Honeywell Mk Vi Users Manual INSTALLATION DESIGN GUIDE 020
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Airlines & Avionics Products Honeywell Inc. 15001 N.E. 36th Street Redmond, WA 98052 MK VI MK VIII Enhanced Ground Proximity Warning System (Class A TAWS) Installation Design Guide Hardware/Software Part Numbers: 965-1180-020 965-1190-020 965-1210-020 965-1220-020 Release Date: July 14, 2003 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 1 OF 326 Honeywell MK VI MK VIII EGPWS Installation Design Guide Copyright 2003 Honeywell, Inc. All rights reserved. This document and all information and expression contained herein are the property of Honeywell International Inc., and is provided to the recipient in confidence on a “need to know” basis. Your use of this document is strictly limited to a legitimate business purpose requiring the information contained therein. Your use of this document constitutes acceptance of these terms. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 2 Honeywell MK VI MK VIII EGPWS Installation Design Guide Typed names constitute approval signatures. Actual signatures are on file at Honeywell in Redmond, WA. DRAWN Larry Matter 14-JULY-03 Larry Matter 14-JULY-03 Jim Mulkins 14-JULY-03 CHECK ENGR MFG QA APVD APVD REVISION STATUS OF SHEETS INDEX ADDED SHEETS ADDED SHEETS SHEET REV SHEET REV SHEET REV SHEET REV SHEET REV SHEET REV NUMBER LTR NUMBER LTR NUMBER LTR NUMBER LTR NUMBER LTR NUMBER LTR REVISIONS SH REV DESCRIPTION DATE APPROVED Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 3 Honeywell MK VI MK VIII EGPWS Installation Design Guide THIS PAGE INTENTIONALLY LEFT BLANK Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 4 Honeywell MK VI MK VIII EGPWS Installation Design Guide TABLE OF CONTENTS SECTION I – GENERAL INFORMATION ..........................................................................................................13 1.1 INTRODUCTION.........................................................................................................................................................13 1.2 APPLICABILITY.........................................................................................................................................................13 1.3 HOW TO USE THIS DOCUMENT ................................................................................................................................13 1.4 REFERENCE DOCUMENTS .........................................................................................................................................14 1.5 DESCRIPTION OF EQUIPMENT ...................................................................................................................................15 1.5.1 MK VI EGPWS Computer ....................................................................................................................................15 1.5.2 MK VIII EGPWS Computer..................................................................................................................................15 1.5.3 MK VI/MK VIII EGPWS Configuration Module ..................................................................................................15 1.5.4 GPS Antenna and Cabling....................................................................................................................................16 1.5.5 OAT Sensor ..........................................................................................................................................................17 1.5.6 Smart Cable (PCMCIA Interface) ........................................................................................................................17 1.6 TECHNICAL CHARACTERISTICS ................................................................................................................................18 1.7 UNITS SUPPLIED .......................................................................................................................................................18 1.7.1 MK VI EGPWS .....................................................................................................................................................18 1.7.2 MK VIII EGPWS.................................................................................................................................................19 1.7.3 Configuration Module ........................................................................................................................................19 1.7.4 Smart Cable (PCMCIA Interface) ......................................................................................................................19 1.8 INSTALLATION KITS AND ACCESSORIES .................................................................................................................19 1.8.1 MK VI/MK VIII EGPWS Installation Kits ..........................................................................................................19 1.8.2 RS-232 Cable......................................................................................................................................................20 1.8.3 Smart Cable ........................................................................................................................................................20 1.8.4 Terrain Database Cards .....................................................................................................................................20 1.8.5 Flight History Card ............................................................................................................................................20 1.9 ACCESSORIES NOT SUPPLIED ..................................................................................................................................20 1.9.1 ARINC 453 Terrain Display wiring....................................................................................................................20 1.9.2 GPS Antenna & Cable ........................................................................................................................................21 1.9.3 Circuit Breaker ...................................................................................................................................................21 1.9.4 Annunciators & Switch/Annunciators ................................................................................................................22 1.9.5 Cockpit Speakers ................................................................................................................................................23 1.9.6 Temperature Probes ...........................................................................................................................................23 1.10 TOOLS REQUIRED .................................................................................................................................................24 1.10.1 Crimping Tool - P1, P2, P3 .............................................................................................................................24 1.10.2 Contact Positioner - P1, P2, P3 ......................................................................................................................24 1.10.3 Insertion/Removal Tool - P1, P2, P3 ...............................................................................................................24 1.10.4 Spare Connectors and Contacts - P1, P2, P3 ..................................................................................................25 1.11 LICENSE REQUIREMENTS ......................................................................................................................................25 SECTION II - INSTALLATION .............................................................................................................................29 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 5 Honeywell MK VI MK VIII EGPWS Installation Design Guide 2.1 INTRODUCTION .......................................................................................................................................................29 2.2 UNPACKING AND INSPECTING THE EQUIPMENT ......................................................................................................29 2.3 EQUIPMENT INSTALLATION ....................................................................................................................................29 2.3.1 General ...............................................................................................................................................................29 2.3.2 MK VI/MK VIII Computer Location...................................................................................................................29 2.3.3 MK VI/ MK VIII Computer Installation..............................................................................................................30 2.3.4 Configuration Module Location .........................................................................................................................31 2.3.5 Configuration Module Installation .....................................................................................................................31 2.3.6 GPS Antenna location.........................................................................................................................................40 2.3.7 GPS Antenna Installation ...................................................................................................................................40 2.3.8 OAT Sensor Location..........................................................................................................................................40 2.3.9 OAT Sensor Installation .....................................................................................................................................40 2.3.10 Cockpit Lights...................................................................................................................................................40 2.3.10.1 Description........................................................................................................................................................................ 41 2.3.10.2 Location ............................................................................................................................................................................ 42 SECTION III – SYSTEM PLANNING ...................................................................................................................51 3.1 INTRODUCTION .......................................................................................................................................................51 3.2 SYSTEM WIRING/ ELECTRICAL INTERFACES ..........................................................................................................51 3.2.1 Primary Power Input ..........................................................................................................................................51 3.2.2 Chassis Ground ..................................................................................................................................................52 3.2.3 GPS Antenna ......................................................................................................................................................52 3.2.4 Analog and Digital Inputs ..................................................................................................................................52 3.2.5 Discrete Inputs....................................................................................................................................................52 3.2.6 Serial Outputs .....................................................................................................................................................52 3.2.7 Audio Output.......................................................................................................................................................53 3.2.8 Discrete Outputs .................................................................................................................................................53 3.2.9 Configuration Module ........................................................................................................................................53 3.3 CATEGORY 1 - AIRCRAFT / MODE TYPE SELECT ...................................................................................................54 3.3.1 Aircraft / Mode Type...........................................................................................................................................54 3.3.2 Mode 1 type ........................................................................................................................................................54 3.3.3 Mode 2 type ........................................................................................................................................................54 3.3.4 Mode 3 type ........................................................................................................................................................55 3.3.5 Mode 4 type ........................................................................................................................................................55 3.3.6 Bank Angle Type.................................................................................................................................................55 3.3.7 Runway Length (MK VIII EGPWS only) ............................................................................................................56 3.3.8 Instructions .........................................................................................................................................................56 3.4 CATEGORY 2 – AIR DATA INPUT SELECT ...............................................................................................................57 3.4.1 Analog (Cat. 2 ID 0, 3, 4, 11, 12) .......................................................................................................................57 3.4.2 Digital – ARINC 429 (Cat. 2 ID 5, 1, 6, 13) .......................................................................................................59 3.4.3 Digital –ARINC 575 (Cat. 2 ID 2)......................................................................................................................60 3.4.4 Shadin 2000 (Cat. 2 ID 10).................................................................................................................................61 3.4.5 Digital – ARINC 429 Dual IOC Buses (Cat. 2. ID 255).....................................................................................62 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 6 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.4.6 Instructions .........................................................................................................................................................62 3.5 CATEGORY 3 – POSITION INPUT SELECT ................................................................................................................63 3.5.1 ARINC 743 Format.............................................................................................................................................63 3.5.2 GPS Altitude (Label 076) Reference...................................................................................................................63 3.5.3 North-South East-West Velocity labels...............................................................................................................63 3.5.4 ARINC 429 BUS (Cat. 3 ID 0,1,4,5,10-13).........................................................................................................64 3.5.5 RS-232 Transmit-Receive, 9600 baud (Cat. 3 ID 3) ...........................................................................................65 3.5.6 Dual ARINC 429 BUS (Cat. 3 ID 253 & 255)....................................................................................................66 3.5.7 Instructions .........................................................................................................................................................66 3.6 CATEGORY 4 – ALTITUDE CALLOUTS ....................................................................................................................67 3.7 CATEGORY 5 – AUDIO MENU SELECT ....................................................................................................................68 3.7.1 Audio Menu Selection .........................................................................................................................................68 3.7.2 Instructions .........................................................................................................................................................68 3.8 CATEGORY 6 – TERRAIN DISPLAY SELECT.............................................................................................................69 3.8.1 TAD & TCF Selection.........................................................................................................................................69 3.8.2 Terrain Display Configuration Group................................................................................................................70 3.8.3 Display Input Control Group..............................................................................................................................70 3.8.4 Output 429 Bus Group........................................................................................................................................71 3.8.5 Instructions .........................................................................................................................................................71 3.8.6 Sample Display Schematics ................................................................................................................................71 3.9 CATEGORY 7 – OPTIONS SELECT GROUP #1...........................................................................................................88 3.9.1 Steep Approach...................................................................................................................................................88 3.9.2 TA&D Alternate Pop-up .....................................................................................................................................88 3.9.3 Peaks Mode ........................................................................................................................................................88 3.9.4 Obstacle Awareness............................................................................................................................................88 3.9.5 Bank Angle Callout Enabling .............................................................................................................................89 3.9.6 Flap Reversal......................................................................................................................................................89 3.9.7 GPS Altitude Reference ......................................................................................................................................89 3.9.8 Instructions .........................................................................................................................................................90 3.10 CATEGORY 8 – RADIO ALTITUDE INPUT SELECT..................................................................................................91 3.10.1 Radio Altitude Input..........................................................................................................................................91 3.10.2 Decision Height Discrete Input ........................................................................................................................91 3.10.3 Digital Radio Altitude Interface (Cat. 8 ID 2) ..................................................................................................91 3.10.4 Analog Radio Altitude Interface (Cat. 8 ID 0,1,3,4).........................................................................................92 3.10.5 Digital – ARINC 429 Dual IOC Buses (Cat. 8 ID 251- 255)............................................................................92 3.10.6 Instructions .......................................................................................................................................................93 3.11 CATEGORY 9 – NAVIGATION INPUTS SELECT .......................................................................................................94 3.11.1 Navigation Inputs Select (Glideslope & Localizer Inputs) ...............................................................................94 3.11.2 Glideslope Validity ...........................................................................................................................................94 3.11.3 Localizer Validity .............................................................................................................................................94 3.11.4 ILS Tuned Discrete Input #1 (+28V) and #2 (GND) ........................................................................................94 3.11.5 Analog Glideslope Interface (Cat. 9 ID 0,1,5)..................................................................................................95 3.11.6 Digital Glideslope / Localizer / ILS Select Interface (Cat. 9 ID 2,3,4).............................................................96 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 7 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.11.7 Digital – ARINC 429 Dual IOC buses (Cat. 9 ID 250 - 255) ...........................................................................96 3.11.8 Instructions .......................................................................................................................................................97 3.12 CATEGORY 10 – ATTITUDE INPUT SELECT ...........................................................................................................98 3.12.1 Roll Angle .........................................................................................................................................................98 3.12.2 Analog Pitch & Roll Angle (Synchro) (Cat. 10 ID 0,2,4) .................................................................................98 3.12.3 Digital Pitch & Roll Angle (ARINC 429 High Speed) (Cat. 10 ID 5 & 6)........................................................99 3.12.4 Digital – ARINC 429 Dual IOC buses (Cat. 10 ID 253 & 255) .......................................................................99 3.12.5 Instructions .......................................................................................................................................................99 3.13 CATEGORY 11 – HEADING INPUT SELECT ..........................................................................................................100 3.13.1 Magnetic Heading ..........................................................................................................................................100 3.13.2 Analog Heading (Synchro) (Cat. 11 ID 0)......................................................................................................100 3.13.3 Digital – ARINC 429 AHRS Input (Cat. 11 ID 2 & 3)....................................................................................101 3.13.4 Digital – ARINC 429 Dual IOC buses (Cat. 11 ID 254 & 255) .....................................................................101 3.13.5 Instructions .....................................................................................................................................................101 3.14 CATEGORY 12 – WINDSHEAR INPUT SELECT .....................................................................................................102 3.14.1 No Windshear .................................................................................................................................................102 3.14.2 Dual ARINC 429 BUS (Cat. 14 ID 253,254,255) ...........................................................................................102 3.14.3 Instructions .....................................................................................................................................................102 3.15 CATEGORY 13 – INPUT / OUTPUT DISCRETE TYPE SELECT ................................................................................103 3.15.1 Input Discretes................................................................................................................................................103 3.15.1.1 Glideslope Inhibit Discrete ............................................................................................................................................. 103 3.15.1.2 Landing Flaps Discrete ................................................................................................................................................... 103 3.15.1.3 Audio Inhibit Discrete..................................................................................................................................................... 104 3.15.1.4 Landing Gear Discrete .................................................................................................................................................... 104 3.15.1.5 Glideslope Cancel Discrete ............................................................................................................................................. 106 3.15.1.6 Momentary Flap Override Discrete................................................................................................................................. 106 3.15.1.7 Mode 6 Low Volume Discrete........................................................................................................................................ 106 3.15.1.8 Autopilot Engaged Discrete ............................................................................................................................................ 107 3.15.1.9 Terrain Awareness and TCF Inhibit Discrete.................................................................................................................. 107 3.15.1.10 Self Test Discrete.......................................................................................................................................................... 107 3.15.1.11 Steep Approach Discrete #2.......................................................................................................................................... 108 3.15.1.12 GPWS INHIBIT Discrete (alternate action).................................................................................................................. 108 3.15.2 Output Discretes .............................................................................................................................................108 3.15.2.1 Lamp Format................................................................................................................................................................... 109 3.15.2.2 Flashing Lamps............................................................................................................................................................... 109 3.15.2.3 GPWS INOP Discrete..................................................................................................................................................... 109 3.15.2.4 TAD INOP Discrete........................................................................................................................................................ 109 3.15.2.5 GPWS Warning Discrete ................................................................................................................................................ 109 3.15.2.6 GPWS Alert Discrete...................................................................................................................................................... 110 3.15.2.7 Glideslope Cancel’d Discrete.......................................................................................................................................... 110 3.15.2.8 Flap Override Discrete .................................................................................................................................................... 110 3.15.2.9 Steep Approach Discrete................................................................................................................................................. 110 3.15.2.10 Audio On Discrete (TCAS/TAS Inhibit)....................................................................................................................... 110 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 8 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.15.2.11 Terrain Display Select #1 & #2 Discrete....................................................................................................................... 111 3.15.2.12 Terrain Pop up Discrete ................................................................................................................................................ 112 3.15.3 Instructions .....................................................................................................................................................113 3.16 CATEGORY 14 – AUDIO OUTPUT LEVEL ............................................................................................................113 3.16.1 Instructions .....................................................................................................................................................113 3.17 CATEGORY 15 - 17 – UNDEFINED INPUT SELECTS .............................................................................................114 3.17.1 Undefined Input Select....................................................................................................................................114 3.17.2 Instructions .....................................................................................................................................................114 SECTION IV – CONFIG MODULE PROGRAMMING AND REGIONAL TDB LOADING ......................117 4.1 INTRODUCTION .....................................................................................................................................................117 4.2 HARNESS CHECKOUT AND POWER CHECK ...........................................................................................................117 4.3 UNIT INSTALLATION .............................................................................................................................................117 4.4 EGPWC INITIALIZATION AND CONFIGURATION ..................................................................................................117 4.4.1 RS-232 Communication with the MK VI/VIII EGPWS .....................................................................................117 4.4.2 EGPWC Front Panel Test Connector...............................................................................................................118 4.4.3 WinVIEWS ........................................................................................................................................................119 4.4.4 WinVIEWS Operation.......................................................................................................................................119 4.5 CONFIGURATION MODULE PROGRAMMING ..........................................................................................................119 4.5.1 CUW and CMR Commands ..............................................................................................................................121 4.5.2 Configuration Module Reprogramming ...........................................................................................................122 4.6 TERRAIN DATABASE LOADING .............................................................................................................................122 4.6.1 Effectivity ..........................................................................................................................................................122 4.6.2 Description .......................................................................................................................................................123 4.6.3 Approval ...........................................................................................................................................................123 4.6.4 Material – Cost and Availability ......................................................................................................................123 4.6.5 Accomplishment Instructions............................................................................................................................123 4.6.6 Verification of the Terrain Database Version ..................................................................................................125 SECTION V – CERTIFICATION.........................................................................................................................128 5.1 INTRODUCTION .....................................................................................................................................................128 5.2 CERTIFICATION PROCEDURE ................................................................................................................................128 5.2.1 Equipment Compatibility ..................................................................................................................................128 5.2.2 Equipment Location..........................................................................................................................................128 5.2.3 FAA Requirements ............................................................................................................................................128 5.2.4 Ground Test ......................................................................................................................................................128 5.2.5 Flight Manual Revision ....................................................................................................................................128 5.2.6 Flight Test.........................................................................................................................................................128 5.2.7 Pilots Guide ......................................................................................................................................................129 5.2.8 Failure Modes, Effects, and Safety Analysis.....................................................................................................129 SECTION VI - MK VI GPWS TO MK VI/VIII EGPWS SIGNAL MAPPING ...............................................131 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 9 Honeywell MK VI MK VIII EGPWS Installation Design Guide APPENDIX A - CUSTOMER WORKSHEET .....................................................................................................137 APPENDIX B - SAMPLE WIRING DIAGRAMS ...............................................................................................141 APPENDIX C – WINVIEWS OPERATION INSTRUCTIONS.........................................................................146 APPENDIX D - VENDOR CONTACT INFORMATION...................................................................................150 APPENDIX E – INTERFACE DESCRIPTION DOCUMENT ..........................................................................153 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 10 Honeywell MK VI MK VIII EGPWS Installation Design Guide SECTION I GENERAL INFORMATION Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 11 Honeywell MK VI MK VIII EGPWS Installation Design Guide SECTION I – GENERAL INFORMATION SECTION I – GENERAL INFORMATION ..................................................................................................................... 13 1.1 INTRODUCTION.............................................................................................................................................................. 13 1.2 APPLICABILITY.............................................................................................................................................................. 13 1.3 HOW TO USE THIS DOCUMENT ..................................................................................................................................... 13 1.4 REFERENCE DOCUMENTS .............................................................................................................................................. 14 1.5 DESCRIPTION OF EQUIPMENT ........................................................................................................................................ 15 1.5.1 MK VI EGPWS Computer ..................................................................................................................................... 15 1.5.2 MK VIII EGPWS Computer................................................................................................................................... 15 1.5.3 MK VI/MK VIII EGPWS Configuration Module ................................................................................................... 15 1.5.4 GPS Antenna and Cabling..................................................................................................................................... 16 1.5.5 OAT Sensor ........................................................................................................................................................... 17 1.5.6 Smart Cable (PCMCIA Interface) ......................................................................................................................... 