directional antenna.) Page 2-14 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA RY -S UB EC TO CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 Rev 0, October/2000 Figure 2-3 KA 815 Antenna Outline Drawing 10609I00.ZIPCDL Page 2-15 B CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA RY -S UB EC TO THIS PAGE IS RESERVED Page 2-16 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 2.2.6.1 NO TI CE 2.2.6 GPS ANTENNA INSTALLATION KA 92 Antenna Installation Considerations (KMH 820 P/N 066-011752101 only) Installation Procedure CH AN 2.2.6.2 GE IT HO UT 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 26. 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 longitudinal and lateral axes when the aircraft is in level flight. PR EL IM NA RY -S UB EC TO A. 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. Rev 0, October/2000 10609I00.ZIPCDL Page 2-17 B CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA RY -S UB EC TO THIS PAGE IS RESERVED Page 2-18 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 2-4 KA 815 Installation and Mounting Drawing Dwg No. 155-06059-0000 Rev 0, October/2000 10609I00.ZIPCDL Page 2-19 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 2-20 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 2-5 KA 815 Doubler Plate Rev 0, October/2000 10609I00.ZIPCDL Page 2-21 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 2-22 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 2-6 KA 92 Outline and Mounting Drawing Dwg. No. 155-06019-0000 R-AA Rev 0, October/2000 10609I00.ZIPCDL Page 2-23 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 2-24 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA RY -S UB EC TO CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 Rev 0, October/2000 Figure 2-7 GPS Antenna Splitter Dwg. No. 071-01600-0001 10609I00.ZIPCDL Page 2-25 B KMH 880/KTA 870 NO TI CE 2.2.7 TAS Coaxial Cable Fabrication UT The 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. HO NOTE IT The 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”. TO CH AN GE 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 recommended 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 assemblies. EC When determining cable type and length make the following assumptions. 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 GHz RY -S UB A. PR EL IM NA Using 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. Page 2-26 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE 2.2.8 GPS Coaxial Cable Fabrication The 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: Description Signal Loss per Item Example Quantity Example Signal Loss 071-01600-001 GPS Antenna Splitter 3.4 dB 1 ea 3.4 dB M17/128-RG400 Coaxial Cable (18 ft max) 0.2dB/ft 10 ft 2.0 dB 030-00134-0000 Straight TNC Connector 0.1dB 2 ea 0.2 dB 030-00134-0001 Rt Angle YNC Connector 0.1dB 2 ea 0.2 dB 030-00101-0002 Panel Mount Plug 0.1dB M39012/28-0504 Bulkhead TNC Connector 0.1dB M39012/29-0504 Panel TNC Connector 0.1dB UB EC TO Part Number CH AN GE IT HO UT 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. 5.8 dB Table 2-1 Signal Loss PR EL IM NA RY -S TOTAL SIGNAL LOSS (8.0 dB max.) Actual Quantity Rev 0, October/2000 10609I00.ZIPCDL Page 2-27 Actual Signal Loss B GE IT HO UT NO TI CE KMH 880/KTA 870 UB EC TO CH AN Figure 2-8 Coax Cable Treatment PR EL IM NA RY -S Figure 2-9 Standard RG-400 Coax Cable Figure 2-10 Bulkhead/In-Line Connection RG-400 Coax Cable Rev 0, October/2000 10609I00.ZIPCDL Page 2-28 B PR EL IM NA RY -S UB EC TO CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 Figure 2-11 TNC Antenna Coax/Connector Assembly Rev 0, October/2000 10609I00.ZIPCDL Page 2-29 B PR EL IM NA RY -S UB EC TO CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 Figure 2-12 TNC Antenna Coax/Connector Assembly Rev 0, October/2000 10609I00.ZIPCDL Page 2-30 B KMH 880/KTA 870 NO TI CE SECTION III SYSTEM PLANNING INTRODUCTION .............................................................................. Applicable Part Numbers Subsection Description ............................ Function Subsection Description ...................................................... Requirements and Limitations Subsection Description. ................... Electrical Characteristics Subsection Description. ............................ Interface Subsection Description ...................................................... 3-1 3-1 3-1 3-1 3-1 3-1 3.1 3.1.1 3.1.2 3.1.3 3.1.4 3.1.5 3.1.6 3.1.7 3.1.8 3.1.9 3.1.10 3.1.11 3.1.12 3.1.12.1 3.1.12.2 3.1.12.3 3.1.12.4 3.1.12.5 3.1.13 3.1.14 3.1.15 3.1.16 3.1.17 GENERAL INTERCONNECT INFORMATION ................................. Power Inputs ..................................................................................... Air/Ground Discrete Input ................................................................. Landing Gear Discrete Input ............................................................. Above/Below/ Normal Input .............................................................. Baro Altitude (ARINC 429) Input ....................................................... Advisory Inhibit Input ........................................................................ TAS Valid Output .............................................................................. Visual Annunciate Traffic (Lamp Output) .......................................... Synthesized Voice output ................................................................. Air Temperature Input ....................................................................... GPS Input ......................................................................................... Factory Test Input ............................................................................. TAS ATE Enable Input ................................................................... TAS Built In Test Equipment (BITE) .............................................. EGPWS Self Test Input ................................................................. Display Select Input ....................................................................... Terrain Awareness Inhibit Discrete ................................................ Terrain Warning ................................................................................ Terrain Caution .................................................................................. Weather Select Output ..................................................................... EGPWS Audio On Discrete .............................................................. EGPWS Terrain Inop and Terrain Not Available Output.................... 3-5 3-5 3-5 3-6 3-6 3-7 3-7 3-7 3-8 3-8 3-9 3-9 3-10 3-10 3-10 3-11 3-12 3-12 3-12 3-12 3-12 3-13 3-13 LIST OF ILLUSTRATIONS KMH 880/KTA 870 Interconnect Family ...................................... KMH 820/KTA 810 Pinout Diagram ............................................. KMH 820/KTA 810 System Interconnect Block Diagram ............. KMH 820/KTA 810 Power Interface ............................................ KMH 820/KTA 810 Discrete Interface ......................................... KMH 820/KTA 810 Configuration Module Interconnect ............... KMH 820/KTA 810 Attitude/Heading Interface............................. KMH 820/KTA 810 Radar/Barometric Altitude Interface ............. PR EL IM Figure 3-1 Figure 3-2 Figure 3-3 Figure 3-4 Figure 3-5 Figure 3-6 Figure 3-7 Figure 3-8 NA RY -S UB EC TO CH AN GE IT HO UT 3.0 3.0.1 3.0.2 3.0.3 3.0.4 3.0.5 Rev 0, Octobert/2000 10609I00.ZIPCDL 3-3 3-15 3-29 3-33 3-35 3-37 3-39 3-41 TOC 3-i B UT HO GE LIST OF TABLES KMH 820/KTA 810 Connector Pin Assignment ........................... 3-97 PR EL IM NA RY -S UB EC TO CH AN Table 3-1 3-49 3-51 3-53 3-59 3-65 3-69 3-73 3-77 3-79 3-81 3-83 3-87 3-95 3-96 NO TI CE KMH 820/KTA 810 Antenna/Suppression Interface .................... KMH 820/KTA 810 EFS 40/50 Interface .................................... KMH 820/KTA 810 GS 362A Interface ....................................... KMH 820/KTA 810 Honeywell GS 362A Interface ....................... KMH 820/KTA 810 Collins GS 362A Interface ............................. KMH 820/KTA 810 Honeywell Primus 1000 Interface.................. KMH 820/KTA 810 Honeywell SPZ-805 Interface........................ KMH 820/KTA 810 Diagnostic/Data Recorder Interface ............. KMH 820/KTA 810 TAS ATE Interface ....................................... KMH 820/KTA 810 CP 66B Interface ........................................... KMH 820/KTA 810 KFS 578A Interface ....................................... KMH 820/KTA 810 Display Interface............................................ KMH 820/KTA 810 Processor Front Connector .......................... KMH 820/KTA 810 Front Connector Cable .................................. IT Figure 3-9 Figure 3-10 Figure 3-11 Figure 3-12 Figure 3-13 Figure 3-14 Figure 3-15 Figure 3-16 Figure 3-17 Figure 3-18 Figure 3-19 Figure 3-20 Figure 3-21 Figure 3-22 KMH 880/KTA 870 TOC 3-ii 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 3.0 NO TI CE SECTION III SYSTEM PLANNING INTRODUCTION UT You 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. GE IT HO 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 interconnect 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 manual. Normal business hours are 8:00 A.M. to 5:00 P.M. CST, Monday through Friday. 3.0.1 Applicable Part Numbers Subsection Description 3.0.2 Function Subsection Description CH AN Information 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. TO Detailed information concerning the purpose and operation of the interface are described in this section. EC 3.0.3 Requirements and Limitations Subsection Description. UB 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. -S 3.0.4 Electrical Characteristics Subsection Description. NA RY 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 Description PR EL IM The 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. Rev 0, October/2000 10609I00.ZIPCDL Page 3-1 B KMH 880/KTA 870 PR EL IM NA RY -S UB EC TO CH AN GE IT HO UT NO TI CE Should 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 requirements. 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 adding the double shielded wire into the aircraft harness. Page 3-2 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-1 KMH 880/KTA 870 Interconnect Family Dwg. No. 155-01735-0000 (08/18/2000) Rev0, October/2000 10609I00.ZIPCDL Page 3-3 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Rev0, October/2000 10609I00.ZIPCDL Page 3-4 B GENERAL INTERCONNECT INFORMATION 3.1.1 NO TI CE 3.1 KMH 880/KTA 870 Power Inputs The Processor is powered with +28 VDC and is protected by a circuit breaker (5 Ampere) in the Aircraft distribution center. GE IT HO UT A. 28 Volts Direct Current J10 - 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 current Power: 46 ± 2.3 Watts CH AN B. DC Return J10 - 127 & 128 These pins connect to airframe ground with 22 gauge wire minimum. TO NOTE Air/Ground Discrete Input -S 3.1.2 UB EC The 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 minimum). IM NA RY The 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. PR EL AIRBORNE = >100Kohms , or +18.5 to +36 VDC. ON GROUND = < 10 ohms, or 0 to +3.5 VDC. J10-4 Air_Gnd* Rev 0, October/2000 10609I00.ZIPCDL Page 3-5 B KMH 880/KTA 870 NO TI CE NOTE The normal mechanical failure mode will be the “airborne” condition Landing Gear Discrete Input UT 3.1.3 IT HO The 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. CH AN NOTE GE RETRACTED = > 100Kohms to airframe DC GND or +18.5 to +36 VDC. EXTENDED = <10 ohms to airframe DC GND or 0 to +3.5 VDC J10-3 Landing_gear*. TO Aircraft with fixed landing gear must be equipped with a bottom monopole antenna. Furthermore, the landing gear discrete must be strapped to the retracted position. EC NOTE UB The normal mechanical failure mode is the “retracted” condition. 3.1.4 Above/Below/Normal Input NA RY -S This 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”. PR EL IM J10-71 ABV_BEL_NORM* Page 3-6 10609I00.ZIPCDL Rev 0, October/2000 B Baro Altitude (ARINC 429) Input NO TI CE 3.1.5 KMH 880/KTA 870 Baro 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 Computer will interface to the TAS Processor using the ARINC 419 input ports. Advisory Inhibit Input UT 3.1.6 IT HO The 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.) GE NOTE TO CH AN The 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 collision. 