17 1.6 TECHNICAL CHARACTERISTICS ..................................................................................................................................... 18 1.7 UNITS SUPPLIED ............................................................................................................................................................ 18 1.7.1 MK VI EGPWS ...................................................................................................................................................... 18 1.7.2 MK VIII EGPWS ................................................................................................................................................... 19 1.7.3 Configuration Module ........................................................................................................................................... 19 1.7.4 Smart Cable (PCMCIA Interface) ......................................................................................................................... 19 1.8 INSTALLATION KITS AND ACCESSORIES ........................................................................................................................ 19 1.8.1 MK VI/MK VIII EGPWS Installation Kits ............................................................................................................. 19 1.8.2 RS-232 Cable......................................................................................................................................................... 20 1.8.3 Smart Cable........................................................................................................................................................... 20 1.8.4 Terrain Database Cards........................................................................................................................................ 20 1.8.5 Flight History Card ............................................................................................................................................... 20 1.9 ACCESSORIES NOT SUPPLIED ......................................................................................................................................... 20 1.9.1 ARINC 453 Terrain Display wiring....................................................................................................................... 20 1.9.2 GPS Antenna & Cable........................................................................................................................................... 21 1.9.3 Circuit Breaker...................................................................................................................................................... 21 1.9.4 Annunciators & Switch/Annunciators ................................................................................................................... 22 1.9.5 Cockpit Speakers ................................................................................................................................................... 23 1.9.6 Temperature Probes .............................................................................................................................................. 23 1.10 TOOLS REQUIRED ........................................................................................................................................................ 24 1.10.1 Crimping Tool - P1, P2, P3................................................................................................................................ 24 1.10.2 Contact Positioner - P1, P2, P3 ......................................................................................................................... 24 1.10.3 Insertion/Removal Tool - P1, P2, P3.................................................................................................................. 24 1.10.4 Spare Connectors and Contacts - P1, P2, P3..................................................................................................... 25 1.11 LICENSE REQUIREMENTS............................................................................................................................................. 25 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 12 Honeywell MK VI MK VIII EGPWS Installation Design Guide SECTION I – GENERAL INFORMATION 1.1 Introductio n The Honeywell MK VI/MK VIII Enhanced Ground Proximity Warning System (MK VI/MK VIII EGPWS) provides alerts and warnings to prevent controlled flight into terrain (CFIT). This Installation Design Guide must be used in conjunction with the Interface Description Document (Appendix E) for the MK VI/MK VIII Enhanced Ground Proximity Warning System (MK VI/MK VIII EGPWS) to select features and design the installation for this system. It is assumed that the user of this document is familiar with avionics installation practices and aircraft systems associated with the installation and operation of the MK VI/MK VIII EGPWS. It also assumes access to pertinent aircraft wiring diagrams, modification records and manuals. The information contained herein, together with general procedures outlined in FAA AC.43.13 must be followed carefully to assure a safe, electrically sound, certifiable and operational installation. The contents of this document are for information and reference only and must not be construed as formal FAA approved work authorization. 1.2 Applicabilit y This manual is applicable only to MK VI/MK VIII EGPWS computers with the following part numbers: MK VI 965-1180-020 965-1190-020 MK VIII 965-1210-020 965-1220-020 Part numbers 965-1190-xxx and 965-1220-xxx include an internal GPS card. 1.3 How To Us e This Document Section 1 provides a system overview. Section 2 provides mechanical installation and location information. Section 3 provides information and instructions for selecting required features of the EGPWS. Section 4 provides Configuration Module programming instructions. Section 5 provides certification requirements. Section 6 provides a pin to pin comparison of the classic MK VI GPWS to the MK VI/MK VIII EGPWS. Appendix A Customer Worksheet. Appendix B Sample Wiring Diagrams. Appendix C provides WinViews operation instructions. Appendix D provides Vendor Contact Information Appendix E Interface Description Document Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 13 Honeywell MK VI MK VIII EGPWS Installation Design Guide 1.4 Reference D ocuments Following is a list of Honeywell reference documents: 965-1180-601 Product Specification for the MK VI and MK VIII Enhanced Ground Proximity Warning System (EGPWS) 965-1180-201 965-1190-201 965-1210-201 965-1220-201 Outline, MK VI EGPWC (without GPS) Outline, MK VI EGPWC (with GPS) Outline, MK VIII EGPWC (without GPS) Outline, MK VIII EGPWC (with GPS) 060-4199-180 Line Maintenance Manual 060-4267-000 MK VIII EGPWS Terrain Database Airport Coverage List (3500’ Runways) 060-4326-000 MK VI / MK VIII EGPWS Terrain Database Airport Coverage List (2000’ Runways) 060-4199-194 MK VI / MK VIII EGPWS Generic AFM Supplement 060-4314-000 MK VI / MK VIII Enhanced GPWS Pilot’s Guide 060-4188-023 MK VIII Bizjet Flight Test Procedure 060-4188-038 Flight Test Procedure for EGPWS with Internal GPS card 060-4188-041 MK VI / MK VIII GA Fast/GA Slow General Flight Test Procedure 060-4167-158 MK VI / MK VIII Installation Ground Test Procedure 060-4199-190 Trouble Shooting Guide 060-4199-182 MK VI / MK VIII Failures Modes, Effects, and Safety Analysis 076-4610-000 MK VI / MK VIII Failure Modes, Effects, and Criticality Analysis Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 14 Honeywell MK VI MK VIII EGPWS Installation Design Guide 1.5 Description of Equipment The MK VI/MK VIII EGPWS is a rack mount ground proximity warning (GPWS) and terrain awareness and warning (Class A TAWS) computer. Some of the system features include: ♦ ♦ ♦ ♦ ♦ ♦ ♦ ♦ ♦ ♦ Basic Ground Proximity Warning Modes 1-5 Mode 6 Altitude Callouts and Bank Angle alert Terrain Clearance Floor Terrain and Obstacle Awareness alert and display Terrain map with runways >= 2000 feet in length (optionally >= 3500 feet in length on the MK VIII EGPWS) Internal GPS card (MK VI 965-1190-0XX and MK VIII 965-1220-0XX only) Front loading updateable database (requires Smart cable) External Configuration Module (with a Real Time Clock for use with Internal GPS) Internal heater blanket for operation outside of the heated area of the aircraft Fixed Gear operation 1.5.1 MK VI EGP WS Computer The MK VI EGPWS computer is available under P/N 965-1180-0XX without internal GPS and P/N 965-11900XX with internal GPS. The MK VI EGPWS computer is intended for small turboprop aircraft that provide a mixture of analog and digital interfaces. The type of supported displays is limited and does not typically include EFIS displays (Collins ProLine II and Bendix EFIS 40/50 are supported). The terrain database included with the MK VI EGPWS computer is regional having three separately defined databases for the AMERICAS (North & South America), ATLANTIC (Europe/Asia/Africa), and PACIFIC (Asia/Australia). 1.5.2 MK VIII EGP WS Computer The MK VIII EGPWS computer is available under P/N 965-1210-0XX without internal GPS and P/N 965-12200XX with internal GPS. The MK VIII EGPWS computer is intended for regional turboprop and small turbofan aircraft that provide a mixture of analog and digital interfaces. The type of supported displays is limited and includes some EFIS displays. The terrain database included with the MK VIII EGPWS computer is global. 1.5.3 MK VI/MK V III EGPWS Configuration Module The MK VI/MK VIII EGPWS Configuration Module is available under P/N 700-1710-020. The MK VI/MK VIII EGPWS use a Configuration Module installed in the aircraft wiring to store aircraft/EGPWS interface configuration and includes a Real Time Clock for EGPWS installations using internal GPS. The Configuration Module is read by the EGPWS only during power up. The configuration is copied into Non Volatile Memory (NVM) of the EGPWS. The Configuration Module is programmable via an RS-232 interface with the EGPWS. The contents of the Configuration Module can also be read back via the same RS-232 interface. An optional Configuration Module is available under P/N 700-1710-001 for non-Internal GPS operation only. The 700-1710-020 Configuration Module includes a GPS Real Time Clock (RTC) counter and position memory to aid in GPS initialization. A capacitor will keep the position memory retained and clock current for Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 15 Honeywell MK VI MK VIII EGPWS Installation Design Guide approximately 35 days. GPS initialization time should be less than 3 minutes with active RTC data. If the capacitor has discharged then GPS initialization time may be as long as 10 minutes. 1.5.4 GPS Anten na and Cabling EGPWS installations using the internal GPS require a GPS antenna and cabling. The GPS antenna should meet the following qualifications: Frequency: Impedance: Gain: Power: Qualification: 1575.42 MHz 50 ohms 33 dB max, 26.5 dB preferred 5 VDC TSO C129 or C129a or C144 Antenna gain is limited to 33dB gain, maximum. Antennas with 26dB gain are preferred. There are Active GPS antennas with higher gain. However, as the active antenna amplifiers amplify noise as well as the signal, this can overdrive the GPS input AGC circuitry and actually reduce performance. The following GPS antennas are found to be compatible with the EGPWS internal GPS card. Other GPS antennas may be found compatible, contact EGPWS engineering for assistance. It is the responsibility of the OEM or owner/operator (and ultimately the regulatory authorities) to assess the antenna acceptance criteria relative to ARINC, MIL, or other specifications. Boeing has certified the Sensor Systems antenna S67-1575-133 (an ARINC 743A antenna with a 33dB gain) for use on all A/C. This antenna is certified for HIRF/EMI, Class 1 flight critical operation. As a result, it is very expensive (about 3X other versions). King KA 92 Sensor Systems Sensor Systems P/N 071-01553-0200 P/N S67-1575-52 P/N S67-1575-133 TSO-C129 TSO-C129, ARINC 743A TSO-C129a, ARINC 743A The EGPWS requires an input signal of no less than -106 dB (at the EGPWS-GPS coax connector). Installers need to calculate signal strength, plus antenna gain, minus cable line loss to ensure that the input signal does not exceed the -106 dB limit. To calculate signal strength at the EGPWS coax connector, assume a received signal strength of -118 dB at the antenna (this is average signal strength from a GPS satellite at zenith over the antenna). Add the gain of the antenna, then subtract the line loss of the coax cable, and insertion loss at each connector, except at the EGPWS. Assume 0.6dB insertion loss per connector. EXAMPLE: Active GPS Antenna with 26dB gain. A 40 foot coax cable run with 1 coax connector (at the rack disconnect). The cable has a specified line loss of 0.25dB/foot. -118dB (received signal) + 26dB (antenna gain) -92dB -10dB (line loss) (0.25dB/foot x 40 foot run) - 0.6dB (rack coax connector insertion loss) = -102.6dB at EGPWS coax connector, better than required -106dB. This is an acceptable installation. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 16 Honeywell MK VI MK VIII EGPWS Installation Design Guide 1.5.5 OAT Senso r The EGPWS uses a separate OAT sensor (Outside Air Temperature) to measure outside air temperature on aircraft that do not have another compatible source of outside air temperature. Outside Air Temperature is used by the EGPWS along with pressure altitude in the Geometric Altitude computation. If Outside Air Temperature is not available, Geometric Altitude is computed using pressure altitude and GPS Altitude with a corresponding reduction in accuracy. Honeywell engineers have determined that the reduction in accuracy is small because the GPS Altitude is the strongest element in the computation. Geometric Altitude is computed by the EGPWS to reduce or eliminate errors potentially induced in corrected barometric altitude by temperature extremes, non-standard altitude conditions, and altimeter miss-sets. Geometric Altitude also allows continuous EGPWS operation in QFE environments without crew intervention. 1.5.6 Smart Cabl e (PCMCIA Interface) The EGPWS Smart Cable (part number 951-0386-001) is a removable PCMCIA card interface. The Smart Cable is compatible with Honeywell supplied ATA style PCMCIA cards for use with MK VI and MK VIII EGPWS. The purpose of the Smart Cable in the EGPWS system is for upload of software and databases and also for download of EGPWS Flight History. The Smart Cable loading operation will closely emulate that of an ARINC 615 Data Loader. (Reference Figure 1-1 MK VI/MK VIII EGPWS SMART CABLE) FIGURE 1-1 MK VI/MK VIII EGPWS SMART CABLE Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 17 Honeywell MK VI MK VIII EGPWS Installation Design Guide 1.6 Technical C haracteristics MK VI / VIII EGPWS TSO Compliance: Physical size (HxWxD): Weight: Mounting: Temperature (operational): Altitude range: Cooling: Shock: Power Consumption (28 VDC): (MK VI) TSO-C92c, TSO-C151b Class A (MK VIII) TSO-C92c, TSO-C151b Class A, TSO-C117a Application for UKCAA Spec 14 is in process 6.20” x 3.04” x 10.30” 3.9 pounds maximum Standard 3 inch King Radio rack -55°C to +70°C (F2) 55,000 feet (F2) No cooling necessary No shock mounting required 2.5 Amps max 9 watts – no warning +7 watts – with warning over 8 ohm speaker +3 watts – with GPS card +49 watts – with heater blanket on Configuration Module TSO Compliance: Physical size: Weight: Mounting: Temperature (operational): Altitude range: Cooling: Shock: Power Consumption (5 VDC): TSO-C151b 2.68” x 1.51” x 0.32” (fits Positronic connector backshell) <1 pound with connector and backshell Mounts to Positronic connector backshell same as MK VI/MK VIII EGPWS same as MK VI/MK VIII EGPWS No cooling necessary No shock mounting required from MK VI/MK VIII EGPWS GPS Antenna Sensor See Section 1.5.4, ARINC 743A,TSO-C129A and Manufacturer’s specifications. OAT Sensor Nominal 500 ohm Temperature probe, resistance at 0°C 500-ohm ± 0.6 ohm, Range -70°C to +60°C (reference ARINC 575 Section 3.8 or ARINC 706 Section 4.8). See Manufacturer’s specifications. 1.7 Units Supp lied 1.7.1 MK VI EGP WS The MK VI EGPWS is available in two versions, with internal GPS card or without. The part number for the units is as follows: 965-1180-XXX without internal GPS card 2 965-1190-XXX with Internal GPS card 2 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 18 Honeywell MK VI MK VIII EGPWS Installation Design Guide The MK VI EGPWS is normally shipped with an AMERICAS Terrain database. When ordering a MK VI EGPWS that will be operating in the ATLANTIC or PACIFIC1 region the specific Terrain database must be specified with the order. NOTE 1: Terrain Database cards for the ATLANTIC or PACIFIC region are no longer required to be ordered separately. NOTE 2: -XXX defines Application software version. 1.7.2 MK VIII EGP WS The MK VIII EGPWS is available in two versions, with internal GPS card or without. The part number for the units is as follows: 965-1210-XXX without internal GPS card 1 965-1220-XXX with Internal GPS card 1 The MK VIII EGPWS is shipped with a world Terrain database. NOTE 1: -XXX defines Application software version. 1.7.3 Configurati on Module The MK VI/MK VIII EGPWS Configuration Module is available in two versions. When ordering the Configuration Module, order part number 700-1710-020 or part number 700-1710-001. The part number 700-1710-020 is required for installations with internal GPS. 1.7.4 Smart Cabl e (PCMCIA Interface) The MK VI/MK VIII EGPWS Smart Cable is available in one version. The Smart Cable is used for Line Maintenance; Application/Configuration code and Terrain Database uploads and Flight History downloads. Only one Smart Cable is required for an installation house or operator. When ordering the Smart Cable, order part number 951-0386-001. 1.8 Installation Kits and Accessories NOTE: Not all installation kits are immediately available, contact Honeywell Order Administration (425-885-8719) for availability. 1.8.1 MK VI/MK V III EGPWS Installation Kits Note: For all parts in the Installation kits the weight of each part is less than 0.25 pounds. (A) Retrofit classic MK VI GPWS installation The MK VI/MK VIII EGPWS Installation Kit, P/N 755-7013-011, contains the following parts: Vendor Name Vendor P/N Description QTY UM Honeywell P/N Positronic Ind. RD50F1OJVLC-15 P2 connector 1 EA 440-1233-001 Honeywell 700-1710-020 Configuration Module 1 EA 700-1710-020 (B) New EGPWS installation The MK VI/MK VIII EGPWS Installation Kit, P/N 755-7013-010, contains the following parts: Vendor Name Vendor P/N Description QTY UM Honeywell P/N Positronic Ind. DD78F1OJVLC-15 P1 connector, female 1 EA 440-1158-009 Positronic Ind. Honeywell RD50F1OJVLC-15 700-1710-020 P2 connector, female Configuration Module 1 1 EA EA 440-1233-001 700-1710-020 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 19 Honeywell MK VI MK VIII EGPWS Installation Design Guide Bendix/King 071-04003-0002 Computer Mounting Tray 1 EA 405-0383-001 1.8.2 RS-232 Cab le The MK VI/MK VIII EGPWS RS-232 Cable can be ordered using the following part numbers: NOTE: The RS-232 Cable can be built by the Installer/Operator per the description in Section 4.4.2. Vendor Name Vendor P/N Description QTY UM Honeywell P/N Honeywell 704-2617-001 RS-232 Cable 1 EA 704-2617-001 1.8.3 Smart Cabl e The MK VI/MK VIII EGPWS Smart Cable can be ordered using the following part numbers: Vendor Name Vendor P/N Description QTY UM Honeywell P/N Honeywell 951-0386-001 Smart Cable 1 EA 951-0386-001 1.8.4 Terrain Dat abase Cards The MK VI EGPWS Terrain Database Cards can be ordered using the following part numbers: Vendor Name Vendor P/N Description QTY UM Honeywell P/N Honeywell Honeywell Honeywell Honeywell 718-1391-xxx 718-1392-xxx 718-1393-xxx 402-6075-xxx North & South America Europe, Africa, Asia Asia, Australia, Pacific Label, TDB Front Panel 1 1 1 1 EA EA EA EA 718-1391-xxx 718-1392-xxx 718-1393-xxx 402-6075-xxx 1.8.5 Flight Histo ry Card The MK VI/MK VIII EGPWS Flight History Card can be ordered using the following part numbers: Vendor Name Honeywell Honeywell Vendor P/N 1 300-1151-006 718-1593-0012 Description QTY UM Honeywell P/N Flight History Download Flight History Download 1 1 EA EA 300-1151-0061 718-1593-001 Note 1: Unprogrammed (blank) 32 Mb card ATA PCMCIA card. Note 2: Programmed 32 Mb card ATA PCMCIA card. 1.9 Accessorie s not Supplied 1.9.1 ARINC 453 Terrain Display wiring The Terrain display wiring (ARINC 453) must meet the display manufacturer’s specifications including termination method. ARINC 453 bus wiring must meet the following requirements: • • • • • Cable length must be less than 300 feet (91.4 meters). Wire to wire capacitance must not exceed 50 pF/foot. Shielded twisted pair with not less than one twist per inch. Impedance of 78 ohms ±10% at 1 MHz (ARINC 708 WXR). Impedance of 70 ohms ±10% at 1 MHz (ARINC 453 bus). Vendor Name Vendor P/N Description QTY UM Pic Wire&Cable D620224 ARINC 453 cable A/R EA Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 20 Honeywell MK VI MK VIII EGPWS Installation Design Guide Pic Wire&Cable Pic Wire&Cable ECS ECS Emteq D5102QX D771553 4122021 312402 D70-022402T-01 M17/176-00002 M83536/6-022M M12883/44-01 Hi Temp Quadraxial MIL-STD 1553 Data Bus ARINC 453 cable (2 shields) ARINC 453 cable (3 shields) ARINC 453 cable Military Specification Relay, 4PDT (Note 1) Relay, Socket (Note 1) A/R A/R A/R A/R A/R A/R A/R A/R EA EA EA EA EA EA EA EA Note 1: Recommended in EFS 40/50 Installation Manual. 1.9.2 GPS Anten na & Cable The GPS Antenna & cable can be ordered from their manufacturers using the following part numbers: Vendor Name Vendor P/N Description QTY UM Honeywell P/N Bendix/King Comant Bendix/King PIC PIC ECS ECS ECS Amp Amphenol S14293 S44191 311901 311601 311201 225554-6 79075 KA 92 GPS Antenna (26dB) KA 92 GPS Antenna (26dB) Antenna Installation Kit S67 GPS Antenna (29dB) S67 GPS Antenna (26dB) S67 GPS Antenna (33dB) Coax Cable, RG400/U Coax Cable, RG-142B/U Coax Cable Coax Cable Coax Cable Coax Cable Coax Cable TNC Angle Plug, Male TNC Angle Plug, Male 1 1 OPT 1 1 1 A/R A/R A/R A/R A/R A/R A/R 1 1 EA EA EA EA EA EA EA EA EA EA EA EA EA EA EA 300-1147-001 300-1147-001 405-0432-001 Thermax 071-01553-0200 CI 405-2 050-03318-0000 S67-1575-38 S67-1575-52 S67-1575-133 M17/128-RG400 Sensor Systems Sensor Systems Sensor Systems 440-1239-001 440-1239-001 NOTE: If a satellite communication system is installed in the aircraft, or the GPS cable run is in the vicinity of a VHF transceiver and/or cable, DO NOT USE R/G 142 or R/G 400 cable. 1.9.3 Circuit Brea ker The Circuit Breaker needs to be a 3 Amp delayed action circuit breaker. Vendor Name Vendor P/N Description QTY UM Klixon (T.I.) 7277-2-3 3 Amp Circuit Breaker, EGPWS power +28 1 EA Klixon (T.I.) 7277-2-1 1 Amp Circuit Breaker, lamp power +28 1 EA Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 21 Honeywell MK VI MK VIII EGPWS Installation Design Guide 1.9.4 Annunciato rs & Switch/Annunciators The devices shown below are West Coast Specialties and Staco switch/annunciators and are representative of those used in some installations. However, there are other comparable devices on the market that may be substituted at the installer/customers choice. The installer/customer is cautioned to verify regulatory approval of the annunciation devices installed. See Appendix D for Vendors. A. GPWS (P/TEST); BELOW G/S (P/CANCEL) switch/annunciator assemblies The ‘GPWS’ annunciator provides visual indication of an EGPWS warning or alert. The GPWS annunciator also has a momentary switch that is used to manually initiate EGPWS Self Test. Two GPWS annunciators are required for each aircraft, one in the direct view of each pilot. If the Lamp Format 2 option is selected (see 3.15.2.1), this switch/annunciator will be labeled ‘PULL UP’ and annunciated in red. The ‘BELOW G/S’ annunciator provides visual indication of an EGPWS glideslope caution. The BELOW G/S annunciator also has a momentary switch that is used to manually inhibit EGPWS Mode 5 glideslope alerts. Two BELOW G/S annunciators are required for each aircraft, one in the direct view of each pilot. If the Lamp Format 2 option is selected (see 3.15.2.1), this switch/annunciator will be labeled ‘GPWS’ and annunciated in amber. Vendor Name Vendor P/N Description QTY UM West Coast Spec. 90-81401-001 GPWS BELOW G/S 2 EA West Coast Spec. 90-81401-003 90-81401-008 90-81401-009 61406-003 61406-004 61406-005 61406-006 GPWS BELOW G/S GPWS BELOW G/S (1) GPWS BELOW G/S (1) GPWS G/S CANCEL PULL UP GPWS TEST GPWS GPWS TEST BELOW G/S G/S CANCEL ALT ALT ALT ALT ALT ALT ALT EA EA EA EA EA EA EA West Coast Spec. West Coast Spec. STACO STACO STACO STACO (1) GPWS – BELOW G/S – GPWS FLAP OVRD – G/S CANCLD B. GPWS FLAP OVRD; GPWS INOP; G/S CANCLD switch/annunciator assemblies The ‘GPWS FLAP OVRD’ annunciator provides visual indication that the EGPWS Flap Override function is activated. The GPWS FLAP OVRD annunciator also has a momentary switch that is used to manually activate the Flap Override function. The ‘GPWS INOP’ annunciator provides visual indication that the EGPWS’ GPWS modes have been disabled or do not function because of an external or internal fault. The ‘G/S CANCLD’ annunciator provides visual indication that the EGPWS Mode 5 function is inhibited. Vendor Name Vendor P/N Description QTY UM West Coast Spec. 90-81401-008 (1) 1 EA West Coast Spec. 90-81401-009 90-81401-010 (2) (3) 1 1 EA EA West Coast Spec. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 22 Honeywell MK VI MK VIII EGPWS Installation Design Guide West Coast Spec. West Coast Spec. STACO 90-81401-011 90-81401-012 61406-007 (4) (5) GPWS FLAP OVERRIDE (1) GPWS – BELOW G/S – GPWS FLAP OVRD – G/S CANCLD (2) GPWS – BELOW G/S – GPWS FLAP OVRD – GPWS INOP (3) GPWS FLAP OVRD – G/S CANCLD (4) GPWS INOP – G/S CANCLD – GPWS FLAP OVRD (5) GPWS FLAP OVRD – GPWS INOP 1 1 1 EA EA EA C. TERR DISPLAY; TERR INHIBIT; GPWS FAIL / TERR FAIL switch/annunciator assemblies The ‘TERR DISPLAY’ annunciator provides visual indication that the EGPWS Terrain Display has been selected for the associated display. The TERR DISPLAY annunciator also has a momentary switch that is used to manually select the Terrain Display. The ‘TERR INHIBIT’ annunciator provides visual indication that the EGPWS Terrain functions have been inhibited. The TERR INHIBIT annunciator also has a alternate action switch that is used to manually inhibit the Terrain functions. The ‘GPWS FAIL / TERR FAIL’ annunciator provides visual indication that the EGPWS GPWS modes or TA&D and TCF modes have a disabled function. Vendor Name Vendor P/N Description QTY UM STACO STACO 61406-001 61406-002 61406-011 TERRAIN DISPLAY ON TERR INHIBIT ON 1 1 1 EA EA EA STACO GPWS FAIL TERRAIN FAIL 1.9.5 Cockpit Sp eakers The MK VI / MK VIII EGPWS can interface to an 8 ohm audio speaker for cockpit annunciation of aural alerts. Vendor Name Vendor P/N Description QTY UM Quam Utah 30A05Z8 SP-3A Audio Speaker Audio Speaker 1 1 EA EA 1.9.6 Temperatur e Probes The MK VI / MK VIII EGPWS may be optionally interfaced to a dedicated 500-ohm temperature probe meeting the specifications of ARINC 575 Section 3.8. The installer may want to discuss availability of a dual-element probe compatible with the EGPWS and with other systems on the aircraft with the manufacturers. Vendor Name Vendor P/N Description QTY UM CIC Norwich Norwich Rosemount Rosemount Rosemount 05257 103-00157-3 103-00034 102CT2CB 102AU1AF 102AU1AG Single element, unheated Single element, unheated Dual element, unheated 500-ohm Single element, heated Dual element, heated 1 1 1 1 1 1 EA EA EA EA EA EA Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 23 Honeywell MK VI MK VIII EGPWS Installation Design Guide Rosemount Rosemount Rosemount Rosemount Rosemount 102EH2BH 102EH2EB 102JE2FG 129H-500 129G-500 Dual element, heated Dual element, heated Triple element, heated Single element, unheated Dual element, unheated 1 1 1 1 1 EA EA EA EA EA 1.10 Tools Requ ired 1.10.1 Crimping T ool - P1, P2, P3 Description UM QTY Vendor Name & Part Number Hand Crimping Tool Hand Crimping Tool Hand Crimping Tool EA EA EA 1 1 1 Positronic Ind. 9507 Daniels AFM8 Military M22520/2-1 Hand Crimping Tool EA 1 Astro 61517 1.10.2 Contact Po sitioner - P1, P2, P3 Description UM QTY Vendor Name & Part Number Contact Positioner, Socket P1 Contact Positioner, Socket P1 Contact Positioner, Socket P1 Contact Positioner, Socket P2 Contact Positioner, Socket P2 Contact Positioner, Socket P2 Contact Positioner, Pin P3 Contact Positioner, Pin P3 EA EA EA EA EA EA EA EA 1 1 1 1 1 1 1 1 Positronic Ind. Daniels Military Positronic Ind. Daniels Military Positronics Daniles 9502-3 K41 (for 22 to 28 AWG) M22520/2-06 9502-5 K13-1 (20-24 AWG) M22520/2-08 9502-4 K42 (22-28 AWG) Contact Positioner, Pin P3 EA 1 Military M22520/2-09 1.10.3 Insertion/R emoval Tool - P1, P2, P3 Description UM QTY Vendor Name & Part Number Removal Tool P1, P3 Removal Tool P1, P3 Removal Tool P2 Insertion Tool P1, P3 Insertion Tool P1, P3 Insertion Tool P2 Insertion/Removal Tool P1, P3 EA EA EA EA EA EA EA 1 1 1 1 1 1 1 Daniels Military Daniels Daniels Military Daniels Military DRK 95-22M M81969/8-02 DRK145 DAK 95-22M M81969/8-01 DAK145 M81969/1-04 Insertion/Removal Tool P2 EA 1 Military M81969/1-02 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 24 Honeywell MK VI MK VIII EGPWS Installation Design Guide 1.10.4 Spare Conn ectors and Contacts - P1, P2, P3 P/N UM QTY Vendor Name & Part Number 440-1223-002 15 pin male with hood 1 15 pin female 440-1223-003 1 440-1223-004 15 pin male 400-5163-002 1 15 pin clamp kit male contacts for 15 pin 22-30 AWG male contacts for 15 pin 22-30 AWG female contacts for 50 pin 20-24 AWG female contacts for 50 pin 20-24 AWG female contacts for 78 pin 22-30 AWG EA EA EA EA EA EA EA EA EA 1 1 1 1 1 1 1 1 1 Positronic Ind. DD15M10YOC-15 Positronic Ind. DD15F10OOC-15 Positronic Ind. DD15M10OOC-15 AMP 745854-3 Positronic Ind. MC8022D M39029/58-360 Positronic Ind. FC6020D M39029/63-368 Positronic Ind. FC8022D female contacts for 78 pin 22-30 AWG EA 1 M39029/57-354 1 Description These parts are available in EGPWS kit PN 755-7013-090. 1.11 License Re quirements There are no Radio license requirements for the MK VI/MK VIII EGPWS Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 25 Honeywell MK VI MK VIII EGPWS Installation Design Guide THIS PAGE INTENTIONALLY LEFT BLANK Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 26 Honeywell MK VI MK VIII EGPWS Installation Design Guide SECTION II INSTALLATION Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 27 Honeywell MK VI MK VIII EGPWS Installation Design Guide SECTION II - INSTALLATION SECTION II - INSTALLATION ........................................................................................................................................ 29 2.1 INTRODUCTION.............................................................................................................................................................. 29 2.2 UNPACKING AND INSPECTING THE EQUIPMENT ............................................................................................................. 29 2.3 EQUIPMENT INSTALLATION ........................................................................................................................................... 29 2.3.1 General.................................................................................................................................................................. 29 2.3.2 MK VI/MK VIII Computer Location...................................................................................................................... 29 2.3.3 MK VI/ MK VIII Computer Installation................................................................................................................. 30 2.3.4 Configuration Module Location ............................................................................................................................ 31 2.3.5 Configuration Module Installation........................................................................................................................ 31 2.3.6 GPS Antenna location ........................................................................................................................................... 40 2.3.7 GPS Antenna Installation ...................................................................................................................................... 40 2.3.8 OAT Sensor Location ............................................................................................................................................ 40 2.3.9 OAT Sensor Installation ........................................................................................................................................ 40 2.3.10 Cockpit Lights...................................................................................................................................................... 40 2.3.10.1 Description........................................................................................................................................................................41 2.3.10.2 Location ............................................................................................................................................................................42 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 28 Honeywell MK VI MK VIII EGPWS Installation Design Guide SECTION II - INSTALLATION 2.1 Introductio n This section contains suggestions and factors to consider before installing the Enhanced Ground Proximity Warning System. Close adherence to these suggestions will assure satisfactory performance from the equipment. NOTE The conditions and tests performed on this article are minimum performance standards. It is the responsibility of those desiring to install this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within these performance standards. The article may be installed only if further evaluation by the applicant documents an acceptable installation and is approved by the airworthiness authority. 2.2 Unpacking and Inspecting the Equipment 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 packing materials to substantiate your claim. The claim should be filed as soon as possible. The shipping container and all packing materials should be retained in the event that storage or reshipment of the equipment is necessary. 2.3 Equipment Installation 2.3.1 General The following paragraphs contain information pertaining to the installation of the MK VI and MK VIII EGPWS, including instructions concerning the location and mounting of the equipment. 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. CAUTION 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 SPECIFIED IN THE INTERWIRING DIAGRAMS IN SECTION III. 2.3.2 MK VI/MK V III Computer Location Care should be exercised to avoid mounting components near equipment operating with high pulse current or high power outputs such as radar and satellite communications equipment. In general, the equipment should be Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 29 Honeywell MK VI MK VIII EGPWS Installation Design Guide installed in a location convenient for operation, inspection, and maintenance, and in an area free from excessive vibration, heat, and noise generating sources. The MK VI and MK VIII EGPWS have an internal heater blanket therefore they can be mounted outside the heated area of the aircraft. The computers have been qualified for operation up to 50,000 feet and -55°C using the heater blanket. All mechanical installation drawings, connector assembly diagrams, interwiring diagrams, and connector pin assignment tables referenced in this section are located at the end of Section II of this manual. Determine the mounting location for the system components following the guidelines below. Prior to installing any equipment, make a continuity check of all wires and cables associated with the system. Then apply power and check for proper voltages at system connectors, and then remove power before completing the installation. To allow for inspection or repair of the wiring of the connector assembly itself, sufficient lead length should be left so that EGPWS may be moved several inches. A bend should be made in the harness to allow water droplets that might form on the harness due to condensation, to drip off at the bend and not collect in the connector. NOTE For retrofit installations of classic MK VI GPWS and installing a EGPWS with internal GPS, the connector backshell of the classic MK VI P1 connector will interfere with the GPS antenna connector on the front of the EGPWS. The connector backshells chosen for the EGPWS kits now extends straight out and does not interfere with the GPS antenna connector. The length of cables from the EGPWS connectors to other system units is not generally critical because unit interfaces are designed with high impedance inputs, low impedance outputs, and low noise susceptibility characteristics. The exception is the wires from the EGPWS Configuration Module, which was designed to be a part of the EGPWS connector backshell because of the requirement for short lead length. Follow aircraft manufacturer’s, sub-system manufacturer’s or ARINC specifications for shield grounding. 2.3.3 MK VI/ MK VIII Computer Installation The MK VI and MK VIII EGPWS 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 will assure a more satisfactory performance from the equipment. A. Plan a location on the aircraft so that the EGPWS is accessible for front panel maintenance controls. Check to be sure that there is adequate space in the front of the computer for connectors and cabling. B. Refer to Figure 2-2 and 2-3 for outline dimensions of the computer and mounting tray. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 30 Honeywell MK VI MK VIII EGPWS Installation Design Guide C. Mount the EGPWS mounting tray in the aircraft radio rack or other location using the four screw mounting holes. Match drill the mounting holes using the Mounting Tray as a template. D. Ensure that the mounting tray is electrically bonded (less than 10 milli-ohm to aircraft ground). E. Slide the EGPWS unit in the mounting tray, and secure it using the Hold Down latch. F. (After Continuity and Power check) Attach the cable harness to the front panel connectors and lock connectors using the slide lock of the P1 & P2 connectors. The EGPWS should be wired according to the interconnect diagrams in Section III, of this manual. 