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. UB EC 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. TAS Valid Output NA 3.1.7 RY -S ADVISORY INHIBIT = GROUND NORMAL ADVISORY/ALERT = OPEN J10-22 ADV_INHIBIT* PR EL IM This 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 discrete will go invalid during power up self tests and operator commanded self tests. VALID = GROUND ( < 10 ohms to ground) INVALID = OPEN J10-25 TAS_VALID* Rev 0, October/2000 10609I00.ZIPCDL Page 3-7 B Visual Annunciate Traffic (Lamp Output) NO TI CE 3.1.8 KMH 880/KTA 870 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. Synthesized Voice output GE 3.1.9 IT HO UT ACTIVE = GROUND ( < 10 ohms to ground), VOLTAGE 0 to +3.5 VDC. INACTIVE = OPEN Current Capability = 200 milliamps., when activated. Voltage Capability = +36 VDC, when not activated. J10-24 VIS_ANNUN_TRAFFIC* TO CH AN KMH 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_ LO The power output will be adjustable based on the audio level inputs. EC The TAS messages available for output are as follows: NOTE NA RY -S UB 1. “TAS System Test OK” 2. “TAS System Test Fail” 3. “Traffic, Traffic” 4. “Traffic” PR EL IM A 1 kHz tone is available for calibration adjustments only. Page 3-8 10609I00.ZIPCDL Rev 0, October/2000 B Air Temperature Input NO TI CE 3.1.10 KMH 880/KTA 870 Outside 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. GPS Input HO 3.1.11 UT J10-109 OAT_H, J10-110 OAT_L, J10-111 OAT_Ref. IT GPS information is furnished in ARINC 429 and RS-232 (NEMA or RNAV) formats. The following Information is required from the GPS: TO CH AN GE 1. Latitude/Longitude 2. Ground Speed 3. True Track Angle 4. GPS Altitude 5. Indication of the quality of the navigation solution. (VFOM and HFOM prefered). Optional information to be used, if available, are: NOTE RY -S UB EC 1. GPS Vertical Velocity 2. Number of satelites tracked 3. Results of RAIM 4. Altitude aiding flag PR EL IM NA An internal GPS xpress Card provides all the needed signals for proper operation. Rev 0, October/2000 10609I00.ZIPCDL Page 3-9 B Factory Test Input NO TI CE 3.1.12 KMH 880/KTA 870 When active, the EGPWS will go into the Factory Test Mode. The TAS Processor and the Automatic Test Equipment will interface via RS-232 and the ATE Test Pins. 3.1.12.1 UT J10-113 GSE_PRES# (Factory Test) (Factory Only) TAS ATE Enable Input TAS Built In Test Equipment (BITE) GE 3.1.12.2 IT HO The 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. TO CH AN BITE enables the TAS Processor to provide internal system performance monitoring under normal bench conditions, under environmental extremes and during 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. RY -S UB EC 1. Automatic System Performance Monitoring (SPM) and Functional Test The TAS Processor SPM and functional test functions will test the TAS Processor 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 performance requirements. NOTE PR EL IM NA 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. The purpose of the TAS Processor automatic system performance monitoring (SPM) and Self Test is to detect malfunctions that degrade or preclude TAS protection. Page 3-10 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 IT HO Set the ‘TAS Valid Output’ discrete to invalid. Inhibit ATCRBS interrogations from TAS. Deactivate the ‘normal’ TAS display functions. Cancel any TA voice message. GE A. B. C. D. UT NO TI CE 2. Failure Processing After 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 category will be initiated: CH AN 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. RY -S UB EC TO 3. Failure Categories A. Catastrophic The severity of a catastrophic failure will preclude any software from executing. 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. NA 3.1.12.3 EGPWS Self Test Input IM Level 1 cockpit self-test will annunciate “System OK” when the system is operating properly. PR EL J10-121 GND_DISC_07 (Self Test) Rev 0, October/2000 10609I00.ZIPCDL Page 3-11 B KMH 880/KTA 870 NO TI CE 3.1.12.4 Display Select Input An input supplied by a momentarily actuated cockpit manual switch that toggles between activating and de-activating the Terrain Awareness Display (TAD). UT J10-123 GND_DISC_12 (Disp. Sel.) 3.1.12.5 Terrain Awareness Inhibit Discrete IT HO Terrain awareness will be provided via Terrain and Runway Databases. All runways >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. 3.1.13 CH AN GE J10-126 GND_DISC_15 (Terrain Awareness Inhibit) Terrain Warning TO This is a means of displaying to the flight crew that there is a critical situation involving terrain clearance and corrective action is required. Terrain Caution UB 3.1.14 EC J10-116 TERRAIN WARNING -S This is a means of displaying to the flight crew that there is a terrain clearance situation developing that needs to be monitored. Weather Select Output NA 3.1.15 RY J10-117 (TERRAIN CAUTION) IM A discrete output for controlling the terrain display. It can be used either to control a picture bus switching relay or connected directly to a symbol generator. PR EL J10-118 (WX/EGPWS DISPLAY SELECT) Page 3-12 10609I00.ZIPCDL Rev 0, October/2000 B EGPWS Audio On Discrete NO TI CE 3.1.16 KMH 880/KTA 870 EGPWS, Terrain Inop and Terrain not available Output IT 3.1.17 ADV_INHIBIT* HO J10-22 UT The 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: CH AN GE 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. PR EL IM NA RY -S UB EC TO J10-120 (EGPWS Inop) Rev 0, October/2000 10609I00.ZIPCDL Page 3-13 B CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA RY -S UB EC TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL Page 3-14 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-2 KMH 820/KTA 810 Pinout Diagram Dwg. No. 155-01735-0001 (Sheet 1 of 7) (08/10/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-15 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-16 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-2 KMH 820/KTA 810 Pinout Diagram Dwg. No. 155-01735-0001 (Sheet 2of 7) (08/10/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-17 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-18 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-2 KMH 820/KTA 810 Pinout Diagram Dwg. No. 155-01735-0001 (Sheet 3of 7) (07/11/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-19 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-20 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-2 KMH 820/KTA 810 Pinout Diagram Dwg. No. 155-01735-0001 (Sheet 4of 7) (08/10/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-21 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-22 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-2 KMH 820/KTA 810 Pinout Diagram Dwg. No. 155-01735-0001 (Sheet 5of 7) (08/10/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-23 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-24 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-2 KMA 820/KTA 810 Pinout Diagram Dwg. No. 155-01735-0001 (Sheet 6 of 7) (08/10/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-25 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-26 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-2 KMH 820/KTA 810 Pinout Diagram Dwg. No. 155-01735-0001(Sheet 7 of 7) (08/11/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-27 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-28 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-3 KMH 820/KTA 810 System Interconnect Block Diagram Dwg. No. 155-01735-0002 (Sheet 1 of 2) (08/22/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-29 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-30 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-3 KMH 820/KTA 810 System Interconnect Block Diagram Dwg. No. 155-01735-0002 (Sheet 2 of 2) (08/22/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-31 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-32 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-4 KMH 820/KTA 810 Power Interface Dwg. No. 155-01735-0003 Rev 0, October/2000 10609I00.ZIPCDL Page 3-33 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-34 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-5 KMH 820/KTA 810 Discrete Interface Dwg. No. 155-01735-0004 (08/14/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-35 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-36 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-6 KMH 820/KTA 810 Configuration Module Interconnect Dwg. No. 155-01735-0005 (08/14/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-37 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-38 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-7 KMH 820/KTA 810 Attitude/Heading Interface Dwg. No. 155-01735-0006 (08/10/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-39 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-40 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-8 KMH 820/KTA 810 Radar/Barometric Altitude Interface Dwg. No. 155-01735-0007 (Sheet 1 of 4) (08/10/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-41 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-42 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-8 KMH 820/KTA 810 Radar/Barometric Altitude Interface Dwg. No. 155-01735-0007 (Sheet 2 of 4) (08/10/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-43 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-44 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-8 KMH 820/KTA 810 Radar/Barometric Altitude Interface Dwg. No. 155-01735-0007 (Sheet 3 of 4) (08/10/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-45 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-46 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-8 KMH 820/KTA 810 Radar/Barometric Altitude Interface Dwg. No. 155-01735-0007 (Sheet 4 of 4) (08/10/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-47 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-48 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-9 KMH 820/KTA 810 Antenna/Suppression Interface Dwg. No. 155-01735-0008 (08/23/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-49 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-50 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-10 KMH 820/KTA 810 EFS 40/50 TAS Interface Dwg. No. 155-01735-0009 (08/14/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-51 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-52 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-11 KMH 820/KTA 810 GC 362A Interface Dwg. No. 155-01735-0010 (Sheet 1 of 3) (08/10/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-53 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-54 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-11 KMH 820/KTA 810 GC 362A Interface Dwg. No. 155-01735-0010 (Sheet 2 of 3) (08/10/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-55 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-56 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-11 KMH 820/KTA 810 GC 362A Interface Dwg. No. 155-01735-0010 (Sheet 3 of 3) (08/10/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-57 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-58 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-12 KMH 820/KTA 810 GC 362A Honeywell Interface Dwg. No. 155-01735-0011 (Sheet 1 of 3) (08/10/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-59 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Page 3-60 10609I00.ZIPCDL Rev 0, October/2000 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-12 KMH 820/KTA 810 GC 362A Honeywell Interface Dwg. No. 155-01735-0011 (Sheet 2 of 3) (08/10/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-61 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL Page 3-62 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-12 KMH 820/KTA 810 GC 362A Honeywell Interface Dwg. No. 155-01735-0011 (Sheet 3 of 3) (07/13/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-63 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL Page 3-64 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-13 KMH 820/KTA 810 GC 362A Collins Interface Dwg. No. 155-01735-0012 (Sheet 1 of 2) (08/10/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-65 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL Page 3-66 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-13 KMH 820/KTA 810 GC 362A Collins Interface Dwg. No. 155-01735-0012 (Sheet 2 of 2) (07/13/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-67 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL Page 3-68 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-14 KMH 820/KTA 810 Honeywell Primus 1000 Interface Dwg. No. 155-01735-0013 (Sheet 1 of 2) (08/10/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-69 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL Page 3-70 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-14 KMA 820/KTA 810 Honeywell Primus 1000 Interface Dwg. No. 155-01735-0013 (Sheet 2 of 2) (08/10/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-71 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL Page 3-72 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-15 KMH 820/KTA 810 Honeywell SPZ-805 Interface Dwg. No. 155-01735-0014 (Sheet 1 of 2) (08/14/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-73 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL Page 3-74 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-15 KMH 820/KTA 810 Honeywell SPZ-805 Interface Dwg. No. 155-01735-0014 (Sheet 2 of 2) (08/10/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-75 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL Page 3-76 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-16 KMH 820/KTA 810 Diagnostic/Data Recorder Interface Dwg. No. 155-01735-0015 (08/14/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-77 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL Page 3-78 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-17 KMH 820/KTA 810 TAS ATE Interface Dwg. No. 155-01735-0016 Rev 0, October/2000 10609I00.ZIPCDL Page 3-79 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL Page 3-80 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-18 KMH 820/KTA 810 CP 66B Interface Dwg. No. 155-01735-0017 (08/11/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-81 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL Page 3-82 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-18 KMH 820/KTA 810 KFS 578A Interface Dwg. No. 155-01735-0018 (Sheet 1 of 2) (07/14/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-83 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL Page 3-84 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-19 KMH 820/KTA 810 KFS 578A Interface Dwg. No. 155-01735-0018 (Sheet 2 of 2) Rev 0, October/2000 10609I00.ZIPCDL Page 3-85 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL Page 3-86 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-20 KMH 820/KTA 810 Display Interface Dwg. No. 155-01735-0019 (Sheet 1 of 4) (08/18/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-87 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL Page 3-88 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-20 KMH 820/KTA 810 Display Interface Dwg. No. 155-01735-0019 (Sheet 2 of 4) (08/22/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-89 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL Page 3-90 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-20 KMH 820/KTA 810 Display Interface Dwg. No. 155-01735-0019 (Sheet 3 of 4) (08/21/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-91 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL Page 3-92 B PR EL IM NA -S UB JE CT TO CH NG IT HO UT NO TI CE KMH 880/KTA 870 Figure 3-20 KMH 820/KTA 810 Display Interface Dwg. No. 155-01735-0019 (Sheet 4 of 4) (08/22/2000) Rev 0, October/2000 10609I00.ZIPCDL Page 3-93 B CH NG IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA -S UB JE CT TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL Page 3-94 B 59 71 82 94 25 50 16 28 18 41 31 21 12 42 43 53 44 13 33 23 45 14 UB 34 46 24 47 86 75 76 54 66 55 77 68 78 67 56 57 58 70 115 96 107 116 122 97 108 117 98 123 118 87 124 109 98 119 88 89 90 99 125 110 100 126 120 111 127 101 112 121 128 91 69 106 102 113 79 80 92 103 114 104 81 93 PR EL IM NA RY -S 35 74 65 32 22 64 30 20 85 52 29 19 11 63 EC 40 73 62 39 95 84 CH AN 10 38 51 17 27 61 TO 37 105 83 IT 26 72 GE 15 60 49 UT 48 HO 36 NO TI CE KMH 880/KTA 870 Figure 3-21 KMH 820/KTA 810 Processor Front Connector Rev 0, October/2000 10609I00.ZIPCDL Page 3-95 B PR EL IM NA RY -S UB EC TO CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 Page 3-96 Figure 3-22 KMH 820/KTA 810 Front Connector Cable 10609I00.ZIPCDL Rev 0, October/2000 B EL Page 3-97 CH AN GE IT HO UT NO TI CE Notes Future Use (Do Not Wire) POWER ON=GND TEST=GND EXTENDED=GND ON GND=GND VALID=GND ANALOG ANALOG ANALOG TO Unit PS TAS TAS TAS TAS TAS TAS TAS BOTH BOTH BOTH BOTH BOTH BOTH BOTH BOTH BOTH TAS TAS TAS TAS BOTH TAS TAS TAS TAS TAS TAS TAS TAS TAS TAS TAS TAS TAS TAS TAS TAS TAS TAS TAS TAS TAS TAS TAS TAS TAS TAS HEADPHONE HEADPHONE MUTE=GND STBY=GND TRAFFIC=GND VALID=GND *** *** NA RY -S UB EC Description ON* FUNCTIONAL_TEST LANDING_GEAR* AIR_GND* DISPLAY_VALID* RADIO_ALT+ RADIO_ALTRAD_ALT_VAL GIL_ALT_A4 GIL_ALT_A2 GIL_ALT_A1 GIL_ALT_B4 GIL_ALT_B2 GIL_ALT_B1 GIL_ALT_C4 GIL_ALT_C2 GIL_ALT_C1 GIL_ALT_D4 GIL_ALT_D2 PH_HI PH_LO ADV_INHIBIT* TAS_STANDBY* VIS_ANNUN_TRAFFIC* TAS_VALID* SPARE_DO1 SPARE_DO2 HEADING_VALID HEADING_H HEADING_C HEADING_X HEADING_Y HEADING_Z RS422_DATA+ RS422_DATARS422_CLK+ RS422_CLKDIAG_RS232_TX DIAG_RS232_RX DIAG_RS232_RDY DIAG_RS232_TERMRDY ATE_A(0) ATE_A(1) ATE_A(2) ATE_D(0) ATE_D(1) ATE_D(2) ATE_D(3) IM Pin 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 PR I/O KMH 880/KTA 870 *** *** Table 3-1 KMH 820/KTA 810 Connector Pin Assignment 10609I00.ZIPCDL Rev 0, October/2000 B Future Use (Do Not Wire) *** *** TO CH AN GE IT HO PS BOTH BOTH TAS TAS TAS TAS TAS TAS >18V=ACTIVE *** TAS TAS TAS Above/Below/Norm TAS TAS TAS TAS TAS TAS *** BOTH TAS TAS TAS TAS PS EGPWS NO TI CE NOTES UT Unit TAS TAS TAS TAS TAS BOTH BOTH TAS TAS NA RY -S UB EC Description ATE_D(4) ATE_D(5) ATE_D(6) ATE_D(7) CALENB* CDU_429_TX_A CDU_429_TX_B RAD_ALTIM_RX_A RAD_ALTIM_RX_B n/c AIRCRAFT POWER BARO_ALT_RX_A BARO_ALT_RX_B HDG_ATT_RX_A HDG_ATT_RX_B SPARE_RS232_TX SPARE_RS232_RX SPARE_RS232_RDY SPARE_RS232_TERMRDY SUPPRESSION CNTL_RX_A CNTL_RX_B ABV_BEL_NORM CONFIG_MOD_DATA_IN CONFIG_MOD_DATA_OUT CONFIG_MOD_CHIP_SEL CM_CLOCK CM_+5V CM_GND SPARE_RX_A SPARE_RX_B SPARE_TX_A SPARE_TX_B AIRCRAFT POWER EGPWS RETURN CHASSIS GROUND RS232TXD_GAMMA RS232RXD_GAMMA GPS_TXA GPS_RXA GPS_TXB GPS_RXB ADC_TXA 429TX_1B 429TX_1A ADC_RXA 429RX_1A 429RX_1B IM PR I/O Pin 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 86 87 88 89 90 91 92 93 94 95 96 EL I/O KMH 880/KTA 870 EGPWS EGPWS EGPWS EGPWS EGPWS EGPWS EGPWS BOTH BOTH EGPWS EGPWS EGPWS 232 OUT A / 422 232 IN A / 422 422 422 JUMPER TO TAS JUMPER TO TAS RANGE INPUT RANGE INPUT Table 3-1 KMH 820/KTA 810 Connector Pin Assignment (Cont’) Rev 0, October/2000 10609I00.ZIPCDL Page 3-98 B UT HO GPS GPS MONITOR PORT *** MONITOR PORT PICT BUS PICT BUS CM DATA OUT *** CM DATA IN CM CLK *** CM SEL *** AIR TEMP + AIR TEMP AIR TEMP REF FACTORY TEST NO TI CE Future Use (Do Not Wire) GE EGPWS EGPWS EGPWS EGPWS EGPWS EGPWS EGPWS EGPWS EGPWS NOTES IT Unit EGPWS EGPWS EGPWS EGPWS TAS CH AN BOTH EGPWS EGPWS LAMP ALERT EGPWS EGPWS WARNING ALERT WX SELECT EGPWS TAS EGPWS INOP EGPWS SELF TEST EGPWS BOTH DISP SEL EGPWS BOTH BOTH EGPWS TERRAIN AWARE PS PS TO Description 429RX_2A 429RX_2B RS232TXD_MON RS232RXD_MON ATE_CLOCK n/c ASPB_1A ASPB_1B SPIMOSI_CM_2 SPIMISO SPICLK_CM_2 SPISEL_CM#_2 OAT_H OAT_L OAT_REF n/c GSE_PRES# ADC_TXB ADC_RXB DISC_OUT_01 DISC_OUT_02 DISC_OUT_03 SPARE_IN_2 MON_OUT_1 GND_DISC_07 GND_DISC_08 GND_DISC_12 GND_DISC_13 GND_DISC_14 GND_DISC_15 AIRCRAFT GROUND AIRCRAFT GROUND EC Pin 97 98 99 100 101 102 103 104 105 106 107 108 109 110 111 112 113 114 115 116 117 118 119 120 121 122 123 124 125 126 127 128 UB I/O KMH 880/KTA 870 RY -S Notes: * indicates active ground *** indicates that this line has a transorb located on the the interconnect board PR EL IM NA Table 3-1 KMH 820/KTA 810 Connector Pin Assignment (Con’t) Page 3-99 10609I00.ZIPCDL Rev 0, October/2000 B CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA RY -S UB EC TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL Page 3-100 B KMH 880/KTA 870 NO TI CE SECTION IV POST INSTALLATION CONFIGURATION AND CHECK OUT INTRODUCTION .............................................................................. 4-1 4.1 LINE SELECT KEYS ........................................................................ 4-1 4.2 4.2.1 4.2.2 4.2.3 4.2.3.1 4.2.3.2 4.2.3.3 4.2.3.4 4.2.3.5 4.2.3.6 4.2.3.7 4.2.3.8 4.2.3.8.1 4.2.3.8.2 4.2.3.8.3 4.2.3.8.4 4.2.3.8.5 4.2.3.8.6 4.2.3.8.7 4.2.3.8.8 4.2.3.8.9 4.2.4 4.2.4.1 4.2.4.2 CONFIGURATION PROCEDURE .................................................... Power On .......................................................................................... Aircraft Configuration ........................................................................ EGPWS Configuration Instructions.................................................... Equipment needed............................................................................. Configuration Module Programming .................................................. Configuration String Format............................................................... RS-232 Maintenance Port (Port SMC1) ............................................ RS-232 Diagnostic Port ..................................................................... Configuration Sequence of Events .................................................... Configuration Types........................................................................... Configuration Tables.......................................................................... Category 1, Aircraft/Mode Type Select............................................ Category 2, Air Data Input Select .................................................... Category 3, Position Input Select .................................................... Category 4, Terrain Display Select .................................................. Category 5, Input/Output Discrete Type Select ............................... Category 6, Audio Menu Select ....................................................... Category 7, Audio Output Level....................................................... Category 8, Altitude Monitor Options ............................................... Category 9, Terrain Display Alternate Pop Up Option ..................... TAS Configuration Options ................................................................ TAS RS-232 Maintenance Port ......................................................... TAS RS-422 Data Recorder .............................................................. 4-1 4-1 4-1 4-2 4-2 4-2 4-2 4-3 4-4 4-4 4-4 4-6 4-6 4-7 4-7 4-8 4-9 4-10 4-10 4-11 4-11 4-12 4-15 4-15 4.3 4.3.1 4.3.2 4.3.3 GROUND TEST PROCEDURES ...................................................... Required Test Equipment .................................................................. EGPWS Ground Test Procedures ..................................................... TAS Ground Test Procedures ........................................................... IM NA RY -S UB EC TO CH AN GE IT HO UT 4.0 4-15 4-15 4-16 4-18 LIST OF ILLUSTRATIONS 4-34 PR EL Figure 4-1 TAS Bearing Measurements............................................................ Rev 0, October/2000 10609I00.ZIPCDL TOC 4-i B KMH 880/KTA 870 NO TI CE LIST OF TABLES 4-5 4-6 4-7 4-8 4-9 4-9 4-10 4-11 4-11 4-12 PR EL IM NA RY -S UB EC TO CH AN GE IT HO UT Table 4-1 Configuration Identification .............................................................. Table 4-2 Aircraft/Mode Type Select ............................................................... Table 4-3 Air Data Input Select........................................................................ Table 4-4 Position Input Select ........................................................................ Table 4-5 Terrain Display Select...................................................................... Table 4-6 Input/Output Discrete Type Select ................................................... Table 4-7 Audio Menu Select........................................................................... Table 4-8 Audio Output Level .......................................................................... Table 4-9 Altitude Monitor Options .................................................................. Table 4-10 Terrain Display Alternate Pop Up Option......................................... Rev 0, October/2000 10609I00.ZIPCDL TOC 4-ii B KMH 880/KTA 870 NO TI CE SECTION IV POST INSTALLATION CONFIGURATION AND CHECK OUT 4.0 INTRODUCTION 4.1 HO UT This Section describes the procedure for configuring and testing the KMH 880/KTA 870 System after it is installed in the aircraft. POST CONFIGURATION TEST GE IT This 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. CH AN 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. TO CAUTION: 4.2 UB EC 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. CONFIGURATION PROCEDURE -S This section describes the configuration options available to be programmed into the Configuration Module of the KMH 880/KTA 870 System. RY 4.2.1 Power On Turn the KMH 880/KTA 870 System on. PR EL IM NA 4.2.2 Aircraft Configuration Aircraft 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, Appendix D of this manual. Rev 0, October/2000 10609I00.ZIPCDL Page 4-1 B KMH 880/KTA 870 NO TI CE 4.2.3 EGPWS Configuration Instructions These instructions will detail the configuration check list, initial configuration (new configuration module) and volume output levels for the EGPWS. HO UT It describes how the EGPWS interfaces to specific aircraft configurations. It contains an overview of the selection categories for the different aircraft sensor interfaces. It defines how the category IDs are selected for the interface to aircraft sensors and to select EGPWS performance options. It defines the specific aircraft applications of the EGPWS. EGPWS Installed and Operating Interconnect Cable IBM or Compatible PC A Copy of Honeywell WINVIEWS CH AN NOTE GE A. B. C. D. IT 4.2.3.1 Equipment Needed TO WinViews 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 operational when communications are established with the EGPWS. EC 4.2.3.2 Configuration Module Programming UB The Configuration Module Programming is completed via the RS-232 port. The application code is capable of loading the Configuration Module with new data. RY -S 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. IM NA 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. PR EL 4.2.3.3 Configuration String Format The EGPWS requires a string of configuration information to be written to the configuration module memory when requested from the keyboard monitor. Page 4-2 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE Example 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. = Category #3 ID = 0 = Category #4 ID = 0 = Category #5 ID = 0 = Category #6 ID = 0 = Category #7 ID = 2 = Category #8 ID = 2 = Category #9 ID = 0 = Separator HO IT = The command to write = String Version = Separator = the number of categories = Category #1 ID = 0 = Category #2 ID = 1 (TSO-C151a Class B curve set) (Altitude Encoder with 500 ohm Temperature Probe) (GPS, Internal GPS Express RS-232) (Display select = ASPB) (I/O Discrete Type Select = Basic, Lamp format 2) (Audio Menu Select = Basic) (Audio Output Level = -12dB) (Altitude Monitor Option Select = Disable) (TA&D Alternate Pop Up = False) TO CH AN GE CUW UT String breakdown Explanations: EC 4.2.3.4 EGPWS RS-232 Maintenance Port (port: SMC1) -S UB 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. 19,200 none 15 meters RS-232TXD_MON RS-232RXD_MON J10-99 J10-100 PR EL IM NA RY Baud Rate Parity Data Bits Stop Bits Maximum Recommended Cable Length Pin Assignment (Signal Mnemonic) Rev 0, October/2000 10609I00.ZIPCDL Page 4-3 B KMH 880/KTA 870 NO TI CE 4.2.3.5 Configuration Sequence of Events (Application) 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 the ENTER key. E. After loading this string in the WINVIEWS, the cursor will flash waiting for an answer “Y” or “N”. F. Type “Y”. CH AN NOTE GE IT HO UT A. At this point the EGPWS will reboot itself. 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. EC TO G. UB 4.2.3.6 Configuration Types (Categories) The selection of the basic interfaces to the EGPWS can be found in the following categories. Category 1 Category 2 Category 3 Category 4 Category 5 Category 6 Category 7 Category 8 Category 9 EL IM NA RY -S Aircraft/Mode Type Air Data Type Position Type Terrain Display Type I/O Discretes Types Audio Menu Type Audio Output Level Type Altitude Monitor Options Type Terrain Display Alternate Pop up Option PR 4.2.3.7 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. Page 4-4 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 STEP (CATEGORY) SIGNAL SELECTION NO TI CE This table provides the procedure to determine the Configuration ID selection required for any given aircraft installation. INSTRUCTION _____ ID # Selects: a) Air Data Source Using Table 4-3 and any sub-tables contained within, locate the desired Air Data signal type. Record the Ident (ID No.) on the space available on Ident column of this table _____ ID # Selects: a) Position Source Using Table 4-4 and any sub-tables contained within, locate the desired Position Signal type. Record the Ident (ID No.) on the space available on Ident column of this table. _____ ID # Selects: a) Display Configuration Using Table 4-5 and any sub-tables contained within, locate the desired Display indicator type/range bus type. Record the Ident (ID No.) on the space available on Ident column of this table. _____ ID # Selects: a) Input discrete Functions b) Output Discrete Functions. Using Table 4-6 and any sub-tables contained within, locate the desired I/O Discrete type. Record the Ident (ID No.) on the space available on Ident column of this table. _____ ID # Selects: a) Audio Menu Using Table 4-7 and any sub-tables contained within, locate the desired Audio Menu type Record the Ident (ID No.) on the space available on Ident column of this table. _____ ID # Using Table 4-8 and any sub-tables contained within, locate the desired Volume type Record the Ident (ID No.) on the space available on Ident column of this table. _____ ID # Selects: a) Audio Output Level EC UB PR EL IM NA TO CH AN GE RY -S UT Record the Ident (ID No.) on the space available on Ident column of this table. HO Using Table 4-2 and any sub-tables contained within, locate the Aircraft/Mode type. IT Selects: a) Aircraft Type b) Mode Type IDENT. NO. Rev 0, October/2000 10609I00.ZIPCDL Page 4-5 B SIGNAL SELECTION Selects: a) TA&D alternate Pop Up Using Table 4-10 and any subtables contained within, select the desired True or False condition for TA&D Alternate Pop Up. NO TI CE Using Table 4-9 and any sub-tables contained within, select the desired True or False Condition for Altitude Monitor Display Disable, Altitude Monitor Callout Disable, and Altitude Monitor Disable. Record the Ident (ID No.) on the space available on Ident column of this table. HO Selects: a) Altitude Monitor Display Disable b) Altitude Monitor Call out Disable c) Altitude Monitor Disable Record the Ident (ID No.) on the space available on Ident column of this table. IT INSTRUCTION UT STEP (CATEGORY) KMH 880/KTA 870 IDENT. NO. _____ ID # _____ ID # GE Table 4-1 Configuration Identification CH AN 4.2.3.8 Configuration Tables TO The 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 Position Input Source, Category 3, is defined in Table 4-4. EC 4.2.3.8.1 Category 1, Aircraft/Mode Type Select UB The following table provides identification of the basic mode types and associated parameters. In this category only the following parameters are to be defined: Aircraft/Mode Type NA ID RY -S • Basic mode alert and warning thresholds Effectivity App. Cfg. TSO-C151a Class B curve set -001 -001 Non-TSO curve set #1 -001 -001 IM Table 4-2 Aircraft / Mode Type Select PR EL Description Page 4-6 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE NOTE When selecting ID 0; Category 6, (Audio Menu Select) must select ID #1 (Alternate) in order to be in compliance with TSO-C151a. UT 4.2.3.8.2 Category 2, Air Data Input Select HO The following table provides identification of the Air Data source type. In this category only the following parameters are to be defined: AIR DATA TYPE DESCRIPTION GE ID IT • Gillham/Gray coded altitude or uncorrected altitude in ARINC 429 format. Temperature, Outside Air or Static Air in analog or ARINC 429 format. EFFECTIVITY App. Cfg. Altitude Encoder (9 wire Gillham/Gray coded altitude) -001 -001 Altitude Encoder (9 wire Gillham/Gray coded altitude) with 500 ohm OAT Temperature Probe -001 -001 Digital - ARINC 429 (Required Labels are 203 and 213) -001 -001 Digital - ARINC 429 (with Corrected Altitude) (Required Labels are 203,204,212,and 213) -001 -001 EC TO CH AN UB Table 4-3 Air Data Input Select 4.2.3.8.3 Category 3, Position Input Select IM NA RY Altitude Date Ground Speed Horizontal Figure of Merit (HFOM) Horizontal Integrity Limit Latitude Position Longitude Position • • • • • • • Sensor Status Track angle Universal Time Correlation Vertical Figure of Merit (VFOM) Vertical Velocity N/S Velocity E/W Velocity PR EL • • • • • • • -S The following table provides identification of the Position Source Signal. In this category, only the following POSITION signals are to be defined: Rev 0, October/2000 10609I00.ZIPCDL Page 4-7 B DESCRIPTION NO TI CE POSITION INPUT TYPE GPS ALTITUDE REFERENCE GPS, Internal GPS-PXPRESS RS-232 MSL GPS, External RS-232 (GPS-PXPRESS format) MSL GPS, ARINC 429 low speed, 743A format MSL GPS, ARINC 429 low speed, 743 format MSL GPS, ARINC 429 low speed, 743 format (GPS Altitude referenced to WGS-84) IT HO UT ID KMH 880/KTA 870 -001 -001 -001 -001 -001 -001 -001 -001 -001 -001 GE WGS-84 EFFECTIVITY App. Cfg. Table 4-4 Position Input Select CH AN NOTE 1 EC TO The 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. UB NOTE 2 RY -S This 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 Select PR EL IM NA The 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. Page 4-8 10609I00.ZIPCDL Rev 0, October/2000 B In this category the following signals are configured by the ID number: SIGNAL NAME SIGNAL TYPE NO TI CE KMH 880/KTA 870 DEFINED BY ASPB or ARINC Display configuration Group Range Bus ARINC 429 Display Input Control Group TA&D Alternate Pop Up Boolean Defined directly in Table 4-10 DISPLAY INPUT CONTROL GROUP (NOTE 1) OUTPUT 429 BUS GROUP None None EC ASPB EFFECTIVITY App. Cfg. -001 -001 No Display -001 -001 Bendix IN 182A, IN 812A -001 -001 Bendix IN 842A, IN 862A -001 -001 Bendix RDR 4A/B PPI (with blue waters modification) -001 -001 CH AN APPLICATION NOTES GE DISPLAY CONFIG. GROUP TO ID IT HO UT Terrain Display Bus UB Table 4-5 Terrain Display Select 4.2.3.8.5 Category 5, Input/Output Discrete Type Select RY -S The following table provides identification of the Input/Output Discrete Type. Input/Output Discrete Type NA ID Basic input/output discretes (Lamp Format: Type 2) Effectivity App. Cfg. -001 -001 Table 4-6 Input/Output Discrete Type Select PR EL IM Description Rev 0, October/2000 10609I00.ZIPCDL Page 4-9 B KMH 880/KTA 870 NO TI CE NOTE 4.2.3.8.6 Category 6, Audio Menu Select DESCRIPTION IT AUDIO MENU TYPE Basic Alternate EFFECTIVITY App. Cfg. -001 -001 -001 -001 CH AN GE ID HO The following table provides identification of the Voice Menu type. UT If 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. Table 4-7 Audio Menu Select NOTE EC TO If 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 Level PR EL IM NA RY -S UB The 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 output. The output power level will be the nominal maximum output 100mW reduced by the selected volume type. Page 4-10 10609I00.ZIPCDL Rev 0, October/2000 B ID VOLUME TYPE NO TI CE KMH 880/KTA 870 EFFECTIVITY App. Cfg. Max (600 ohm ≈ 100mW) -001 -6 dB -001 -12dB -001 -001 -18dB -001 -001 -24dB -001 -001 IT HO UT -001 -14db for ΚΜΗ 880/ΚΤΑ 870 configuration -001 -001 GE 255 -001 CH AN Table 4-8 Audio Output level 4.2.3.8.8 Category 8, Altitude Monitor Options ALTITUDE MONITOR CALLOUT DISABLE ALTITUDE MONITOR DISPLAY DISABLE EFFECTIVITY App. Cfg. False False False -001 -001 False False True -001 -001 False True False -001 -001 False True True -001 -001 True True -001 -001 RY -S UB ALTITUDE MONITOR DISABLE NA True IM NOTE: TRUE = Disable Table 4-9 Altitude Monitor Options EL 4.2.3.8.9 Category 9, Terrain Display Alternate Pop Up Option The following table provides identification of the Terrain Display Alternate Pop Up Option. PR ID EC TO The following table provides identification of the Altitude Monitor Options. Each entry in the ID column corresponds to a particular combination of Altitude Monitor Display Disable, Altitude Monitor Callout Disable and Altitude Monitor Disable. TA&D Alternate Pop Up = False allows automatic Pop Up On Caution or Warnings. Rev 0, October/2000 10609I00.ZIPCDL Page 4-11 B KMH 880/KTA 870 TA&D ALTERNATE POP UP DISABLE EFFECTIVITY False -001 -001 True -001 -001 UT ID NO TI CE TA&D Alternate Pop Up = True disables the automatic Pop Up feature. TAS Configuration Options IT 4.2.4 HO Table 4-10 Terrain Display Alternate Pop Up Option CH AN NOTE GE The TAS Processor will acquire the following hardware strap information from the configuration module. Format is as follows: Configuration Option; Configuration Option Description. Display Intruder Limit; 3 (Minimum) Display Intruder Limit 30 (Maximum), incremented by 1. TO A. UB EC 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). NOTE Heading Type; Synchro Data or ARINC 429 Data NA B. RY -S The TAS Processor will transmit a maximum of 30 intruders to the traffic display. IM The Heading Type Program will indicate the type of heading source (either ARINC 429 or Synchro) that interfaces to the TAS. PR EL C. Page 4-12 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. 10609I00.ZIPCDL Rev 0, October/2000 B Radio Altimeter Type; Not Installed, ARINC 429, Bendix/King Analog, Sperry Analog, Collins Analog or ARINC 552A. NO TI CE D. KMH 880/KTA 870 UT 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. IT HO 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. CH AN NOTE GE The Radio Altimeter Type Program will indicate which type of radio altimeter input is used. Due to tolerances in the TAS Processor analog I/O hardware, the accuracy for the 0 - 100 foot range may be ± 10 feet. On Ground Display Mode; TAS in Standby Mode On-Ground or TAS in TA Only Mode On-Ground. TO E. Baro Altimeter Type; Gillham, ARINC 575, ARINC 706. -S F. UB EC 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. Controller Type; ARINC 735 Protocol, or Discrete Control. NA G. RY 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. EL IM The Controller Type will determine the type of control data, either the Control Panel to the TAS Processor via the CNTL HD RX (ARINC 429) input bus or via Discrete Control switches. PR 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. Rev 0, October/2000 10609I00.ZIPCDL Page 4-13 B Airborne Headphone Volume; 1.25, 2.5, 5, 10, 20, 40, 80, 100 mw. NO TI CE I. KMH 880/KTA 870 The airborne headphone level will be configurable to the above levels. J. Airborne Functional Test; Inhibited or Allowed. UT When the Airborne Functional Test is inhibited, the TAS Processor will inhibit Functional Test while in the air. ATE Output; Enabled or Disabled. IT K. HO When the Airborne Functional Test is allowed, the TAS Processor will allow Functional Test in the air. Intruder File Protocol CH AN L. GE The ATE Output will be used to enable the ATE lines for the Anechoic Chamber and the RGS stations. ARINC 735a or Honeywell Business and Commuter Aviation Systems (BCAS) protocol. Display Valid Input Usage: Used or Ignored. TO M. RS-422 Output Drivers: enabled or disabled UB N. EC If “Used“ is selected, TAS will use the Display Valid Input for BITE purposes. If “Ignored” is selected, TAS will ignore the Display Valid Input for BITE purposes. PR EL IM NA RY -S When 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. Page 4-14 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE 4.2.4.1 TAS RS-232 Maintenance Port DIAG_RS232_TX DIAG_RS232_RX DIAG_RS232_RDY DIAG_RS232_TERMRDY J10-38 J10-39 J10-40 J10-41 HO 38,400 none 15 Meters CH AN GE IT Baud Rate Parity Data Bits Stop Bits Maximum Recommended Cable Length Pin Assignment (Signal Mnemonic) UT One 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 addition to the internal data, other items such as unit configuration and flight history can also be accessed. 