2.3.4 Configurati on Module Location The aircraft configuration is programmed into the EGPWS Configuration Module installed in the aircraft wiring. The Configuration Module is identified as Honeywell part number 700-1710-020 (optional part number 7001710-001). The Configuration Module is installed as one side of the P2 (50 pin) mating connector backshell and contains electrically reprogrammable memory for configuration storage. The Configuration Module when installed is wired directly to the appropriate pins in the P2 connector. 2.3.5 Configurati on Module Installation The purpose of this procedure is to give an assembly sequence for assembly of the Configuration Module with the P2 connector and backshell. A. The P2 connector, Honeywell part number 440-1233-001, vendor part number RD50F1OJVLC-15, when ordered comes with 50 contacts and a plastic backshell (hood). B. The Configuration Module will replace the Backshell Plate. The Backshell Plate can be discarded. C. Wire the Configuration Module to the P2 connector using contacts provided with the connector. Wire per the following wire list: Wire Color Violet Blue Orange Black White Red P2 pin # P2-17 P2-16 P2-33 P2-50 P2-49 P2-32 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 31 Honeywell MK VI MK VIII EGPWS Installation Design Guide D. Position Slide Lock and Spring Clip onto connector. E. Install Backshell Housing onto connector. The Ground wire (used for ESD discharge) is terminated with shielded pigtails inside the backshell to the P2 connector. F. Organize and dress wire exiting from the backshell, route Configuration Module wires in a coil. Install Cable Clamp, do not tighten Cable Clamp screws. G. Secure the Configuration Module to the connector using screws provided. Tighten Cable Clamp screws as required. CONFIGURATION MODULE ASSEMBLY REQUIRED: Two items as follows: 1.0 Connector (P2) Positronic Ind. RD50F10JVLC-15 * 2.0 Configuration Module Honeywell 700-1710-020 * This item may be available from Honeywell under Part No. (440-1233-001) ITEM 2 DESCRIPTION: Connector P2 (Positronic Ind. PN RD50F10JVLC-15) is a packaged kit consisting of the following parts: 1.1 Connector, 50 socket D-Sub Qty - 1 1.2 Contacts, size 20 crimp Qty - 50 1.3 Backshell housing Qty - 1 1.4 Backshell plate Qty - 1 1.5 Screws, Phillips CSK Qty - 2 1.6 Spring Clip Qty - 1 1.7 Slide Lock Qty - 1 1.8 Screws, Slotted Qty - 2 1.9 Cable Clamp Qty - 1 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 32 Honeywell MK VI MK VIII EGPWS Installation Design Guide INSTALLATION ASSEMBLY SEQUENCE STEP 1 Install all MK VI/MK VIII system aircraft wiring to this connector using items 1.2 (Crimp Contacts) and item 1.1 (Connector). See figure 2.1-1 below. FIGURE 2.1-1 MK VI/MK VIII EGPWS CONFIGURATION MODULE Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 33 Honeywell MK VI MK VIII EGPWS Installation Design Guide STEP 2 Wire item 2.0 (Configuration Module). This part will replace item 1.4 (Backshell plate). Install the pre-crimped colored wires into item 1.1 (Connector) as shown in figure 2.1-2 below. FIGURE 2.1-2 MK VI/MK VIII EGPWS CONFIGURATION MODULE Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 34 Honeywell MK VI MK VIII EGPWS Installation Design Guide STEP 3 Position item 1.7 (Slide lock) onto wired connector as shown in figure 2.1-3 below: FIGURE 2.1-3 MK VI/MK VIII EGPWS CONFIGURATION MODULE Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 35 Honeywell MK VI MK VIII EGPWS Installation Design Guide STEP 4 Install item 1.3 (Backshell Housing) onto connector using item 1.8 (Screws) as shown in figure 2.1-4 below: Ground Wire (used for electrostatic discharge {ESD} protection) is terminated with shielded pigtails of wires at this connector. FIGURE 2.1-4 MK VI/MK VIII EGPWS CONFIGURATION MODULE Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 36 Honeywell MK VI MK VIII EGPWS Installation Design Guide STEP 5 Install item 1.6 (Spring Clip) as shown figure 2.1-5 below: FIGURE 2.1-5 MK VI/MK VIII EGPWS CONFIGURATION MODULE Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 37 Honeywell MK VI MK VIII EGPWS Installation Design Guide STEP 6 Organize and dress wiring exiting from backshell. Route Configuration Module wires exiting from connector, then coil as shown in figure 2.1-6 below. Install item 1.9 (Cable Clamp) as shown. Do not tighten screws yet. FIGURE 2.1-6 MK VI/MK VIII EGPWS CONFIGURATION MODULE Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 38 Honeywell MK VI MK VIII EGPWS Installation Design Guide STEP 7 Secure Configuration Module to connector assembly using item 1.5 (Screws) as shown in figure 2.1-7 below. Tighten Cable Clamp screws as required. FIGURE 2.1-7 MK VI/MK VIII EGPWS CONFIGURATION MODULE Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 39 Honeywell MK VI MK VIII EGPWS Installation Design Guide 2.3.6 GPS Anten na location The GPS antenna should be mounted on top of the fuselage in the centerline of the aircraft. Avoid mounting the antenna near any projections, the propeller, and the T-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 antenna on the aircraft. The GPS antenna baseplate must be level within ± 5° in both axis when the aircraft is level (level is defined as the aircraft attitude required when weighing the aircraft for weight and balance). If the GPS antenna is tilted more than 5° or is mounted close to other objects that shadow it, loss of some of the satellites will occur and system performance degraded. See manufacturer for specifications of GPS antennas. Some GPS Antenna cable and connector information, including vendor information, is listed below. Cable Length Cable Part Number (VPN) EGPWS TNC Connector (VPN) Antenna TNC Connector (VPN) Max Loss* 0 to 40 ft RG142B/U RG400/U TED Mfg. 5-10-30 TED Mfg. 5-30-102-1 8.0 0 to 80 ft ECS 311601 TED Mfg. 5-10-307 TED Mfg. 5-10-307 8.0 0 to 100 ft ECS 311201 TED Mfg. 5-10-306 TED Mfg. 5-10-306 8.0 100 to 165 ft Contact TED, ECS or PIC for complete cable/connector assembly * Maximum Allowable Loss (dB) @ 1575 MHz for cable and connector using nominal 26.5 dB gain. TED Manufacturing Corp. 11415 Johnson Drive Shawnee, Kansas 66203 Tel: (913) 631-6211 Electronic Cable Specialists (ECS) 5300 W. Franklin drive Franklin, Wisconsin 53132 Tel: (800) 327-9473 PIC Wire & Cable N63 W 22619 Main Street Sussex, Wisconsin 53089 Tel: (800) 742-3191 2.3.7 GPS Anten na Installation Refer to manufacturer’s procedures or applicable STC documentation. 2.3.8 OAT Senso r Location The OAT sensor should be mounted on the underside (belly) of the aircraft or other convenient location meeting the following conditions. Avoid mounting the sensor where it can be affected by direct sunlight, or exhaust gases from engines or heaters. The probe tip should extend beyond the aircraft boundary layer into the turbulent airflow. See manufacturer for specifications. 2.3.9 OAT Senso r Installation Refer to manufacturer’s procedures or applicable STC documentation. 2.3.10 Cockpit Lig hts This section provides information for selecting, locating and mounting of the MK VI and MK VIII EGPWS Cockpit lights. NOTE: The nomenclature given for each lamp is an example only. Other manufacturers use nomenclature that is also acceptable. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 40 Honeywell MK VI MK VIII EGPWS Installation Design Guide NOTE: All lights 1. Refer to Honeywell Product Specification 965-1176-601 for additional information and for electrical loads specification. 2. All lights are +28 VDC, dual bulb, sun light readable, non-flashing. 3. In the “OFF” condition, all lights have dark background with visible nomenclature for action. 4. If desired the lights may be put on a “dimmer” circuit for night operation. 2.3.10.1 Description EGPWS alert/warning (Lamp Format 1) GPWS P/TEST This assembly is illuminated with red background and activated during any Mode 1 through Mode 4, and Terrain Awareness alert or warning. This assembly also includes a momentary switch that will activate EGPWS Self Test. EGPWS warning (Lamp Format 2) PULLUP P/TEST This assembly is illuminated with red background and activated during any Mode 1, Mode 2, or Terrain Awareness PullUp warning. This assembly also includes a momentary switch that will activate EGPWS Self Test. GLIDESLOPE alert (Lamp Format 1) BELOW G/S P/CANCEL This assembly is illuminated with amber background and activated during any Mode 5 alert. This assembly also includes a momentary switch that will de-activate (cancel) EGPWS Mode 5 alerts during backcourse or low altitude approaches. EGPWS caution (Lamp Format 2) GPWS G/S CANCEL This assembly is illuminated with amber background and activated during any EGPWS alert (non-Pullup). This assembly also includes a momentary switch that will de-activate (cancel) EGPWS Mode 5 alerts during backcourse or low altitude approaches. Glideslope Canceled G/S CANCLD (optional but recommended) This assembly is illuminated with white, blue or amber background and activated after the flight crew has initiated the manual cancel of Mode 5 by pressing the BELOW G/S – P/CANCEL light/switch described above. EGPWS Flap Override GPWS FLAP OVRD (optional but recommended) This guarded light/switch assembly is illuminated with blue background and activated after the flight crew has initiated the manual selection of the GPWS Flap Override feature. This assembly also includes a momentary switch that will activate GPWS Flap Override. Note: the light color may also be white background with black legend or black background with white legend. Colors are per FAR 23.1322. GPWS system validity GPWS INOP This assembly is illuminated with amber background and activated during any detected partial or total failure of the GPWS modes 1-5. TERRAIN select TERR DISPLAY ON Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 41 Honeywell MK VI MK VIII EGPWS Installation Design Guide This assembly is illuminated with white background and activated after the flight crew has initiated the manual selection of the EGPWS terrain display for the associated cockpit display. This assembly also includes a momentary switch that will activate EGPWS Terrain display feature. TERRAIN inhibit TERR INHIBIT ON This assembly is illuminated with amber background and activated after the flight crew has initiated the manual inhibit of the EGPWS Terrain Awareness & display and Terrain Clearance Floor functions during an approach to an airport not in the EGPWS Terrain/Runway database. This assembly also includes a alternate action switch that will inhibit EGPWS TA&D and TCF functions. TERRAIN system validity TERR FAIL This assembly is illuminated with amber background and activated during any detected partial or total failure of the TA&D or TCF functions. 2.3.10.2 Location Cockpit layout, size and operator’s preference will determine if only one set of lights is used (i.e., mounted in the center), or if dual sets of lights are used (one set on each side), or a combination thereof is desired. For a typical example of cockpit light locations refer to Figure 2-3. For panel cutouts and assembly options see the manufacturer’s specifications. The following are recommended locations: GPWS & BELOW G/S or PULLUP & GPWS These lights should be located together and in the flight crew’s “primary field of view”. This would include either the instrument panel or the edge of the glareshield. GPWS FLAP OVRD -OptionalThis light should be located in the flight crew’s “field of view” and within reach of both crew members. This light/switch may be located in an assembly with the GPWS and BELOW G/S lights and/or other EGPWS annunciators. GPWS CANCLD -OptionalIf used, this light should be located within at least one crew member’s “field of view”. GPWS INOP This light should be located within at least one crew member’s “field of view” or with other system INOP lights of similar importance. It is recommended that this light not be located in the flight crew’s “primary field of view”. The reason being that in the event of a GPWS system failure at the beginning of a flight, this light will remain “ON” until the problem is fixed. This light may be combined with the TERR FAIL light. TERR DISPLAY ON This light should be located near the associated cockpit display, in the flight crew’s “field of view” and within reach of one or both crew members. This light/switch may be located in an assembly with the TERR INHIBIT light(s) and/or other EGPWS annunciators. TERR INHIBIT ON This light should be located in the flight crew’s “field of view” and within reach of both crew members. This light/switch may be located in an assembly with the TERR DISPLAY light(s) and/or other EGPWS annunciators. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 42 Honeywell MK VI MK VIII EGPWS Installation Design Guide TERR FAIL This light should be located within at least one crew member’s “field of view” or with other system INOP lights of similar importance. Note: Annunciators are available with split legend GPWS FAIL / TERR FAIL in one assembly. It is recommended that this light not be located in the flight crew’s “primary field of view”. The reason being that in the event of a GPWS system failure at the beginning of a flight, this light will remain “ON” until the problem is fixed. TERR ON PULLUP TERR INHB TERR FAIL GPWS PULLUP GPWS The above picture is an example of lamp location and does not restrict lamp location or format Figure 2.3 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 43 Honeywell MK VI MK VIII EGPWS Installation Design Guide FIGURE 2-2 MK VI/MK VIII EGPWS OUTLINE Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 44 Honeywell MK VI MK VIII EGPWS Installation Design Guide FIGURE 2-3 MK VI/MK VIII EGPWS MOUNTING TRAY Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 45 Honeywell MK VI MK VIII EGPWS Installation Design Guide THIS PAGE INTENTIONALLY LEFT BLANK Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 46 Honeywell MK VI MK VIII EGPWS Installation Design Guide SECTION III SYSTEM PLANNING Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 47 Honeywell MK VI MK VIII EGPWS Installation Design Guide SECTION III – SYSTEM PLANNING SECTION III – SYSTEM PLANNING..............................................................................................................................51 3.1 INTRODUCTION.............................................................................................................................................................. 51 3.2 SYSTEM WIRING/ ELECTRICAL INTERFACES ................................................................................................................. 51 3.2.1 Primary Power Input.............................................................................................................................................51 3.2.2 Chassis Ground .....................................................................................................................................................52 3.2.3 GPS Antenna .........................................................................................................................................................52 3.2.4 Analog and Digital Inputs .....................................................................................................................................52 3.2.5 Discrete Inputs ......................................................................................................................................................52 3.2.6 Serial Outputs........................................................................................................................................................52 3.2.7 Audio Output .........................................................................................................................................................53 3.2.8 Discrete Outputs....................................................................................................................................................53 3.2.9 Configuration Module ...........................................................................................................................................53 3.3 CATEGORY 1 - AIRCRAFT / MODE TYPE SELECT .......................................................................................................... 54 3.3.1 Aircraft / Mode Type .............................................................................................................................................54 3.3.2 Mode 1 type ...........................................................................................................................................................54 3.3.3 Mode 2 type ...........................................................................................................................................................54 3.3.4 Mode 3 type ...........................................................................................................................................................55 3.3.5 Mode 4 type ...........................................................................................................................................................55 3.3.6 Bank Angle Type....................................................................................................................................................55 3.3.7 Runway Length (MK VIII EGPWS only) ...............................................................................................................56 3.3.8 Instructions............................................................................................................................................................56 3.4 CATEGORY 2 – AIR DATA INPUT SELECT ...................................................................................................................... 57 3.4.1 Analog (Cat. 2 ID 0, 3, 4, 11, 12)..........................................................................................................................57 3.4.2 Digital – ARINC 429 (Cat. 2 ID 5, 1, 6, 13)..........................................................................................................59 3.4.3 Digital –ARINC 575 (Cat. 2 ID 2).........................................................................................................................60 3.4.4 Shadin 2000 (Cat. 2 ID 10) ...................................................................................................................................61 3.4.5 Digital – ARINC 429 Dual IOC Buses (Cat. 2. ID 255)........................................................................................62 3.4.6 Instructions............................................................................................................................................................62 3.5 CATEGORY 3 – POSITION INPUT SELECT ....................................................................................................................... 63 3.5.1 ARINC 743 Format ...............................................................................................................................................63 3.5.2 GPS Altitude (Label 076) Reference .....................................................................................................................63 3.5.3 North-South East-West Velocity labels..................................................................................................................63 3.5.4 ARINC 429 BUS (Cat. 3 ID 0,1,4,5,10-13) ...........................................................................................................64 3.5.5 RS-232 Transmit-Receive, 9600 baud (Cat. 3 ID 3)..............................................................................................65 3.5.6 Dual ARINC 429 BUS (Cat. 3 ID 253 & 255).......................................................................................................66 3.5.7 Instructions............................................................................................................................................................66 3.6 CATEGORY 4 – ALTITUDE CALLOUTS ........................................................................................................................... 67 3.7 CATEGORY 5 – AUDIO MENU SELECT ........................................................................................................................... 68 3.7.1 Audio Menu Selection............................................................................................................................................68 3.7.2 Instructions............................................................................................................................................................68 3.8 CATEGORY 6 – TERRAIN DISPLAY SELECT ................................................................................................................... 69 3.8.1 TAD & TCF Selection ...........................................................................................................................................69 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 48 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.8.2 Terrain Display Configuration Group ..................................................................................................................70 3.8.3 Display Input Control Group ................................................................................................................................70 3.8.4 Output 429 Bus Group ..........................................................................................................................................71 3.8.5 Instructions............................................................................................................................................................71 3.8.6 Sample Display Schematics...................................................................................................................................71 3.9 CATEGORY 7 – OPTIONS SELECT GROUP #1 ................................................................................................................. 88 3.9.1 Steep Approach .....................................................................................................................................................88 3.9.2 TA&D Alternate Pop-up........................................................................................................................................88 3.9.3 Peaks Mode ...........................................................................................................................................................88 3.9.4 Obstacle Awareness ..............................................................................................................................................88 3.9.5 Bank Angle Callout Enabling................................................................................................................................89 3.9.6 Flap Reversal ........................................................................................................................................................89 3.9.7 GPS Altitude Reference .........................................................................................................................................89 3.9.8 Instructions............................................................................................................................................................90 3.10 CATEGORY 8 – RADIO ALTITUDE INPUT SELECT ........................................................................................................ 91 3.10.1 Radio Altitude Input ............................................................................................................................................91 3.10.2 Decision Height Discrete Input ...........................................................................................................................91 3.10.3 Digital Radio Altitude Interface (Cat. 8 ID 2).....................................................................................................91 3.10.4 Analog Radio Altitude Interface (Cat. 8 ID 0,1,3,4)............................................................................................92 3.10.5 Digital – ARINC 429 Dual IOC Buses (Cat. 8 ID 251- 255) ..............................................................................92 3.10.6 Instructions..........................................................................................................................................................93 3.11 CATEGORY 9 – NAVIGATION INPUTS SELECT ............................................................................................................. 94 3.11.1 Navigation Inputs Select (Glideslope & Localizer Inputs)..................................................................................94 3.11.2 Glideslope Validity ..............................................................................................................................................94 3.11.3 Localizer Validity ................................................................................................................................................94 3.11.4 ILS Tuned Discrete Input #1 (+28V) and #2 (GND)...........................................................................................94 3.11.5 Analog Glideslope Interface (Cat. 9 ID 0,1,5) ....................................................................................................95 3.11.6 Digital Glideslope / Localizer / ILS Select Interface (Cat. 9 ID 2,3,4) ...............................................................96 3.11.7 Digital – ARINC 429 Dual IOC buses (Cat. 9 ID 250 - 255)..............................................................................96 3.11.8 Instructions..........................................................................................................................................................97 3.12 CATEGORY 10 – ATTITUDE INPUT SELECT .................................................................................................................. 98 3.12.1 Roll Angle............................................................................................................................................................98 3.12.2 Analog Pitch & Roll Angle (Synchro) (Cat. 10 ID 0,2,4)....................................................................................98 3.12.3 Digital Pitch & Roll Angle (ARINC 429 High Speed) (Cat. 10 ID 5 & 6) ..........................................................99 3.12.4 Digital – ARINC 429 Dual IOC buses (Cat. 10 ID 253 & 255) ..........................................................................99 3.12.5 Instructions..........................................................................................................................................................99 3.13 CATEGORY 11 – HEADING INPUT SELECT ................................................................................................................. 100 3.13.1 Magnetic Heading .............................................................................................................................................100 3.13.2 Analog Heading (Synchro) (Cat. 11 ID 0).........................................................................................................100 3.13.3 Digital – ARINC 429 AHRS Input (Cat. 11 ID 2 & 3).......................................................................................101 3.13.4 Digital – ARINC 429 Dual IOC buses (Cat. 11 ID 254 & 255) ........................................................................101 3.13.5 Instructions........................................................................................................................................................101 3.14 CATEGORY 12 – WINDSHEAR INPUT SELECT ............................................................................................................ 102 3.14.1 No Windshear....................................................................................................................................................102 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 49 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.14.2 Dual ARINC 429 BUS (Cat. 14 ID 253,254,255)..............................................................................................102 3.14.3 Instructions........................................................................................................................................................102 3.15 CATEGORY 13 – INPUT / OUTPUT DISCRETE TYPE SELECT ....................................................................................... 103 3.15.1 Input Discretes ..................................................................................................................................................103 3.15.1.1 Glideslope Inhibit Discrete .............................................................................................................................................103 3.15.1.2 Landing Flaps Discrete ...................................................................................................................................................103 3.15.1.3 Audio Inhibit Discrete.....................................................................................................................................................104 3.15.1.4 Landing Gear Discrete ....................................................................................................................................................104 3.15.1.5 Glideslope Cancel Discrete .............................................................................................................................................106 3.15.1.6 Momentary Flap Override Discrete.................................................................................................................................106 3.15.1.7 Mode 6 Low Volume Discrete ........................................................................................................................................106 3.15.1.8 Autopilot Engaged Discrete ............................................................................................................................................107 3.15.1.9 Terrain Awareness and TCF Inhibit Discrete..................................................................................................................107 3.15.1.10 Self Test Discrete ..........................................................................................................................................................107 3.15.1.11 Steep Approach Discrete #2..........................................................................................................................................108 3.15.1.12 GPWS INHIBIT Discrete (alternate action)..................................................................................................................108 3.15.2 Output Discretes................................................................................................................................................108 3.15.2.1 Lamp Format...................................................................................................................................................................109 3.15.2.2 Flashing Lamps ...............................................................................................................................................................109 3.15.2.3 GPWS INOP Discrete .....................................................................................................................................................109 3.15.2.4 TAD INOP Discrete........................................................................................................................................................109 3.15.2.5 GPWS Warning Discrete ................................................................................................................................................109 3.15.2.6 GPWS Alert Discrete ......................................................................................................................................................110 3.15.2.7 Glideslope Cancel’d Discrete..........................................................................................................................................110 3.15.2.8 Flap Override Discrete ....................................................................................................................................................110 3.15.2.9 Steep Approach Discrete.................................................................................................................................................110 3.15.2.10 Audio On Discrete (TCAS/TAS Inhibit).......................................................................................................................110 3.15.2.11 Terrain Display Select #1 & #2 Discrete.......................................................................................................................111 3.15.2.12 Terrain Pop up Discrete ................................................................................................................................................112 3.15.3 Instructions........................................................................................................................................................113 3.16 CATEGORY 14 – AUDIO OUTPUT LEVEL ................................................................................................................... 113 3.16.1 Instructions........................................................................................................................................................113 3.17 CATEGORY 15 - 17 – UNDEFINED INPUT SELECTS .................................................................................................... 114 3.17.1 Undefined Input Select ......................................................................................................................................114 3.17.2 Instructions........................................................................................................................................................114 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 50 Honeywell MK VI MK VIII EGPWS Installation Design Guide SECTION III – SYSTEM PLANNING 3.1 Introductio n This section provides information for selecting features and wiring the electrical interfaces of the MK VI/MK VIII EGPWS. Appendix E Section 5.2 groups features (functions) into sets called Categories. This document follows the Category structure of the Appendix E. It provides descriptions of the features and instructions for selecting features and for determining the correct wiring. Sample wiring diagrams for the most commonly used MK VI/MK VIII EGPWS configurations are provided in Appendix B. Make copies of Appendix E Table 5-2 to use for recording feature selections. Section 6 provides a cross-reference between the MK VI GPWS (Classic) and the MK VI/MK VIII EGPWS (Enhanced) interfaces. 3.2 System Wir ing/ Electrical Interfaces System wiring is broken down into the following main components: - Electrical Interfaces (power and ground) - GPS Antenna - Analog and Digital Inputs - Discrete Inputs - Serial Outputs - Audio Outputs - Discrete Outputs - Configuration Module Many of these inputs and outputs will be defined as the Categories are selected for Configuration Module programming. Appendix E Table 8.1-1 shows the typical usage for each pin on the Left (J1), Right (J2) and Upper (J3) connectors and provides a place for recording the actual usage for this installation. 3.2.1 Primary Po wer Input The MK VI/VIII EGPWC requires a primary power input (28 VDC input power) and ground. The Primary power should be connected as follows for the MK VI/VIII EGPWC. Pin Signal *Pin pairs J1-40/J1-60 and J1-40, J1-60 * +28 VDC Input J1-41/J1-61 are internally J1-41, J1-61 * +28 VDC Return shorted to each other. Recommended EGPWC Power Control Device: 3 Amp Delayed Action Circuit Breaker Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 51 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.2.2 Chassis Gr ound Chassis ground provides a redundant metal connection and should not be used as a normal current carrying conductor. Chassis ground should be connected as follows: Pin Signal J1-42, J1-53 GND Pins J1-42 and J1-53 are both connected to chassis ground internally. It is not necessary to tie them both to ground in the aircraft wiring. Pin J1-53 was made available to provide a convenient way to supply a ground to external equipment. If the OAT probe is not present, nothing needs to be tied to J1-53. 3.2.3 GPS Anten na A GPS antenna connector is available on the front of the MK VI EGPWS 965-1190-0XX and MK VIII EGPWS 965-1220-0XX. See Appendix E paragraphs 3.2.2 and 4.2.9 for connector details. The J1 connector backshell supplied with classic MK VI GPWS installation kits can interfere with the GPS antenna connector for this reason a new J1 backshell is supplied with MK VI-VIII installation kits. 3.2.4 Analog and Digital Inputs The analog and digital inputs to the MK VI/VIII EGPWS are defined as the Categories are selected. Instructions for documenting these interfaces are provided with the Category selection instructions. 3.2.5 Discrete Inp uts The discrete inputs are defined in Appendix E Section 6.6. Additional information for some discretes is provided within the Category in which they are used. 3.2.6 Serial Outp uts The EGPWC provides for ARINC 453 and ARINC 429 serial outputs. Terrain display data is output on two ARINC 453 channels when the Terrain Awareness display function is enabled. Low speed ARINC 429 output buses are provided by the EGPWC are described in Appendix E Section 7. The ARINC 429 output data includes: 1. Internal data (data output for test purposes only such as internal logic booleans, Geometric Altitude, and Terrain Clearance information). 2. Alert/Warning status (Voice and Lamp activity can be provided to display systems and flight recorders). 3. Internal mode status. 4. Terrain display messages for TAD cockpit integration. Note: During EGPWS Self Test, the SSM of each output label is set to the Functional Test status code. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 52 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.2.7 Audio Outp ut The audio outputs consist of both an 8-ohm amplifier and a transformer isolated 600-ohm output. Audio output messages are provided as specified in the selected Audio Menu (Category 5) when inputs are valid and the audio inhibit discretes are not active. When audio inhibit is enabled, the output discrete(s) associated with suppressed message(s) are active. 3.2.8 Discrete Ou tputs The MK VI/MK VIII EGPWS provides for up to twelve 0.5 amp nominal (1 amp maximum) Ground/Open discrete outputs. The discrete outputs are defined in Appendix E Section 4.2.11 and Category 13. The discrete outputs are optional if the ARINC 429 output data is used for driving the alert/warning lamps via a symbol generator. Most Aircraft Types do not use the ARINC 429 output data for lamp control. (This data is typically sent to the Flight Data Recorder.) All outputs to lamps are driven by solid state switches to ground. These outputs can also be used as discrete drivers for other devices (e.g. terrain display switching). Output discretes are intended to operate with +28 VDC lamp sources and will not operate with +5 VDC lamp sources. 3.2.9 Configurati on Module The EGPWS aircraft configuration is programmed into a configuration module installed in the aircraft wiring. This Configuration Module is identified as Honeywell part number 700-1710-020. The configuration module is installed as part of the P2 mating connector backshell and contains electrically reprogrammable memory for configuration storage. By this method the aircraft configuration is stored in the configuration module on the aircraft and each newly installed EGPWS computer does not require operator assisted programming before or during installation. The aircraft configuration in the Configuration Module can be changed at any time by use of the WinVIEWS software, as explained in Section 4. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 53 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.3 Category 1 - Aircraft / Mode Type Select Category 1 specifies the general aircraft type, warning mode differences, bank angle alert curve, fixed or retractable gear, and 3500 ft or 2000 ft min runway length (as an option for MK VIII EGPWS only). Appendix E Tables 5.2 and 5.3.1 include some information required by MK VI/MK VIII EGPWS development personnel and not pertinent to the installation design process. Only items relevant to the installation design process are discussed in this document. 3.3.1 Aircraft / M ode Type The Aircraft Type identifies the aircraft as GA Fast (Turboprop), GA Slow (Turboprop), or Bizjet (Turbofan). The aircraft category defines configurable airspeed limits for mode expansion and gear and flaps stuck down conditions (reasonable test) and also define the Mode 1, 2, 3, 4, & Bank Angle warning/alert curve options. The MK VI EGPWS only supports aircraft types 0,1,2,3,4 that are designed for turboprop aircraft (and emulate the mode curves of the MK VI GPWS). The MK VIII EGPWS has Aircraft types 254 & 255 that are designed for turbofan aircraft (and emulate the mode curves of the MK V GPWS), along with aircraft types 0,1,2,3,4. Modes 1,2,3,&4 are different between these aircraft types. For reference compare the mode 1-4 turbofan curves to the turboprop curves in the MK VI/VIII EGPWS Product Specification 965-1180-601. Appendix E Table 5.3.1 lists the combinations of Aircraft/Mode Types, identifies the first MK VI/MK VIII EGPWS version in which the option was available (see the Effectivity entry), and describes the options available with each Aircraft/Mode type (see Description column). 3.3.2 Mode 1 typ e Two Mode 1 alert curves are defined, GA (Turboprop) and Bizjet (Turbofan). The lower boundary of the GA Mode 1 curves is 50 feet, the same lower boundary is extended to 10 feet for Bizjet aircraft. 3.3.3 Mode 2 typ e Two Mode 2 alert curves are defined, one for GA Fast & Bizjet and one for GA Slow. Mode 2A airspeed expansion increases the Mode 2 expanded alert area linearly from 1650 feet to 2450 feet for airspeeds of 220 knots to 310 knots in GA Fast and Bizjet defined aircraft (same as MK V and MK VII EGPWS). Mode 2 airspeed expansion occurs for airspeeds from 190 knots to 280 knots in GA Slow defined aircraft. MODE 2 AIRSPEED EXPANSION GA FAST (Turboprop) 220 knots to 310 knots GA SLOW (Turboprop) 190 knots to 280 knots BIZJET (Turbofan) 220 knots to 310 knots Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 54 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.3.4 Mode 3 typ e Two Mode 3 alert curves are defined, GA (Turboprop) and Bizjet (Turbofan). The GA (Turboprop) Mode 3 curve is equivalent to the (classic) MK VI Mode 3 curve. The Bizjet (Turbofan) Mode 3 curve is equivalent to the MK V and MK VII EGPWS Mode 3 curves. 3.3.5 Mode 4 typ e Mode 4A (Too Low Gear) expanded alert transition occurs at 178 knots for GA Fast aircraft, 148 knots for GA Slow aircraft, and 190 knots for Bizjet aircraft. Mode 4B (Too Low Flaps) upper boundary has four defined levels, 245 ft, 200 ft, 170 ft, and 150 ft. The 245 ft boundary is added to emulate the MK V, VII Mode 4B boundary. The 200 ft boundary is added to emulate the MK II Mode 4B boundary. The 150 ft boundary (Alternate Mode 4B) is for those aircraft types that routinely delay full flap deployment. All other aircraft types would use the 170 ft boundary (Normal Mode 4B). For aircraft with previously installed (classic) MK VI GPWS, the Normal / Alternate Mode 4B correspond to the “Alternate Mode 4B” program pin (J1-25). The following table compares Mode 4 boundaries for each Aircraft type / Alternate Mode 4B Mode 4A Gear Down at 500 ft, < X knots Boundaries Mode 4B Flaps Down feet / < X knots Mode 4 A/B Maximum Mode 4 A/B Type 178 knots 170 ft / 150 knots 750 ft 6 GA Fast, Normal Mode 4B GA Fast, Alternate Mode 4B 178 knots 150 ft / 148 knots 750 ft 8 GA Slow, Normal Mode 4B 148 knots 170 ft / 120 knots 1 750 ft 7 GA Slow, Alternate Mode 4B 148 knots 1 750 ft 9 GA Fast, MK II emulation 178 knots 200 ft / 148 knots 1000 ft 5 Bizjet, MK V, VII emulation 190 knots 245 ft / 159 knots 1000 ft 1 150 ft / 118 knots NOTE 1: Some installations that have chosen the GA SLOW aircraft type have found during flight test that the aircraft can not (or does not) slow to less than 120 knots on normal approach. Thus the installation is prone to nuisance TOO LOW TERRAIN alerts. These installations should choose the GA FAST aircraft type. 3.3.6 Bank Angle Type Two Bank Angle callout curves are defined, GA (Turboprop) and Bizjet (Turbofan). Both Bank Angle callout curves have an Autopilot Engaged warning area. The Bizjet (Turbofan) Bank Angle callout curve is equivalent to the MK V and MK VII EGPWS Bank Angle callout curves when the autopilot is not engaged. Aircraft Type Lower Cutoff Lower Boundary Upper Boundary Slope GA (Turboprop) 10 ft 10 ft / 15° 210 ft / 50° 2450 ft / 50° Bizjet (Turbofan) 5 ft 30 ft / 10° 150 ft / 40° 2450 ft / 55° Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 55 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.3.7 Runway Le ngth (MK VIII EGPWS only) Two minimum runway length options are defined for Bizjet (Turbofan) aircraft. A 2000 ft minimum runway length or a 3500 ft minimum runway length may be chosen based on aircraft type as is identified in Appendix E Table 5.3.1. This option does not effect the mode curves as discussed above, and it is only available on MK VIII EGPWS. 3.3.8 Instruction s Using Appendix E Tables 5.2 and 5.3.1 as described above, select the Aircraft/Mode Type that matches the aircraft configuration, feature preferences and version (part number) being installed. Step 1: Is the aircraft a turbofan? YES, goto Step 2. NO, goto Step 3. Step 2: Aircraft can operate from runways less than 3500’? YES, use ID 255 NO, use ID 254 Step 3: Landing speed is typically > 120 knots? YES, goto Step 4. NO, goto Step 5. Step 4: 200’ / 170’ / 150’ Flap alert preferred? 200’ use ID 2 170’ use ID 0 150’ use ID 1 Step 5: 170’ / 150’ Flap alert preferred? 170’ use ID 3 150’ use ID 4 Record the ID number for the Aircraft/Mode Type from Appendix E Table 5.3.1 under the Ident No. heading for Step (Category) 1 in Appendix E Table 5.2. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 56 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.4 Category 2 – Air Data Input Select Category 2 defines the Air Data interface. The Air Data input currently defines 4 analog and 6 digital air data types. Appendix E Table 5.3.2 defines the Air Data interface options and identifies the first MK VI/MK VIII EGPWS version in which the option was available (see the Effectivity entry). Appendix E Tables 5.3.2-x, where x is the Air Data Type number, define the electrical interfaces required to support each Air Data Type. 3.4.1 Analog (Ca t. 2 ID 0, 3, 4, 11, 12) Air Data Type 0 (CIC 04077 or equivalent) uses Uncorrected Barometric Altitude input scaled from –1500 feet (+5 volts) to +30,000 feet (+15 volts) (see Appendix E section 6.1.3). Baro Altitude Rate and Computed Airspeed are not required. Baro Altitude Valid is standard +28 volt discrete. Total Air Temperature is from a dedicated (EGPWS) 500-ohm probe using +5 volt excitation from the MK VI/MK VIII EGPWC. Air Data Type 3 (ADS-65 or equivalent) uses Uncorrected Barometric Altitude input scaled from -1500 feet (0.18 volts) to +46,000 feet (+5.52 volts), zero volts equals zero feet (see Appendix E section 6.1.10). Baro Altitude Rate and Computed Airspeed are not required. Baro Altitude Valid is standard +28 volt discrete. Total Air Temperature is from a dedicated (EGPWS) 500-ohm probe using +5 volts excitation from the MK VI/MK VIII EGPWC. Air Data Type 4 (CIC 02702 or equivalent) uses Uncorrected Barometric Altitude input scaled from -1000 feet (0.244 volts) to +40,000 feet (+9.756 volts) (see Appendix E section 6.1.14). Baro Altitude Rate and Computed Airspeed are not required. Baro Altitude Valid is standard +28 volt discrete. Total Air Temperature is from a dedicated (EGPWS) 500-ohm probe using +5 volt excitation from the MK VI/MK VIII EGPWC. Air Data Types 11 and 12 (AZ-241, AZ-242, AZ-800, AZ-810 or equivalent) uses Uncorrected Barometric Altitude input scaled from -3750 feet ( 0 volts) to +50,000 feet (+10.75 volts) (see Appendix E section 6.1.16). Baro Altitude Rate and Computed Airspeed are not required. Baro Altitude Valid is standard +28 volt discrete. ID 11 requires a dedicated (EGPWS) 500-ohm Total Air Temperature probe using +5 volt excitation from the MK VI/MK VIII EGPWC. ID 12 is configured without a connection to outside air temperature with temperature set not available. As a result, when using ID 12 the EGPWS calculation of Geometric Altitude will be less accurate than using ID 11. NOTE: The analog air data interface for the MK VI / MK VIII EGPWS uses a dedicated 500-ohm temperature probe. This may be an unused element in a dual element probe but must not be paralleled with any other system. The EGPWS provides the 5 volt excitation for the element. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 57 Honeywell MK VI MK VIII EGPWS Installation Design Guide EGPWS MK VI / MK VIII Uncorrected Barometric Altitude J1 Analog Air Data Computer (+) 62 Altitude Out (-) 43 Signal Common Baro Altitude Valid +28V BIT Out 9 +5V Excitation 25 Temp. Input (+) 63 500 ohm Temperature Probe (-) 44 Chassis Ground 53 Analog-ADC.vsd Uncorrected Baro Altitude 1 Cat 2 Vendor Model ID Altitude Out Common BIT Out CIC 04077 0 J1-F J1-G J1-E Collins ADS-65 3 J1-12 J1-13 J1-5 CIC 02702 4 J1-A J1-B J1-E Honeywell AZ-241 Honeywell AZ-242 4 J1A-63 J1A-11 (CGND) J1A-12 11/12 2 4 J1B-17 J1A-11 (CGND) J1A-12 J1-J J1-G J1-U 11/12 2 J1A-78 J1A-10 (CGND) J1A-34 11/12 2 J1A-78 J1A-10 (CGND) J1A-34 11/12 2 J1A-17 J1A-10 (CGND) J1A-34 11/122 Honeywell AZ-648 Honeywell AZ-800 3 Honeywell AZ-810 3 Honeywell AZ-252 11/12 2 NOTES: 1 The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer’s customer service to confirm your installation. 2 ID 12 does not require an OAT input, instead a constant temperature of 25 deg C is assumed. 3 Honeywell AZ-810 should only be used as an analog source if it does not have a digital interface. 4 Honeywell AZ-242 with part numbers 4013242-708, -709, -710, -712, -713 and –742 have DC Altitude out at pin J1B-17. Part numbers 4013242-709 and -711 have DC Altitude out at pin J1A-40. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 58 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.4.2 Digital – AR INC 429 (Cat. 2 ID 5, 1, 6, 13) Air Data Type 1 is a low speed, digital ARINC 429 signal having the air data labels 203, 206, 212, and 213. Air Data Type 5 is a low speed, digital ARINC 429 signal having the air data labels 203, 204, 206, 212, and 213. Air Data Type 6 is a low speed, digital ARINC 429 signal having the air data labels 203, 206, and 213. Air Data Type 13 is a low speed, digital ARINC 429 signal having the air data label 203 only. If the hardware is capable of transmitting all label sets, the preferred Air Data Type is 5. If only label 204 is missing, use Air Data Type 1, and if both labels 204 and 212 are missing use Air Data Type 6. Some aircraft have only label 203 available (or no temperature) for those choose Air Data Type 13. EGPWS MK VI / MK VIII ARINC 429 Low Speed Air Data Bus J2 ARINC 429 Air Data A 39 A ARINC 429 Bus - Hi B 38 B ARINC 429 Bus - Lo Digital-ADC.vsd Cat 2 Bus 1 Bus 2 Vendor Model ID A B A B Honeywell AZ-6XX, AZ-8XX 5* J1B-26 J1B-27 J1B-70 J1B-71 CIC 04471 5* J1-12 J1-13 CIC 02702 mod 6 * J2-J J2-K KDC 281 * P2811-5 P2811-6 KDC 481 * P4811-U P4811- i B&D 90004 5* J1-27 J1-9 B&D 2600 6** 6 8 B&D 2601 6** 14 13 B&D 2800 * P201-11 P201-28 Collins ADC 85/86 5* P2-9 P2-10 P2-29 P2-30 Shadin ADC-2000 5* J1-40 J1-22 (s/w mod 71.73.01) NOTE: The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer’s customer service to confirm your installation. * Category 2, ID 5, 1, 6 or 13 depending on availability of labels 204 and 212. ID 5 is the preferred selection, then ID’s 1, 6, and 13 in order of preference. CIC air data computers installed without Baro Set pots should be configured as Cat 2 ID 1. ** EGPWS installations with the B&D 2600 ADC should be configured for Cat 2 ID 6 because the B&D 2600 Altitude Rate ARINC 429 label 212 has a poor response to altitude changes and causes nuisance alerts. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 59 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.4.3 Digital –AR INC 575 (Cat. 2 ID 2) Air Data Type 2 (ADC-80 or equivalent) is a low speed, digital ARINC 575 signal having the air data labels 203, 206, 212, and 213. EGPWS MK VI / MK VIII ARINC 575 Air Data Bus J2 ARINC 575 Air Data A 39 A ARINC 575 Bus - Hi B 38 B ARINC 575 Bus - Lo ARINC575-ADC.vsd Cat 2 Bus 1 Bus 2 Vendor Model ID A B Collins ADC-80( ) Collins ADC-82A 2 P3-35 P3-36 B&D 90004 2 J1-27 J1-9 NOTE: A B The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer’s customer service to confirm your installation. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 60 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.4.4 Shadin 200 0 (Cat. 2 ID 10) Air Data Type 10 (Shadin 2000 or equivalent) is a low speed, digital ARINC 429 signal having the air data labels 203, 204, 206, and 212. Total Air Temperature is from a dedicated (EGPWS) 500-ohm probe using +5 volt excitation from the MK VI/MK VIII EGPWC. EGPWS MK VI / MK VIII ARINC 429 Low Speed Air Data Bus ARINC 429 Air Data J2 A 39 A ARINC 429 Bus - Hi B 38 B ARINC 429 Bus - Lo J1 +5V Excitation 25 Temp. Input 500 ohm Temperature Probe (+) 63 (-) 44 Chassis Ground 53 Shadin2000.vsd Cat 2 Bus 1 Bus 2 Vendor PN ID A B 962830-1,2,3 962830A-1,2,3 962830A-X-S-4 962830A-X-S-5 10 J2-7 J1-40 J2-8 J1-22 NOTE: A B 10 The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer’s customer service to confirm your installation. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 61 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.4.5 Digital – AR INC 429 Dual IOC Buses (Cat. 2. ID 255) Air Data Type 255 (IOC bus or equivalent) is a dual, high speed, digital ARINC 429 signal having the air data labels 203, 204, 206, 210, 212, and 213. ID 255 may only be used in conjunction with other IOC bus selections for categories 6, 8, 9, 10, 11 and 12. EGPWS MK VI / MK VIII J2 IOC Buses ARINC 429 High Speed A 37 A B 36 B ARINC 429 High Speed A 41 A B 40 B IOC Bus 1 IOC Bus 2 ARINC429-IOC.vsd Cat 2 Vendor Model BD-100 CJ-1/CJ-2 NOTE: IOC Bus 1 IOC Bus 2 ID A B A B 255 255 A4P1-1 P1-1 A4P1-2 P1-2 A4P101-1 P101-1 A4P101-2 P101-2 The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer’s customer service to confirm your installation. 3.4.6 Instruction s Using Appendix E Tables 5.2, 5.3.2 and 5.3.2-x as described above, select the Air Data Type that matches the aircraft air data configuration, feature preferences and version (part number) being installed. Record the ID number for the Air Data Type from Appendix E Table 5.3.2 under the Ident No. heading for Step (Category) 2 in Appendix E Table 5.2. Using the Air Data Type number from Appendix E Table 5.3.2 as “x”, go the Air Data Input Select x Table. The electrical interfaces (pin-outs) for the Air Data Input Select are shown in Appendix E Table 5.3.2-x and are used to generate the installation wiring diagrams. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 62 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.5 Category 3 – Position Input Select Category 3 defines the Global Position System bus type and interface. The EGPWS requires a GPS with 8 channels minimum and RAIM capability. Appendix E Table 5.3.3 defines the Position Input Select options and identifies the first MK VI/VIII EGPWS version in which the option was available (see the Effectivity entry). Appendix E Tables 5.3.3-x, where x is the Position Input Type number, define the label set and electrical interface required to support each Position Input Type. GPS Input selection is available in the following formats: ARINC 429 low speed, ARINC 429 high speed, RS232, and Internal. The Internal GPS uses ID 2. A unit equipped with an internal GPS (965-1190-XXX and 965-1220-XXX) may use an external GPS source. See Category 7 to select GPS Altitude Reference (mean sea level or WGS-84) for ARINC 429 label 076. 3.5.1 ARINC 743 Format This option provides the ability to specify the GPS input data format as ARINC 743 instead of the ARINC 743A data format. For ARINC 743A the VFOM is in feet and the HFOM is in nautical miles (nm). For ARINC 743 both VFOM and HFOM are in meters. Note: Universal UNS-1 C/D/K/M GPS only, output is in ARINC 743 format. 3.5.2 GPS Altitud e (Label 076) Reference The GPS Altitude (label 076) may be referenced to mean sea level or WGS-84. Determine which reference your GPS position uses and program the GPS Altitude Reference accordingly in Category 7. Note: Universal UNS-1 C/D/K/M GPS only, output the Altitude Label 076 referenced to WGS-84. 3.5.3 North-Sout h East-West Velocity labels ID’s 10-13 and 253 are provided to support GPS interfaces that do not provide North-South East-West Velocity labels 166 & 174. ID’s 0,1,4,5, and 255 are preferred. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 63 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.5.4 ARINC 429 BUS (Cat. 3 ID 0,1,4,5,10-13) EGPWS MK VI / MK VIII ARINC 429 GPS Bus J2 ARINC 429 GPS A 25 A ARINC 429 Bus - Hi B B ARINC 429 Bus - Lo 8 ARINC429-GPS.vsd Vendor Model Collins GNLU-910A Collins GPS-4000 Cat 3 429 GPS Alt ARINC Bus 1 Bus 2 ID Speed Ref. 743/743A A B Note 5 High MSL 743A LMP-2J LMP-2K 2 2 MSL 743A MP-11A MP-11B A B 0/4 H/L UNS GPS-1000 1 Low WGS-84 743 TP-12A TP-12B TP-11A TP-11B UNS GPS-1200 0 Low MSL 743A TP-12A TP-12B TP-11A TP-11B UNS-1C 1 Low WGS-84 743 P1-a P1-b 1 Low WGS-84 743 MP-10J MP-10K 0 Low MSL 743A MP-10J MP-10K MP-4J MP-4K 1 Low WGS-84 743 MP-4C MP-4D 1 Low WGS-84 743 P2-K P2-L 0 Low MSL 743A J101-N5 1 J101-N6 1 0 Low MSL 743A J101-N5 1 J101-N6 1 0 Low MSL 743A JA-A01 JA-A02 1/5 2 H/L2 MSL 743 J1-38 J1-39 J1-24 J1-25 2 2 MSL 743A J1-38 J1-39 J1-24 J1-25 J1-58 J1-57 (1017-3X-XXX) or (1017-4X-XXX) UNS-1D (1192-00-1111XX) or (1192-30-1111XX) UNS-1F, -1E, -1L (2192-00-11110X) UNS-1K (1116-3X-111X) or (1116-4X-111X) UNS-1M (1013-4X-XXX) GNS-XLS (17960-0203-) SM04 (17960-0102-) SM07 GNS-XL (18355-) SM06 GNS-X / CDU-XLS (14141-0624-) SM04 HG2021GBXX HG2021GC/GDXX 0/4 H/L HT1000/HT9100 FreeFlight (Trimble) 2101 I/O Approach Plus 10/12 H/L WGS-84 743A MP-C02 MP-C01 0 Low MSL 743A J1-16 J1-23 (81440-XX software ver. 241F) NOTE: 1 2 3 4 5 The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer’s customer service to confirm your installation. The Enhanced GNS-XLS ARINC 429 bus also contains Range label HG2021G: Pin 21 open = high speed; Pin 21 GND = Low speed; GPS-4000: North/South Velocity (label 166) and East/West Velocity (label 174) are required in MK VI / MK VIII -008 software and on. NOT COMPATIBLE with MK VI / MK VIII EGPWS Honeywell HT-9000 / KLN-89 / KLN-90 / HG2021AB / GNS-XES IIMorrow Apollo 2101 Trimble 2100 / 2101 / TNL8100 Universal GPS-950, UNS-1B Check manufacturer for compatibility with North-South, East-West Velocities. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 64 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.5.5 RS-232 Tra nsmit-Receive, 9600 baud (Cat. 3 ID 3) EGPWS MK VI / MK VIII RS – 232 GPS Bus J2 RS-232 GPS NC TX 45 RX 29 TX – Transmit Out CM 28 GND RX – Receive In RS232-GPS.vsd Vendor Model GARMIN GNS430/530 2 GPS Alt ARINC NS3 Ref. 743/743A EW MSL N/A MSL MSL RS-232 RX TX GND Note 3 P4001-56 Chassis N/A OK P9002-13 Chassis N/A OK P941-6 Chassis Software Version 2.21 KLN 900 066-04034-0104 or 066-04034-0204 KLN 94 NOTE: The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer’s customer service to confirm your installation. 1 The KLN 89/89B/90/90A/90B are not compatible. 2 The GNS 430 software mod is also applicable to the GPS 400 and GNC 420 units. 3 Check manufacturer for compatibility with North-South, East-West Velocities. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 65 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.5.6 Dual ARINC 429 BUS (Cat. 3 ID 253 & 255) NOTE: If GPS #2 is not installed in the aircraft, then use ID 4 or GPS bus #1 must be connected in parallel to both EGPWS GPS input ports. NOTE: Non-IOC aircraft can use ID 253 or 255 to activate dual GPS inputs for redundancy and improved system availability, but the interface must have dual High Speed 743A GPS, and this cannot be used if using Category 10 ID 5 or Category 11 ID 2. EGPWS MK VI / MK VIII ARINC 429 GPS Bus ARINC 429 GPS Bus J2 ARINC 429 GPS A 25 A Hi B 8 B Lo A 23 A Hi B B Lo ARINC 429 Bus 1 ARINC 429 Bus 2 6 ARINC429-DualGPS.vsd Aircraft Model Cat 3 429 GPS Alt ARINC ID Speed Ref. 743/743A A B A B 253 Bus 1 Bus 2 1 BD 100 255 High MSL 743A A25BP1-6A A25BP1-6B A24BP1-6A A24BP1-6B CJ1/CJ2 255 High MSL 743A TBD TBD TBD TBD NOTE: 1 The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer’s customer service to confirm your installation. ID 253 is a optional configuration for compatibility with IOC that are missing North-South, East-West Velocities labels. 3.5.7 Instruction s Using Appendix E Tables 5.2, 5.3.3 and 5.3.3-x as described above, select the Position Input Type that matches the aircraft Position Input configuration, feature preferences and version (part number) being installed. Record the ID number for the Position Input Type from Appendix E Table 5.3.3 under the Ident No. heading for Step (Category) 3 in Appendix E Table 5.2. Using the Position Input Type number from Appendix E Table 5.3.3 as “x”, go the Position Input Select x Table. The electrical interfaces (pin-outs) for the Position Input Select are shown in Appendix E Table 5.3.3-x and are used to generate the installation wiring diagrams. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 66 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.6 Category 4 – Altitude Callouts Category 4 defines the Altitude Callout menu choices and Smart ‘500’ Callout selection. Appendix E Table 5.3.4 defines the Altitude Callout Menu options and identifies the first MK VI/MK VIII EGPWS version in which the option was available (see the Effectivity entry). The Altitude callout menus have selected combinations of “Minimums-Minimums”, “Minimums”, “1000”, Smart “500”, “500”, “500 Above” Field, “400”, “300”, “200”, “100”, “50”, “40”, “30”, “20”, and “10”. No altitude callouts may also be selected. The Altitude Callout menu provides altitude annunciation for descent below predefined altitudes (example: “One Hundred” is annunciated when descending through 100 feet radio altitude). A “500” foot callout is available that will issue a “500” callout once during each approach when the aircraft is 500’ AGL. A “Smart 500” foot callout is available that will issue a “500” callout when the aircraft is 500’ AGL. This callout is active only during non-precision approaches or when the Glideslope or Localizer deviation is greater than 2 dots. The “500 Above” Field callout will be annunciated once during each approach when the aircraft is within 5 nm of a runway in the database and descends through 500 ft above that runway. It compares the GPS-based geometric altitude with the closest runway field elevation. The callout may be optionally chosen to annunciate “Five Hundred” or “Five Hundred Above”. This requires Category 6 ID other than 2 (TAD/TCF must be active). “Minimums-Minimums” callout can be selected or deselected from these combinations by connecting or not connecting the Decision Height (DH) discrete (J1-33) of Category 8. Recommendation: Honeywell recommends at least a Smart ‘500’ callout and a “Minimums-Minimums” callout. FAA and JAA approved installations require a 500 foot callout. Using Appendix E Table 5.2 and 5.3.4 as described above, select the preferred Altitude Callout Menu Type (ID) that matches the feature preferences and version (part number) being installed. Record the ID number for the Altitude Callout Menu Type from Appendix E Table 5.3.4 under the Ident No. heading for Step (Category) 4 in Appendix E Table 5.2. If the “Minimums-Minimums” callout will be used, use the electrical interfaces (pin-outs) for Radio Altitude Input Select Type (Category 8) shown in Appendix E Table 5.3.8-x to generate the installation wiring diagrams. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 67 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.7 Category 5 – Audio Menu Select Category 5 defines four Audio Menu options. Retractable Gear aircraft, Type 0 (basic) and Type 1 (alternate) and Fixed Gear aircraft, Type 2 (basic) and Type 3 (alternate). Appendix E Table 5.3.5 defines the Audio Menu select options and identifies the first MK VI/MK VIII EGPWS version in which the option was available (see the Effectivity entry). Appendix E Tables 5.3.5-x, where X is the Audio Menu Type, defines the voice callouts for each menu. DGACregistered aircraft are required to use Alternate Audio Menu. Recommendation: Honeywell recommends the Basic Audio Menu (except for DGAC-registered aircraft). 3.7.1 Audio Menu Selection Audio menu must be selected to provide EGPWS callouts. The differences in the Audio Menu Types are shown in the following comparison tables. ALERT/WARNING Audio Menu CONDITION Basic (Type 0 and 2) Alternate (Type 1 and 3) Terrain Awareness Preface Terrain Terrain Terrain Ahead Obstacle Awareness Preface Obstacle Obstacle Obstacle Ahead Terrain Awareness Caution Caution Terrain Terrain Ahead Obstacle Awareness Caution Caution Obstacle Obstacle Ahead ALERT/WARNING Audio Menu Retractable Gear Fixed Gear (Type 0 and 1) (Type 2 and 3) CONDITION Mode 4 Too Low Gear Too Low Gear Too Low Flaps 3.7.2 Instruction s Using Appendix E Tables 5.2, 5.3.5 and 5.3.5-x as described above, select the Audio Menu Type that matches the feature preferences and version (part number) being installed. • • Basic or Alternate menu Retractable Gear or Fixed Gear Record the ID number for the Audio Menu Type from Appendix E Table 5.3.5 under the Ident No. heading for Step (Category) 5 in Appendix E Table 5.2. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 68 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.8 Category 6 – Terrain Display Select Category 6 defines the Terrain Display options available. TA&D and TCF mode enabling/disabling is controlled by Category 6. Peaks mode availability is controlled by Category 6 since its availability is determined by the display configuration. Peaks mode enabling/disabling is controlled by Category 7. Each of the options controlled by Category 6 is described below. Appendix E Table 5.3.6 defines the Terrain Display Select options (Display Configuration Group Tables, Display Input Control Group Tables and Output 429 Bus Group Tables) and identifies the first MK VI/MK VIII EGPWS version in which the option was available (see the Effectivity entry). Appendix E Table 5.3.6 also defines the EGPWS version (MK VI or MK VIII) in which the option is available (see the EGPWS entry). Appendix E Tables 5.3.6.1-x, where x is the Display Configuration group number, define the display options and the electrical interface required to support each Display Configuration. Appendix E Tables 5.3.6.2-x, where x is the Display Input Control group number, define the label set and the electrical interface required to support each Display Configuration. Appendix E Tables 5.3.6.3-x, where x is the Output 429 Bus group number, define the label set and the electrical interface supporting each Display Configuration output requirements. Figure 3.8-1 is an example of single tube Wx/Terrain display wiring connections. 3.8.1 TAD & TCF Selection The Terrain Clearance Floor (TCF) algorithm identifies premature descent for approaches regardless of aircraft configuration. It creates a terrain clearance envelope around the airport to provide protection against controlled flight into terrain situations beyond that of the basic GPWS. The Terrain Awareness & Display feature consists of a Terrain Awareness Alerting feature and a Terrain Awareness Display feature. The Terrain Awareness Alerting feature continuously computes terrain clearance envelopes ahead of the aircraft and issues alerts if the boundaries of these envelopes conflict with terrain elevation data in the terrain database. The Terrain Awareness Display feature displays the data terrain relative to aircraft altitude. Both TA&D and TCF are Enabled for all ID’s in Appendix E Table 5.3.6 except for “TA&D and TCF Disable” (ID 2). Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 69 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.8.2 Terrain Dis play Configuration Group This option provides the ability to specify the type of Terrain Display compatible with the aircraft configuration. A definition of each of the entries in the Display Configuration Group tables is provided in the table below. Function Value Reference section Display Type Display manufacturer, model, etc. Sweep Type The type of sweep used for terrain data (fan, standard, etc.) Auto Pop Up Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True The TA&D Alternate Pop Up is set to The TA&D Alternate Pop Up is set to False or True in Category 7. If False, False or True in Category 7. If True, Pop Up behavior for the terrain Pop Up behavior for the terrain display is described here. display is described here. Category 7, Options Select Group #1 Peaks Mode See Note 1 Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type Peaks Enable: False Peaks Enable: True Peaks Enable is set to False or True Peaks Enable is set to False or True in Category 7. The effect of setting it in Category 7. The effect of setting it to False is described here. to True is described here. Describes if/when terrain display(s) can be manually selected Describes if/when terrain display(s) can be manually deselected Defines if the display data is automatically scaled and, if so, the scale used (such as 10 nautical miles) Indicates whether or not a moving marker is provided Describes where “TERR” and Peaks Elevations overlays will be located on the display screen. Defines the display bus type ‘KC Picture Bus’ (KCPB was ASPB), ‘Honeywell Picture Bus’ or ‘ARINC 453’. CHANNEL CONNECT TO: TX453-1 A = J1-58 Indicates the correct connection for these pins B = J1-59 CHANNEL CONNECT TO: TX453-2 A = J1-56 Indicates the correct connection for these pins B = J1-57 Notes: 1 Peaks Mode “(Not Available)” or “(Elevations via overlay)” shown here. Peaks mode “Not Available” means that this display type cannot display Peaks Mode. Table 3.8.2-1 Definition of Display Configuration Group Tables (Appendix E Section 5.3.6) 3.8.3 Display Inp ut Control Group This input bus is connected to the display (or display controller) and transmits Range settings, Display Mode, and Display status to the MK VI/MK VIII EGPWC. In some installations where the terrain display(s) is controlled from one source (controller) the Range inputs to the EGPWS must be paralleled to satisfy dual input requirements of the EGPWS. Display Input Control Group CHANNEL 429_422RX_1 A = J2-37 B = J2-36 CHANNEL 429RX_3 A = J2-41 B = J2-40 CONNECT TO: WXR Output 429 bus 1 Data Range Status CONNECT TO: WXR Output 429 bus 1 Data Range Status Fault Designation: DISPLAY BUS 1 Bus Type: Basic Reference Label Sig. Bits Range Signal Type Resolution Rate (ms) Resolution Rate (ms) Fault Designation: DISPLAY BUS 2 Bus Type: Basic Reference Label Sig. Bits Range Signal Type Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 70 Honeywell MK VI MK VIII EGPWS Installation Design Guide In some installations where the Radar (Terrain) displays are controlled from one source, the Range input buses into the EGPWS must be paralleled to satisfy EGPWS dual input requirements. CONN PIN # REFERENCE NAME PIN FUNCTION J1-32 GND_DISC_12 Reference 6.6.18 J1-31 GND_DISC_13 Reference 6.6.19 Display Select Discrete #1 Display Select Discrete #2 Polarity/Configuration Type 1 (Momentary) Gnd = Display Select ToggleGnd = Normal Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal 3.8.4 Output 429 Bus Group This output bus is commonly connected to EFIS and/or EICAS displays and Flight Recorders. The output transmits MK VI/MK VIII EGPWC alert, fault, and mode status to other systems. Channel Pins 429TX_1 A = J2-43 B = J2-42 A = J2-26 B = J2-9 429TX_2 Output 429 Bus Group Comments Transmits Label sets: (Section 7) No Connection (No Data Output) 3.8.5 Instruction s Using Appendix E Tables 5.2, 5.3.6, and 5.3.6.1-x as described above, select the Terrain Display Select Type (ID) that matches the aircraft configuration, feature preferences and version (part number) being installed. Record the ID number for the Terrain Display Select Type from Appendix E Table 5.3.6 under the Ident No. heading for Step (Category) 6 in Appendix E Table 5.2. Record the Display Configuration Group number here ! _______________. Note: This information is used to determine TA&D Alternate Pop Up and Peaks Mode availability for Category 7. The electrical interfaces (pin-outs) for the Display Configuration Group, Display Input Control Group, and Output 429 Bus Group are shown in the Appendix E Table 5.3.6.1-x and are used to generate the installation wiring diagrams. 