4.2.4.2 TAS RS-422 Data Recorder EC TO One 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. 15 Feet RS422_DATA+ RS422_DATARS422_CLK+ RS422_CLK- J10-34 J10-35 J10-36 J10-37 GROUND TEST PROCEDURES 4.3.1 Required Testing Equipment NA 4.3 RY -S UB Maximum Recommended Cable Length Pin Assignment (Signal Mnemonic) IM • Personal Computer with Diagnostic Program (WinViews for the EGPWS ground tests and TASDIAG for TAS ground tests. (See Appendix D). PR EL • TCAS Ramp Test Set; TCAS 201, or equivalent. • Transponder Ramp Test Set. Rev 0, October/2000 10609I00.ZIPCDL Page 4-15 B KMH 880/KTA 870 NO TI CE • Pitot-Static Test Set. • Radio Altimeter Test Set, or equivalent. • Volt-Ohmmeter (DVM) (optional). EGPWS Ground Test Procedures (066-01175-x101 only). HO 4.3.2 UT • 429 Bus reader (optional). IT This Ground Test Procedure is designed to minimize potential equipment damage and verify proper operation of the Honeywell EGPWS as installed in the aircraft. Review your aircraft installation drawings against the manufacturer’s data sheets and verify that all necessary connections are included on your drawings 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 minutes 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 configuration 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. PR EL IM NA RY -S UB EC TO CH AN GE A. I. Page 4-16 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). 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 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 Gillham Alt ft. and verify that the altitude shown agrees with the aircraft altimeter, ± 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 accomplished 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: PR EL IM NA RY -S UB EC TO CH AN GE IT HO UT NO TI CE J. 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. Rev 0, October/2000 10609I00.ZIPCDL Page 4-17 B KMH 880/KTA 870 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 display 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. UT NO TI CE R. 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 increment. You can record this test using the data collection feature of WinViews. CH AN GE T. IT HO 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 Altitude 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. 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. RY -S UB U. (TAS) Ground Test Procedure NA 4.3.3 EC TO 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. PR EL IM Installation of the TAS System requires three stages of testing to ensure the proper operation 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. Page 4-18 10609I00.ZIPCDL Rev 0, October/2000 B To check the aircraft system interconnections, perform the following: NO TI CE A. KMH 880/KTA 870 Check that all cables and interwiring are installed according to the Interwiring and Cable Fabrication instructions. (paragraph 2.2.7 and 2.2.8) HO IT 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 Option GE • • • • • • • • • UT Check that the following functions are properly strapped to reflect the aircraft system configuration. (paragraph 4.2.3.6) CH AN Using the interconnect diagrams (Figures 3-1 through Figure 3-23), check wiring for proper destinations, opens and shorts. TO Check RF Cable for electrical length matching, insertion loss and VSWR. (See paragraph 2.2.7 and 2.2.8) EC Check the transponder and DME interface. NOTE -S UB The only required interface between the KMH/KTA TAS and the transponder is the suppression line. Some installations may use a common control for the transponder and the TAS. In these cases, the TAS control comes from the transponder control unit. 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 performing 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. PR EL IM NA RY B. 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. Rev 0, October/2000 10609I00.ZIPCDL Page 4-19 B KMH 880/KTA 870 NO TI CE Check 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. UT Check that the Transponder, TAS, and Radar Systems are OFF. If applicable, the selected encoding altitude source should be #1. If applicable, the ADC (Air Data Computer) source should be set to normal. IT HO Operate the appropriate aircraft circuit breakers to apply power to the TAS Processor, Traffic Advisory displays and all other aircraft equipment connected to the TAS Processor subsystem. Check that the circuit breakers remain closed (pushed in). GE 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. CH AN 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: TO • No “TAS” flag annunciation. • “TAS STBY”. • If installed, the TA/VSI vertical speed needle should indicate 0 fpm. UB EC 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. -S On the TAS Control Unit, select the ON position. The following conditions should exist: IM NA RY • 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. PR EL D. Page 4-20 Perform the Self-test by initiating the TAS System Self-test on the TAS Control 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, 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE the word “TEST” is displayed on the display. The following symbols are displayed: HO UT • 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. Perform the Ground Test. GE E. IT 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”. CH AN 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 completed in a random order to accommodate other conditions. The person performing these tests should be familiar with the TAS equipment, the aircraft installation and the supporting test equipment. TO NOTE Perform the TAS Power Checks UB 1. EC In 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. Verify aircraft power to TAS -S Pull the 5 amp TAS Processor circuit breaker. RY Verify that the “TAS” flag appears on the traffic display. NA Reset the circuit breaker. Verify that the flag clears. PR EL IM Pass/Fail _____. Pull the 1 amp TAS Control circuit breaker. Verify that the “TAS” flag appears on the traffic display. Reset the circuit breaker. verify that the flag clears. Rev 0, October/2000 10609I00.ZIPCDL Page 4-21 B KMH 880/KTA 870 NO TI CE Pass/Fail _____ NOTE UT The following three steps should only be performed when the configuration module is set to use the Display Valid input. IT NOTE HO Pull the Traffic Display circuit breaker. CH AN GE The above circuit breaker should be for the unit providing a valid to the TAS Processor at pin 5. Verify that the appropriate flag appears INVALID. Reset the circuit breaker. Verify that the flag clears. TO Pass/Fail _____ EC Disable the 26Vac 400 Hz source used as a reference for the Hg and Alt inputs. UB Verify that the “TAS” flag appears on the traffic display. Reset the circuit breaker. Verify that the flag clears. On the TAS Control Panel exercise all the TAS control functions and observe for correct operation. RY 2. -S Pass/Fail _____ NA Test the ON/OFF and STB/ON functions as follows: PR EL IM Set the PWR switch to the OFF condition. (If applicable) Page 4-22 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” annunciation is displayed. 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE Pass/Fail _____ Test the ABOVE/NORMAL/BELOW function as follows: HO UT 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. IT 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. CH AN Traffic Display _____ GE 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. On the traffic display, check the TAS ranges to observe the range annunciations and range rings. TO NOTE UB EC There 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. NOTE -S The 2 nm range ring is visible on all TAS RANGE selections less than 20 nm. NA RY Set TAS RANGE switch to 3 nautical miles. The following properly scaled range rings should be visible: PR EL IM 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: Rev 0, October/2000 10609I00.ZIPCDL Page 4-23 B KMH 880/KTA 870 ______ NO TI CE 2 and 10 nautical mile range rings. Set TAS RANGE switch to 15 nautical miles. The following properly scaled range rings should be visible: ______ UT 2 and 15 nautical mile range rings. ______ IT 5, 10, and 20 nautical mile range rings. HO Set TAS RANGE switch to 20 nautical miles. The following properly scaled range rings should be visible: CH AN NOTE GE Set TAS RANGE switch to 40 nautical miles. The following properly scaled range rings should be visible: On the traffic display unit, an outer ring represents maximum nautical (nm) display scaling as selected on the RANGE switch. TO If applicable, test the FL (Flight Level) function as follows: EC Press the FL switch. UB 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. -S Pass/Fail _____ RY 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: PR EL IM NA 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. Page 4-24 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. 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 3. NO TI CE Pass/Fail _____ 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). HO UT Observe that the traffic display (radar indicator) annunciates “TA AUTO”, but unless TA traffic is present only the radar picture is displayed. IT Set the T/WX switch to “T/WX” (TAS and Weather). GE Observe that the traffic display annunciates “TA” or “TA ONLY” and shows both traffic and weather if the radar is ON. Select “TCAS” (TAS ONLY) with the T/WX switch. CH AN Observe that the traffic display annunciates “TA” or “TA ONLY” and shows TAS traffic but no weather is displayed. Pass/Fail ______ TO 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. EC 4. UB 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. RY -S 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. PR EL IM NA 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. Rev 0, October/2000 10609I00.ZIPCDL Page 4-25 B KMH 880/KTA 870 NO TI CE Verify that the Heading Status goes INVALID. Verify that the “TAS” flag appears on the traffic display. Reset the circuit breaker. Verify that the TAS flag clears. Verify that the encoding altitude is properly interfaced to the TAS Processor. Confirm that the encoding altitude of the transponder and TAS agree. HO 5. UT Pass/Fail ______ IT CAUTION CH AN GE PRECAUTIONS 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 ANTENNAS IS THE BEST WAY TO PREVENT INTERFERENCE WITH OTHER AIRCRAFT. EC TO 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 TASDIAG Input Data program and observe the following on the Diagnostic Computer. UB 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. -S The Enc. Alt. Status in the computer should indicate VALID. PR EL IM NA RY Confirm the following Encoding Altitudes at the altimeter, Diagnostic Computer and transponder: Page 4-26 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. 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE Transponder indicates ______ feet. Altitude at 31,800 feet, the computer screen indicates ______ feet. Transponder indicates ______ feet. UT NOTE IT HO The 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. GE Verify that the Enc. Alt. Status goes INVALID. CH AN Verify that the ”TAS” flag appears on the traffic display. Reset the circuit breaker. Verify that the “TAS” flag clears. Enc. Altitude Source #1 Pass/Fail ______. EC TO If applicable, select the other encoding source and repeat the above steps. Enc. Altitude Source #2 Pass/Fail ______. UB If applicable, verify the attitude interface to the TAS Processor. Confirm the pitch and roll attitude source and measure the inputs at the KMH/KTA Processor. RY -S The TAS and attitude 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 computer screen. PR EL IM NA Monitor the attitude source in the cockpit. Observe the Pitch and Roll attitude readouts. The computer screen readouts should agree to within a few degrees of the cockpit heading display. Record a pitch and roll attitude other than (0.0°) ______. Is it consistent with the aircraft’s attitude? The Pitch and Roll Status on the computer should indicate VALID. Flag the attitude source by pulling the circuit breaker. Rev 0, October/2000 10609I00.ZIPCDL Page 4-27 B KMH 880/KTA 870 NO TI CE Verify 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 “TAS” flag clears. Pass/Fail ______. If applicable, verify that the Radio Altimeter is properly interfaced to the TAS Processor. Confirm the radio altitude configuration straps and measure the input at the KMH/KTA Processor. HO UT 6. GE IT The TAS and radio altitude source(s) should be operating normally for the 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. CH AN Monitor the radio altitude source in the cockpit. Observe the Radio Altitude readout. The computer readout should agree with the cockpit radio altimeter indicator. If the computer display is too erratic, measure the voltage with an alternative test. The Rad. Alt. Status on the computer should indicate VALID TO Using the radio altimeter self-test, confirm the following: EC With Radio Altitude source at 0 feet (on Ground), the computer indicates ______feet. UB When Radio altitude self-test (40-50’) is pressed, the computer indicates ______ feet. Yes/No -S Do these readings agree with the cockpit display? RY An alternate method can be by using a Radio Altimeter tester. Confirm the following: When the Radio altitude is at 1,000 feet, the Diagnostic Computer indicates ______ feet. When the Radio altitude is at 2,000 feet, the Diagnostic Computer indicates ______ feet. PR EL IM NA When the Radio altitude is at 0 feet, the Diagnostic Computer indicates ______ feet. Page 4-28 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE When 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. UT Verify that the “TAS” flag appears on the traffic display. Check that the configuration module and logic discretes are correct. Refer to supporting drawings and documentation if necessary to confirm the following items. GE 7. IT Rad. Altitude Source #1 Pass/Fail ______. HO Reset the circuit breaker. Verify that the “TAS” flag clears. CH AN 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 and observe the following on the Diagnostic Computer. EC Pass/Fail ______. TO Disable the WOW logic and check that the air/ground (J10-4) mode changes from “ON-GROUND” (GND) to “AIRBORNE” (OPEN). UB Disable the landing gear logic and check that the gear position (J10-3) changes from “EXTENDED (GND) to “RETRACTED (OPEN). Pass/Fail ______. RY -S If applicable, confirm that ADVISORY INHIBIT (J10-22) changes from “INHIBITED” (GND) to NOT-INHIBITED (OPEN). when testing the GPWS. PR EL IM NA 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 _____ _____ _____ _____. Rev 0, October/2000 10609I00.ZIPCDL Page 4-29 B KMH 880/KTA 870 NO TI CE The HEX value of the bottom directional antenna elements should indicate 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 ______? 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 is correct. IT HO UT 8. CH AN GE Evaluate proper operation of the TAS system by observing traffic advisories, 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. WARNING TO PRECAUTIONS MUST BE TAKEN TO INSURE THAT THIS TEST DOES NOT INTERFERE WITH OTHER TCAS/TAS EQUIPPED AIRCRAFT. UB EC Apply static pressure to the airplane using the pitot-static tester. Increase the altitude to 20,000 feet. NOTE RY -S The TAS and Transponder controls should be in Standby until the test altitude is set. PR EL IM NA 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. Page 4-30 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. 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE Using TASDIAG, enable the “Ramp Tester Mode under the “File” drop down menu. NOTE HO UT Once “Ramp Tester Mode” is entered, power must be cycled on the KMH/KTA before any flight Set up the TCAS Ramp Test Set. GE IT 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. CH AN Initiate the intruder test on the TCAS Ramp Tester. TO Verify that the intruder symbol corresponds to the scenario in bearing, distance and relative altitude. Confirm that the audio announcement agrees with the scenario. UB EC 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. -S “TRAFFIC, TRAFFIC” voice announcement should occur around 3.75 NM. Taffic Announcement ______. RY Traffic Display ______, PR EL IM NA 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. 9. Traffic Display ______. 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. Rev 0, October/2000 10609I00.ZIPCDL Page 4-31 B KMH 880/KTA 870 NO TI CE Another test to check the Advisory Inhibit Inputs can be performed with the Diagnostic Computer. Initiate the TAS self-test. UT As soon as the “TAS SYSTEM TEST OK” message begins, press the GPWS Test switch or simulate a GPWS advisory. TAS audio is interrupted. HO Pass/Fail ______. IT Initiate the TAS self-test. GE 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. CH AN Pass/Fail ______. 10. TAS Bearing Accuracy is required for STC Approval. TO Evaluate the performance of the directional antenna for 360° coverage at 30° intervals. EC NOTE PR EL IM NA RY -S UB Whenever 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 directional 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 bottom antenna, the test antenna should not be within line-of sight of the top directional 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. Page 4-32 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 elevated slightly above the height of the top directional antenna. 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE When 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. UT Position the aircraft outside on a heading of north away from hangers and other aircraft. HO Static pressure to the aircraft using the static tester is not required unless local conditions make it necessary. GE IT 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” mode Set up the TCAS Ramp Tester on headings listed in the following Figure. CH AN 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. PR EL IM NA RY -S UB EC TO Whenever testing the bottom directional antenna, set the landing gear logic to “RETRACTED” (GEAR UP). Repeat the above steps for the bottom antenna. Rev 0, October/2000 10609I00.ZIPCDL Page 4-33 B -S UB EC TO CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 NA RY Figure 4-1 TAS Bearing Measurements NOTE PR EL IM Bearing Error equals the heading to TCAS Ramp Tester less the relative bearing of intruder. Relative bearing to the intruder should be a positive number measured clockwise from north on the traffic display unit. Page 4-34 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE NOTE The largest acceptable TAS bearing error is +/- 30° except between 135° and 225° (aft of the wings) where the error may be 45°. UT 11. Perform the Power and Frequency tests shown in the TAS Operator’s Guide. IT HO 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 ______. GE 13. Determine that the system suppression is active. PR EL IM NA RY -S UB EC TO CH AN 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)”. Rev 0, October/2000 10609I00.ZIPCDL Page 4-35 B CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA RY -S UB EC TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL Page 4-36 B KMH 880/KTA 870 NO TI CE SECTION V CERTIFICATION INTRODUCTION ................................................................................. 5-1 5.1 5.1.1 5.1.2 5.1.3 5.1.4 5.1.5 5.1.6 5.1.7 5.1.8 5.1.9 CERTIFICATION PROCEDURE ......................................................... Equipment Compatibility ...................................................................... Equipment Location ............................................................................. Federal Communication Commission Rules ....................................... TSO Category ..................................................................................... FTZ Requirement ................................................................................ FAA Requirements .............................................................................. FAA Form 337 ..................................................................................... Flight Manual Revision ........................................................................ Pilot Briefing ........................................................................................ 5-1 5-1 5-1 5-2 5-2 5-2 5-2 5-3 5-3 5-3 PR EL IM NA RY -S UB EC TO CH AN GE IT HO UT 5.0 Rev 0, October/2000 10609I00.ZIPCDL TOC 5-i B GE IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA RY -S UB EC TO CH AN THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL TOC 5-ii B KMH 880/KTA 870 5.0 NO TI CE SECTION V CERTIFICATION INTRODUCTION CERTIFICATION PROCEDURE Equipment Compatibility Careful 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 Honeywell International Inc. Product Support at (800) 257-0726, for information regarding the compatibility of equipment not listed in Section III. Normal business hours are 8:00 AM to 5:00 PM Central Time, Monday through Friday. CH AN GE IT 5.1.1 HO 5.1 UT This section outlines the procedures required to obtain IFR certification for the KMH 880/ KTA 870 System. Recommended flight test procedures are also included. TO 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 performance of the transponder beyond its specified limits. Equipment Location RY 5.1.2 -S UB EC 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. PR EL IM NA The 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. Rev 0, October/2000 10609I00.ZIPCDL Page 5-1 B Federal Communication Commission Rules NO TI CE 5.1.3 KMH 880/KTA 870 The equipment will comply with all applicable rules of the Federal Communication Commission. TSO Category UT 5.1.4 FTZ Requirement CH AN 5.1.5 GE IT HO All aircraft, which are required by Federal Aviation Regulations to have a Terrain 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. The KMH 880/KTA 870 system is compliant to FTZ document 17 TR 2010. FAA Requirements TO 5.1.6 -S UB EC The 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 Certificate (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. FAA Form 337 PR EL 5.1.7 IM NA RY 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. Page 5-2 FAA Form 337 (if applicable) must be completed and submitted to the FAA. A sample checklist is provided in the Certification Appendix of this manual. 10609I00.ZIPCDL Rev 0, October/2000 B Flight Manual Revision NO TI CE 5.1.8 KMH 880/KTA 870 Pilot Briefing The 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. PR EL IM NA RY -S UB EC TO CH AN GE IT 5.1.9 HO UT A Flight Manual Supplement is usually required for approval. A sample supplement 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. Rev 0, October/2000 10609I00.ZIPCDL Page 5-3 B IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA RY -S UB EC TO CH AN GE THIS PAGE IS RESERVED Page 5-4 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE SECTION VI OPERATION INTRODUCTION..................................................................................... 6-1 PR EL IM NA RY -S UB EC TO CH AN GE IT HO UT 6.0 Rev 0, October/2000 10609I00.ZIPCDL TOC 6-i B CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA RY -S UB EC TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL TOC 6-ii B KMH 880/KTA 870 NO TI CE SECTION VI OPERATION 6.0 INTRODUCTION PR EL IM NA RY -S UB EC TO CH AN GE IT HO UT Refer 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 006-182650000, for complete operating instructions. Rev 0, October/2000 10609I00.ZIPCDL Page 6-1 B CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA RY -S UB EC TO THIS PAGE IS RESERVED Page 6-2 10609I00.ZIPCDL Rev 0, October/2000 B GE IT HO UT NO TI CE KMH 880/KTA 870 CH AN APPENDIX A PR EL IM NA RY -S UB EC TO Antenna Surveillance Range Rev 0, October/2000 10609I00.ZIPCDL Page A-1 B PR EL IM NA RY -S UB EC TO CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 Page A-2 10609I00.ZIPCDL Rev 0, October/2000 B CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA RY -S UB EC TO THIS PAGE IS RESERVED Rev 0, October/2000 10609I00.ZIPCDL Page A-3 B CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 TO APPENDIX B PR EL IM NA RY -S UB EC STC Appendix Rev 0, October/2000 10609I00.ZIPCDL Page STC-1 B GE IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA RY -S UB EC TO CH AN Information to be added, if required. Page STC-2 10609I00.ZIPCDL Rev 0, October/2000 B CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 APPENDIX C TO CERTIFICATION APPENDIX PR EL IM NA RY -S UB EC SAMPLE CERTIFICATION CHECKLIST Rev 0, October/2000 10609I00.ZIPCDL Page CERT-1 B TO CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA RY -S UB EC THIS PAGE IS RESERVED Page CERT-2 10609I00.ZIPCDL Rev 0, October/2000 B SAMPLE CERTIFICATION CHECKLIST NO TI CE KMH 880/KTA 870 _______________________________ AIRCRAFT MODEL: _______________________________ AIRCRAFT SERIAL NUMBER: _______________________________ AIRCRAFT REGISTRATION NUMBER: _______________________________ DATE WORK COMPLETED: _______________________________ IT HO UT AIRCRAFT MAKE: CH AN GE 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. EC TO 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 objectionable electromagnetic interference. Proper operation and accuracy were verified, and the unit functions properly and safely in accordance with the manufacturer’s specifications. UB 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. PR EL IM NA RY -S 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. Rev 0, October/2000 10609I00.ZIPCDL Page CERT-3 B TO CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA RY -S UB EC THIS PAGE IS RESERVED Page CERT-4 10609I00.ZIPCDL Rev 0, October/2000 B CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 APPENDIX D PR EL IM NA RY -S UB EC TO DIAGNOSTIC APPENDIX Rev 0, October/2000 10609I00.ZIPCDL D-1 B CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA RY -S UB EC TO THIS PAGE IS RESERVED D-2 10609I00.ZIPCDL Rev 0, October/2000 B KMH 880/KTA 870 TASDIAG-TAS Processor Field Diagnotic Program User Instructions NO TI CE DIAGNOSTIC APPENDICES HO UT WARNING: DO NOT USE THE “TASDIAG PROCESSOR FIELD DIAGNOSTIC PROGRAM” WHILE AIRBORNE. THE PROGRAM IS USED ONLY WHILE THE AIRCRAFT IS ON THE GROUND. THE SYSTEM IS DEGRADED TO PERFORM MAINTENANCE FUNCTIONS AND IS NOT AIRWORTHY WHILE RUNNING THE DIAGNOSTIC SOFTWARE. IT NOTE PR EL IM NA RY -S UB EC TO CH AN GE The diagnostic tests are performed with KMH 880/KTA 870 installed in the aircraft. Rev 0, October/2000 10609I00.ZIPCDL D-3 B IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA RY -S UB EC TO CH AN GE THIS PAGE IS RESERVED D-4 10609I00.ZIPCDL Rev 0, October/2000 B EL IM NA RY -S UB EC TO CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 PR ____________________________________________________________________ Honeywell International Inc. TAS Diag for Windows User Manual D-5 10609I00.ZIPCDL P/N 700-01055-0000 RevisionPage 1 of 18 Rev 0, October/2000 B CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 IM NA RY -S UB EC TO THIS PAGE IS RESERVED EL ____________________________________________________________________ PR Honeywell International Inc. TAS Diag for Windows User Manual D-6 10609I00.ZIPCDL P/N 700-01055-0000 RevisionPage 2 of 18 Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE Table of Contents 1. Introduction.........................................................................................................4 2. Computer Requirements ....................................................................................4 UT 3. Installing the TAS Diag Program.........................................................................4 HO 4. Starting TAS Diag ...............................................................................................5 4.1 TAS Diag. Demonstration Mode ................................................................6 IT 5. Inspecting Current Processor I/O Data...............................................................6 5.1 Snapshot View...........................................................................................6 5.2 Continous View .........................................................................................7 GE 6. Inspecting TAS Unit’s Internal Diagnostic and Log Data....................................7 TO CH AN 7. Configuration Module Options ...........................................................................7 7.1 View Strap Data.........................................................................................7 7.2 Modify Strap Data......................................................................................8 7.3 Save to Text File ........................................................................................9 7.4 Save to Binary File ....................................................................................9 7.5 Copy from Binary File ................................................................................9 7.6 Initialize Config Module .............................................................................10 UB EC 8. Intruder Data ......................................................................................................10 8.1 Overwrite View ..........................................................................................12 8.2 Capture View .............................................................................................12 9. Viewing Cable Calibration Data ..........................................................................12 -S 10. Viewing Current System Status..........................................................................13 RY 11. TAS S/W Info ......................................................................................................14 NA 12 Ramp Tester Mode .............................................................................................14 IM 13 Suggestions and Hints........................................................................................14 13.1 TAS Diag Doesn’t Communicate with TAS Unit .......................................14 EL ____________________________________________________________________ PR Honeywell International Inc. TAS Diag for Windows User Manual D-7 10609I00.ZIPCDL P/N 700-01055-0000 RevisionPage 3 of 18 Rev 0, October/2000 B NO TI CE Introduction The 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). IT HO UT GE 1. KMH 880/KTA 870 Main Diagnostic Window IO Continuous Window Intruder Data Window System Status Window TO • • • • CH AN TAS Diag for Windows has four different diagnostic windows: EC All data may be written to a user-specified file by clicking Save from the File menu. The active (selected) window will be saved. UB 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. -S 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. RY The following Part Numbers identify the TAS Diag program and documentation: EL IM NA 700-01055-0000 User Manual (this documentation) 731-30007-0000 CD-ROM containing TAS Diag for Windows and User Manual PR ____________________________________________________________________ Honeywell International Inc. TAS Diag for Windows User Manual Rev 0, October/2000 10609I00.ZIPCDL P/N 700-01055-0000 RevisionPage 4 of 18 D-8 B KMH 880/KTA 870 Computer Requirements The 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 Program • • UT HO IT GE 4. 5. Insert the TAS Diag CD into your CD-ROM drive. Select the “Start” button then “Run”. 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:\setup Click the OK button. Follow the instructions that appear on the screen. If Setup prompts you to replace some of the system files with newer versions: Select OK, then Yes when prompted to restart Windows. After Windows restarts, repeat steps 1 through 5. CH AN 1. 2. 3. NO TI CE 2. A Program Group called “TAS Diag” should have been created. Starting TAS Diag TO 4. UB EC The TAS Diag program may be started at any time. If the TAS unit is currently powered on, TAS Diag will automatically establish communications. If the TAS unit is not currently powered on, TAS Diag will continuously attempt to establish communications until communication is established or the Cancel button is pressed. Once communications are established and the TAS unit has completed initialization, TAS Diag will accept user input. -S NOTE IM NA RY If 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 connected and check TAS Diag COM port properties EL The TAS Diag program is started by selecting the “TAS Diag for Windows” icon in the “Start-Programs-TAS Diag’ group. ____________________________________________________________________ PR Honeywell International Inc. TAS Diag for Windows User Manual D-9 10609I00.ZIPCDL P/N 700-01055-0000 RevisionPage 5 of 18 Rev 0, October/2000 B KMH 880/KTA 870 -S UB EC TO CH AN GE IT HO UT NO TI CE Once communications are established and the TAS unit has completed initialization, theTAS Diag main screen appears (see Figure 1). The main window consists of a menu bar and button bar at the top and TAS Processor specific information at the bottom of the window. The processor specific information consists of the TAS Processor serial number, software version, hardware version (if available), and the Engineering software version. Figure 1 Main Window RY The menu and button bars contain the available options for the TAS Diag program. NA WARNING EL IM TAS Diag is not intended for use during flight. PR ____________________________________________________________________ Honeywell International Inc. TAS Diag for Windows User Manual Rev 0, October/2000 10609I00.ZIPCDL P/N 700-01055-0000 RevisionPage 6 of 18 D-10 B KMH 880/KTA 870 NO TI CE 4.1 TAS Diag Demonstration Mode The TAS Diag program contains a demonstration mode (in the file menu) which is useful for familiarizing the user with available options. The demonstration mode does not require an RS-232 connection to a TAS unit. Any option may be selected, and a simulation TAS unit response will occur. UT Inspecting Current Processor I/O Data HO 5. -S UB EC TO CH AN GE IT There are two options for inspecting the TAS unit’s I/O data: single snapshot or continuous ( see Figure 2). NA RY Figure 2 I/O Data View Continuous Window IM 5.1 Snapshot View EL On the I/O Data menu, click Snapshot View to request a snapshot ( one time) of the I/O Data. The TAS unit sends the data to the “Main Diagnotic Window”. ____________________________________________________________________ PR Honeywell International Inc. TAS Diag for Windows User Manual D-11 10609I00.ZIPCDL P/N 700-01055-0000 RevisionPage 7 of 18 Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE 5.2 Continuous View Inspecting TAS Unit’s Internal Diagnostic and Log Data HO 6. UT On the I/O Data Menu, click Continuous View to request continuous updates of the I/O data. Continuous mode is the single snapshot repeated every one to two seconds. The TAS unit sends the data to the “I/O Continuous Window”. A slight screen flicker will be noticeable as each new screen of data is written. The red Stop button on the button bar will be enabled as long as communications are on going and the window is being updated. To stop the update, click the Stop button. IM NA RY -S UB EC TO CH AN GE IT On the Diag Log Menu, click View Log to request the TAS unit’s Internal Diagnotic and Log Data. The TAS unit sends the data to the “Main Diagnostic Window” ( see Figure 3). Figure 3 Diagnostic and Log Data Window EL ____________________________________________________________________ PR Honeywell International Inc. TAS Diag for Windows User Manual Rev 0, October/2000 10609I00.ZIPCDL P/N 700-01055-0000 RevisionPage 8 of 18 D-12 B KMH 880/KTA 870 NO TI CE NOTE Failures for the current power cycle are not in the Diagnostic and Log Data, since the Log is written at the end of each power cycle. Configuration Module Options UT 7. IT HO The user will be offered options to view the strap data, modify the strap data, save to a text file, save to a binary file, copy from a binary file, and initialize the configuration module. GE 7.1 View Strap Data IM NA RY -S UB EC TO CH AN This option allows the user to view the current strap settings in an easy to read layout. The TAS unit sends the data to the “Main Diagnostic Window” ( see Figure 4). Figure 4 View Strap Data Window EL ____________________________________________________________________ PR Honeywell International Inc. TAS Diag for Windows User Manual D-13 10609I00.ZIPCDL P/N 700-01055-0000 RevisionPage 9 of 18 Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE 7.2 Modify Strap Data UT The strap data is read from the TAS unit and displayed in a dialog box ( see Figure 5). The dialog box has two pages, Strap Page 1 and Strap Page 2. Click on the top of each page to view/modify the different straps. The user may modify any of the straps by selecting the desired configuration. The selections are made using list boxes and radio buttons. Click the down arrow on the list boxes and click the desired configuration. For radio buttons, click the desired configuration button. IT HO Once the user is satisfied with the strapping, click the OK button and the user will be prompted as to whether or not to write the data to the configuration module. Click the cancel button to exit without saving changes. EL IM NA RY -S UB EC TO CH AN GE If the user opts to write the data to the configuration module, a message window will appear informing the user that the data is being written, the TAS unit is resetting, and the user should wait until the initialization is complete. When the TAS unit is initialized, a message will be displayed in the window. At this point the user may click the OK button to continue. Figure 5 Modify Straps Window PR ____________________________________________________________________ Honeywell International Inc. TAS Diag for Windows User Manual Rev 0, October/2000 10609I00.ZIPCDL P/N 700-01055-0000 RevisionPage 10 of 18 D-14 B KMH 880/KTA 870 NO TI CE 7.3 Save to Text File This option creates a specific file containing the configuation module’s strap and bearing correction data. The file will have a header containing the TAS unit’s serial number, the software version, the current PC date, and the current PC time. The file will be an ASCII text file. HO UT 7.4 Save to Binary File IT This option allows the user to save configuration module set-ups and recall them at a later time, if needed ( see section ). The user will be prompted for a brief description to be attached to the binary file. File names of the format: GE TASCFG.xxx, CH AN where xxx is from 000 to 999 are created in the current PC directory. 7.5 Copy from Binary File EC TO This option allows the user to program the configuration module with data previously stored in a binary file ( see section ). When this option is selected, a window allowing access to all binary file names in the current PC directory is displated ( see Figure 6 ). When a file is clicked, the description entered when it was saved is displayed in the File Description Field. When a file is selected ( by clicking the open button ), the user is prompted for the data to be written to the configuration module. EL IM NA RY -S UB If the user opts to write the data to the configuration module, a message window will appear informing the user that the data is being written, the TAS unit is resetting, and the user should wait until the initialization is complete. When the TAS unit is initialized, a message will be displayed in the window for the user. At this point the user may click the OK button to continue. PR ____________________________________________________________________ Honeywell International Inc. TAS Diag for Windows User Manual D-15 10609I00.ZIPCDL P/N 700-01055-0000 RevisionPage 11 of 18 Rev 0, October/2000 B EC TO CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 UB Figure 6 Copy Binary File Window 7.6 Initialize Config Module RY -S This option sets the configuration module’s strap data to default values. The user must view both Strap Pages ( see Modify Strap Data ) to verify/modify the configuration. The user may click the Cancel button at any time to end the initialization process without actually writing to the configuration module. EL IM NA When the Strap configuration is complete, click the OK button to save it to the configuration module. PR ____________________________________________________________________ Honeywell International Inc. TAS Diag for Windows User Manual Rev 0, October/2000 10609I00.ZIPCDL P/N 700-01055-0000 RevisionPage 12 of 18 D-16 B Intruder Data NO TI CE 8. KMH 880/KTA 870 TO CH AN GE IT HO UT There are two options for viewing tracked intruder data ( currently under TAS surveillance ). Overwrite View and Capture View ( see Figure 7). EC Figure 7 Intruder Data Window UB The following information is presented to the user: This is the number of interrogation update periods the TAS unit has been through since power up. survno-- This is the unique internal surveillance number assigned to an intruder. This number remains assigned to an intruder the entire time that it is under surveillance. RY The bearing ( in degrees ) of the intruder relative to own aircraft. 0 degrees is at the 12 o’clock position, 90 degrees is at the 3 o’clock position, 180 ( or - 180 ) degrees is at the 6 o’clock position, and - 90 is at the 9 o’clock position. A series of -----’s indicates that a bearing could not be determined for the intruder. ____________________________________________________________________ PR EL IM NA bear-- -S TISI-- Honeywell International Inc. TAS Diag for Windows User Manual D-17 10609I00.ZIPCDL P/N 700-01055-0000 RevisionPage 13 of 18 Rev 0, October/2000 B KMH 880/KTA 870 The slant range from own aircraft to the intruder in nautical miles. alt-- The intruder’s altitude in feet (MSL). A series of -----’s indicates that the intruder is non-altitude reporting (NAR). Ant-- This is an indication of the antenna on which the intruder is being surveilled. A ‘T’ indicates the top antenna, while a ‘B’ indicates the bottom antenna. power-- The measure power of the last received from the intruder. A power of 255 indicates no reply was received from the intruder. A power of zero indicates that a power and/or bearing could not be computed for the intruder during the current TISI. IT HO UT NO TI CE range-- GE 8.1 Overwrite View CH AN On the Intruder Data Menu, click Overwrite View. The user is prompted for the maximum range in nautical miles-- this allows the user to limit the range at which intruders are displayed. TO When this option is selected, the intruder information is erased before each update is sent to the screen. It is updated at approximately one TISI per second. To stop the update, click the Stop button on the button bar. EC 8.2 Capture View EL IM NA RY -S UB On the Intruder Data Menu, click Capture View. This option allows the user to capture specified number of TISI’s of data. The number of TISIs to be captured is entered, then the maximum range is requested (see Overwrite). When the number of TISIs have been captured, the updates are stopped. If the stop button on the button bar is clicked, the updates will also stop before completion of the specified number of TISIs. PR ____________________________________________________________________ Honeywell International Inc. TAS Diag for Windows User Manual Rev 0, October/2000 10609I00.ZIPCDL P/N 700-01055-0000 RevisionPage 14 of 18 D-18 B Viewing Cable Calibration Data NO TI CE 9. KMH 880/KTA 870 Figure 8 Cable Calibration Data Window IM NA RY -S UB EC TO CH AN GE IT HO UT Cable calibrations are performed periodically by the TAS unit so that bearings may be computed as accurately as possible. This option allows the user to view the results of the most recent cable calibration and causes the cable calibrations to be performed at an accelerated rate. Cable calibrations are normally spaced at two minute intervals, but this option causes the spacing between the end of one cable calibration and the start of the next to be 10 seconds. An internal TAS unit variable that displays messages on retries and/or errors is enabled. A cable calibration sequence for a dual directional system requires about 24 seconds to complete, so a new cable calibration summary will be displayed every 34 seconds. To view the cable calibration data, View Data on the Cable Cal Menu (see Figure 8). EL ____________________________________________________________________ PR Honeywell International Inc. TAS Diag for Windows User Manual D-19 10609I00.ZIPCDL P/N 700-01055-0000 RevisionPage 15 of 18 Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE NOTE Viewing Current System Status HO 10 UT The second cable calibration summary could take as long as 2 minutes and 34 seconds before being displayed, due to the nature of the multi-tasking environment of the TAS unit and the method by which tasks are delayed. GE IT This option allows the user to view the current TAS unit system status without having to try to read the LEDs located on the side or front of the TAS unit (see Figure 9). This data may be viewed two different ways; Overwrite or Continuously. The status is updated every second or two. The system’s status is indicated along with the state of the LED indicator. When a fault occurs, a brief description is added to the LED fault information. To stop the update, click the Stop button on the button bar. EL IM NA RY -S UB EC TO CH AN In the Overwrite mode, the data is erased before each update. For the overwrite mode, click Overwrite View on the Sys Status Menu. For continuously, click Continuous View on the Sys Status Menu. Figure 9 System Status Window PR ____________________________________________________________________ Honeywell International Inc. TAS Diag for Windows User Manual Rev 0, October/2000 10609I00.ZIPCDL P/N 700-01055-0000 RevisionPage 16 of 18 D-20 B KMH 880/KTA 870 NO TI CE 11. TAS S/W Info EC TO CH AN GE IT HO UT This option allows the user to retrieve TAS unit specific software (see Figure 10). -S 12. Ramp Tester Mode UB Figure 10 TAS S/W Window IM NA RY This option turns on the P2 pulse of TAS ATCRBS interrogations so a IFR 401B ramp tester can be used to reply to the TAS unit. To turn this option on or off, click Ramp Tester Mode on the File Menu. When the option is on, a check mark appears to the left of Ramp Tester Mode on the File Menu. EL ____________________________________________________________________ PR Honeywell International Inc. TAS Diag for Windows User Manual D-21 10609I00.ZIPCDL P/N 700-01055-0000 RevisionPage 17 of 18 Rev 0, October/2000 B KMH 880/KTA 870 NO TI CE 13. Suggestions and Hints Below is a list of some of the problems that have been encountered to date along with possible solutions and/or work-arounds. UT 13.1 TAS Diag doesn’t Communicate with the TAS unit. IT HO If TAS Diag can not establish communications with the TAS unit, the first thing to check is the Comm port to which the RS-232 is connected. The RS-232 setting on the File-Properties dialog box should not be changed. However, the Comm (serial) port needs to be selected for the port connected to the TAS unit. Usually ‘Comm 1’ is the correct port. If you have several ports you may have to experiment by changing the Comm Port setting. EL IM NA RY -S UB EC TO CH AN GE Some Laptops use Comm 1 for Modems and Infrared Sensors. If this is the case and you have only one serial port, you will need to disable the device using the Comm Port and enable it for external communications. This is usually done in the “My Computer” properties or in the BIOS setting. You should call your computer manufacturer if you can not free up the port. PR ____________________________________________________________________ Honeywell International Inc. TAS Diag for Windows User Manual Rev 0, October/2000 10609I00.ZIPCDL P/N 700-01055-0000 RevisionPage 18 of 18 D-22 B CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 TO TSO APPENDIX PR EL IM NA RY -S UB EC ENVIRONMENTAL QUALIFICATION FORM Rev 0, October/2000 10609I00.ZIPCDL TSO-1 B CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA RY -S UB EC TO THIS PAGE IS RESERVED TSO-2 10609I00.ZIPCDL Rev 0, October/2000 B RTCA DO-160D ENVIRONMENTAL QUALIFICATION FORM NO TI CE KMH 880/KTA 870 NOMENCLATURE: KTA 810 Remote Mount Traffic Advisory Unit KMH 820 Remote Mount Multi-Hazard Awareness Unit CM 805 TAS / GPWS Configuration Module PART NUMBER: 066-01152-0101 066-01175-0101 066-01175-2101 071-00112-0100 050-03361-0000 047-12545-0003 TSO NUMBER: C147 (Class A), C151a (Class B) MANUFACTURER’S SPECIFICATION: MPS 004-02050-4000 MANUFACTURER: Honeywell International Inc. ADDRESS: One Technology Center CH AN GE IT HO UT KTA 810 KMH 820 w/o GPS KMH 820 w/ GPS CM 805 Installation Kit Mounting Tray TO 23500 W. 105th Street Olathe, KS 66061 DO-160D SECTION Temperature and Altitude Low Temperature NA RY -S UB High Temperature In-Flight Loss of Cooling Altitude Decompression Overpressure Temperature Variation Humidity Shock (operational & crash safety) Vibration EC CONDITIONS PR EL IM Explosion Waterproofness Fluids Susceptibility Sand and Dust Fungus Salt Spray Magnetic Effect Rev 0, October/2000 USA DESCRIPTION OF CONDUCTED TESTS 4.0 4.5.1 Category A2D2 (Low Temp. -55°C) 4.5.2 &4.5.3 4.5.4 4.6.1 4.6.2 4.6.3 5.0 6.0 7.0 8.0 (High Temp. +70°C) Category X (Not Tested) (Alt. tested to 51,500 feet) (Decomp., 8K to 51.5K < 15 sec.) (Overpressure, 170 kPa) Category B Category A Category B Category S (curves B & M) (See Notes 1, 2, &3) Category X, (Not Tested) Category X (Not Tested) Category X (Not Tested) Category X (Not Tested) Category X (Not Tested) Category X (Not Tested) Class A 9.0 10.0 11.0 12.0 13.0 14.0 15.0 10609I00.ZIPCDL TSO-3 B KMH 880/KTA 870 Category BZ Category A Category BZ Category A Category RRR (See Note 4) Category L Category A3E3 (See note 5) Category 1B Category X (Not Tested) Category A UT NO TI CE 16.0 17.0 18.0 19.0 20.0 21.0 22.0 23.0 24.0 25.0 HO Power Input Voltage Spike Conducted Audio Frequency Conducted Susceptibility Induced Signal Susceptibility Radio Frequency Susceptibility Radio Frequency Emission Lightning Induced Transient Susceptibility Lightning Direct Effects Icing ESD IT Notes: Longitudinal (Front to Back) TBD TBD Lateral (Side to Side) TBD EC TO CH AN Vertical (Top to Bottom) GE 1. Vibration Critical Frequencies – The following critical frequencies are mechanical resonances of the unit under test that have peak acceleration amplitudes greater than twice the input acceleration amplitude. Observed changes in performance of the unit under test are to be determined (TBD). UB 2. Observed changes in the above resonant frequencies during the test are to be determined. 3. The unit shall comply with DO-160C, vibration category N and Y for helicopters. -S 4. RF susceptibility degradation information placed here if applicable. EL IM NA RY 5. The unit shall comply with A3E3 on all signal lines and A4E4 on the power leads. P/N 004-02050-4800 Revision - PR Honeywell International Inc. Environmental Qualification Form TSO-4 10609I00.ZIPCDL Rev 0, October/2000 B REVISION HISTORY Revision PRN/CO # PRN ______ Date Original Issue TBD EL IM NA RY -S UB EC TO CH AN GE IT HO UT Description of Change NO TI CE KMH 880/KTA 870 P/N 004-02050-4800 Revision - PR Honeywell International Inc. Environmental Qualification Form Rev 0, October/2000 10609I00.ZIPCDL TSO-5 B CH AN GE IT HO UT NO TI CE KMH 880/KTA 870 PR EL IM NA RY -S UB EC TO THIS PAGE IS RESERVED TSO-6 10609I00.ZIPCDL Rev 0, October/2000
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