3.8.6 Sample Dis play Schematics Honeywell GNS-XLS Honeywell KMD 540 / 550 / 850 Honeywell Grimes TRA-45A Honeywell Primus UDI with Avtech DSU Honeywell Primus 440/660/880 Integrated Honeywell Primus 1000 Honeywell Bendix RDR 2000 / IN182A Honeywell Bendix PPI-4B Honeywell Bendix EFS-40/50 Collins WXI-701/711 Collins Pro-Line II / IV Honeywell SPZ8000 / SG-802/803/806 Universal MFD-640 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 71 CAGE CODE: 97896 SCALE: NONE SIZE: A No connection 28V Lamp Dimming Bus N6 B B 36 B 57 A 56 B 59 A 58 DWG NO: 060-4314-150 REV: MK VI 965-11X0-020 or later. MK VIII 965-12X0-020 or later. Terrain INOP (out) 55 TERR INHIB TERR INOP Note: GNS-XLS will not perform auto pop-up during Alert. For interface and operation of the GNS-XLS see Honeywell GNS-XLS System Installation Manual 006-10528-0000 Alternate Action Lamp Test Q5 KCPB Video in (L) B 40 J1 Q6 B 70-ohm termination A 41 Honeywell GNS-XLS GNS-XLS-1.vsd 17960-0203-XXXX SM04 Q4 A KCPB Video in (H) Range & GPS out GNS-XLS 8 B A 25 N5 A J101 A 37 J2 Terrain Inhibit (in) 12 KCPB Video #2 Out KCPB Video #1 Out ARINC 429 Range #2 In ARINC 429 GPS In ARINC 429 Range #1 In EGPWS Honeywell MK VI MK VIII EGPWS Installation Design Guide Proprietary notice on title page applies SHEET 72 CAGE CODE: 97896 SCALE: NONE SIZE: A B 57 A 56 B 59 A 58 J1 B 40 A 41 No connection DWG NO: 060-4314-150 REV: MK VI 965-11X0-020 or later. MK VIII 965-12X0-020 or later. Terrain INOP (out) 55 28V Lamp Dimming Bus TERR INHIB TERR INOP Note: For interface and operation of the Honeywell KMD 540/550/850 see Honeywell Installation Manual P/N 006-10608-0001 Alternate Action Lamp Test 429 Out Honeywell KMD 540/ 550/850 KMD540-1.vsd 12 A KCPB Video in 13 B (No termination) 31 30 B 11 B 36 KMD 540/550/850 29 A J3001 A 37 J2 Terrain Inhibit (in) 12 KCPB Video #2 Out KCPB Video #1 Out ARINC 429 Range #2 In ARINC 429 Range #1 In EGPWS Honeywell MK VI MK VIII EGPWS Installation Design Guide Proprietary notice on title page applies SHEET 73 CAGE CODE: 97896 SCALE: NONE SIZE: A Lamp Test 28V Lamp Dimming Bus DWG NO: 060-4314-150 REV: MK VI 965-11X0-020 or later. MK VIII 965-12X0-020 or later. Terrain INOP (out) 55 Note: For interface and operation of the Honeywell Grimes TRA-45A see Honeywell TRA-45A Equipment Installation Manual P/N 34-40-01 Alternate Action 80-5145-X-2 TRA45.vsd A KCPB Video in B 70-ohm termination Range out Honeywell Grimes TRA-45A 3 B 57 TERR INHIB TERR INOP 1 A 56 13 B B 59 TRA-45A 80-5145-X-2 28 A J1 3 A 58 J1 B 40 A 41 Range out TRA-45A A KCPB Video in B 70-ohm termination 13 B B 36 1 28 A J1 A 37 J2 Terrain Inhibit (in) 12 KCPB Video #2 Out KCPB Video #1 Out ARINC 429 Range #2 In ARINC 429 Range #1 In EGPWS Honeywell MK VI MK VIII EGPWS Installation Design Guide Proprietary notice on title page applies SHEET 74 CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 open TERR momentary A B 57 A 56 REV: MK VI 965-11X0-020 or later. MK VIII 965-12X0-020 or later. Terrain INOP (out) 55 TERR INHIB TERR INOP 19 13 18 9 6 18 9 Lamp Test 28V Lamp Dimming Bus Terrain Status 32 Terrain Select 2 J2 3 3 KCPB Video in Note: For interface and operation of the Avtech 6001 DSU see Avtech DSU Installation and Operation Procedure P/N 6001-1680 Alternate Action ON 6 Display Invalid 48 B B 59 13 16 12 16 10 4 8 15 7 17 11 5 NC 4 8 15 7 17 11 5 P/N 6001-1 14 PrimusUDI-1.vsd AVTECH DSU 10 F MK L AGC P B V 1 AVTECH DSU Primus WXR UDI 12 J E S U T D HR 19 Range out 2 N 2 7 47 A 9 B 49 8 A 58 J1 B 40 J1 440, 650 w/ Lightning, 660, 700, 870, 880 B 36 A 41 450, 650 w/o Lightning, 800 90, 100, 200, 300, 300SL, 400, 500, AVQ30 PRIMUS SERIES A 37 Terrain Inhibit (in) 12 KCPB Video #2 Out KCPB Video #1 Out ARINC 429 Range #2 In ARINC 429 Range #1 In EGPWS J2 Honeywell MK VI MK VIII EGPWS Installation Design Guide Proprietary notice on title page applies SHEET 75 CAGE CODE: 97896 SCALE: NONE SIZE: A NC B 57 A 56 B 59 A 58 DWG NO: 060-4314-150 REV: MK VI 965-11X6-004 or later. MK VIII 965-12X6-004 or later. Terrain INOP (out) 55 Terrain Inhibit (in) 12 Terrain Display Select (out) 54 NC J1 B 40 A 41 TERR INHIB TERR INOP momentary Lamp Test 28V Lamp Dimming Bus Note: For interface and operation of the Honeywell Weather Radar Indicator WI-440, 660, 880 see Honeywell Service Bulletin 7007700-34-15 Alternate Action ON TERR P N WXPD Bus IntP880.vsd Integrated Primus 440/660/880 28V EGPWS PWR Bus WI-440, 660, 880 7007700-X1X X EGPWS Selected L M P SCI Bus Honeywell Radar Indicator G N 4 B 37 3 F 71 72 WU-440, 660, 880 A 36 Terrain Display Select (in) 32 ARINC 453 Video #2 Out ARINC 453 Video #1 Out Range #2 In RS-422 Serial Range #1 In EGPWS J2 Honeywell WRX R/T Honeywell MK VI MK VIII EGPWS Installation Design Guide Proprietary notice on title page applies SHEET 76 CAGE CODE: 97896 SCALE: NONE SIZE: A B 40 DWG NO: 060-4314-150 REV: MK VIII 965-12X0-020 or later. Terrain Inhibit (in) 12 58 ARINC 453 Symbol A Generator Out B 59 ARINC 429 Range #2 In A 41 J1 Lamp Test 28V Lamp Dimming Bus Alternate Action TERR INHIB 25 B B 36 PILOT 7017000 EGPWS Cont 429 Out 453 Bus In 7014300 453 Bus In 7014300 25 B 12 A 42 B 41 A Honeywell Primus 1000 Primus1000.vsd 7017000 429 Out CO-PILOT EGPWS Cont Integrated Avionics Computer IC-600 75 B 61 Display Unit DU-870 74 A 75 B Display Unit DU-870 74 A 42 B 41 A 12 A Integrated Avionics Computer IC-600 A 37 J2 ARINC 429 A 43 Control Bus Out B 42 ARINC 429 Range #1 In EGPWS Honeywell MK VI MK VIII EGPWS Installation Design Guide Proprietary notice on title page applies SHEET 77 CAGE CODE: 97896 SCALE: NONE SIZE: A B 57 A 56 B 59 A 58 DWG NO: 060-4314-150 REV: MK VI 965-11X0-020 or later. MK VIII 965-12X0-020 or later. Terrain INOP (out) 55 Terrain Inhibit (in) 12 Terrain Display Select (out) 54 NC J1 B 40 A 41 TERR INHIB TERR INOP momentary Lamp Test 28V Lamp Dimming Bus Note: For interface and operation of the Honeywell RDR 2000 Color Weather Radar system see Honeywell Installation Manual 006-00643-0000 Alternate Action ON TERR 42 43 H T/R Data Bus RDR2000.vsd Honeywell / Bendix RDR 2000 / IN182A 28V EGPWS PWR Bus IN182A 066-3084-XX 31 RT On/Off 1 20 C 1 2 Control Bus A Honeywell Radar Indicator B 31 B 36 3 27 A 2 ART 2000 A 37 Terrain Display Select (in) 32 ARINC 453 Video #2 Out ARINC 453 Video #1 Out ARINC 429 Range #2 In ARINC 429 Range #1 In EGPWS J2 Honeywell WRX R/T Honeywell MK VI MK VIII EGPWS Installation Design Guide Proprietary notice on title page applies SHEET 78 CAGE CODE: 97896 SCALE: NONE SIZE: A B 57 A 56 B 59 A 58 DWG NO: 060-4314-150 REV: MK VI 965-11X0-020 or later. MK VIII 965-12X0-020 or later. Terrain INOP (out) 55 Terrain Inhibit (in) 12 Terrain Display Select (out) 54 NC J1 B 40 A 41 Alternate Action ON TERR TERR INHIB TERR INOP momentary Lamp Test 28V Lamp Dimming Bus H T/R Data Bus L T/R Data Bus PPI4A4B.vsd Honeywell / Bendix PPI-4B 28V EGPWS PWR Bus PPI-4B 2041222-XXXX 15 RT On/Off 1 5 12 C 70-ohm termination 5 Control Bus A Honeywell Radar Indicator 11 B 2D 3D B 36 6B 10 A BP 3B 4B RTA-4B A 37 Terrain Display Select (in) 32 ARINC 453 Video #2 Out ARINC 453 Video #1 Out ARINC 429 Range #2 In ARINC 429 Range #1 In EGPWS J2 Honeywell WRX R/T Honeywell MK VI MK VIII EGPWS Installation Design Guide Proprietary notice on title page applies SHEET 79 CAGE CODE: 97896 SCALE: NONE SIZE: A 51 TERRAIN POP-UP OUT DWG NO: 060-4314-150 REV: 12 32 TERRAIN INOP TERRAIN INHIBIT SWITCH IN TERRAIN SELECT SWITCH IN 54 TERRAIN SELECT RELAY OUT 55 60 40 +28VDC POWER IN +28VDC POWER IN SEE NOTE 3. 58 59 J1 41 37 36 40 J2 KCPB A OUT KCPB B OUT NO. 2 DISPLAY RANGE 429 A IN NO. 1 DISPLAY RANGE 429 A IN NO. 1 DISPLAY RANGE 429 B IN NO. 2 DISPLAY RANGE 429 B IN MARK VI/VIII ENHANCED GROUND PROXIMITY WARNING COMPUTER 429 CONTROL BUS 1A IN 429 CONTROL BUS 1B IN SEE NOTE 2. 453 DATA BUS A OUT 453 DATA BUS B OUT BENDIX/KING WEATHER RADAR R/T EGPWS ANNUNCIATOR PRESS-TO-TEST ANNUNCIATOR DIMMER BUS SEE NOTE 1. SEE NOTE 1. +28VDC AVIONICS POWER SEE NOTE 1. SEE NOTE 1. ANNUNCIATOR DIMMER BUS (ALTERNATE ACTION) EGPWS FAIL TERRAIN INHIBIT SEE NOTE 1. (MOMENTARY) ON TERRAIN STANDBY NORMAL ANNUNCIATOR PRESS-TO-TEST DISPLAY DOWN NORMAL SEE NOTE 1. SEE NOTE 1. SEE NOTE 1. TERRAIN SELECTED DISCRETE IN TERRAIN POP-UP DISCRETE IN 453 DATA BUS A IN 453 DATA BUS B IN R/T TRANSMITTER 429 A OUT R/T TRANSMITTER 429 B OUT MFD SYMBOL GENERATOR BENDIX/KING SG 465 R/T TRANSMITTER 429 A OUT R/T TRANSMITTER 429 B OUT SYMBOL GENERATOR #1 BENDIX/KING SG 465 4. THIS CONFIGURATION IS NOT SUPPORTED PRIOR TO EGPWS COMPUTER PART NUMBERS: 965-1180-020 MARK VI EGPWS 965-1190-020 MARK VI EGPWS W/INTERNAL GPS 965-1210-020 MARK VIII EGPWS 965-1220-020 MARK VIII EGPWS W/INTERNAL GPS 3. THE CATEGORY 6 DISPLAY TYPE ID 10 (INTEGRATED EFIS 40/50) IS THE REQUIRED CONFIGURATION. THE CATEGORY 13 I/O DISCRETE TYPE ID 1 (LAMP FORMAT 2) IS THE PREFERRED CONFIGURATION. 2. REFER TO THE WEATHER RADAR SECTION OF THIS MANUAL (3.13) FOR THE COMPLETE INTERFACE TO THE BENDIX/KING WEATHER RADARS. 1. USE M17/176-0002 SHIELDED WIRE OR 024-00064-0000 QUADRAX CABLE FOR THE 453 DATA BUS AND THE KCPB. NOTES: 22 P465 1A 37 P465 1B 22 49 68 81 P465 2B 22 49 P465 2B Honeywell MK VI MK VIII EGPWS Installation Design Guide Proprietary notice on title page applies SHEET 80 CAGE CODE: 97896 SCALE: NONE 51 60 40 54 TERRAIN POP-UP OUT +28VDC POWER IN +28VDC POWER IN TERRAIN SELECT RELAY OUT SIZE: A 55 12 32 TERRAIN INOP TERRAIN INHIBIT SWITCH IN TERRAIN SELECT SWITCH IN SEE NOTE 3. 58 59 J1 41 37 36 40 J2 KCPB A OUT KCPB B OUT NO. 2 DISPLAY RANGE 429 A IN NO. 1 DISPLAY RANGE 429 A IN NO. 1 DISPLAY RANGE 429 B IN NO. 2 DISPLAY RANGE 429 B IN MARK VI/VIII ENHANCED GROUND PROXIMITY WARNING COMPUTER 453 DATA BUS A OUT 453 DATA BUS B OUT 429 CONTROL BUS 1A IN 429 CONTROL BUS 1B IN SEE NOTE 2. BENDIX/KING WEATHER RADAR R/T EGPWS ANNUNCIATOR PRESS-TO-TEST ANNUNCIATOR DIMMER BUS SEE NOTE 1. SEE NOTE 1. +28VDC AVIONICS POWER SEE NOTE 1. SEE NOTE 1. (MOMENTARY) ON EGPWS FAIL (ALTERNATE ACTION) TERRAIN TERRAIN INHIBIT SEE NOTE 1. ANNUNCIATOR PRESS-TO-TEST ANNUNCIATOR DIMMER BUS SEE NOTE 1. TERRAIN SELECTED DISCRETE IN TERRAIN POP-UP DISCRETE IN 453 DATA BUS A IN 453 DATA BUS B IN R/T TRANSMITTER 429 A OUT R/T TRANSMITTER 429 B OUT MFD SYMBOL GENERATOR BENDIX/KING SG 465 965-1180-020 MARK VI EGPWS 965-1190-020 MARK VI EGPWS W/INTERNAL GPS 965-1210-020 MARK VIII EGPWS 965-1220-020 MARK VIII EGPWS W/INTERNAL GPS 4. THIS CONFIGURATION IS NOT SUPPORTED PRIOR TO EGPWS COMPUTER PART NUMBERS: 3. THE CATEGORY 6 DISPLAY TYPE ID 10 (INTEGRATED EFIS 40/50) IS THE REQUIRED CONFIGURATION. THE CATEGORY 13 I/O DISCRETE TYPE ID 1 (LAMP FORMAT 2) IS THE PREFERRED CONFIGURATION. 2. REFER TO THE WEATHER RADAR SECTION OF THIS MANUAL (3.13) FOR THE COMPLETE INTERFACE TO THE BENDIX/KING WEATHER RADARS. 1. USE M17/176-0002 SHIELDED WIRE OR 024-00064-0000 QUADRAX CABLE FOR THE 453 DATA BUS AND THE KCPB. NOTES: 22 P465 1A 37 P465 1B 22 49 68 81 P465 2B Honeywell MK VI MK VIII EGPWS Installation Design Guide Proprietary notice on title page applies DWG NO: 060-4314-150 REV: SHEET 81 CAGE CODE: 97896 SCALE: NONE SIZE: A B 57 A 56 B 59 A 58 DWG NO: 060-4314-150 REV: MK VI 965-11X0-020 or later. MK VIII 965-12X0-020 or later. Terrain INOP (out) 55 Terrain Inhibit (in) 12 Terrain Display Select (out) 54 NC J1 B 40 A 41 Alternate Action ON TERR 8 TERR INHIB TERR INOP momentary 6B 9 Lamp Test 28V Lamp Dimming Bus H T/R Data Bus L T/R Data Bus WXI-701.vsd Rockwell Collins WXI-701/711 28V EGPWS PWR Bus 2041222-XXXX 15 RT On/Off 1 6 12 C 70-ohm termination 5 Control Bus A Collins WXI-701 Radar Indicator 11 B ? B 36 ? 10 A J1 A 37 Terrain Display Select (in) 32 ARINC 453 Video #2 Out ARINC 453 Video #1 Out ARINC 429 Range #2 In ARINC 429 Range #1 In EGPWS J2 WRT-XXX Collins WRX R/T Honeywell MK VI MK VIII EGPWS Installation Design Guide Proprietary notice on title page applies SHEET 82 J1 CAGE CODE: 97896 B 59 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: J1 B 57 A 56 MK VI 965-11X0-020 or later. MK VIII 965-12X0-020 or later. Terrain Display Select (out) 49 ARINC 453 Video #2 To WX R/T 28V EGPWS PWR Bus Note: For interface and operation of the Collins Proline II displays see Collins SIL 2-99 ON ARINC 429 Range CollinsP2.vsd ARINC 453 Picture Collins ProLine II with WXP-840/850 19 B 18 A 11 Remote ON ARINC 429 Range Collins Wx Pnl WXP-840/850 16 B 15 A 16 B 28V Lamp Dimming Bus Lamp Test ARINC 453 Picture 11 Remote ON B 40 momentary momentary 19 B 18 A Collins Wx Pnl WXP-840/850 15 A TERR ON TERR To WX R/T 28V EGPWS PWR Bus A 41 B 36 A 37 Terrain Display Select (in) 31 ARINC 429 Range #2 ARINC 429 Range #1 J2 Terrain Display Select (in) 31 ARINC 453 Video #1 A 58 Terrain Display Select (out) 54 EGPWS Honeywell MK VI MK VIII EGPWS Installation Design Guide Proprietary notice on title page applies SHEET 83 Honeywell MK VI MK VIII EGPWS Installation Design Guide HONEYWELL MK VI-VIII EGPWS 965-1XXX-0XX PROLINE 4 INTERFACE MK VI-VIII EGPWS Category 6, ID 5 or 6 #1 - IOC (ICC-4000) J2 P1 P * ICC-851A pins 13 & 14 P RANGE INPUT (A) 37 3* RANGE INPUT (B) 36 4* LA-GP-5 bus (Label 271) #2 - IOC (ICC-4000) P1 P * ICC-851A pins 13 & 14 P RANGE INPUT (A) 41 3* RANGE INPUT (B) 40 4* RA-GP-5 bus (Label 271) +28 VDC TERR J1 MOM TERR SELECT #1 32 70!* * In the OEM installations a single weather radar 453 bus enters the left MFD, passes through, and is terminated (70 ohm) at the right MFD. For EGPWS installations break the 453 radar bus between the MFDs, install switching relays, and wire one relay to each MFD. The right MFD connection is moved to remove the 70 ohm termination at that MFD. To allow proper radar termination when EGPWS is passing through the relays, the radar picture bus has a 70 ohm resistor (added externally). P1 P P #1 - MFD 8D H - ARINC 453 ARINC 453 OUTPUT (A) 58 11D L - (unterminated) ARINC 453 OUTPUT (B) 59 10D L - (70 ohm terminated) +28 VDC TERR RLY SELECT #1 54 #1 - WXR P1 P +28 VDC 4 H ARINC 453 OUT 29 L TERR MOM TERR SELECT #2 31 #2 - MFD P1 P P 8D H - ARINC 453 ARINC 453 OUTPUT (A) 56 11D L - (unterminated) ARINC 453 OUTPUT (B) 57 10D L - (70 ohm terminated) TERR RLY SELECT #2 49 +28 VDC Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 84 DC-810 J1 CAGE CODE: 97896 J1A 1 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: +28V GND PN 7003400-802 Radar Serial Data WX/TERR PICTURE BUS IN 3 5 J2A 22 23 1 2 J1B 78 Controller Serial Data 77 LEFT SYMBOL GENERATOR SG-802 GND WX pushbutton 23 34 Controller Serial Data 35 LEFT DISPLAY CONTROLLER L H L H L H L H L-EFIS +28 VDC TERR L-EFIS +28 VDC L H L H RT RELAY SELECT RT DISP SELECT DISPLAY BUS #2 Radar R/T WU-650 (HPN 7008470-XXX) Right EFIS Control Bus e f q Picture Bus Shield m Left EFIS n Control Bus k s Right Picture Bus J1 RT SCI RANGE CAT 6: ID 243 36 LT SCI 37 RANGE J2 54 LT RELAY SELECT 32 SELECT LT DISP 51 POP UP TERRAIN 58 DISPLAY 59 BUS #1 (HPN 965-12XX-020) MK VIII EGPWS g Left Picture h Bus J1 L H L H J1 L H L H 10 11 J2 49 31 56 57 J1 SG-802/803 CAT. 6: ID 243 L H L H R-EFIS +28 VDC TERR R-EFIS +28 VDC L H L H L H L H 3 +28V 5 GND PN 7003400-802 J2A 22 Radar Serial Data 23 1 WX/TERR 2 PICTURE BUS IN J1B 78 77 Controller Serial Data J1A SG-802 RIGHT SYMBOL GENERATOR 1 GND 23 WX pushbutton 34 35 Controller Serial Data J1 DC-810 RIGHT DISPLAY CONTROLLER Honeywell MK VI MK VIII EGPWS Installation Design Guide Proprietary notice on title page applies SHEET 85 J1 CAGE CODE: 97896 J1A 1 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: +28V GND PN 7013788-806 Radar Serial Data WX/TERR PICTURE BUS IN 1 8 J2A 32 33 30 31 J2B 67 Controller Serial Data 68 LEFT SYMBOL GENERATOR SG-806 GND WX pushbutton 23 34 Controller Serial Data 35 LEFT DISPLAY CONTROLLER DC-811 L H L H L H L H L-EFIS +28 VDC TERR L-EFIS +28 VDC L H L H TERRAIN 58 DISPLAY 59 BUS #1 LT DISP Right EFIS Control Bus e f q Picture Bus Shield m Left EFIS n Control Bus k s 31 56 57 J1 L H L H 10 11 J2 49 J1 Right Picture Bus g Left Picture h Bus Radar R/T RT SCI RANGE RT RELAY SELECT RT DISP SELECT WU-650 (HPN 7008470-XXX) 36 LT SCI 37 RANGE J2 54 LT RELAY SELECT 32 SELECT DISPLAY BUS #2 (HPN 965-12XX-020) MK VIII EGPWS 51 POP UP J1 L H L H J1 SG-806 CAT 6: ID 244 L H L H R-EFIS +28 VDC TERR R-EFIS +28 VDC L H L H L H L H RIGHT DISPLAY CONTROLLER 1 +28V 8 GND PN 7013788-806 J2A 32 Radar Serial Data 33 30 WX/TERR 31 PICTURE BUS IN J1B 67 68 Controller Serial Data J1A SG-806 RIGHT SYMBOL GENERATOR 1 GND 23 WX pushbutton 34 35 Controller Serial Data J1 DC-811 Honeywell MK VI MK VIII EGPWS Installation Design Guide Proprietary notice on title page applies SHEET 86 CAGE CODE: 97896 SCALE: NONE SIZE: A B 57 A 56 B 59 DWG NO: 060-4314-150 Terrain INOP (out) 55 NC J1 A 58 B 42 A 43 B 40 A 41 Lamp Test 28V Lamp Dimming Bus REV: Note: For interface and operation of the Universal MFD-640 see Universal Avionics Multi-Function Disaply Installation Manual 34-20-02 Alternate Action TERR INHIB TERR INOP B 36 Video in * Display Control In * Range out * MFD-640 6402-1XXX1-0X Universal MFD-640 * configurable by MFD-640 67 80 B 68 70 ohm termination 81 A 95 B 96 94 A 106 115 B A 37 P1 105 A J2 Terrain Inhibit (in) 12 KCPB Video #2 Out KCPB Video #1 Out ARINC 429 Control Out ARINC 429 Range #2 In ARINC 429 Range #1 In EGPWS Honeywell MK VI MK VIII EGPWS Installation Design Guide Proprietary notice on title page applies SHEET 87 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.9 Category 7 – Options Select Group #1 Category 7 enables/disables the following Options: Steep Approach, TA&D Alternate Pop Up, Peaks Mode, Obstacle Awareness, Bank Angle, Flap Reversal, and GPS Altitude Reference. Appendix E Table 5.3.7 defines the Options Select group and identifies the first MK VI/VIII EGPWS version in which the option was available (see the Effectivity entry). 3.9.1 Steep Appr oach This feature desensitizes the Mode 1 (Excessive Descent Rate) alert boundaries to permit safe but steeper than normal instrument precision approaches (e.g. MLS or GPS approaches) without unwanted Mode 1 alerts. Category 7 enables Steep Approach mode, Category 13 Steep Approach discrete (J2-31) cockpit switch, activates/deactivates the Steep Approach function during flight. 3.9.2 TA&D Alter nate Pop-up The Display Configuration Group Type (Category 6) defines default and alternate definitions for EGPWS alert “Pop-up” behavior, when no terrain displays are active or when a combination of terrain and non-terrain displays are active. (Some Display Configuration Group Types do not support an Alternate Pop-up definition.) See Appendix E 5.3.6.1-X for definitions. Category 7 enables/disables TA&D Alternate Pop Up. 3.9.3 Peaks Mod e Peaks mode is an alternate means of displaying terrain data. The standard terrain display mode displays terrain relative to the aircraft altitude that is within the aircraft envelope (the terrain is above or not more than 2000 feet below the aircraft). The standard terrain display mode is typically blank during the cruise portion of a flight. Peaks mode provides increased situational awareness by providing the same information as the standard terrain display mode as well as displaying terrain outside of the aircraft envelope and the highest and lowest elevations of terrain displayed. Peaks mode displays terrain based on the absolute terrain elevations. Note: TAD and TCF must be enabled if Peaks mode is enabled. The Display Configuration Group (Category 6) defines Peaks Mode availability by defining the effects of enabling and disabling the Peaks Mode enable. See Appendix E 5.3.6.1-X for definitions. Category 7 enables/disables Peaks Mode. 3.9.4 Obstacle A wareness The Obstacle Awareness feature adds a database of (man-made) obstacles that are at least 100 feet taller than the surrounding terrain and continuously computes obstacle clearance envelopes ahead of the aircraft, issuing Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 88 Honeywell MK VI MK VIII EGPWS Installation Design Guide alerts if the boundaries of these envelopes conflict with obstacle elevation data in the obstacle database (similar to the Terrain Awareness function). Obstacle data is currently available for North America and parts of the Caribbean and Europe. Not all obstacles will be contained in the database. Category 7 enables Obstacle Awareness if TA&D is not disabled in Category 6. Note: TAD & TCF must be enabled if Obstacle Awareness is enabled. 3.9.5 Bank Angle Callout Enabling The Bank Angle feature provides protection for over banking during maneuvering on approach or climb-out and while at altitude. In addition, it protects against wing or engine strikes close to the runway. For airplanes fitted with an autopilot, additional protection is provided if the autopilot is engaged by advancing the roll angle limit to 33 degrees. The additional ‘autopilot engaged’ protection applies to all software versions for GA FAST and GA SLOW aircraft types, whereas it is available in software version –008 or later for Bizjet aircraft types. The Bank Angle callout can be enabled or disabled as appropriate for this installation. 3.9.6 Flap Revers al The Landing Flap discrete input is defined in Category 13. The Category 7 control is used to reverse the defined logic to match aircraft wiring, if necessary. +28 VDC Landing Flap discrete (J1-37) active position: Flap Reversal Flap Discrete (Category 13) Landing Flap discrete = +28V Landing Flap Discrete = Open (or GND) False True Flaps Up Flaps Down Flaps Down Flaps Up Ground seeking Landing Flap discrete (J1-18) active position: Flap Reversal Flap Discrete (Category 13) Landing Flap discrete = GND Landing Flap Discrete = Open (or +28V) False True Flaps Up Flaps Down Flaps Down Flaps Up 3.9.7 GPS Altitud e Reference The GPS Altitude (ARINC 429 label 076, Category 3) may be referenced to mean sea level (MSL) or WGS-84. Determine which reference the GPS position uses and set the GPS Altitude Reference accordingly in this Category. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 89 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.9.8 Instruction s Review the sections above for information on Steep Approach, TA&D Pop Up, Peaks Mode, Obstacle Awareness, Bank Angle, Flap Reversal, and GPS Altitude Reference. Using Appendix E Tables 5.2 and 5.3.7 as described above, select the preferred Category 7 (Options Select Group #1) ID that matches the aircraft configuration, features preferences and version (part number) being installed. Record the ID number for the Options Select Group #1 from Appendix E Table 5.3.7 under the Ident No. heading for Step (Category) 7 in Appendix E Table 5.2. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 90 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.10 Category 8 – Radio Altitude Input Select Category 8 defines the Radio Altitude and Decision Height interface. 3.10.1 Radio Altitu de Input Appendix E Table 5.3.8 defines the Radio Altitude Types and identifies the first MK VI/MK VIII EGPWS version in which the option was available (see Effectivity entry). Appendix E Tables 5.3.8-x, where x is the Radio Altitude Type number, define the format and electrical interfaces required to support each Radio Altitude Type. 3.10.2 Decision H eight Discrete Input The Decision Height discrete (J1-33, Category 8) indicates to the MK VI/MK VIII EGPWC whether the aircraft is above or below the selected Decision Height. This discrete is typically connected to the Decision Height output on the Radio Altimeter indicator. If the ‘Minimums-Minimums’ callout is not wanted the Decision Height discrete should be left open. 3.10.3 Digital Rad io Altitude Interface (Cat. 8 ID 2) EGPWS MK VI / MK VIII J2 ARINC 429 Radio Altitude Radio Altimeter R/T A 21 A B 4 B J1 ARINC 429 Radio Altimeter Indicator DH wiper DH Discrete (Gnd) 33 DH out Digital-RA.vsd Vendor Model R/T Collins RAC-870 Ind. DH Indicator SCALE wiper/out A B ALI-55 ARINC 429 P1-R/V P1-2 P1-3 MP-B2 MP-B3 P1-M/A P4051-B P4051-C Honeywell ALA-52A/B Honeywell KRA-405B NOTE: R/T ARINC 429 KNI-415/416 ARINC 429 The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer’s customer service to confirm your installation. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 91 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.10.4 Analog Rad io Altitude Interface (Cat. 8 ID 0,1,3,4) J1 EGPWS MK VI / MK VIII Analog Radio Altitude Radio Altimeter R/T + ARINC 552, ALT 55, - RT-200/300 (+) 64 (-) 45 Valid Radio Altitude Valid +28V 29 Radio Altimeter Indicator DH wiper DH Discrete (Gnd) 33 DH out Analog-RA.vsd Vendor Model R/T Collins ALT 55 Honeywell HG7502(BC) Cat. Ind. DH R/T Indicator ID wiper/out + - Valid ALI-55 1 P1-R/V P1-57 P1-59 P1-49 JG1072( ) 0 P1-e P4-47 P4-46 P4-27 Honeywell RT-221/300 (1) RA-315 0 P1-F P1-X P1-N P1-Y Honeywell RT-220/300 (2) RA-215 3 P1-F P1-N P1-W P1-Y Honeywell KRA-405 KNI-415/416 4 P1-M/A P1-B P1-g P1-L Honeywell KRA-405B KNI-415/416 4 P1-M/A P1-i P1-k P1-j Honeywell ALA-51A INA-51( ) 0 P2-e P1B-47 P1B-46 P1B-27 Collins 860F-1 339H-1/-2 0 P1-e P1B-47 P1B-46 P1B-27 NOTE: The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer’s customer service to confirm your installation. NOTE 1: The following RT-300 part numbers meet ARINC 552 for the Auxiliary Output: 7001840 -902, -906, -912, 916, -917, -918, -922, -926, -928, -932, -936, -937, and -938. RT-221’s are also compatible, consult your Honeywell representative. NOTE 2: This is the Precision Output from the R/T. Note the + and – signals are swapped to convert the – 4mV to +4mV. RT-300 (-901, -903, -905) should use the Precision Output, same as RT-220. 3.10.5 Digital – AR INC 429 Dual IOC Buses (Cat. 8 ID 251- 255) Radio Altitude Type 251 (IOC bus or equivalent) is a dual high speed, digital ARINC 429 signal having labels 164 and 170. Radio Altitude Type 252 (IOC bus or equivalent) is a dual high speed, digital ARINC 429 signal having labels 164 and 370. Radio Altitude Type 253 (IOC bus or equivalent) is a dual high speed, digital ARINC 429 signal having label 164 and a analog discrete DH input. Radio Altitude Type 254 (IOC bus or equivalent) is a dual high speed, digital ARINC 429 signal having labels 164, 170 and 370. Radio Altitude Type 255 (IOC bus or equivalent) is a dual high speed, digital ARINC 429 signal having labels 164 and 370. For interface description see paragraph 3.4.5 Air Data Type 255. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 92 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.10.6 Instruction s Using Appendix E Tables 5.2, 5.3.8 and 5.3.8-x as described above, select the Radio Altitude Input Type that matches the aircraft configuration, features preferences and version (part number) being installed. Record the ID number for the Radio Altitude Type from Appendix E Table 5.3.8 under the Ident No. heading for Step (Category) 8 in Appendix E Table 5.2. Using the Radio Altitude Type number from Appendix E Table 5.3.8 as x, go to Appendix E Table 5.3.8-x. The electrical interfaces (pin-outs) for Radio Altitude Type are shown in Appendix E Table 5.3.8-x and are used to generate the installation wiring diagrams. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 93 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.11 Category 9 – Navigation Inputs Select Category 9 selects the Glideslope and Localizer Deviation interfaces and Glideslope Validity and ILS Tuned discretes. Appendix E Table 5.3.9 defines the Category 9 Navigation Inputs Select options (called Navigation Inputs Select Types) and identifies the first MK VI/VIII EGPWS version in which the option was available (see the Effectivity entry). Appendix E Tables 5.3.9-x, where x is the Navigation Inputs Select Type number, define the format and electrical interfaces required to support each Navigation Input Select Type. 3.11.1 Navigation Inputs Select (Glideslope & Localizer Inputs) Glideslope Deviation is basic (required) and is available in analog and digital formats. Localizer Deviation is an enhancement (not required). Note: Numerous (but not all) Envelope Modulation cases require a localizer input. Therefore a NAV ID that supplies both Glideslope and Localizer should be selected in this category if possible. However, due to hardware limitations, use of localizer for installations that can only provide low level validity is not supported. In these cases only ID #1 can be selected. Envelope Modulation will still function for these glideslope only installations, but not for those envelope modulation areas that require a localizer crosscheck. 3.11.2 Glideslope Validity Glideslope Validity (+28V Super Flag) is required for Navigation Inputs Select 0 or 5 at pin J1-11. Glideslope Validity (Low Level) is required for Navigation Inputs Select 1 at pins J1-30 (+) and J1-10 (-). Digital 429 Glideslope interfaces do not require Glideslope Validity input. 3.11.3 Localizer V alidity Localizer Validity (+28V Super Flag) is required for Navigation Inputs Select 5 at pin J1-48. Digital 429 Localizer interfaces do not require Localizer Validity input. 3.11.4 ILS Tuned D iscrete Input #1 (+28V) and #2 (GND) The ILS Tuned Discretes (+28V and GND) indicate that an Instrument Landing System frequency has been selected on the Captain’s (or selected) ILS (only one is required). These discretes are used with the analog Glideslope inputs. When an ILS is tuned, the MK VI/MK VIII EGPWS checks the Glideslope Validity discretes and monitors the Glideslope inputs. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 94 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.11.5 Analog Glid eslope Interface (Cat. 9 ID 0,1,5) EGPWS MK VI / MK VIII J1 ILS Receiver + 65 - 46 GS Deviation +Up +Dn GS Valid +28 11 + 30 - 10 +28 39 Low Level GS Valid ILS Tuned Super Flag +28V + GS Flag - (Low Level) Delayed ILS Mode ILS Energize GND 20 LOC Deviation GS Deviation + 30 +L - 10 +R LOC Valid +28 48 LOC Deviation LOC Val +28V GS Inhibit (BC) +28 38 Backcourse GS Inhibit (BC) GND 19 Backcourse Analog-ILS-1.vsd Vendor Model Honeywell KNR 6030 Honeywell KNR 660 Honeywell KNR 634 1 Honeywell KGM-691 Honeywell KNR 600A Collins 51RV-1, 51RV-4( ) Collins VIR-30, -31, -32 Honeywell VNS 41A Honeywell RNA-34A Honeywell KN 53 Honeywell KN 72 Honeywell RNZ 850 Honeywell KX-155/165 NOTE: GS Valid Cat. 9 SuperFlag Low Level ID +28V Flag J1003-21 5 J1003-27 J1003-22 P1-e 1 P1-q P6342-34 5 P6342-50 P6342-18 P692-S 0 P692-W P692-T P601-e 1 P601-q TP-21 2 5 TP-27 TP-22 P1-9 5 P1-17 P1-13 5 P1001-60 5 TP-27 ILS Tuned J1002-50 J1002-18 P1-A74 1 P1-B60 P1-B106 P901-U P901-R GND P1-k P6342-49 P6341-17 P692-a P601-A P601-k BP-50 BP-18 P2-18 P2-40 P1001-101 J1001-56 BP-50 BP-18 P2-13 P2-R 1 5 TP-21 LOC Valid SuperFlag +28V P2-12 P1-B91 P1-B64 P401-14 P401-8 Deviation GS +up LOC +R +dn +L J1003-8 J1002-39 J1003-9 J1002-40 P1-T P1-V P6342-36 P6342-23 P6342-35 P6342-7 P692-B P692-C P601-r P601-m P601-s P601-n TP-8 BP-39 TP-9 BP-40 P1-5 P2-10 P1-1 P2-13 J1001-90 J1001-38 J1001-23 J1001-92 TP-8 BP-39 TP-9 BP-40 P2-P P2-14 P1-2 P1-10 P1-B79 P1-B78 P1-B75 P1-B75 P901-S P901-s (KX-165) P901-T P901-k (only The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. ePlease contact the manufacturer’s customer service to confirm your installation. 1 066-1078-00, -01, -04, -05, -10, -11, -14 and –15 only. 2 51RV-4( ) only. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 95 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.11.6 Digital Glid eslope / Localizer / ILS Select Interface (Cat. 9 ID 2,3,4) EGPWS MK VI / MK VIII J2 ARINC 429 ILS ILS 429 Bus A ARINC 429 B Low Speed A 22 B 5 Digital-ILS.vsd Vendor Model Cat 9 ID ARINC 429 Bus 1 A B Honeywell KNR 634A 2,3 Chelton VNS 411A 2,3 P1-C P1-D Chelton VNS 411B 2,3 P1001-62 P1001-103 Honeywell RNA-34A 2,3 P1024-24 Honeywell KN 40A(B) 4 Collins VIR-432 Garmin GNS-430 NOTE: P6342-41 P6342-42 ARINC 429 Bus 2 A B P6342-44 P6342-45 P1024-28 P1024-21 P1024-25 P401(403)-41 P401(403)-42 P401(403)-44 P401(403)-45 2,3 P1-35 P1-36 P1-22 P1-23 2,3 P4006-24 P4006-23 The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer’s customer service to confirm your installation. 3.11.7 Digital – AR INC 429 Dual IOC buses (Cat. 9 ID 250 - 255) Navigation Input Select Type 250 - 255 (IOC bus or equivalent) are dual high speed, digital ARINC 429 buses having the following labels: 250 100, 163, 173, and 174 253 173 and 174 251 100, 173, and 174 254 163, 173, and 174 252 173 and 174 * 255 117 and 116 For interface description see paragraph 3.4.5 Air Data Type 255. Note * ID 252 uses a special interface to input channels 2 and 5. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 96 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.11.8 Instruction s Using Appendix E Tables 5.2, 5.3.9 and 5.3.9-x as described above, select the Navigation Input Select Type that matches the aircraft configuration, feature preferences, and version (part number) being installed. Record the ID number for the Navigation Inputs Select Type from Appendix E Table 5.3.9 under the Ident No. heading for Step (Category) 9 in Appendix E Table 5.2. Using the Navigation Inputs Select number from Appendix E Table 5.3.9 as “x”, go to Appendix E Table 5.3.9-x. The electrical interfaces (pin-outs) for the Navigation Inputs Select Type are shown in Appendix E Table 5.3.9-x) and are used to generate the installation wiring diagrams. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 97 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.12 Category 1 0 – Attitude Input Select Category 10 defines the Roll Angle interface. Appendix E Table 5.3.10 defines the Attitude Input Select type and identifies the first MK VI/VIII EGPWS version in which the option was available (see the Effectivity entry). Appendix E Tables 5.3.10-x, where x is the Attitude Input Select Type number, define the format and electrical interfaces required to support each Attitude Input Select Type. 3.12.1 Roll Angle Roll Angle is used for Bank Angle callout and Terrain Awareness display. Each leg of the Roll Synchro is required. The sign is used to determine left/right wing down. This input improves the TAD look ahead algorithm. 3.12.2 Analog Pitc h & Roll Angle (Synchro) (Cat. 10 ID 0,2,4) EGPWS MK VI / MK VIII Roll Synchro Pitch Synchro J1 Vertical Gyro X 1 X Y Z 21 2 Y Roll Angle X 5 X Y Z 7 6 Y Pitch Angle Z Z +28 = Valid Attitude Validity 68 Analog-VG.vsd Vendor Model Vertical Gyro Valid +28 X Aeronetics RVG 801 P1-U P1-A P1-B P1-C P1-D P1-E P1-F Collins AHC-85( ) P1-13 P2-50 P2-51 P2-52 P2-42 P2-43 P2-44 Collins 332D-11 P1-N P1-A P1-B P1-C P1-D P1-E P1-F Honeywell HG1075 J1B-G3 J1B-C9 J1B-C10 J1B-C11 J1B-D9 J1B-D10 J1B-D11 Honeywell HG1095 J1B-G3 J1B-C9 J1B-C10 J1B-C11 J1B-D9 J1B-D10 J1B-D11 P1-U P1-A P1-B P1-C P1-D P1-E P1-F King KVG-350 GG/FF X Y Z P Q R Litef LTR-81 MP-A11 MP-B1 MP-B2 MP-B3 MP-B4 MP-B5 MP-B6 Litef LCR-92 & 93 Note 2 J3-11 J3-40 J3-26 J3-16 J3-39 J3-25 Sperry VG-14A GG/FF X Y Z P Q R Sperry VG-311 P1-45 P1-5 P1-4 P1-6 P1-7 P1-8 P1-9 JET VG-208 Note 1: Note 2: Attitude Pitch Synchro (Note 1) Y Z X Roll Synchro (Note 1) Y Z The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer’s customer service to confirm your installation. See LCR installation manual. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 98 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.12.3 Digital Pitc h & Roll Angle (ARINC 429 High Speed) (Cat. 10 ID 5 & 6) EGPWS MK VI / MK VIII J2 ARINC 429 AHRS AHRS 429 Bus A ARINC 429 B High Speed A 23 B 6 Digital-AHRS.vsd Vendor Model Cat 10 ID Collins AHC-85(D/E only) ARINC 429 Bus 1 A B ARINC 429 Bus 2 A B 6* P1-16 P1-14 P1-24 P1-22 Litef LTR-81 AHRS 6* MP-G7 MP-G8 MP-E5 MP-E6 Litef LCR-92/LCR-93 AHRS 6* J4-08 J4-29 J4-49 J4-07 Honeywell HG1075/1095 IRU 6* J1B-G7 J1B-G8 J1B-E5 J1B-E6 NOTE: The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer’s customer service to confirm your installation. * ID 6 is preferred with Category 2 Air Data with ARINC 429 Barometric Altitude Rate (label 212), otherwise ID 5. ID 6 cannot be used with analog Air Data interfaces. 3.12.4 Digital – AR INC 429 Dual IOC buses (Cat. 10 ID 253 & 255) Attitude Input Select Type 253 (IOC bus or equivalent) is a dual high speed, digital ARINC 429 signal having labels 324, 325, 326, 327, 365 and 361. Attitude Input Select Type 255 (IOC bus or equivalent) is a dual high speed, digital ARINC 429 signal having labels 324, 325, 333 and 331. For interface description see paragraph 3.4.5 Air Data Type 255. 3.12.5 Instruction s Using Appendix E Tables 5.2, 5.3.10 and 5.3.10-x as described above, select the Attitude Input Select type that matches the aircraft configuration, feature preferences, and version (part number) being installed. Record the ID number for the Attitude Input Select from Appendix E Table 5.3.10 under the Ident No. heading for Step (Category) 10 in Appendix E Table 5.2. Using the Attitude Input Select ID number from Appendix E Table 5.3.10 as “x”, go to Appendix E Table 5.3.10-x. The electrical interfaces (pin-outs) for the Attitude Input Select Type are shown in Appendix E Table 5.3.10-x and are used to generate the installation wiring diagrams. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 99 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.13 Category 1 1 – Heading Input Select Category 11 defines the Magnetic Heading interface. Appendix E Table 5.3.11 defines the Heading Input Select types and identifies the first MK VI/VIII EGPWS version in which the option was available (see the Effectivity entry). Appendix E Tables 5.3.11-x, where x is the Heading Input Select number, define the format and electrical interfaces required to support each Heading Input Select Type. 3.13.1 Magnetic H eading Magnetic Heading is used for Terrain Awareness alert and display. 3.13.2 Analog Hea ding (Synchro) (Cat. 11 ID 0) EGPWS MK VI / MK VIII J1 X Heading Synchro 26 VAC Reference Directional Gyro X 22 Y 23 Z 3 Y Heading Z H H 4 24 C C Mag Hdg Validity 28 Heading Ref +28V = Valid Analog-HDG.vsd Vendor Model Heading Directional Gyro Valid Heading Reference H C Heading Synchro (Note 1) X Y Z Aeronetics Model 9100 P1-28 P1-6 P1-7 P1-8 P1-9 P1-10 Collins 332E-4 P1-F P1-D P1-E P1-A P1-B P1-C Collins AHC-85( ) P1-9 P2-57 P2-58 P2-34 P2-35 P2-36 Collins DGS-65 P1-50 P1-6 P1-3 P1-25 P1-40 P1-24 Honeywell HG1075/1095 J1B-G2 P1-V J1B-F13 P1-P 1 P1-C 2 J1B-G13 P1-D 1 P1-F 2 J1B-E10 P1-Z 1 P1-T 2 J1B-E11 P1-W 1 P1-P 2 J1B-E12 P1-T 1 P1-K 2 Honeywell KI-525 (KG-102) J2-P J2-R J2-U J2-S J2-V J2-T JET DN-104 P2-31 P2-9 P2-10 P2-1 P2-2 P2-3 Honeywell KSG 105 3 Litef LTR-81 MP-E15 MP-B12 MP-B13 MP-B9 MP-B10 MP-B11 Litef LCR-92/LCR-93 Note 2 J3-05 J3-20 J3-13 J3-42 J3-28 Sperry C-14A3 P1-e P1-H 1 P1-J 1 P1-L 1 P1-M 1 P1-K 1 Sperry C-14D3 P1-DD P1-X P1-Y P1-AA P1-BB P1-Z Sperry DG-234 P2-F P1-L P1-K P1-J Sperry DG-207 J1-B P1-L P1-K P1-J Note 1: Note 2: J1-C(115VAC) J1-M The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer’s customer service to confirm your installation. See LCR installation manual. 1 #1 Heading Output Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 100 Honeywell MK VI MK VIII EGPWS Installation Design Guide Note 3: 2 #2 Heading Output 3 Do not use #2 output, reserved for autopilot only. The KI-525 must have the proper mod for HEADING TRANSMITTER output. The Heading valid output at J2-P needs to be converted from ground active output to +28V active output using a external relay for use with EGPWS. 3.13.3 Digital – AR INC 429 AHRS Input (Cat. 11 ID 2 & 3) Heading Input Select Type 2 (AHRS bus or equivalent) is a high speed, digital ARINC 429 signal having label 320. Heading Input Select Type 3 (AHRS bus or equivalent) is a high speed, digital ARINC 429 signal having labels 320 and 314. For interface description see paragraph 3.12.3 Attitude Input Type 5. 3.13.4 Digital – AR INC 429 Dual IOC buses (Cat. 11 ID 254 & 255) Heading Input Select Type 254 (IOC bus or equivalent) is a dual high speed, digital ARINC 429 signal having label 314. Heading Input Select Type 255 (IOC bus or equivalent) is a dual high speed, digital ARINC 429 signal having label 320. For interface description see paragraph 3.4.5 Air Data Type 255. 3.13.5 Instruction s Using Appendix E Tables 5.2, 5.3.11 and 5.3.11-x as described above, select Heading Input Select type that matches the aircraft configuration, feature preferences, and version (part number) being installed. Record the ID number for the Heading Input Select from Appendix E Table 5.3.11 under the Ident No. heading for Step (Category) 11 in Appendix E Table 5.2. Using the Heading Input Select number from Appendix E Table 5.3.11 as “x”, go to Appendix E Table 5.3.11-x. The electrical interfaces (pin-outs) for the Heading Input Select Type are shown in Appendix E Table 5.3.11-x and are used to generate the installation wiring diagrams. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 101 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.14 Category 1 2 – Windshear Input Select Category 12 defines the Windshear interface. Appendix E Table 5.3.12 defines the Windshear Input Select options and identifies the first MK VI/VIII EGPWS version in which the option was available (see the Effectivity entry). 3.14.1 No Windsh ear Select ID 0 (No Windshear) for all aircraft configurations without Windshear. Windshear options will be added as new installations types are propagated. 3.14.2 Dual ARINC 429 BUS (Cat. 14 ID 253,254,255) Windshear Input Select Types 253, 254 and 255 (IOC bus or equivalent) is a dual high speed, digital ARINC 429 signal having labels 224, 225 and 236. For interface description see paragraph 3.4.5 Air Data Type 255. NOTE: Windshear is currently available only for Bombardier Challenger 300 airplanes with MK VIII EGPWS installations. 3.14.3 Instruction s Using Appendix E Table 5.2 and 5.3.12 as described above, select the Windshear Input Select type that matches the aircraft configuration, feature preferences and version (part number) being installed. Record the ID number for the Windshear Input Select from Appendix E Table 5.3.12 under the Ident No. heading for Step (Category) 12 in Appendix E Table 5.2. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 102 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.15 Category 1 3 – Input / Output Discrete Type Select Category 13 defines the input and output discretes not defined as part of any of the other Categories. Appendix E Table 5.3.13 defines the Input/Output discretes options and identifies the first MK VI/VIII EGPWS version in which the option was available (see the Effectivity entry). 3.15.1 Input Discr etes The discrete inputs are defined in Appendix E Section 6.6 Additional information for the discretes is provided below. Note: When there are two discrete pin choices for the same pin function in Appendix E Table 5.3.13-x, use only the one that matches the aircraft wiring either +28V or Ground. 3.15.1.1 Glideslope Inhibit Discrete The Glideslope Inhibit discrete is used for Backcourse Inhibit of Mode 5 Glideslope. Either the +28V (J1-38) discrete or the ground (J1-19) discrete may be used. If Backcourse is not available these discretes may be left open. Discrete Position / Status Connector Pin Glideslope Inhibit +28 Inhibit = +28V Not Inhibit = Gnd/Open J1-38 Glideslope Inhibit Gnd Inhibit = Gnd Not Inhibit = +28V /Open J1-19 3.15.1.2 Landing Fla ps Discrete Landing Flap discrete is supplied by a Flap or Flap handle switch. The active position (+28V or GND) indicates “Not Landing Flaps” (or Flaps Up) and should be connected to a contact that will indicate Flaps Up until the Flaps are lowered to landing position prior to landing. The Landing Flap discrete active position can be reversed by the ‘Flap Reversal Option’ of Appendix E Table 5.3.7 as shown in the following tables. Flap Override for MK VIII EGPWS can be done by a guarded (or illuminated) cockpit switch that simulates the Flap Down condition. +28 VDC Landing Flap discrete active position: Flap Reversal (Category 7) False True Flap Discrete (J1-37) Landing Flap discrete = +28V Flaps Up Flaps Down Flaps Down Flaps Flap Override = OVRD +28V +28V Flap Override = NORM Open Open Landing Flap Discrete = Open (or GND) Cat. 13 ID 254/255 only * * Category 13 ID 254/255 must use this method for Flap Override. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 103 Honeywell MK VI MK VIII EGPWS Installation Design Guide Ground seeking Landing Flap discrete active position: Flap Reversal (Category 7) False True Flap Discrete (J1-18) Landing Flap discrete = GND Flaps Up Flaps Down Flaps Down Flaps Flap Override = OVRD GND GND Flap Override = NORM Open Open Landing Flap Discrete = Open (or +28V) Cat. 13 ID 254/255 only * * Category 13 ID 254/255 must use this method for Flap Override. 3.15.1.3 Audio Inhib it Discrete The Audio Inhibit discrete is an optional input but is strongly recommended to maintain audio and visual prioritization. When activated, this discrete inhibits all audio (Ground Proximity and Terrain Awareness). Activation of the Audio Inhibit input for more than 60 seconds will result in the “All Modes Inhibit” fault. The Audio Inhibit discrete input can be connected to any or all of the following (as applicable to the aircraft configuration): - the Stall Warning computers (this is required for CAA-registered aircraft) the Predictive Windshear (PWS) Audio Inhibit output discrete a separately labeled guarded cockpit switch the reactive Windshear system if separate from the EGPWS. For some existing GPWS installations, this discrete may have been tied to the analog Radio Altimeter ReceiverTransmitter Self-Test output. This connection is no longer required but may be left intact for retrofit installations. Discrete Position / Status Connector Pin Audio Inhibit +28 Inhibit = +28V Not Inhibit = Gnd/Open J1-36 Audio Inhibit Gnd Inhibit = Gnd Not Inhibit = +28V /Open J1-17 3.15.1.4 Landing Ge ar Discrete Landing Gear discrete is supplied by the Gear (or Gear handle) switch. The active position (+28V or GND) indicates “Gear Down” and should be connected to a contact that will indicate Gear Down when the Gear are lowered prior to 500 feet Radio altitude. Discrete Position / Status Connector Pin Landing Gear +28 Down = +28V Not Down = Gnd/Open J1-35 Landing Gear Gnd Down = Gnd Not Down = +28V /Open J1-16 For Fixed Gear aircraft the Audio Menu in Category 5 should be ID 2 or 3 and one of the following Gear Discrete arrangements should be used to simulate Gear Down to the EGPWS. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 104 Honeywell MK VI MK VIII EGPWS Installation Design Guide FIXED LANDING GEAR/FLOAT AIRCRAFT ALTERNATE AIR SWITCH ARRANGEMENT (Example Shown: Twin Otter) Not LANDING P1 J1 FULL LANDING FLAP POSITION (16°-18°) 18 MK VI EGPWS COMPUTER Landing Flap Discrete (Gnd) LANDING FLAPS UP APPROACH FLAP POSITION (5°-7°) APPROACH FLAPS EGPWS 35 Landing Gear Discrete (+28) 40 60 Power Input: +28VDC AIRCRAFT +28VDC 3 AMP KRA 405B Adjustable Trip W* * KRA 405B Adjustable Trip pins W,V, & F. 16 Landing Gear Discrete On Ground = DC Gnd The Honeywell KRA 405B provides 3 programmable Adjustable Trip outputs that can be used to supply a ground to the Landing Gear input discrete when the aircraft is less than 5 to 20 feet Radio Altitude. See the Honeywell KRA 405B Installation Manual (006-10536-0003) for details of the Adjustable Trip output. Use of Adjustable Trip outputs of the KRA 405B requires CM2000 Configuration Module along with KPA900 Configuration Module Programmer, PC and software. The Collins ALT-55 (622-2855-001 only) also provides 4 shop adjustable Trip outputs, pins 41,43,46, and 48, contact Collins Avionics for details. FIXED LANDING GEAR/FLOAT AIRCRAFT ALTERNATE AIR SWITCH ARRANGEMENT (Example Shown: Twin Otter) Not LANDING P1 FULL LANDING FLAP POSITION (16°-18°) APPROACH FLAP POSITION (5°-7°) FLAPS UP APPROACH FLAPS EGPWS 35 Landing Gear Discrete (+28) 40 Power Input: +28VDC 60 AIRCRAFT +28VDC 3 AMP NC 16 Landing Gear Discrete On Ground = DC Gnd NO DIODE +28VDC AIR STREAM ~40 ~ KNOTS MK VI EGPWS COMPUTER 18 Landing Flap Discrete (Gnd) LANDING OPTIONAL EQUIPMENT EXISTING ON AIRCRAFT HOUR METER J1 NO AIR SWITCH RELAY AIR SWITCH (SHOWN AS A/C ON GROUND) Some aircraft (ex: Twin Otter) have an air switch (flapper on the wing) that can be used to provide a Landing Gear discrete ground when the aircraft is less than approximately 40 knots airspeed (approach airspeed varies by aircraft). Contact Honeywell EGPWS engineering for assistance in adapting this discrete input design to your aircraft. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 105 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.15.1.5 Glideslope Cancel Discrete The Glideslope Cancel discrete provides the crew with the capability to manually cancel Mode 5 alerts during an approach. The Glideslope Cancel latch is automatically reset when the aircraft descends below 30 feet or ascends above 2000 feet or by selecting a non-ILS frequency. This discrete is typically supplied by a momentary action cockpit Glideslope mode manual inhibit switch, typically part of the Glideslope Lamp assembly (Below GS). Discrete Position / Status Connector Pin Glideslope Cancel Cancel = Gnd Normal = Open J1-15 3.15.1.6 Momentary Flap Override Discrete The Momentary Flap Override discrete provides the crew with the capability to manually desensitize mode 4 of the EGPWS when the pilot must land with flaps up or partial flaps. For Category 1 GA Fast and GA Slow aircraft only, the Flap Override will also bias mode 1 by –300 fpm during operations at airports located in terrain where steep or incompatible terrain clearances are involved. Honeywell recommends the installation of the momentary Flap Override switch. Category 13 ID’s 254 & 255 do not support this function (see 3.15.1.2). This feature is activated by momentarily pressing a light switch located in the cockpit within sight of each pilot. When Flap Override is selected and active, the EGPWS will illuminate a ‘GPWS FLAP OVRD’ light (J1-73) (see 3.14.2.8) to remind the pilots that this feature has been activated. After landing, both the function and the light will automatically reset to the OFF condition. The Flap Override function and light can also be manually deactivated in flight by again pressing the light switch. Each pressing of the light switch during flight will alternate the ON/OFF state of this function (minimum of 5 seconds between presses). The use of the Flap Override switch will be controlled by the Operator’s (Air Carrier/Airline) Operational Procedures. Discrete Position / Status Connector Pin Flap Override OVRD Toggle = Gnd Normal = Open J1-14 3.15.1.7 Mode 6 Low Volume Discrete The Mode 6 Low Volume discrete permanently or temporarily modifies the volume of the Mode 6 altitude and bank angle callouts. This discrete operates independent of the Category 14 options. The Mode 6 Low Volume discrete is used to reduce the Mode 6 volume by 6dB from the volume level select in Category 14. This discrete is typically connected to ground to lower the volume an additional 6dB. In some installations, it is connected to the windshield wiper control to decrease the Mode 6 Volume level under normal conditions and automatically increase Mode 6 volume 6dB when the cabin noise increases due to the windshield wipers being on. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 106 Honeywell MK VI MK VIII EGPWS Installation Design Guide Discrete Position / Status Connector Pin Mode 6 Low Volume Low Volume = Gnd Not Low Volume = Open J1-13 3.15.1.8 Autopilot E ngaged Discrete For airplanes fitted with an Autopilot, additional Bank Angle mode protection is provided when the Autopilot is engaged. If the Autopilot is engaged the Bank Angle roll angle limit advances to 33 degrees from 50 degrees. This input discrete should be connected to a +28V active (engaged) output discrete from the Autopilot system that indicates the Autopilot has authority over the controls of the aircraft. For aircraft with Touch Control Steering, the input should be connected to the clutch engaged output discrete. Discrete Position / Status Connector Pin Autopilot Engaged Engaged = +28V Not Engaged = Open J1-8 3.15.1.9 Terrain Aw areness and TCF Inhibit Discrete The Terrain Awareness and TCF Inhibit discrete inhibits the Terrain Awareness and TCF modes of the MK VI/VIII EGPWS. This discrete is required for all installations that do not disable TA&D and TCF in Category 6. This discrete is typically connected to an “alternate action switch” in the cockpit. The recommended label for this switch is “Terrain Override” although labeling for this switch should be consistent with existing cockpit nomenclature. “Terrain Inhibited” will be annunciated during cockpit Self-Test if these functions are inhibited. Discrete Position / Status Connector Pin TA & TCF Inhibit Inhibit = Gnd Not Inhibit = Open J1-12 3.15.1.10 Self Test D iscrete The cockpit Self Test discrete is provided to manually initiate test of the EGPWC, EGPWS aircraft interface, and to enunciate system configuration and status information. This discrete is typically supplied by a momentary action cockpit ‘push to test’ switch, typically part of the GPWS WARN Lamp assembly. This discrete must be momentarily connected to ground to activate the Self Test. Activation of this discrete continuously for more than 60 seconds will result in the ‘Self Test Invalid’ fault which will cause a GPWS INOP indication. Discrete Position / Status Self Test Self Test = Gnd Normal = Open Connector Pin J1-34 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 107 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.15.1.11 Steep Appr oach Discrete #2 For some installations a Steep Approach bias can be optionally applied to the Mode 1 curves. If Steep Approach is enabled (Category 7) and the Steep Approach discrete is selected (Category 13), then fixed positive biases are added to both the Sinkrate curve (500 fpm), and the Pull Up curve (200 fpm). Category 7 enables the Steep Approach function for the installation. Steep Approach is activated using the Steep Approach discrete. Steep Approach discrete #2 is selected in flight when starting a steep approach. Steep Approach discrete #2 should not be hardwired. On ground self-test is inhibited if Steep Approach is active. Momentary action (Category 13, ID’s 6 and 7 only) Discrete Position / Status Steep Approach Connector Pin Steep Approach Toggle = Gnd Normal (no action) = Open J2-31 Alternate action (Category 13, all ID’s except ID 6 and 7) Discrete Position / Status Connector Pin Steep Approach Selected = Gnd Not Selected = Open J2-31 Momentary action (preferred method) enables a (non-latching) cockpit switch. Reference 3.15.2.9 Steep Approach Discrete for associated lamp output. The Steep Approach output lamp activates when the switch is pressed or when Envelope Modulation automatically activates steep approach and deactivates on landing. 3.15.1.12 GPWS INHI BIT Discrete (alternate action) The GPWS INHIBIT discrete inhibits the GPWS modes of the MK VI/VIII EGPWS (all audio and visual except for WS, TA & TCF). This discrete is typically connected to an “alternate action switch” in the cockpit. The recommended label for this switch is “GPWS INHIBIT” although labeling for this switch should be consistent with existing cockpit nomenclature. Activation of this switch for more than 5 seconds will result in a GPWS INOP indication. Discrete Position / Status Connector Pin GPWS INHIBIT Inhibit = Gnd Normal = Open J1-67 3.15.2 Output Disc retes The discrete outputs are defined in Appendix E Section 7.4. The MK VI/VIII EGPWS supports two kinds of Ground/Open discrete outputs used to indicate various conditions. Monitor outputs are used to indicate failure conditions for the EGPW system. Monitor outputs default to an active state when there is a failure or if power is removed from the EGPWS (no connection if the EGPWC is removed from the rack). The Discrete Out Lamp driver outputs are used to indicate alert modes (GPWS WARN, BELOW GS, etc.) or mode control status (FLAP OVRD, Terrain Display Select, etc.) of the EGPWS. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 108 Honeywell MK VI MK VIII EGPWS Installation Design Guide Short-term current limit protection is provided on all drivers for output shorting conditions. Ground going output discretes may be connected together to produce a ‘wired OR’ function for the active low state of the outputs. If output discretes are ‘wire OR’d’ then diodes must be installed for isolation. Output discretes are intended to operate with +28 VDC lamp sources and will not operate with +5 VDC lamp sources. 3.15.2.1 Lamp Form at The Lamp Format Type (configuration) is a function of the discrete output pin functions and defines the operation of the red and amber GPWS cockpit lamps. For Lamp Format Type 1, the amber “Below G/S” lamp is driven by the GPWS Alert (Glideslope only) discrete and the red “GPWS” lamp is driven by the remaining alerts and warnings. For Lamp Format Type 2, the red “GPWS” lamp is driven by the GPWS Warning (Pull Up, Terrain Pull Up, and Obstacle Pull Up only) discrete and the amber “GPWS” lamp is driven by the remaining alerts and warnings. Note: Lamp Format 2 is highly recommended by Honeywell. As of April 2002 the FAA position paper on Lamp Format is in draft form, the FAA may require that all new installation of EGPWS use Lamp Format 2. 3.15.2.2 Flashing La mps The Flashing Lamps option is configurable as a function of the discrete output pin functions and defines the operation of the red and amber GPWS cockpit lamps. If the Flashing Lamps option is selected, both the red and amber GPWS cockpit lamps will flash when they are illuminated, if Flashing Lamps is not selected, they will be illuminated as steady lights. 3.15.2.3 GPWS INOP Discrete The GPWS INOP discrete (J1-72) indicates GPWS modes are inoperative. This feature activates a ‘GPWS INOP” lamp located in the cockpit within sight of the pilots. 3.15.2.4 TAD INOP D iscrete The TAD INOP discrete (J1-55) indicates Terrain Clearance Floor (TCF), Terrain Awareness (TA), and Terrain Display are ‘Not Available’. This feature activates a ‘TERRAIN NOT AVAILABLE” lamp located in the cockpit within sight of the pilots. 3.15.2.5 GPWS War ning Discrete (Lamp Format Type 1 definition) GPWS Warning discrete (J1-78) will activate during any Mode 1 through Mode 4 alert or warning, Terrain Awareness caution/warning, or Obstacle Awareness caution/warning. This feature activates a ‘GPWS’ lamp located in the cockpit within sight of each pilot. Note that Mode 6 does not activate any lamp outputs, only voices. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 109 Honeywell MK VI MK VIII EGPWS Installation Design Guide (Lamp Format Type 2 definition) GPWS Warning discrete (J1-78) will activate during any Mode 1 or 2 Pull Up warning, Terrain Awareness warning, or Obstacle Awareness warning. This feature activates a ‘GPWS’ lamp located in the cockpit within sight of each pilot. 3.15.2.6 GPWS Aler t Discrete (Lamp Format Type 1 definition) GPWS Alert discrete (J1-77) will activate during Mode 5 Glideslope cautions only. This feature activates a ‘BELOW GS’ amber lamp located in the cockpit within sight of each pilot. (Lamp Format Type 2 definition) GPWS Alert discrete (J1-77) will activate during any Mode 1 Sinkrate, Mode 3 Don’t Sink, Mode 4 Too Low Gear, Too Low Flaps, Too Low Terrain, Mode 5 Glideslope, Terrain Awareness caution, or Obstacle Awareness caution. This feature activates a ‘GPWS’ amber lamp located in the cockpit within sight of each pilot. 3.15.2.7 Glideslope Cancel’d Discrete -Optional- Glideslope Cancel’d discrete (J1-76) will activate when the Glideslope Cancel discrete (momentary) has been pressed any time below 2000 feet Radio Altitude if the ILS is tuned. This feature activates a ‘G/S CANCLD” amber lamp located in the cockpit within sight of the pilots. 3.15.2.8 Flap Overri de Discrete -Optional- Flap Override discrete (J1-73) will activate after either pilot has initiated the manual selection of the Flap Override (momentary) discrete. This feature activates a ‘GPWS FLAP OVRD” blue lamp located in the cockpit within sight of the pilots. The lamp serves to remind the flight crew that this function is active. 3.15.2.9 Steep Appro ach Discrete Steep Approach discrete (J1-52) will activate when the Steep Approach discrete (momentary action) has been pressed. This feature activates a “STP APR” amber lamp located within sight of the pilots. 3.15.2.10 Audio On D iscrete (TCAS/TAS Inhibit) -Optional- Audio On discrete (J1-69) will activate during any EGPWS voice annunciation. This output is used to inhibit other systems (such as TCAS or TAS) from talking during EGPWS annunciation. This feature does not have a lamp associated with it. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 110 Honeywell MK VI MK VIII EGPWS Installation Design Guide TCAS/TAS Connector Vendor Model Honeywell CAS-81, TCAS II, TPA-81A Collins TTR-920, TCAS II CAS 66, 67 Function TA Only Inhibit Audio TA Only Inhibit Audio Standby Inhibit Audio PIN # RBP-5C RBP-5D RBP-5C RBP-5D P1A-17 P1A-18 Inhibit Audio P1-34 P1-32 P1-9 Goodrich* Skywatch HP (SKY899) Skywatch (SKY497) TCAS I (TCAS791/A) * Interface with the Goodrich Skywatch TAS requires a +28V pullup resistor in the aircraft wiring as shown in Figure 3.15-1 below. EGPWS J1-34 J1-78 Self-Test Discrete Input PULLUP A BRT / DIM / TEST (7 places) GPWS Warning Alert Discrete Output P / TEST J1-15 J1-77 J1-72 J1-55 J1-12 Momentary G/S Cancel Discrete Input A GPWS GPWS Caution Alert Discrete Output P / CANCEL GPWS INOP TERR FAIL GPWS Inoperative Discrete Output Terrain Not Available Discrete Output Momentary A TERR INHIB Terrain Inhibit Discrete Input A ON J1-76 G/S Canceled Discrete Output G/S CANCLD A Alternate Guarded GPWS STP APR Steep Approach Select Discrete Input J2-31 J1-52 Steep Approach Select Discrete Output J1-14 J1-73 ON Guarded GPWS Flap Override Discrete Input FLP OVRD Flap Override Discrete Output A A ON Optional +28V pullup Momentary * * Requires -008 software or later 100K ohm Momentary J1-69 Audio On Discrete Output Note: All EGPWS Outputs are Ground active and are intended to operate with a +28V lamp source or +28V pullup external to the EGPWS TCAS INHIBIT Lamps2.vsd FIGURE 3.15-1 Example of Light/switch Interface (Lamp Format 2) 3.15.2.11 Terrain Dis play Select #1 & #2 Discrete Terrain Display Select #1 & #2 discrete (J1-54 & J1-49) will activate after the related pilot has initiated manual selection of the Terrain Display Select (momentary) discrete #1 or #2 (J1-32 & J1-31, Category 6). This feature activates a ‘TERR” white lamp located in the cockpit within sight of each pilot. The lamp serves to remind the flight crew that this function is active. The select switches (J1-32 & J1-31) and the indicator lamps (J1-54 & J149) are commonly combined in switch-lamp assemblies mounted near the displays being selected. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 111 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.15.2.12 Terrain Pop up Discrete Terrain Pop Up discrete (J1-51) will activate when a Terrain/Obstacle Caution or Warning alert event has occurred. This feature activates the pop up in an integrated display or will switch a relay to pop up Terrain display over selected weather radar display. The Pop Up discrete can be used by a display system to differentiate between a manual Terrain display selection or Terrain display selection due to a Terrain/Obstacle Caution or Warning alert event. A 429 Tx B J2-43 J2-42 Range #1 A B J2-37 J2-36 Range #2 A B J2-41 J2-40 A 453 #1 B J1-58 J1-59 A 453 #2 B J1-56 J1-57 Discrete J1-51 DSD #1 Gnd J1-32 DSD #2 Gnd J1-31 WXR System R/T Spare #2 429 IN WXR/TERR Display 453 OUT ARINC 429 RANGE BUS ARINC 453 TERRAIN BUS #1 Spare #2 A B 429 Range Output Bus A B 453 WX / TERR BUS TERRAIN POP-UP Terrain Pop-Up Discrete Output Display Select Discrete #1 Input Spare #2 TERR TERRAIN SELECTED A DISPLAY RELAY * ON 28 VDC Momentary Discrete J1-54 Terrain Display Select #1 Discrete Output * Display relay specifications: - 4PDT - Continuous Duty Cycle - Pickup Voltage: 13.5 Vdc Max. - Dropout Voltage: 7.5 - 2.0 Vdc - Coil Resistance: nominal 500 Ohms (~100mA @ 28 Vdc) - Coil Rating: 26.0 Vdc (nominal) 34 Vdc (max.) - Contact V drop: < 125mV @ rated load - Contact current rating: 2 Amps resistive @ 28 Vdc EM6-disp.vsd FIGURE 3.15-2 Example of Terrain Display Interface EGPWS J1-32 TERR DISPLAY +28V EGPWS J1-54 OFF Amber ON +28V Green TerrDisSw.vsd Figure 3.15-3 Example of Terrain Display switch with relay Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 112 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.15.3 Instruction s Using Appendix E Tables 5.2, 5.3.13 and 5.3.13-x as described above, select the Input/Output Discrete Type number that matches the aircraft configuration, feature preferences and version (part number) being installed. Record the ID number for the Input/Output Discrete Select number from Appendix E Table 5.3.13 under the Ident No. heading for Step (Category) 13 in Appendix E Table 5.2. Using the Input/Output Discrete Type number from Appendix E Table 5.3.13 as “x”, go the Appendix E Table 5.3.13-x. The electrical interfaces for the Input/Output Discrete Type are shown in Appendix E Table 5.3.13-x and are used to generate the installation wiring diagrams. Note: When there are two discrete pin choices for the same pin function in Appendix E Table 5.3.13-x, use only the one that matches the aircraft wiring (use only the +28V and 0V or the Ground and Open definitions). 3.16 Category 1 4 – Audio Output Level Category 14 controls the Audio Output level for alert menu callouts (cautions and warnings). Refer to Category 13 for information on the Mode 6 Low Volume discrete. Appendix E Table 5.3.14 defines the Audio Output Level options and identifies the first MK VI/VIII EGPWS version in which the option was available (see the Effectivity entry). The Nominal Volume Select is equivalent to MK VI (classic) MAX volume level. The –6dB through –24 dB are successively lower volume from Nominal. The Nominal output is 4 watts rms into an 8-ohm load and 100 milliwatts rms into a 600-ohm load. The audio output level for Mode 6 alerts can be reduced an additional 6 dB by activating the Mode 6 Low Volume discrete of Category 13. 3.16.1 Instruction s Using Appendix E Tables 5.2 and 5.3.14 as described above, select the Audio Output Level ID number that matches the feature preferences and version (part number) being installed. Record the ID number for the Audio Output Level from Appendix E Table 5.3.14 under the Ident No. heading for Step (Category) 14 in Appendix E Table 5.2. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 113 Honeywell MK VI MK VIII EGPWS Installation Design Guide H L J1-70 J1-71 High level audio H L J1-75 J1-74 Low level audio 8 ohm 600 ohm Audio Panel FIGURE 3.16-1 Audio Interface 3.17 Category 1 5 - 17 – Undefined Input Selects Category 15-17 are undefined input selects at this time. Appendix E Table 5.3.15, 5.3.16, and 5.3.17 define the Select options and identifies the first MK VI/VIII EGPWS version in which the option was available (see the Effectivity entry). 3.17.1 Undefined Input Select Select ID 0 for all aircraft configurations. Input Select options will be added as new installations types are propagated. 3.17.2 Instruction s Using Appendix E Table 5.2, 5.3.15, 5.3.16, and 5.3.17 as described above, select the Input Select type that matches the aircraft configuration, feature preferences and version (part number) being installed. Record the ID number for the Input Select from Appendix E Table 5.3.15, 5.3.16, and 5.3.17 under the Ident No. heading for Step (Category) 15, 16, & 17 in Appendix E Table 5.2. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 114 Honeywell MK VI MK VIII EGPWS Installation Design Guide SECTION IV CONFIGURATION MODULE PROGRAMMING AND TERRAIN DATABASE LOADING Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 115 Honeywell MK VI MK VIII EGPWS Installation Design Guide SECTION IV – CONFIGURATION MODULE PROGRAMMING AND REGIONAL TERRAIN DATABASE LOADING SECTION IV – CONFIG MODULE PROGRAMMING AND REGIONAL TDB LOADING ................................. 117 4.1 INTRODUCTION............................................................................................................................................................ 117 4.2 HARNESS CHECKOUT AND POWER CHECK .................................................................................................................. 117 4.3 UNIT INSTALLATION ................................................................................................................................................... 117 4.4 EGPWC INITIALIZATION AND CONFIGURATION ......................................................................................................... 117 4.4.1 RS-232 Communication with the MK VI/VIII EGPWS ........................................................................................ 117 4.4.2 EGPWC Front Panel Test Connector ................................................................................................................. 118 4.4.3 WinVIEWS ........................................................................................................................................................... 119 4.4.4 WinVIEWS Operation.......................................................................................................................................... 119 4.5 CONFIGURATION MODULE PROGRAMMING................................................................................................................. 119 4.5.1 CUW and CMR Commands................................................................................................................................. 121 4.5.2 Configuration Module Reprogramming .............................................................................................................. 122 4.6 TERRAIN DATABASE LOADING ................................................................................................................................... 122 4.6.1 Effectivity............................................................................................................................................................. 122 4.6.2 Description .......................................................................................................................................................... 123 4.6.3 Approval .............................................................................................................................................................. 123 4.6.4 Material – Cost and Availability ......................................................................................................................... 123 4.6.5 Accomplishment Instructions............................................................................................................................... 123 4.6.6 Verification of the Terrain Database Version ..................................................................................................... 125 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 116 Honeywell MK VI MK VIII EGPWS Installation Design Guide SECTION IV – Config Module Programming And Regional TDB Loading 4.1 Introduction The following procedures outline the steps necessary to accomplish a complete configuration of the MK VI/MK VIII EGPWS. This section must be accomplished in the order presented to minimize errors in configuring and operating the system(s). If problems are encountered in performing these procedures, the installer may refer to aircraft wiring diagrams for harness troubleshooting or the aircraft maintenance manual to isolate faulty equipment. All discrepancies should be resolved before proceeding. This section will also load the Regional Terrain Database in MK VI EGPWS that will be operating outside the AMERICAS region. 4.2 Harness Ch eckout and Power Check Prior to installing any equipment, it is important to verify that all interfaces have been made, and that power and ground at each unit connector is correct using the wiring diagrams for the installation. Any discrepancies in the wiring must be resolved before proceeding. The wire harness should also be checked for proper clearance near any control cables and other potential areas that may cause binding and/or chafing. 4.3 Unit Installa tion After the harness check has been completed and any discrepancies have been resolved, the units should be installed into their respective racks, and all connections to the wiring harness should be made (connectors attached). Verify that all of the units are secure in their respective racks, panels, etc., and all harness connections are secure. Refer to aircraft installation drawings for the unit locations and mounting information. 4.4 EGPWC Ini tialization and Configuration The first time a MK VI/MK VIII EGPWS is turned on in a new installation, the Configuration Module in the EGPWS harness must be programmed to the specific interface configuration for the aircraft. This programming is done via RS-232 cable connection between the EGPWC and a PC running the Honeywell WinViews software. This interface capability is provided to facilitate diagnostic and configuration functions with the EGPWC during post installation checkout. Refer to Appendix C for instructions related to using the WinViews software. 4.4.1 RS-232 Com munication with the MK VI/VIII EGPWS The MK VI/MK VIII EGPWS computer contains software that allows monitoring of its internal parameters, for testing purposes, without altering its operation. The monitoring of these parameter values enables the operator to quickly determine if the EGPWC is using the correct signal and scaling. The communication link utilizes the RS-232 communication protocol configured as follows: 19200 Baud, No Parity, 8 Bits, and 1 Stop Bit Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 117 Honeywell MK VI MK VIII EGPWS Installation Design Guide 4.4.2 EGPWC Fro nt Panel Test Connector The RS-232 interface with the EGPWC is accomplished via a test connector provided on the EGPWC front panel (J3). This provides access for a PC test monitor and portable data loading capabilities. The mating connector for the EGPWC test plug (P3) is a male, 15 pin, double density D-subminiature type (or equivalent). The connection between the PC serial port connector (with standard DB9) and the EGPWC RS-232 interface is defined as follows: RS-232 Receive RS-232 Transmit RS-232 Ground EGPWS Front Connector (J3) Pin 3 Pin 4 Pin 1 Standard (PC)* DB9 Connector Pin 2 Pin 3 Pin 5 *NOTE: Some PC Comm Ports have Pins 2 & 3 reversed from what is described above. Connector, AMP 204513-2* Pin Contact, 204370-2, QTY 4* M39029/58-360 Backshell, AMP 745854-5 Jackscrew, AMP 747784-3 Grommet Set, AMP 747746-1 P3 Connector, AMP 205161-1 Socket Contact, AMP 205090-1, QTY 3 M39029/63-368 PCOM 2 3 3 4 5 1 Length as required (5' to 50') * Alternate part number 748364-1 connector and 748333-4 or -7 pin contact. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 118 Honeywell MK VI MK VIII EGPWS Installation Design Guide 4.4.3 WinVIEWS (Windows Virtual Interface to the Enhanced Warning System) WinVIEWS is a software tool developed by Honeywell to communicate with the EGPWS. WinVIEWS provides a detailed status of the software configuration and input signals, which enables quick identification of system configuration, and is utilized for programming the system Configuration Module. To obtain a copy of the WinVIEWS software, contact: Honeywell Aerospace Electronic Systems PO Box 97001 Redmond, WA 98073-9701 USA Attn: Order Administration M/S 33 Phone: (425) 885-8719 FAX: (425) 885-8988 or Honeywell Aerospace Electronic Systems PO Box 97001 Redmond, WA 98073-9701 USA Attn: EGPWS Applications Engineering Phone: (425) 885-3711 FAX: (425) 885-2994 GPWS Hotline: (800) 813-2099 WinVIEWS can be sent via e-mail when an e-mail address is provided. 4.4.4 WinVIEWS Operation 1. 2. 3. 4. Connect the PC to the EGPWC using the RS-232 cable as described in section 4.4.2 On the PC, start Windows 3.1, or higher. Start the WinVIEWS.EXE program. Use F6 to select the Terminal Mode. Various commands are available in this mode. Type “HELP” or “?” for a list of the commands available. 4.5 Configurati on Module Programming The EGPWC reads the aircraft configuration from the Configuration Module, which is installed in the EGPWC connector. The Configuration Module must have the aircraft specific configuration ID string written to it before the EGPWS is operational. The ID string is defined by 15 separate categories listed in Appendix E Table 5.2, Category ID Selection Procedure. For programming the Configuration Module, the following procedure is used: 1. Verify EGPWC interface to P2 connector (including Configuration Module) and RS-232 interface to PC. 2. Power EGPWC and PC and start WinVIEWS. 3. With WinVIEWS active in the Terminal Mode, configuration sub-mode commands are available for programming purpose. Type “CFG” at the Terminal Mode prompt (>). At this point, the CFG> prompt is displayed and the program and EGPWC are ready for entering the program command and data string. Type “HELP” or “?” to display a list of the Terminal Mode commands and their description. “CUW” is the preface command for entering the ID string. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 119 Honeywell MK VI MK VIII EGPWS Installation Design Guide 4. Using the Category ID’s as chosen from the Appendix E (refer to completed Table 5.2), create a command string with the following structure: CFG> CUW 0/15 # # # # # # # # # # # # # # #/ - CUW 0 is the command and version number. CUW writes the category ID’s defined by version 0 definition (0 is the only version currently available) to the Configuration Module via the EGPWC without a CRC (checksum) value attached (this is generated by the EGPWC when the data is transmitted). - /15 indicates the beginning of the data string (/) with 15 being the number of categories to follow. - … / each Cat ID# is the chosen ID for the category from the Appendix E Table 5.2. The ending slash (/) indicates the end of the data string. Note: If 15 ID’s do not follow “/15”, the error message “Invalid Parameter. Not enough ID’s. Configuration update failed, please try again.” will be given. The value entered for each category must be an available ID for the associated category or a similar error message will be given. If the number of categories provided is less than 15 (e.g., “/8 # … #/” with eight ID’s defined), then the remaining categories (9 through 15) will be set to 0. After completing the data string as defined above and pressing ENTER, the following message may appear: “Confirm this data reflects configuration to be programmed (Y/N)”. If the message does not appear, the cursor will flash. In either case, it is waiting for an answer “Y” or “N”. Pressing the Y (or y) key confirms the data and sends the data to the EGPWC to write to the Configuration Module. Following the writing to the Configuration Module the EGPWC is automatically rebooted in order for the new configuration to take affect. Note: If when the ENTER key is pressed the question response is not given (cursor just moves to the next line), pressing any character key should provide the proper response. Pressing the N key results in the message “Command aborted – No configuration module change has been made”. If necessary, revise the data to correct or change as necessary and continue as above. The backspace key can be used to make corrections. 5. Following the successful writing to the Configuration Module (no error messages) and EGPWC reboot, pressing Control Z (Ctrl-Z) restarts the WinVIEWS Terminal Mode communication. 6. There are a couple ways to now confirm the Configuration Module programming with the following being the preferred. As above, type “CFG” to restart the Configuration sub-mode. At the CFG> prompt, type “CMR ”. Each category and its associated ID is read from the Configuration Module and listed on the PC screen. Alternately, when not in the Configuration sub-mode, the command “PS ” (Present Status) will display EGPWC and configuration data. 7. Configuration Module programming is complete. If the “CFG >” prompt is still present type “Exit ” to exit the Configuration sub-mode. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 120 Honeywell MK VI MK VIII EGPWS Installation Design Guide 4.5.1 CUW and C MR Commands An example CUW command/data string, its definition, and the corresponding CMR list is provided below. CUW command/data string: CFG > CUW 0/15 2 3 2 0 0 3 93 1 0 0 0 0 0 0 0/ Type “Y” or “y” to confirm the data and send the data to the EGPWC to write to the Configuration Module Above configuration defined: Category 1 Aircraft/Mode Type: Category 2 Air Data Type: Category 3 Position Type: Category 4 Altitude Callouts Menu: Category 5 Audio Menu: Category 6 Display Type: Category 7 Options Select Group #1: 2 3 2 0 0 3 93 Category 8 Radio Altitude Type: Category 9 Navigation Type: Category 10 Attitude Type: Category 11 Heading Type: Category 12 Windshear select Type: Category 13 Discrete I/O Type: Category 14 Audio Output Level Type: Category 15 Undefined Type: 1 0 0 0 0 0 0 0 (Basic menu) (Steep Approach True) (TA&D Alternate pop-up False) (Peaks Mode True) (Obstacle Awareness True) (Bank Angle True) (Flap Reversal False) (GPS Altitude Ref. MSL) CMR list: (based on the previous configuration) CFG > CMR CONFIGURATION MODULE: Format Version: 0 Category 1 ID: 2 Category 2 ID: 3 Category 3 ID: 2 Category 4 ID: 0 Category 5 ID: 0 Category 6 ID: 3 Category 7 ID: 93 Category 8 ID: 1 Category 9 ID: 0 Category 10 ID: 0 Category 11 ID: 0 Category 12 ID: 0 Category 13 ID: 0 Category 14 ID: 0 Category 15 ID: 0 CRC: 527518533 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 121 Honeywell MK VI MK VIII EGPWS Installation Design Guide 4.5.2 Configurati on Module Reprogramming Reprogramming the EGPWS Configuration Module is accomplished similar to the programming process above. Prior to reprogramming, the desired new configuration should be determined based on the MK VI/VIII Interface Description Document (Appendix E), document number 060-4314-401. For reprogramming the Configuration Module, the following procedure is used: 1. Verify EGPWC interface to P2 connector (including Configuration Module) and RS-232 interface to PC. 2. Power EGPWC and PC and start WinVIEWS. 3. With WinVIEWS active in the Terminal Mode, start the Configuration sub-mode by typing “CFG” at the prompt (>). At this point, either all the ID’s can be rewritten using the CUW command as before, or individual categories can be changed as follows: 4. At the CFG > prompt use the CAT command with the following structure: - CAT is the Appendix E Category to change (example 7) is the new ID to change to (example 92) is True or False for rebooting the EGPWC. Use “T” if only one category is to be changed and the EGPWC will reboot following . Use “F” if another individual ID is to be changed by another CAT operation. Example: CFG > CAT 7 92 T 5. After inputting the desired change information, pressing will transmit the data to the EGPWC to write to the Configuration Module. If a reboot is commanded (T), then the EGPWC will reboot at the completion of the write process. If a reboot is not commanded (F), then a message “Writing to configuration module … Category 7 ID updated successfully.” is given and the CFG > prompt is again displayed. At this point the Configuration Module has been changed, but the change will not be effective until the EGPWC is rebooted. Additional changes can be made with the final change set to command the EGPWC to reboot (or cycle EGPWC power to reboot). 6. Verification of the changes made is the same as before. As above, type “CFG” to restart the Configuration sub-mode. At the CFG > prompt, type “CMR ”. Each category and its associated ID is read from the Configuration Module and listed on the PC display. Alternately, when not in the Configuration sub-mode, the command “PS ” (Present Status) will display the EGPWC and Configuration Module data. 7. Configuration Module reprogramming is complete. 4.6 Terrain Dat abase Loading 4.6.1 Effectivity The MK VI EGPWS (965-1180-0XX and 965-1190-0XX) are shipped from the factory loaded with the Regional Terrain Database requested when the purchase order was placed. Use (operation) of a MK VI EGPWS outside of the loaded Regional Terrain Database will result in the Terrain Awareness function being unavailable. Aircraft operating outside the loaded Regional Terrain Database region will have to load one of the other two Regional Terrain Databases before beginning the ground test. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 122 Honeywell MK VI MK VIII EGPWS Installation Design Guide The MK VIII EGPWS (965-1210-0XX and 965-1220-0XX) have a Global Terrain Database. 4.6.2 Description This modification consists of loading the PCMCIA card into the EGPWS either In The Aircraft or On The Bench. An optional verification procedure is provided. 4.6.3 Approval This procedure contains no modification information that revises the approved configuration and therefore does not require FAA or other regulatory agency approval. 4.6.4 Material – C ost and Availability The AMERICAS, ATLANTIC or PACIFIC region PCMCIA card is available at no charge to Operators. Order part from: Honeywell Airlines & Avionics Products Order Administration M/S 33 PO Box 97001 Redmond, WA 98073-9701 Phone: 425-885-8719 Fax: 425-885-8988 Honeywell Aerospace Toulouse Office Centreda, Avenue Didier Daurat 31700 Blagnac, France Phone: (33) 5-6171-0079 Fax: (33) 5-6130-0497 Vendor Name Vendor P/N Description QTY UM Honeywell P/N Honeywell 718-1391-xxx AMERICAS Region Card 1 EA 718-1393-xxx Honeywell 402-6075-xxx AMERICAS Region Label 1 EA 402-6075-xxx Honeywell Honeywell 718-1392-xxx 402-6075-xxx ATLANTIC Region Card ATLANTIC Region Label 1 1 EA EA 718-1392-xxx 402-6075-xxx Honeywell Honeywell 718-1393-xxx 402-6075-xxx PACIFIC Region Card PACIFIC Region Label 1 1 EA EA 718-1393-xxx 402-6075-xxx 4.6.5 Accomplish ment Instructions Load the PCMCIA card data as described in paragraphs 4.6.5 A. or 4.6.5 B. below. Loading time will be approximately 10 minutes. A. Loading the PCMCIA Card Data with Computer Mounted in the Aircraft. (1) Connect the Smart Cable (Honeywell PN 951-0386-001) to the EGPWC J3 connector. (2) Ensure that the 28 VDC circuit breaker to the EGPWC in ON and that the COMPUTER OK LED on the EGPWC front panel is on. (3) Insert the PCMCIA card into the Smart Cable PCMCIA card slot. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 123 Honeywell MK VI MK VIII EGPWS Installation Design Guide NOTE: Precautionary notes on the PCMCIA card, regarding insertion and/or removal while power is applied, should be ignored since the EGPWC automatically handles the application and removal of PCMCIA card power. (4) While the loading is in progress, the IN PROG LED on the Smart Card remains ON and the COMPUTER OK LED on the EGPWC is OFF. (5) When loading is complete the XFER COMP LED on the Smart Card turns ON. (6) Remove the PCMCIA card from the Smart Card slot. (7) After approximately 15 seconds the COMPUTER OK LED comes ON to indicate that the contents of the PCMCIA card were successfully transferred. (8) Remove the Smart Card connector from the EGPWC front panel J3 connector. (9) To perform the verification of the Terrain Database version, go to paragraph 4.6.6 below. B. Loading the PCMCIA Card Data with Computer Mounted on the Bench (1) Locate a 28 VDC Power Supply with a minimum supply current of 2 amps. (2) With the Power Supply turned OFF, connect the Power Supply to the J1 connector of the EGPWC as follows (pin J1-53 is connected to chassis ground internally and does not need to be ground in aircraft wiring): J1 connector Pin J1-40, J1-60 J1-41, J1-61 J1-42, J1-53 Pin Nomenclature 28 VDC (+) 28 VDC (-) Chassis GND Pins J1-42 and J1-53 are both connected to chassis ground internally. It is not necessary to tie them both to ground in the aircraft wiring. Pin J1-53 was made available to provide a convenient way to supply a ground to external equipment. If the OAT probe is not present, nothing needs to be tied to J153. (3) Connect the Smart Cable (Honeywell PN 951-0386-001) to the EGPWC J3 connector. (4) Turn the Power Supply ON and that the COMPUTER OK LED on the EGPWC front panel is on. (5) Insert the PCMCIA card into the Smart Cable PCMCIA card slot. NOTE: Precautionary notes on the PCMCIA card, regarding insertion and/or removal while power is applied, should be ignored since the EGPWC automatically handles the application and removal of PCMCIA card power. (6) While the loading is in progress, the IN PROG LED on the Smart Card remains ON and the COMPUTER OK LED on the EGPWC is OFF. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 124 Honeywell MK VI MK VIII EGPWS Installation Design Guide (7) When loading is complete the XFER COMP LED on the Smart Card turns ON. (8) Remove the PCMCIA card from the Smart Card slot. (9) After approximately 15 seconds the COMPUTER OK LED comes ON to indicate that the contents of the PCMCIA card were successfully transferred. (10)Remove the Smart Card connector from the EGPWC front panel J3 connector. (11)To perform the verification of the Terrain Database version, go to paragraph 4.6.6 below. 4.6.6 Verification of the Terrain Database Version Since the EGPWC software verifies the PCMCIA card loading process, this verification is to assure the operator/installer that the correct Regional Terrain Database version is installed. Terrain Database version verification is accomplished with the EGPWS Self Test (ST) function. The ST function may be initiated from the aircraft cockpit with the GPWS Test Switch. NOTE: Initiation of the cockpit ST function may vary from one aircraft to another. For example, the ST function may be initiated by pressing the GPWS (PULL-UP) light assembly, or by activating a separate ST switch. The EGPWS ST function has 6 levels that describe the current condition and configuration of the EGPWS, the fault and warning history, and the condition of the various inputs. To help navigate through the various levels, there are 2 cancel functions: SHORT CANCEL (press and hold the ST button for more than 0.5 seconds, but less than 2 seconds) and LONG CANCEL (press and hold the ST button for more than 2 seconds, but less than 8 seconds). The Short Cancel and Long Cancel functions operate differently, depending upon the ST level. To initiate a ST sequence, or to continue from level-to-level, the ST button must also be ‘pressed and held’ for more than 0.5 seconds, but less than 2 seconds, which is identical to the Short Cancel function. Therefore, for simplicity, the phrase “Press ST Button” in the verification procedure means to press and hold the ST button for more than 0.5 seconds, but less than 2 seconds. The procedure guides the operator directly to ST Level 3, “System Configuration”, skipping most of ST Level 1 and Level 2. To verify the Regional Terrain Database that was just loaded into the EGPWC, perform these steps: NOTE: ‘On the Bench’, this test requires an audio speaker and a self test button. These may not be available ‘On the Bench’ unless when using a Break-Out-Box. (1) Ensure the EGPWC power is ON (2) Press ST button to initiate ST Level 1. (3) After ST Level 1 message starts, Press ST button to cancel Level 1 and start Level 2. (4) After ST Level 2 message, “Current Faults”, is heard, Press ST button to cancel Level 2. (5) When the message, “Press to Continue”, is heard, Press ST button to start ST Level 3. (6) Verify the Terrain Database version annunciated in the following sequence: Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 125 Honeywell MK VI MK VIII EGPWS Installation Design Guide a) “SYSTEM CONFIGURATION” b) “PART NUMBER 965-11X0-XXX” c) “MOD STATUS XX” d) “SERIAL NUMBER XXXX” e) “APPLICATION SOFTWARE VERSION XXXXX” f) “TERRAIN DATABASE VERSION XXXX” The following example of Terrain Database Version annunciation: “419A” (for ATLANTIC), “419P” (for PACIFIC), or “419N” (for AMERICAS). Other versions will follow the same pattern (e.g. “421P”). (7) Other messages that follow the Terrain Database Version can be ignored. When ST Level 3 finishes, the message “Press to Continue” is heard. If the ST button is not pressed again the ST sequence terminates. NOTE: If power was connected to the EGPWC per steps B1 through B4, perform shut-down per steps (7) and (8) following. (8) Turn Power Supply OFF. (9) Disconnect Power leads from the EGPWC. END OF TEST Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 126 Honeywell MK VI MK VIII EGPWS Installation Design Guide SECTION V CERTIFICATION Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 127 Honeywell MK VI MK VIII EGPWS Installation Design Guide SECTION V – CERTIFICATION 5.1 Introductio n This section outlines the procedures required to obtain FAA approval for the MK VI/MK VIII EGPWS installation. Recommended flight test procedures are also included. 5.2 Certificatio n Procedure 5.2.1 Equipment Compatibility Careful consideration must be paid to the electrical characteristics of existing equipment or possible additions that will be interfaced to the MK VI/MK VIII EGPWS, in order to ensure system compatibility. Section III of this manual provides system planning guidelines, and defines the electrical characteristics of the EGPWS. The installing agency should contact Honeywell Product Support (800-813-2099), for information regarding the compatibility of equipment not listed in Section III. Normal business hours are 8:00 AM to 5:00 PM Pacific Time, Monday through Friday. 5.2.2 Equipment Location The EGPWS and associated indicators, annunciators, and switches should be clearly visible and within easy reach of the pilot(s). Refer to Section II of this manual for complete installation information. 5.2.3 FAA Requir ements The installing agency should contact a local FAA Inspector who will determine whether the installation may be approved by Supplemental Type Certificate (STC) or by submitting FAA Form 337 with an applicable STC package. 5.2.4 Ground Tes t Honeywell has developed a generic Installation Ground Test Procedure for the MK VI/MK VIII EGPWS, drawing number 060-4167-158. 5.2.5 Flight Manu al Revision Honeywell has developed a generic Airplane Flight Manual Supplement for the MK VI/MK VIII EGPWS, drawing number 060-4199-194. 5.2.6 Flight Test Honeywell has developed a generic Flight Test procedure for the MK VI/MK VIII EGPWS (GA-Fast and GASlow aircraft), drawing number 060-4188-041. A separate generic Flight Test procedure has been developed for MK VIII EGPWS Bizjet aircraft, drawing number 060-4188-023. The Flight Test procedures were developed for Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 128 Honeywell MK VI MK VIII EGPWS Installation Design Guide first of type installations, for these installations all sections of the Flight Test procedure shall be performed. Precedence has been established for testing only the Terrain Awareness functions when replacing an existing MK VI GPWS. Installers should contact their local FAA office for confirmation of this approach. For follow on installations of the same aircraft type and interface, the flight test is not required. When updating an STC to the current part number it is only necessary to flight test significant new features. The notice of change is available in Honeywell Service Bulletins. Suggestions for recording of the EGPWS data during a Flight Test for follow on analysis: • • • • • In WinViews change the recording Sample Rate to 1 second intervals (WinViews / Terminal Mode / Options / Settings / 1000 ). This sample rate will record adequate data for future analysis. Continue recording between tests. Missing data is aggravating. Recording in flight between test sites (hundreds of miles apart) is not necessary but continuous recording when Mode 1 ends and Mode 4 begins is helpful. Recording of the take off from brakes locked through climb out also aids later analysis, as does continuous recording of approach to aircraft off the runway. The WinViews software program records in 1.44 megabyte files that can be transferred from Laptop computer to other computers with ease. Using 1 second sample rate the EGPWS will record approximately 40K bytes per minute of data. 1 hour of recorded time would be approximately 2.4MB, most laptops have 1GB or more free space. Use the Event Marker, F9 key, to identify events during tests. Use the F10 key to roll (increment) the history file name between test sequences. Rolling adds a number to the end of the filename (or increments the existing number, if possible.) Example: use tail number (N3GC) in the file name with a file number (01), this gives a filename N3GC01.hst which will roll to N3GC02.hst when the F10 key is pressed. 5.2.7 Pilots Guid e Honeywell has developed a Pilot’s Guide for the MK VI/MK VIII EGPWS, drawing number 060-4314-000 that provides a description of the modes and the controls of the EGPWS. 5.2.8 Failure Mod es, Effects, and Safety Analysis Honeywell has developed a Failure Modes, Effects, and Safety Analysis document for the MK VI/MK VIII EGPWS, drawing number 060-4199-182 that provides an analysis of the failure modes of the EGPWS. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 129 Honeywell MK VI MK VIII EGPWS Installation Design Guide SECTION VI MK VI GPWS (classic) to EGPWS MK VI/VIII Pin to Pin Comparison Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 130 Honeywell MK VI MK VIII EGPWS Installation Design Guide SECTION VI - MK VI GPWS to MK VI/VIII EGPWS Signal Mapping Connector Pin-Out Sorted By Pin Number (USE FOR REFERENCE ONLY) shaded area indicates function change Signal Name –MK-VI GPWS (965-0686-001, -020) Roll Attitude Synchro (X) X=Indicates same function Signal Type Same Conn/Pin Synchro X Signal Type < IN Out > Signal Name -MK-VI/MK VIII EGPWS (Enhanced) J1-01 < AC Analog3W1 Roll Attitude Synchro (X) GND J1-02 < AC Analog3W3 Roll Attitude Synchro (Z) Spare #1 Program Pin ProgPin J1-03 < AC Analog3W1 Magnetic Heading Synchro (Z) Alternate Airspeed Expansion Program Pin ProgPin J1-04 < AC Analog (H) 26 VAC Reference #1 (H) Fixed Landing Gear Program Pin ProgPin J1-05 < AC Analog3W1 Pitch Synchro (X) Audio Volume Control #2 Program Pin ProgPin J1-06 < AC Analog3W3 Pitch Synchro (Z) 200’ Altitude Callout Program Pin ProgPin J1-07 < AC Analog3W2 Pitch Synchro (Y) Chassis Ground Radio Altimeter ALT 55 Scale Program Pin ProgPin J1-08 < 28vDisc Autopilot Engaged Discrete (+28VDC) Barometric Altitude Rate Validity (+28VDC) Discrete X J1-09 < 28vDisc Glideslope Deviation Low Level Validity (L) DC-AnalogL X J1-10 < Analog (-) Glideslope Deviation Validity (+28VDC) Discrete J1-11 < 28vDisc Spare Reserved J1-12 < GDisc Terrain Awareness & TCF Inhibit Discrete (GND) Altitude Callouts Volume Reduction Discrete (GND) Discrete J1-13 < GDisc Mode 6 Low Volume Discrete (GND) GPWS Flap Override Discrete (GND) Discrete X X X X Barometric Altitude Validity (+28VDC) Glideslope Deviation Low Level Validity (-) and Localizer Deviation Low Level (-Left) Glideslope Deviation Validity (+28VDC) J1-14 < GDisc Glideslope Manual Cancel Discrete (GND) Discrete X J1-15 < GDisc Landing Gear Discrete (GND) Discrete J1-16 < GDisc External GPWC Audio Suppression Discrete (GND) Discrete J1-17 < GDisc Audio Inhibit Discrete (GND) Landing Flap Discrete (GND) Discrete J1-18 < GDisc Landing Flaps Discrete (GND) ILS Backcourse Approach Selected Discrete (GND) Discrete J1-19 < GDisc Glideslope Inhibit Discrete (GND) ILS Frequency Selected Discrete (GND) Discrete J1-20 < GDisc ILS Tuned Discrete (GND) Roll Attitude Synchro (Y) Synchro X X X X X X Flap Override Discrete (GND) (from FLAP OVRD SW) Glideslope Cancel Discrete (Gnd) (from GS Cancel SW) Landing Gear Discrete (GND) J1-21 < AC Analog3W2 Roll Attitude Synchro (Y) Spare Reserved J1-22 < AC Analog3W1 Magnetic Heading Synchro (X) Spare Reserved J1-23 < AC Analog3W2 Magnetic Heading Synchro (Y) Landing Flap Logic Inversion Program Pin Progpin J1-24 < AC Analog (L) 26 VAC Reference #1 (L) Alternate Mode 4B Threshold Program Pin Progpin J1-25 5Vref+ > Air Temperature Reference (+5VDC) Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 131 Honeywell MK VI MK VIII EGPWS Installation Design Guide Signal Name –MK-VI GPWS (965-0686-001, -020) Signal Type Same Conn/Pin Signal Type < IN Out > Signal Name -MK-VI/MK VIII EGPWS (Enhanced) Audio Volume Control #1 Program Pin Progpin J1-26 < Analog (+) Spare 500’ Altitude Callout Program Pin Progpin J1-27 < Analog (-) Spare Spare Discrete (+28VDC) Discrete J1-28 < 28vDisc Magnetic Heading Validity Discrete (+28VDC) Radio Altimeter Validity (+28VDC) 28vDisc X J1-29 < 28vDisc DC-AnalogL X J1-30 < Analog (+) Spare #1 Discrete Discrete J1-31 < GDisc Radio Altitude Validity Discrete (+28VDC) Glideslope Deviation Low Level Validity (+) and Localizer Deviation Low Level (+Right) Display Selected Discrete #2 (GND) Airspeed Expansion Discrete Discrete J1-32 < GDisc Display Selected Discrete #1 (GND) Decision Height DH Discrete (GND) Discrete X J1-33 < Gdisc GPWS Self Test Discrete (GND) Discrete X J1-34 < GDisc Landing Gear Discrete (+28VDC) Discrete J1-35 < 28vdisc External GPWS Audio Suppress Discrete (+28VDC) Discrete J1-36 < 28vdisc Audio Inhibit Discrete (+28VDC) Landing Flap Discrete (+28VDC) Discrete J1-37 < 28vdisc Landing Flaps Discrete (+28VDC) ILS Backcourse Approach Selectd Discrete (+28V) Discrete X X X X X X X X DH Discrete (GND) Self Test Discrete (GND) (from GPWS push to test Sw) Landing Gear Discrete (+28VDC) J1-38 < 28vdisc Glideslope Inhibit Discrete (+28VDC) J1-39 < 28vdisc ILS 1 Tuned Discrete (+28VDC) J1-40 < PWRH Glideslope Deviation Low Level Validity (H) ILS Frequency Selected Discrete (+28VDC) Discrete Power Input (+28VDC) PWR/GND Power Input (GND) PWR/GND Chassis Ground GND J1-41 < PWRL J1-42 < GND__C Power Input 28VDC (+) Power Input 28VDC (return) Chassis Ground Barometric Altitude Rate Input (-) DC-AnalogL J1-43 < Analog (-) Barometric Altitude (-) Airspeed Input (-) DC-AnalogL J1-44 < Analog (-) Radio Altimeter Input (-) DC-AnalogL X J1-45 < Analog (-) Glideslope Deviation Input (+ down) DC Analog X J1-46 < Analog (-) Air Temperature (-) Radio Altitude: ARINC 552 or ALT-55 (-) RT-200/300 Precision (+) Glideslope Deviation Low Level (+down) Test Point #1 Test point J1-47 < Analog (-) Spare Test Point #2 Test point J1-48 < 28vdisc Test Point #3 Test point J1-49 Lampout > (gnd) Test Point #4 Test point J1-50 Monitor Out > (gnd) Test Point #5 Test point J1-51 Lampout > (gnd) Test Point #6 Test point J1-52 Lampout > (gnd) Test Point #7 Test point J1-53 < GND Test Point #8 Test point J1-54 Lampout > (gnd) Localizer Validity Discrete (+28VDC) Terrain Select Relay Output #2 (to TERR lamp and/or Relay) Windshear Inop Lamp Output (monitor) Terrain Pop Up Discrete Output Steep Approach Windshear Caution Temperature Probe (GND) Terrain Select Relay Output #1 (to TERR lamp and/or Relay) Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 132 Honeywell MK VI MK VIII EGPWS Installation Design Guide Signal Name –MK-VI GPWS (965-0686-001, -020) Signal Type Same Conn/Pin Signal Type < IN Out > Signal Name -MK-VI/MK VIII EGPWS (Enhanced) Test Point #9 Test point J1-55 Monitor Out > (gnd) Test Point #10 Test point J1-56 453 Out (A) > Terrain Display Output Data #2 (A leg) Test Point #11 Test point J1-57 453 Out (B) > Terrain Display Output Data #2 (B leg) Test Point #12 Test point J1-58 453 Out (A) > Terrain Display Output Data #1 (A leg) Test Point #13 Test point J1-59 453 Out (B) > Power Input (+28VDC) PWR/GND J1-60 < PWRH Power Input 28VDC (+) Power Input (GND) PWR/GND Power Input 28VDC (return) X X TAD / TCF INOP Output (monitor) Terrain Display Output Data #1 (B leg) J1-61 < PWRL Barometric Altitude Rate Input (+) DC-AnalogL J1-62 < Analog (+) Barometric Altitude (+) Airspeed Input (-) DC-AnalogL J1-63 < Analog (+) Radio Altimeter Input (+) DC-AnalogL X J1-64 < Analog (+) Glideslope Deviation Input (+ Up) DC Analog X J1-65 < Analog (+) Air Temperature (+) Radio Altitude: ARINC 552 or ALT-55 (+) RT-200/300 Precision (-) Glideslope Deviation Low Level (+up) Spare Reserved J1-66 < Analog (+) Spare Spare Reserved J1-67 < GDisc Spare Lamp Output Output TCAS II Inhibit Output Output Audio Speaker Output – 8-ohm (H) Output Audio Speaker Output – 8-ohm (L) Output GPWS System Status Lamp GPWS Inhibit J1-68 < 28vdisc J1-69 Lampout > (gnd) J1-70 HL Audio Out (H) > High Level Audio Output - 8Ω (+) J1-71 HL Audio Out (L) > High Level Audio Output - 8Ω (-) Output X X X X J1-72 Monitor Out > (gnd) GPWS Flap OVRD Output X J1-73 Lampout > (gnd) Audio Low Level (C) Output J1-74 LLAud Out (L) > GPWS INOP (monitor) (to GPWS Fail/Inop lamp) Flap Override Output (to FLAP OVRD lamp) Windshear Warning Low Level Audio 600-ohm (C) Audio Low Level (H) Output Glideslope Cancelled Lamp Output X X X Glideslope Alert Lamp Output GPWS Alert/Warning Lamp Output Attitude Validity Discrete (+28VDC) Audio ON Output J1-75 LLAud Out (H) > Low Level Audio 600-ohm (H) J1-76 Lampout > (gnd) X J1-77 Lampout > (gnd) X J1-78 Lampout > (gnd) Glideslope Cancel Output (to GS CANCL’D lamp) Lamp Format 1: Glideslope Alert Output Lamp Format 2: GPWS, Terrain or Obstacle Caution GPWS Warning Output (to red GPWS or Pull Lamp) Terrain Caution or Warning Obstacle Caution or Warning Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 133 Honeywell MK VI MK VIII EGPWS Installation Design Guide Signal Name –MK-VI GPWS (965-0686-001, -020) Signal Type Same Conn/Pin Signal Type < IN Out > Signal Name -MK-VI/MK VIII EGPWS (Enhanced) NEW CONNECTOR J2-01 < AC Analog3W1 Configurable Synchro #1 (X leg) J2-02 < AC Analog3W2 Configurable Synchro #1 (Y leg) J2-03 < AC Analog3W3 J2-04 < 429 IN (B) J2-05 < 429 IN (B) Configurable Synchro #2 (Z leg) Radio Altitude ARINC 429 Input (B leg) IOC #2 (Nav) ARINC 429 Input (B leg) ILS ARINC 429 Input (B leg) J2-06 < 429 IN (B) J2-07 < 429 IN (B) AHRS ARINC 429 Input (B leg) GPS #2 ARINC 429 Input (B leg) Spare ARINC 429 Input (B leg) J2-08 < 429 IN (B) GPS ARINC 429 Input (B leg) J2-09 429 OUT (B) > J2-10 < 232 IN (B) J2-11 < 232 IN (A) J2-12 < 232 IN (B) EGPWS ARINC 429 Output #2 (B leg) Spare RS-422 Input (B leg) SCI Display Range #2 RS-422 Input (A leg) Spare RS-232 Input (Rcv) Spare RS-422 Input (A leg) SCI Display Range #2 RS-422 Input (B leg) GPS RS-422 Input (B leg) J2-13 J2-14 < GND J2-15 < 28vDisc Spare RS-232 Common Spare Discrete (+28VDC) J2-16 < PWR (L) Configuration Module Power (GND) J2-17 < PWR (H) Configuration Module Power (+5VDC) J2-18 < AC Analog3W3 Configurable Synchro #1 (Z leg) J2-19 < AC Analog3W1 Configurable Synchro #2 (X leg) J2-20 < AC Analog3W2 J2-21 < 429 IN (A) J2-22 < 429 IN (A) Configurable Synchro #2 (Y leg) Radio Altitude ARINC 429 Input (A leg) IOC #2 (Nav) ARINC 429 Input (A leg) ILS ARINC 429 Input (A leg) J2-23 < 429 IN (A) J2-24 < 429 IN (A) AHRS ARINC 429 Input (A leg) GPS #2 ARINC 429 Input (A leg) Spare ARINC 429 Input (A leg) J2-25 < 429 IN (A) GPS ARINC 429 Input (A leg) J2-26 429 OUT (A) > EGPWS ARINC 429 Output #2 (A leg) Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 134 Honeywell MK VI MK VIII EGPWS Installation Design Guide Signal Name –MK-VI GPWS (965-0686-001, -020) Signal Type Same Conn/Pin Signal Type < IN Out > Signal Name -MK-VI/MK VIII EGPWS (Enhanced) Spare RS-232 Input (Tx) Spare RS-422 Input (A leg) GPS/Spare RS-232 Common J2-27 < 232 IN (A) J2-28 < GND J2-29 < 232 IN (A) GPS RS-232 Input (Rcv) Spare RS-422 Input (A leg) J2-31 < GDisc Steep Approach #2 (GND) J2-32 Clock > Configuration Module Serial Clock J2-33 Data > Configuration Module Serial Input J2-34 < AC Analog (H) 26 VAC Reference #2 (H) J2-35 < AC Analog (L) 26 VAC Reference #2 (L) J2-36 < 429 input (B) J2-37 < 429 input (A) J2-38 < 429 input (B) J2-39 < 429 input (A) J2-40 < 429 input (B) J2-41 < 429 input (A) J2-42 429 Output (B) > Display Range #2 ARINC 429 Input (A leg) IOC #2 ARINC 429 Input (A leg) EGPWS ARINC 429 Output #1 (B leg) J2-43 429 Output (A) > EGPWS ARINC 429 Output #1 (A leg) J2-44 < 232 input (B) J2-45 < 232 input (A) J2-46 < 232 input (B) J2-30 Display Range #1 ARINC 429 Input (B leg) SCI Display Range #1 RS-422 Input (A leg) IOC #1 ARINC 429 Input (B leg) Display Range #1 ARINC 429 Input (A leg) SCI Display Range #1 RS-422 Input (B leg) IOC #1 ARINC 429 Input (A leg) Air Data ARINC 429 Input (B leg) IOC #1 (Nav) ARINC 429 Input (B leg) Air Data ARINC 429 Input (A leg) IOC #1 (Nav) ARINC 429 Input (A leg) Display Range #2 ARINC 429 Input (B leg) IOC #2 ARINC 429 Input (B leg) Spare RS-422 Input (B leg) GPS RS-232 Input (Tx) Spare RS-422 Input (A leg) Spare RS-422 Input (B leg) J2-47 J2-48 J2-49 < GDisc Configuration Module Serial Select J2-50 < Data Configuration Module Serial Output Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 135 Honeywell MK VI MK VIII EGPWS Installation Design Guide Signal Name –MK-VI GPWS (965-0686-001, -020) Signal Type Same Conn/Pin Signal Type < IN Out > Signal Name -MK-VI/MK VIII EGPWS (Enhanced) NEW CONNECTOR J3-01 PWR (L) > SmartCable Power Return (GND) J3-02 < Gdisc PCMCIA Card Present J3-03 < Data EGPWS Monitor Port RS-232 (RCV) J3-04 Data > EGPWS Monitor Port RS-232 (XMT) J3-05 J3-06 PWR (H) > SmartCable Power (+5VDC) J3-07 < Clock SmartCable Serial Clock J3-08 < Data SmartCable Serial Input J3-09 Data > SmartCable Serial Output J3-10 < Gdisc SmartCable Serial Select J3-11 < Gdisc GSE present J3-12 < GND Ground J3-13 < GND Ground J3-14 < GND Ground J3-15 GPS ANT < RF GPS COAX Connection Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 136 Honeywell MK VI MK VIII EGPWS Installation Design Guide APPENDIX A - Customer Worksheet Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 137 Honeywell MK VI MK VIII EGPWS Installation Design Guide Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 138 MK VI / MK VIII EGPWS ENHANCED GROUND PROXIMITY WARNING SYSTEM CUSTOMER INTERFACE WORK SHEET DATE: The purpose for this work sheet is to obtain the necessary aircraft data for determining the specific interface configuration for the MK VI or MK VIII Enhanced Ground Proximity Warning System (EGPWS). For defined MK VI and MK VIII EGPWS interface data, refer to Appendix E, Interface Description Document (IDD) for the Mark VI and VIII Enhanced Ground Proximity Warning System (MKVI/VIII EGPWS). For product description information, refer to Honeywell document No. 965-1176-601, Product Specification for the Mark VI and VIII Enhanced Ground Proximity Warning System. Contact Honeywell EGPWS Applications Engineering for assistance (800-813-2099 or 425-885-8719). Aircraft Operator: Contact: Installer: Contact: Phone: Aircraft Type (be specific): Phone: Engine Type (model number): CURRENT GPWS INSTALLATION: If GPWS is currently installed in the aircraft, please provide the following information: Manufacturer: Model No. Part No. COCKPIT DISPLAYS: Please provide the following information for intended EGPWS display purposes (include any new displays planned): SYSTEM QTY MANUFACTURER MODEL NO. PART NO. EFIS Symbol Generator EFIS Display EFIS Display Control Panel Multifunction Display (MFD) Weather Radar Indicator Weather Radar R/T Weather Radar Controller Other (specify) Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 139 SOFTWARE NO. Honeywell MK VI MK VIII EGPWS Installation Design Guide AIRCRAFT SYSTEMS INFORMATION: (Use “N/A” if Not Applicable) Please provide the manufacturer, model number, part number, software part number, quantity per aircraft, and output data information for: OUTPUT DATA FORMAT – NOTES SYSTEM MFGR. MODEL NO. PART NO. S/W PART NO. QTY (ARINC 429, 547, 552, 575, DC, synchro, potentiometer, discrete, etc. Identify available ARINC 429 labels) Air Data Computers Radio Altimeters ILS Receivers AHRS / IRU / INU VG DG GPS * * GPS Altitude Reference: WGS-84 MSL DISCRETE INPUTS: Please check applicable boxes for both up and down positions. PARAMETER Flaps Down (landing configuration) Flaps Up Landing Gear Down Landing Gear Up GND > < OPEN +28 VDC > ° < ° ° ° Notes: ________________________________________________________________________________________________________________________ ________________________________________________________________________________________________________________________ ______________________________________________________________________________________________________________________________ Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 140 Honeywell MK VI MK VIII EGPWS Installation Design Guide APPENDIX B - Sample Wiring Diagrams Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 141 GLIDESLOPE AND/OR LOCALIZER RADIO ALTITUDE DISPLAY CONFIGURATION AUDIO Honeywell MK VI MK VIII EGPWS Installation Design Guide Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 142 ATTITUDE/MAGNETIC HEADING POSITION AIR DATA INPUT/OUTPUT DISCRETE FUNCTIONS Honeywell MK VI MK VIII EGPWS Installation Design Guide Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 143 AUTOPILOT ENGAGED FLAP SWITCH GEAR SWITCH CONFIG MODULE CONFIGURATION MODULE PROGRAMING Honeywell MK VI MK VIII EGPWS Installation Design Guide Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 144 Honeywell MK VI MK VIII EGPWS Installation Design Guide APPENDIX C WinVIEWS OPERATION INSTRUCTIONS Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 145 Honeywell MK VI MK VIII EGPWS Installation Design Guide APPENDIX C – WinVIEWS Operation Instructions RS-232 COMMUNICATION WITH THE EGPWS The EGPWS contains software that allows monitoring of its internal parameters, for testing purposes, without altering its operation. The monitoring of these parameter values enables the operator to quickly determine if the correct signal and scaling is being used by the EGPWS computer. The communication link utilizes the RS-232 Communication Protocol configured as follows: 19200 Baud, No Parity, 8 bits, and 1 stop bit. The RS-232 interface with the EGPWS is accomplished via the J3 test connector on the front of the EGPWS. The connection between a PC (with a standard DB9 serial port connector) and the EGPWS RS-232 interface is defined as follows: (Please note that the EGPWS will activate its RS-232 port only when it receives the command CONTROL Z after power is applied to the EGPWS. The CONTROL Z command is automatically sent by WinVIEWS) RS-232 Receive RS-232 Transmit RS-232 Ground EGPWS Front Connector Pin 3 Pin 4 Pin 1 Standard DB9 Connector (for a PC)* Pin 2 Pin 3 Pin 5 *NOTE:Some PC Comm Ports have Pins 2 & 3 reversed from what is described above. The mating connector for the EGPWS J3 test connector is a male (pins) 15 pin double density D-subminiature type, Positronics Industries (kit) part number ODD15M1OYOZ or the following individual parts: Nomenclature (AMP) Connector Shell (HDP-22 Crimp Snap In Contact) Size 22 DM Crimp Snap In Contacts Pin 0.030 Amp Part Number Military Part Number 748364-1 reference MIL-C-24308 748333-4 or -7 Backshell (Shielded Cable Clamp Assembly) 745854-5 Jackscrews, 2 required (4-40 Male Jackscrew Kit) 747784-8 Grommet Sets 747746-1 M39029/58-360 The following tools will work with Positronics, Amp, and Mil Spec Connectors: Insertion / Extraction Tool 91067-1 M81969/1-04 Hand Crimp Tool M22520/2-01 Positioner M22520/2-09 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 146 Honeywell MK VI MK VIII EGPWS Installation Design Guide WinVIEWS OPERATION: Windows Virtual Interface to the Enhanced Warning System WinVIEWS software is a tool developed by Honeywell to monitor or view values within the EGPWS. The WinVIEWS software provides a monitor function that does not alter the operation of the EGPWS. The monitoring of values assists in the installation testing of the EGPWS by allowing the operator to quickly determine if the correct signal and scaling is being used by the EGPWS. Additionally, WinVIEWS provides a detailed status of the software configuration and input signals which enables quick identification of system anomalies. The command file is a simple text file that should include each CVT Item used in this test procedure. A sample command file for this test procedure is found on the following page. The file must be a ‘Text Only’ type of file, such as those created in the Microsoft Windows NotePad program. It should have a filename extension of .CMD. Once this file is loaded, WinVIEWS can automatically display the current value of each parameter listed in the file. Normal Operation for Ground Testing the EGPWS: STEP 1 - Connect the PC to the EGPWS via the RS-232 cable as defined above. STEP 2 - On the PC, start Windows 3.1, or higher. STEP 3 - Start the WinVIEWS program. STEP 4 - Under the File Menu select the “Load Command File” option and load the appropriate Command File. STEP 5 - Use F6 to select Data Display Mode. Each CVT Item listed in the Command File will be continuously updated at a rate of greater than once per second. The values shown for the CVT Items listed will be the test values. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 147 Honeywell MK VI MK VIII EGPWS Installation Design Guide Command File: MK68_GTP.CMD The format for the WinVIEWS command file is: 1. ASCII Text Only; no spaces 2. A CVT Item as specified in the test procedure 3. Each CVT Item Name is followed by a or AnAtt1Val RawAACMHD AACMHdVal RawIMHd1 LandFlDsc MFlpOvrd LandGrDsc HiLandGrDsc GndLandGrDs GSCan TerrDis AudInhDsc GPWSInhDsc M6LwVolDsc APEngDisc1 GSInh StpAppSel MomSASel TAWxRng1 TAWxRng2 DispRngOut1 DispRngOut2 PosUncert GPWInop WSInop TA_NotAvail RawRA1 ARA1Val DHDsc RawBAlt1 RawBCAlt1 RawCAS1 RawBaroRt1 AUBaroVal RawAACSAT RawSAT1 ILSTuned1 AGS1Val RawAACGS1 ALoc1Val RawAACLoc1 RawGS1 RawLoc1 RawGLat1 GPSLatude1 RawGLng1 GPSLngude1 RawGAlt1 RawHFOM1 RawVFOM1 RawRoll1 RawPitch1 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 148 Honeywell MK VI MK VIII EGPWS Installation Design Guide APPENDIX D VENDOR CONTACT INFORMATION CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 149 Honeywell MK VI MK VIII EGPWS Installation Design Guide APPENDIX D - Vendor Contact Information Vendor Contact Information The vendor contact information provided below is current at the time of publication of this document. AMP 2800 Fulling Mill Road MS 038-035 Middletown, PA 17507 800 806-0480 http://www.amp.com Amphenol 20 Melford Drive Scarborough, Ontario, Canada M1B 2X6 Ph: 416-291-4401 Fax: 416-292-0647 http://www.amphenol.com Avidyne Corporation 55 Old Bedford Road Lincoln, MA 01773 Ph: 888-723-7592 http://www.avidyne.com Avtech Corporation 3400 Wallingford Ave North Seattle, WA 98103 Ph: 206-634-2540 http://www.avtcorp.com Barry Controls Burbank, CA 818 843-1000 United Kingdom: Surrey, England 44 (0932) 22-4122 Germany: Raunheim, Germany 49 (6142) 43077/8/9 Brighton, MA 616 787-1555 BF Goodrich Aircraft Sensors 14300 Judicial Road Burnsville, MN 55306-4898 Ph: 952-892-4000 Fax: 952-892-4800 1000 Shames Drive Westbury, New York 11590 Ph: 516-876-8400 Fax: 516-876-9153 http://www.bfg-aerospace.com Comant 12920 Park Street Sante Fe Springs, CA 90670 Ph: 562-946-6694 Fax: 562-946-5150 Email: sales@comant.com http://www.comant.com Dallas Avionics, Inc. 2525 Santa Anna Ave. Dallas, Texas 75228 Ph: 800-527-2581 distributor for Eaton switches http://www.dallasavionics.com Eaton Corporation (see Dallas Avionics) Lighted Switches, Displays 1640 Monrovia Avenue Costa Mesa, CA 92627 Ph: 800-300-9320 http://www.aerospace.eaton.com EDMO Distributors Inc. 5505 E. Rutter Ave. Spokane, WA 99212-1333 Ph: 800-235-3300 distributor for STACO switches http://www.edmo.com BF Goodrich Aerospace Computer Instruments Corp. CAGE CODE: 97896 SCALE: NONE SIZE: A Email: info@computerinstruments.com http://www.computerinstruments.com DWG NO: 060-4314-150 REV: SHEET 150 Honeywell MK VI MK VIII EGPWS Installation Design Guide Electronic Cable Specialists and Electrical Conservation Systems, Inc. 5300 W Franklin Drive Franklin, WI 53132-8642 414 421-5300 http://www.ecsdirect.com Electrical & Mechanical Technologies (EMTEQ) S84 W18693 Enterprise Drive Muskego, WI 53150 PH: 262 679-6170 Fax: 262 679-6175 888 679-6170 Email: Sales@emteq.com http://www.emteq.com Hollingsead International Sante Fe Springs, CA 213 921-3436 http://www.hollingsead.com IDD Aerospace Redmond, WA 425 885-4353 ITT Cannon Santa Ana, CA 714 557-4700 Korry Electronics 901 Dexter Avenue North Seattle, WA Ph: 800 257- 8921 Fax: 206 281-3576 Master Specialties Co. Costa Mesa, CA 714 642-2427 Email: info@korry.com http://www.korry.com Mid-Continent Instruments http://midcontinentinstruments.com Norwich Aero Products http://www.norwichaero.com PIC Wire & Cable Supply N53 W24747 S. Corporate Circle Positronic Industries 423 North Campbell Avenue Springfield, Missouri 65801 Email: info@positronic.com http://www.positronic.com Sensor Systems, Inc. 8929 Fullbright Avenue Chatsworth, CA 91311 818 341-5366 Fax: 818 341-9059 http://www.sensorantennas.com Shadin Co. 6831 Oxford Street St. Louis Park, MN 55426 Ph: 800-328-0584 Fax: 612-924-1111 http://www.shadin.com Email: sales@shadin.com Spirent Systems Penny & Giles Aerospace 8710 E. 32nd Street N. Wichita, KS 67226 Ph: 316-636-2000 Fax: 316-636-9098 http://www.spirent-systems.com Email: denniss@pgaerospace.com Staco Switch (see EDMO Distributors) 1139 Baker Street Costa Mesa, CA 92626-4191 Ph: 714-549-3041 Fax: 714-549-0930 http://www.stacoswitch.com CAGE CODE: 97896 P.O. Box 330 Sussex, WI 53089-0330 414 246-0500 Fax: 414 246-0450 SCALE: NONE SIZE: A Email: BHackett@Picwire.com http://www.picwire.com DWG NO: 060-4314-150 REV: SHEET 151 Honeywell MK VI MK VIII EGPWS Installation Design Guide West Coast Specialties CAGE CODE: 97896 P.O. Box 5010 Preston, WA 98050 Ph: 425 222-3118 Fax: 425-222-3119 SCALE: NONE SIZE: A Contact: Bruce Maxwell, (Rep) 206-232-2871 Fax: 206-232-3174 DWG NO: 060-4314-150 REV: SHEET 152 Honeywell MK VI MK VIII EGPWS Installation Design Guide APPENDIX E Interface Description Document Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 153 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table of Contents APPENDIX E - INTERFACE DESCRIPTION DOCUMENT 159 1 INTRODUCTION 1.1 PART NUMBER 1.2 PURPOSE 1.3 SYSTEM OVERVIEW 1.4 DOCUMENT OVERVIEW 159 159 159 159 159 2 REFERENCES 159 3 MECHANICAL INTERFACE 3.1 WEIGHT 3.2 SYSTEM INTERFACE COMPONENTS 3.2.1 EGPWC Mounting 3.2.2 EGPWC Connectors 3.2.3 Configuration Module 3.3 OUTLINE 160 160 160 160 160 161 162 4 ELECTRICAL INTERFACE 4.1 INTRODUCTION 4.2 SIGNAL INTERFACES 4.2.1 Grounds 164 164 164 164 4.2.1.1 4.2.1.2 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 4.2.4 4.2.4.1 4.2.4.2 4.2.4.3 4.2.4.4 4.2.4.5 4.2.5 4.2.6 4.2.6.1 4.2.6.2 4.2.6.3 4.2.6.4 4.2.6.5 4.2.7 4.2.8 4.2.9 4.2.10 4.2.11 4.2.11.1 4.2.11.2 4.2.12 4.2.12.1 4.2.12.2 4.2.13 4.2.13.1 4.2.13.2 Chassis Ground DC Ground 164 164 Primary Power Input DC Analog Inputs 164 165 Radio Altitude Low Level Glideslope Localizer Deviation or Low Level Glideslope Validity Barometric Altitude Outside Air Temperature Configuration Defined DC Inputs 165 165 165 166 166 166 AC Analog Inputs 166 Synchro Roll Attitude Synchro Magnetic Heading Synchro Pitch Attitude Configuration Defined Synchro Inputs Signal Timing Reference Inputs 166 167 167 167 167 ARINC 429/575 Digital Serial Bus Inputs RS-232 / RS-422 Digital Serial Bus Inputs 168 168 GPS RS-232 Digital Serial Bus (serial port 3) GPS RS-422 Digital Serial Bus (serial port 3) Air Data RS-232 Digital Serial Bus (serial port 2) Air Data RS-422 Digital Serial Bus (serial port 2) SCI Range RS-422 Digital Serial Bus (serial port 1) 169 169 169 169 169 Discrete Inputs Configuration Module Interface GPS Antenna Input OAT Voltage Reference Output Lamp Driver Outputs 170 170 170 171 171 Monitor Output Characteristics Discrete Output Characteristics 171 171 Audio Outputs 171 High Level (Speaker) Audio Output Low Level (Interphone) Audio Output 171 172 ARINC Digital Serial Output Buses 172 ARINC 429 Output Bus ARINC 453 Output Bus 172 172 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 154 Honeywell MK VI MK VIII EGPWS Installation Design Guide 4.3 FRONT PANEL TEST INTERFACE 4.3.1 RS-232 Maintenance Port (serial port 4) 4.3.2 PCMCIA / SmartCable Port 4.3.3 GSE Present Discrete Input 4.4 FRONT PANEL STATUS INDICATORS 172 173 173 173 173 5 AIRCRAFT APPLICATION DATA 5.1 CONFIGURATION TYPES 5.2 CONFIGURATION SELECTION 5.3 CONFIGURATION SELECTION TABLES 5.3.1 Category 1, Aircraft / Mode Type Select 5.3.2 Category 2, Air Data Input Select 5.3.3 Category 3, Position Input Select 5.3.4 Category 4, Altitude Callouts 5.3.5 Category 5, Audio Menu Select 5.3.6 Category 6, Terrain Display Select 5.3.7 Category 7, Options Select Group #1 5.3.8 Category 8, Radio Altitude Input Select 5.3.9 Category 9, Navigation Input Select 5.3.10 Category 10, Attitude Input Select 5.3.11 Category 11, Heading Input Select 5.3.12 Category 12, Windshear Input Select 5.3.13 Category 13, Input / Output Discrete Type Select 5.3.14 Category 14, Audio Output Level 5.3.15 Category 15, Undefined for this software release 5.3.16 Category 16, Undefined for this software release 5.3.17 Category 17, Undefined for this software release 174 174 174 177 177 179 187 193 194 198 241 244 248 252 255 257 258 269 269 269 269 6 CONFIGURABLE INPUT DATA DEFINITION 6.1 ANALOG INPUT DATA 6.1.1 ARINC 552 Radio Altimeter 6.1.2 ALT 55 Radio Altimeter 6.1.3 Uncorrected Barometric Altitude 6.1.4 Outside Air Temperature (500 ohm probe) 6.1.5 Outside Air Temperature (Internal Constant) 6.1.6 ARINC 547/578-4 Low Level Glideslope Deviation with Discrete Valid 6.1.7 ARINC 547/578-4 Low Level Glideslope Deviation with Low Level Valid 6.1.8 Roll Attitude, 3 Wire Synchro (11.8 VAC ) 6.1.9 Magnetic Heading, 5 Wire Synchro 6.1.10 Uncorrected Barometric Altitude (ADS-65) 6.1.11 RT-221/300 Radio Altimeter 6.1.12 Pitch Synchro Attitude, 3 Wire Synchro (11.8 VAC ) 6.1.13 Uncorrected Barometric Altitude (CIC 02702) 6.1.14 ARINC 547/578-4 Low Level Glideslope Deviation Validity 6.1.15 Roll Attitude, 3 Wire Synchro (11.8 VAC ) with Validity 6.1.16 Uncorrected Barometric Altitude (AZ-241, AZ-800) 6.1.17 ARINC 547 Localizer Deviation with Discrete Valid 6.2 DIGITAL INPUT DATA, ARINC 429 6.2.1 Uncorrected Barometric Altitude (203) 6.2.2 Static Air Temperature (213) 6.2.3 Barometric Altitude Rate (212) 6.2.4 Altitude (076) - GPS (MSL) 6.2.5 Horizontal Integrity Limit (130) - GPS 6.2.6 Ground Speed (112) - GPS 6.2.7 Latitude (110) - GPS 6.2.8 Longitude (111) - GPS 6.2.9 Track Angle (103) - GPS 270 270 270 270 271 271 271 272 272 272 273 273 273 274 274 275 275 275 276 276 278 278 278 278 278 278 279 279 279 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 155 Honeywell MK VI MK VIII EGPWS Installation Design Guide 6.2.10 6.2.11 6.2.12 6.2.13 6.2.14 6.2.15 6.2.16 6.2.17 6.2.18 6.2.19 6.2.20 6.2.20.1 Horizontal Figure Of Merit (247) – GPS (ARINC 743A) Horizontal Figure Of Merit (247) – GPS (ARINC 743) Horizontal Figure Of Merit from HDOP (101) – GPS (ARINC 743) Vertical Figure Of Merit (136) – GPS (ARINC 743A) Vertical Figure Of Merit (136) – GPS (ARINC 743) Vertical Figure Of Merit from VDOP (102) – GPS (ARINC 743) Sensor Status (273) - GPS Universal Time Correlation (125) - GPS Date (260) - GPS Control Word (154) - MFD Control Word 2 (271/273) 279 279 279 279 279 279 280 280 280 281 281 Control Word 2 (271/273) Type 2 281 6.2.21 Discrete Word (155 or 176) - MFD 6.2.22 Hazard Range Output (077) 6.2.23 Range (050) - Multifunction Signal Generator (MG) or IC600 6.2.24 Query / Continuous Response (011) - KCPB 6.2.25 Key Press Data (012) – KCPB 6.2.26 Control Word 1 (270) 6.2.27 Discrete Word (273) – Bendix Weather Radar Vertical Profile Mode 6.2.28 Discrete Word (275) – IC600 only 6.2.29 Radio Altitude (164) 6.2.30 Glideslope Deviation (174 or 117) 6.2.31 Roll Angle (325) 6.2.32 Magnetic Heading (320) 6.2.33 Localizer Deviation (173 or 116) 6.2.34 Pitch Angle (324) 6.2.35 Range (271) - KCPB 6.2.36 DSU Status Word (350) 6.2.37 True Heading (314) 6.2.38 Corrected Barometric Altitude (204) 6.2.39 Computed Airspeed (206) 6.2.40 True Airspeed (210) 6.2.41 Decision Height (370) – IOC Scaling 6.2.42 Normal Acceleration (333) 6.2.43 Longitudinal Acceleration (331) 6.2.44 Left Body Angle of Attack (224) 6.2.45 Right Body Angle of Attack (225) 6.2.46 VOR/ILS Frequency (034) 6.2.47 PFD Mode Select Word (163) 6.2.48 FWC & GP Discrete Word (171) 6.2.49 Body Pitch Rate (326) 6.2.50 Body Roll Rate (327) 6.2.51 Minimum Descent Altitude (170) – IOC Scaling 6.2.52 Normal Angle of Attack (236) 6.2.53 North/South Velocity (166) - GPS 6.2.54 East/West Velocity (174) - GPS 6.2.55 Discrete Word (017) - KMD 550/850 6.2.56 Inertial Vertical Speed (365) 6.2.57 Inertial Altitude (361) 6.2.58 Vertical Velocity (165) - GPS 6.2.59 Latitude Fine (120) - GPS 6.2.60 Longitude Fine (121) - GPS 6.2.61 Selected Course (100) - IOC 6.2.62 DH/MDA Selected (170) – DAU Scaling 6.3 DIGITAL DATA, ARINC 575 6.3.1 Static Air Temperature (213) 6.3.2 Uncorrected Barometric Altitude (203) 282 282 283 283 284 284 285 285 285 285 286 286 286 286 286 286 287 287 287 287 287 287 288 288 288 288 288 289 290 290 290 290 291 291 291 291 291 291 292 292 292 292 292 292 293 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 156 Honeywell MK VI MK VIII EGPWS Installation Design Guide 6.3.3 Barometric Altitude Rate (212) 6.3.4 Computed Airspeed (206) 6.4 DIGITAL DATA, RS-232 6.4.1 Xpress GPS Packets ID 15: Lat/Lon/Estimated Horizontal Position Error 6.4.2 Xpress GPS Packets ID 16: Altitude/Estimated Vertical Position Error 6.4.3 Xpress GPS Packets ID 17: Ground Speed/Track Angle 6.4.4 Xpress GPS Packets ID 18: East/North/Up Velocity 6.4.5 Xpress GPS Packets ID 1C: GPS State 6.5 DIGITAL DATA, RS-422 6.5.1 Honeywell RS-422 Serial Control Interface (SCI) Mode/Range Word 6.5.1.1 6.5.1.2 293 293 293 293 293 293 294 294 295 295 Serial Control Interface (SCI) Mode/Range Word 1 (80) Serial Control Interface (SCI) Status Word 1 (FF) 295 296 6.5.2 Honeywell RS-232 Serial Control Interface for DC811 Up/Down Range 6.6 DISCRETE INPUTS 6.6.1 Analog Radio Altitude Validity Flags 6.6.2 GND Landing Gear Discrete 6.6.3 +28V Landing Gear Discrete 6.6.4 GND Landing Flap Discrete 6.6.5 +28V Landing Flap Discrete 6.6.6 Momentary Flap Override Discrete 6.6.7 Self-Test Discrete 6.6.8 GND ILS Tuned Discrete #1 6.6.9 +28V ILS Tuned Discrete #1 6.6.10 Glideslope Validity Discrete #1 6.6.11 GND Glideslope Inhibit Discrete 6.6.12 +28 V Glideslope Inhibit Discrete 6.6.13 Glideslope Cancel Discrete 6.6.14 Decision Height Discrete 6.6.15 Mode 6 Low Volume Discrete 6.6.16 GND Audio Inhibit Discrete 6.6.17 +28V Audio Inhibit Discrete 6.6.18 Display Select Discrete #1 6.6.19 Display Select Discrete #2 6.6.20 Terrain Awareness & TCF Inhibit Discrete 6.6.21 Autopilot Engaged Discrete #1 6.6.22 Barometric Altitude Validity Discrete 6.6.23 Magnetic Heading Validity Discrete 6.6.24 Attitude Validity Discrete 6.6.25 Steep Approach Discrete #2 6.6.26 Timed Audio Inhibit Discrete 6.6.27 GPWS Inhibit Discrete 6.6.28 Localizer Validity Discrete #1 296 297 297 297 297 298 298 298 298 298 299 299 299 299 299 300 300 300 300 300 301 301 301 301 301 301 302 302 302 302 7 OUTPUT DATA DEFINITION 7.1 ARINC 429 OUTPUT DATA 7.1.1 Discrete Output Words 7.1.1.1 7.1.1.2 7.1.1.3 7.1.1.4 7.1.1.5 7.1.1.6 7.1.2 7.1.2.1 7.1.2.2 7.1.2.3 7.1.2.4 7.1.2.5 7.1.2.6 303 303 305 EGPWS Alert Discrete #1 (270) EGPWC Logic Discretes (271) Mode 6 Callouts Discrete #1 (272) Mode 6 Callouts Discrete #2 (273) EGPWS Alert Discrete #2 (274) EGPWC Alert Discrete #3 (300) 305 305 306 306 307 307 Internal Data Outputs 308 Geometric Altitude VFOM (135) Terrain Clearance (164) Geometric Altitude (261) Computed Terrain Clearance (067) Latitude – Selected EGPWS (310) Longitude – Selected EGPWS (311) 308 308 308 308 308 308 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 157 Honeywell MK VI MK VIII EGPWS Installation Design Guide 7.1.2.7 7.1.2.8 7.1.2.9 7.1.2.10 7.1.2.11 7.1.2.12 7.1.2.13 7.1.2.14 7.1.2.15 7.1.3 7.1.3.1 7.1.3.2 7.1.3.3 7.1.3.4 7.1.3.5 7.1.3.6 7.1.4 7.1.4.1 7.1.5 7.1.5.1 7.1.5.2 7.1.5.3 7.1.6 7.1.6.1 7.1.6.2 Body Angle of Attack—Right (223) – MKVIII EGPWS w/ Windshear only Body Angle of Attack—Left (224) – MKVIII EGPWS w/ Windshear only Corrected Airspeed (242) – MKVIII EGPWS w/ Windshear only Windshear Warning Threshold (331) – MKVIII EGPWS w/ Windshear only Corrected Longitudinal Acceleration (332) – MKVIII EGPWS w/ Windshear only Raw Total Shear (362) – MKVIII EGPWS w/ Windshear only Corrected Normal Acceleration (364) – MKVIII EGPWS w/ Windshear only Computed Flight Path Angle (375) – MKVIII EGPWS w/ Windshear only Scaled Total Shear (376) – MKVIII EGPWS w/ Windshear only Terrain Display Outputs 310 Displayed Range (050) Terrain Display Status Word (051) Message Word #1 (052) Message Word #2 (053) Message Word #3 (054) Message Word #4 (055) 310 310 311 311 312 312 Equipment Identification 313 Equipment Identification Word (377) 313 Fault Summary Words (for Proline 4/21) 313 Fault Diagnostic Word #1 (350) Fault Diagnostic Word #2 (351) Fault Diagnostic Word #3 (355) 313 313 314 Peak Binary Labels 314 Peaks Upper Elevation (011) Peaks Lower Elevation (012) 314 315 7.2 ARINC 708A OUTPUT 7.3 AUDIO OUTPUT 7.4 DISCRETE OUTPUTS 7.4.1 Ground Proximity Alerts Discrete (Lamp) Outputs 7.4.2 Audio On Discrete 7.4.3 Monitor Discretes (GPWS INOP & Terrain INOP or Terrain Not Available) 7.4.4 Terrain Display Switching Discretes (WxR/EGPWS Display Select) 7.4.5 Flap Override Discrete 7.4.6 Glideslope Cancel Discrete 7.4.7 Terrain / Obstacle Awareness Alert Discretes 7.4.7.1 7.4.7.2 308 309 309 309 309 309 309 309 309 315 315 315 315 316 316 316 316 316 316 Terrain / Obstacle Caution Terrain / Obstacle Warning 316 316 7.4.8 Terrain Pop Up 7.4.9 Windshear INOP Monitor Discretes 7.4.10 Windshear Warning 7.4.11 Windshear Caution 7.4.12 Steep Approach Discrete 7.5 SYSTEM CONFIGURATION STATUS 7.5.1 System Status Messages 316 316 316 317 317 317 318 8 CONNECTOR INTERFACE 8.1 PINOUT FOR FRONT CONNECTORS SORTED BY PIN NUMBER 319 319 9 DEFINITIONS 324 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 158 Honeywell MK VI MK VIII EGPWS Installation Design Guide APPENDIX E - Interface Description Document 1 INTRODUCTION 1.1 Part Number This document is the Interface Description Document for the MK VI and MK VIII Enhanced Ground Proximity Warning System (EGPWS). The EGPWS computer (EGPWC) for these systems are identified by Honeywell part numbers: 965-1180-0XX MK VI EGPWC With upgraded CPU 965-1190-0XX MK VI EGPWC With upgraded CPU and internal GPS 965-1210-0XX: MK VIII EGPWC With upgraded CPU 965-1220-0XX: MK VIII EGPWC With upgraded CPU and internal GPS Differences, where they exist, between the different part numbers, are highlighted within this document. The EGPWC 10 digit part number will identify the configuration of the EGPWC as follows: 965-1ABC-DDD (example 965-1180-020) A = 1 (MK VI) or 2 (MK VIII) B = Functionality of hardware (with or without internal GPS or Upgraded CPU). Refer to part number list above for details. C = MK VI or MK VIII EGPWC hardware (including boot code). C = 0 as hardware part numbers roll. DDD = Application Software (including Configuration Software) The Terrain Database (including the Envelope Modulation Database) Version is not identified in the 10-digit part number but with a separate identifier on the nameplate. All modification changes not affecting form, fit or function will be identified via “mod dots”. The digits identifying the Application software will match the respective version number of the Application software. 1.2 Purpose The Interface Description Document describes all of the system external interfaces for the MK VI and MK VIII Enhanced Ground Proximity Warning System (EGPWS). 1.3 System Overview Refer to the EGPWS Product Specification document referenced in section 2. 1.4 Document Overview This document is organized as follows. Section 1 Introduction, identifies this Description Document and describes the content and organization of the document. Section 2 Referenced Documents. Section 3 Mechanical Interface, summarizes the outline, mounting tray outline and weight of the EGPWS. Section 4 Electrical Interface, summarizes the number and type of electrical interfaces available. Section 5 Aircraft Application Data, specifies the available interfaces as well as specific data provided on each interface Section 6 Input Data Definition, provides definition of digital and analog input characteristics. Section 7 Output Data Definition, describes the characteristics of the EGPWC outputs. Section 8 Connector Interface, describes pin out and function for the front panel connectors. Section 9 Definitions, provides a list of acronyms. 2 REFERENCES MK VI/MK VIII EGPWS Product Specification MK VI/MK VIII EGPWS Pilot Guide MK VI/MK VIII EGPWS Line Maintenance Manual MK VI/MK VIII EGPWS Terrain Database EGPWS Interface Methodology 965-1180-601 060-4314-000 060-4199-180 060-4326-000 060-4303-000 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 159 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3 MECHANICAL INTERFACE 3.1 Weight The maximum weight for all MK VI and MK VIII EGPWC part numbers is 3.9 pounds. 3.2 System Interface Components Refer to section 3.3 for outline drawings. 3.2.1 EGPWC Mounting The mounting rack for the EGPWC is identified as follows: TRAY Honeywell P/N Source/Vendor 405-0383-001 Bendix/King Vendor Part Number 071-04003-0002 3.2.2 EGPWC Connectors There are two connectors that interface the aircraft with the MK VI and MK VIII EGPWC. The 78-pin (J1) and 50 pin (J2) front panel interface connectors of the MK VI and VIII EGPWC contain all the interfaces for signals and power. The 78 pin is a Subminiature-D, High-Density Series connector conforming to Mil-C-24308. The 50 pin is a Subminiature-D Connector conforming to Mil-C-24308. P1 Vendor/Supplier Positronics 78 pin Connector Supplier P/N DD78F10JVLC-15 P2 Vendor/Supplier Positronics 50 pin Connector Supplier P/N RD50F10JVLC-15 Honeywell P/N 440-1158-009 Honeywell P/N 440-1233-001 A GPS Antenna connector is required for Enhanced MK VI and MK VIII units with internal GPS receiver. GPS Connector Vendor/Supplier Supplier P/N Honeywell P/N AMP 225554-6 440-1239-001 For a pictoral of the front panel connectors, see Figure 8.1-1 and 8.1-2. Also, refer to Section 8 for pin-out information. A test connector (J3) is provided on the EGPWC front panel. This provides access for a PC test monitor and future portable data loading capabilities. The mating connector for the EGPWC test plug is a male (pins) 15 pin double density D-subminiature type, Positronics Industries (kit) part number ODD15M1OYOZ or the following individual parts: Nomenclature (AMP) Amp Part Number Military Part Number Connector Shell (HDP-22 Crimp Snap In Contact) 748364-1 reference MIL-C-24308 Size 22 DM Crimp Snap In Contacts Pin 0.030 748333-4 or –7 M39029/58-360 Backshell (Shielded Cable Clamp Assembly) 745854-5 Jackscrews (4-40 Male Jackscrew Kit) 747784-8 (specify quantity of 2 per connector) Grommet Sets 747746-1 The following tools will work with Positronics, Amp, and Mil Spec Connectors: Insertion / Extraction Tool 91067-1 Hand Crimp Tool Positioner M81969/1-04 M22520/2-01 M22520/2-09 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 160 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.2.3 Configuration Module The EGPWS aircraft configuration is programmed into a configuration module installed in the aircraft wiring. This configuration module is identified as follows: Vendor/Supplier Supplier P/N Honeywell 700-1710-001 Honeywell 700-1710-020 * The configuration module is installed as part of the P2 mating connector backshell and contains reprogrammable memory for configuration storage. Configuration module part number 700-1710-020, contains a Real Time Clock (RTC) circuit that supplies the EGPWS with date and time to allow the internal GPS receiver to determine GPS constellation shift and provide faster satellite signalacquistion and navigation. The Configuration module, part number 700-1710-020, will only operate with EGPWC hardware part numbers 965-1180, 965-1190, 965-1210, 965-1220 and software versions -020 or later. Configuration module, part number 700-1710-001, can be used with all EGPWC hardware part numbers and software versions. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 161 Honeywell MK VI MK VIII EGPWS Installation Design Guide 3.3 Outline Dimensions of the MK VI and MK VIII EGPWC hardware and their associated mounting rack are given in this section. The mounting rack is identical to that of the MK VI GPWC. FIGURE 3.3-1: OUTLINE DRAWING FOR THE MK VI AND MK VIII EGPWC Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 162 Honeywell MK VI MK VIII EGPWS Installation Design Guide FIGURE 3.3-2: MOUNTING RACK FOR THE MK VI AND MK VIII EGPWC Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 163 Honeywell MK VI MK VIII EGPWS Installation Design Guide 4 ELECTRICAL INTERFACE 4.1 Introduction The MK VI and MK VIII EGPWS provide electrical interfaces for aircraft systems and to support maintenance functions. The interfaces are made via the front panel aircraft interface connectors, front panel maintenance/test port and front panel LED’s. A TNC coaxial connector is located on the front panel for internal GPS receivers in the 965-1190-0XX MK VI EGPWC, and 965-1220-0XX MK VIII EGPWC only. The following sections describe the types of electrical interfaces provided in the EGPWC. See Section 5 for the specific interface configuration capabilities of the MK VI and MK VIII EGPWS. 4.2 Signal Interfaces This section identifies and describes the number and characteristics of each interface type provided in the front panel aircraft interface connectors. The aircraft interface connectors are defined as P1 (78 pins) and P2 (50 pins). Section 8 identifies the connector pin assignments. The signal mnemonic for each signal in Section 8 is included in the following sections. All synchro inputs are brought in as three or five wire devices. No two wire absolute AC signals are available. All analog inputs provide broken wire detection on all input signal legs. Unless otherwise stated, the “Maximum reverse fault current” is defined as the current resulting from an internal component failure, with the input signal at zero volts. 4.2.1 Grounds 4.2.1.1 Chassis Ground Used for redundant metal connection. This pin is internally connected to DC Ground (see section 4.2.1.2). Pin Assignment (Signal Mnemonic): J1-42, J1-53 (GND) 4.2.1.2 DC Ground For discrete inputs and lamp driver outputs. These pins are also internally connected to Chassis Ground (see section 4.2.1.1). Pin Assignment (Signal Mnemonic): (same as +28 VDC Return) NOTE: All analog signals are differential input. J1-41, J1-61 (PWR_L) 4.2.2 Primary Power Input Nominal Input Normal Voltage Range Normal Surge Voltage Range Abnormal Voltage Range Abnormal Surge Voltage Range Normal Frequency Range Frequency Transients Power Requirements Recommended Power Control Device Pin Assignment (Signal Mnemonic): +28 VDC Input +28 VDC Return 28 VDC 22.0 to 30.3 VDC 15 to 40VDC (30 mSec) 20.5 to 32.2 VDC 37.8 VDC (1sec); 46.3 VDC (100 mSec) not applicable not applicable 9 Watts - No Warnings +7 Watts with warning voice over 8 Ω speaker +3 Watts with Internal GPS (includes antenna power)1 +49 Watts (typical) with heater blanket on2 3 Amp delayed action circuit breaker. J1-40, J1-60 J1-41, J1-61 (PWR_H3) (PWR_L3) 1 Based on the Honeywell GPS Pxpress card specification and applies to 965-1190-0XX and 965-1220-0XX only. The heater blanket turns on at temperatures ≤ -23° C and turns off at temperatures ≥ -20° C. 3 Note that this is not a floating input. +28 VDC must be applied to both PWR_H and +28 VDC Return to both PWR_L inputs. 2 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 164 Honeywell MK VI MK VIII EGPWS Installation Design Guide 4.2.3 DC Analog Inputs Unless otherwise specified, Input Signal accuracy is 1% linearity +0.1% full scale offset. 4.2.3.1 Radio Altitude Quantity Input Impedance, each leg Maximum Reverse Fault Current Signal Range Input Voltage Range (VRA) Conversion Range (VC) Input Filter Broken Wire Detect Pin Assignment (Signal Mnemonic): Signal (+) Return (-) 1 > 83 KΩ < 200 µA 0 to 2500 feet 37.7V ≥ VRA ≥ -2.5V 29.7V ≥ VC ≥ -0.4V 0.1 Second Low Pass, ± 10% Input will be biased to less than -50 feet J1-64 J1-45 (RALT_H) (RALT_L) 4.2.3.2 Low Level Glideslope Quantity Input Impedance, each leg Reverse Fault Current Signal Range Input Voltage Range Input Filter Input Type Common Mode Voltage Range (VCM) Broken Wire Detect Pin Assignment (Signal Mnemonic): +Up, Below Beam, Fly Up +Down, Above Beam, Fly Down 1 > 2.5 MΩ < 6.2 µA ±12 Dots ±0.9 VDC 0.1 Second Low Pass, ± 10% Differential 11V ≥ VCM ≥ -2V Input will be biased less than -15 dots J1-65 J1-46 (GSDEV_H) (GSDEV_L) 4.2.3.3 Localizer Deviation or Low Level Glideslope Validity This input can be configured as either a low level glideslope valid, or as a localizer deviation input. Installations that only have the low level validity signal for glideslope can not activate the analog localizer input. See section 5.3.9 for more information. Quantity Input Impedance, each leg Reverse Fault Current Input Filter Input Type Common Mode Voltage Range (VCM) When used as a validity input: Pin Assignment (Signal Mnemonic): + Flag – Flag Active Voltage Range (Logic True) Inactive Voltage Range (Logic False) Broken Wire Detect When used as a localizer input: Pin Assignment (Signal Mnemonic): CRS DEV + Fly Right CRS DEV + Fly Left Signal Range Input Voltage Range Broken Wire Detect 1 > 2.5 MΩ < 6.2 µA 0.1 Second Low Pass, ± 10% Differential 11V ≥ VCM ≥ -2V J1-30 (GS_VAL_H) J1-10 (GS_VAL_L) +160 to +840 mVDC 0 to 50 mVDC Input will be biased less than –1 VDC J1-30 (LCDEV_H) J1-10 (LCDEV_L) ±12 Dots ±0.9 VDC Input will be biased less than -15 dots Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 165 Honeywell MK VI MK VIII EGPWS Installation Design Guide 4.2.3.4 Barometric Altitude Quantity Input Impedance, each leg Reverse Fault Current Input Voltage Range Input Filter Input Type Broken Wire Detect Pin Assignment (Signal Mnemonic): Signal (+) Return (-) 1 > 83 KΩ < 200 µA -0.18 VDC to +15 VDC 0.1 Second Low Pass, ± 10% Differential Input will be biased less than -3000 feet J1-62 J1-43 (ALT_H) (ALT_L) 4.2.3.5 Outside Air Temperature Quantity Input Impedance, each leg Reverse Fault Current Input Voltage Range Input Filter Input Type Broken Wire Detect Pin Assignment (Signal Mnemonic): Signal (+) Return (-) 1 > 100 KΩ < 200 µA +0.3 VDC to +0.6 VDC 0.1 Second Low Pass, ± 10% Differential Input will be biased less than -80° C J1-63 J1-44 (OAT_H) (OAT_L) NOTE: For temperature probe voltage reference see section 4.2.10. 4.2.3.6 Configuration Defined DC Inputs Quantity Input Impedance, each leg Reverse Fault Current Input Voltage Range Input Filter Input Type Broken Wire Detect Pin Assignment (Signal Mnemonic): #1 Signal (+) #1 Return (-) #2 Signal (+) #2 Return (-) 2 > 83 KΩ < 200 µA ±5 VDC 0.1 Second Low Pass, ± 10% Differential Input will be biased less than -6 VDC J1-26 J1-27 J1-66 J1-47 4.2.4 AC Analog Inputs Unless otherwise specified Input Impedance: X leg Input Impedance: Y leg Input Impedance: Z leg Maximum Reverse Fault Current Input Voltage Range Accuracy > 140 KΩ > 140 KΩ > 140 KΩ < 200 µA ±11.8 VACRMS ± 20% (leg to leg) 2.5% linearity + 0.1% full scale offset 4.2.4.1 Synchro Roll Attitude Quantity Synchro Angle Range Reference Voltages Pin Assignment (Signal Mnemonic): X leg Y leg Z leg 1 ±80 deg Not Required J1-1 J1-21 J1-2 (SYN_1X) (SYN_1Y) (SYN_1Z) Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 166 Honeywell MK VI MK VIII EGPWS Installation Design Guide 4.2.4.2 Synchro Magnetic Heading Quantity Synchro Angle Range Reference Voltages Pin Assignment (Signal Mnemonic): X leg Y leg Z leg 1 ±180 deg ±26 VACRMS ± 20% (see 4.2.4.4) J1-22 J1-23 J1-3 (SYN_2X) (SYN_2Y) (SYN_2Z) 4.2.4.3 Synchro Pitch Attitude Quantity Synchro Angle Range Reference Voltages Pin Assignment (Signal Mnemonic): X leg Y leg Z leg 1 ±80 deg Not Required J1-5 J1-7 J1-6 (SYN_3X) (SYN_3Y) (SYN_3Z) 4.2.4.4 Configuration Defined Synchro Inputs Quantity Reference Voltages Pin Assignment (Signal Mnemonic): #2 X leg #2 Y leg #2 Z leg 2 ±26 VACRMS ± 20% #3 X leg #3 Y leg #3 Z leg J2-1 J2-2 J2-18 (SYN_4X) (SYN_4Y) (SYN_4Z) J2-19 J2-20 J2-3 (SYN_5X) (SYN_5Y) (SYN_5Z) 4.2.4.5 Signal Timing Reference Inputs These inputs accept 400 Hz AC signals, and detect the “zero crossings” of these signals. These zero crossings are used to time the conversion and input of AC signals. Absolute voltage level of these signals is not measured, but it must be within the range specified below. Voltage below the specified minimum value may result in intermittent or “jittery” zero cross detection. Timing reference signals are required for input of most AC devices (not required for pitch and roll). These references can be brought into the appropriate timing reference input, or the system can be configured to derive a reference from the signal. Timing reference signals are specified for synchro inputs requiring a range greater than ± 80 degrees. Inputs requiring less (i.e., Roll Attitude) are configured to derive a reference from the synchro input signal and do not require a separate reference voltage input. Quantity Input Impedance Maximum Reverse Fault Current A/C Input Signal Frequency Range Maximum Input Voltage Swing (differential) Maximum Input Voltage Swing (ref. to Gnd) Input Hardware Filtering Minimum Input Voltage Pin Assignment (Signal Mnemonic): 26VAC Reference #1 H 26VAC Reference #1 C 26VAC Reference #2 H 26VAC Reference #2 C 2 > 140KΩ each line to signal ground < 120 µA 400 Hz, ±10% 50V between input legs 50V from any leg to signal ground None ± 0.5 VAC J1-4 J1-24 (26REF_1H) (26REF_1L) J2-34 J2-35 (26REF_2H) (26REF_2L) Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 167 Honeywell MK VI MK VIII EGPWS Installation Design Guide 4.2.5 ARINC 429/575 Digital Serial Bus Inputs Quantity Format Low Speed Data Rate High Speed Data Rate Direction of Information Flow Word/Frame Structure Data definition Channel Receive #1 A leg Receive #1 B leg 8 DITS, ARINC 429/575 Low or high speed 1 12.0 KBPS to 14.5 KBPS 100 KBPS ± 1% Type ‘A’ broadcast for ARINC 429/575 Type ‘B’ 32 bit words consisting of 8 bits label and 24 bits data/status Refer to Section 6 of this document (Signal Mnemonic): Pin Assignment (429/422RX_1A) J2-37 (429/422RX_1B) J2-36 Receive #2 A leg Receive #2 B leg J2-39 J2-38 (429RX_2A) (429RX_2B) Receive #3 A leg Receive #3 B leg J2-41 J2-40 (429RX_3A) (429RX_3B) Receive #4 A leg Receive #4 B leg J2-25 J2-8 (429RX_4A) (429RX_4B) Receive #5 A leg Receive #5 B leg J2-21 J2-4 (429RX_5A) (429RX_5B) Receive #6 A leg Receive #6 B leg J2-22 J2-5 (429RX_6A) (429RX_6B) Receive #7 A leg Receive #7 B leg J2-23 J2-6 (429RX_7A) (429RX_7B) Receive #8 A leg Receive #8 B leg SSM/SDI Definition: (429RX_8A) J2-24 (429RX_8B) J2-7 Refer to Section 6.2 of this document 4.2.6 RS-232 / RS-422 Digital Serial Bus Inputs Two full duplex RS-232 / RS-422 buses and a third RS-422 receiver are provided at the aircraft interface connectors. The RS-422 transceivers are electrically multiplexed with the RS-232 transceivers, and are selected through the configuration process. The third RS-422 receiver is electrically multiplexed with the ARINC 429 channel 1 receiver. The maintenance RS-232 bus is described in section 4.3.1. The specific characteristics (data rate, parity, data bits, stop bits) is defined in the configuration selection, see Section 5 and 6 for details. RS-422 cable termination will not be required for typical applications, see TIA/EIA-422-B Annex A. The RS-232 bus meets the characteristics specified in RS232C and supports the following characteristics: Data Rate Parity Data bits Stop bits Maximum Recommended Cable Length Data definition 1200, 2400, 4800, 9600, 19200 or 38400 bits/Sec None, Odd or Even 7 or 8 1 or 2 15 meters Refer to Section 6 of this document The RS-422 bus meets the characteristics of TIA/EIA-422-B and supports the following characteristics: Data Rate 1200, 2400, 4800, 9600, 12000, 19200 or 38400 bits/Sec Maximum Transceivers on Bus 20 Receiver Input Impedance 12 KΩ Word/Frame Structure Refer to Section 6 of this document Data definition Refer to Section 6 of this document 1 The bus speed is defined in the configuration selection, see Section 5 for details. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 168 Honeywell MK VI MK VIII EGPWS Installation Design Guide 4.2.6.1 GPS RS-232 Digital Serial Bus (serial port 3) One port is provided for use with external or internal RS-232 GPS interfaces. This port is common with the GPS RS-422 port described in Section 4.2.6.2 and can only function as a RS-232 interface or a RS-422 interface but not both. Pin Assignment (Signal Mnemonic): Transmit J2-45 (GPS_TXA) Receive J2-29 (GPS_RXA) Common J2-28 (GND) NOTE: If an internal GPS configuration is used (965-1190-0XX or 965-1220-0XX) then the receive input will be nonfunctional. 4.2.6.2 GPS RS-422 Digital Serial Bus (serial port 3) One port is provided for use with external GPS interfaces. This port is common with the GPS RS-232 port described in Section 4.2.6.1 and can only function as a RS-232 interface or a RS-422 interface but not both. Pin Assignment (Signal Mnemonic): Transmit A leg J2-45 (GPS_TXA) Transmit B leg J2-46 (GPS_TXB) Receive A leg Receive B leg J2-29 J2-12 (GPS_RXA) (GPS_RXB) NOTE: If an internal GPS configuration is used (965-1190-0XX or 965-1220-0XX) then the receive input will be nonfunctional. 4.2.6.3 Air Data RS-232 Digital Serial Bus (serial port 2) One port is provided for use with Air Data computer or Static Pressure Sensor interfaces. This port is common with the Air Data RS-422 port described in Section 4.2.6.4 and can only function as a RS-232 interface or a RS-422 interface but not both. Pin Assignment (Signal Mnemonic): Transmit J2-27 (ADC_TXA) Receive J2-11 (ADC_RXA) Common J2-28 (GND) 4.2.6.4 Air Data RS-422 Digital Serial Bus (serial port 2) One port is provided for use with Air Data computer or Static Pressure Sensor interfaces. This port is common with the Air Data RS-232 port described in Section 4.2.6.3 and can only function as a RS-232 interface or a RS-422 interface but not both. Pin Assignment (Signal Mnemonic): Transmit A leg J2-27 (ADC_TXA) Transmit B leg J2-44 (ADC_TXB) Receive A leg Receive B leg J2-11 J2-10 (ADC_RXA) (ADC_RXB) 4.2.6.5 SCI Range RS-422 Digital Serial Bus (serial port 1) Two ports are provided for use with the SCI range bus interfaces. Port 1 is common with the ARINC 429 channel 1 port described in Section 4.2.5 and can only function as a RS-422 interface or an ARINC 429 interface but not both. Port 2 is common with the RS-232 port described in Section 4.2.6.4 and can only function as a RS-422 interface or an RS-232 interface but not both. Pin Assignment (Signal Mnemonic): Receive A leg J2-36 (429/422RX_1B) Receive B leg J2-37 (429/422RX_1A) Receive A leg Receive B leg J2-10 J2-11 (232/422RX_2A) (232/422RX_2B) Note: SCI Display Range RS-422 bus A and B legs are reversed from ARINC 429. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 169 Honeywell MK VI MK VIII EGPWS Installation Design Guide 4.2.7 Discrete Inputs Discrete signals are intended for remote switching through the aircraft, and are therefore subject to being connected to other signals, and are also subject to transient voltage conditions. For these reasons, the following rules apply to each input, unless otherwise stated. Each input is capable of withstanding voltage transients of ± 600VDC for 10 µs and ± 50VDC continuously, without damage. The +28 VDC discretes are internally biased via a pull down resistor, and are externally pulled up to +28VDC when active. The characteristics of each +28 VDC discrete input are as follows: +28 VDC Discrete Characteristics Quantity 13 Active Voltage Range (Logic True) > +17 VDC Inactive Voltage Range (Logic False) < +4.4 VDC Diode Isolation None Input Impedance > 95 KΩ Maximum Fault Current < 60 µA Pin Assignment (Signal Mnemonic): See specific discrete in Category 13 (28V_DISC_xx) The Ground discretes are internally biased via a pull up resistor, and are externally pulled down to ground when active. The characteristics of each Ground discrete input are as follows: Ground Discrete Characteristics Quantity 15 Active Voltage Range (Logic True) < +3 VDC Inactive Voltage Range (Logic False) > 100 KΩ (to ground) or > +3.5 VDC Diode Isolation Each input is diode isolated to prevent current sinking Input Impedance > 10 KΩ Maximum Fault Current < 100 µA (at +28 VDC input) Pin Assignment (Signal Mnemonic): See specific discrete in Category 13 (GND_DISC_xx) 4.2.8 Configuration Module Interface System configuration is defined via a Configuration Module, which resides in the MK VI/VIII EGPWS aircraft wiring harness backshell. The EGPWS Configuration Module contains the aircraft interface and functionality definitions specific to the installed aircraft. Refer to Section 5 for interface and functional definitions by category. Note that both configuration module part numbers, 700-1710-003 and 700-1710-020, have identical electrical interfaces. Electrical Characteristics Data definition Pin Assignment (Signal Mnemonic): Clock Master Data Out Master Data In Configuration Module Select Configuration Module +5VDC Configuration Module +5VDC Return Refer to the EGPWS Configuration Module specification Refer to the EGPWS Configuration Module specification J2-32 (RED) J2-50 (BLK) J2-33 (ORN) J2-49 (WHT) J2-17 (VIO) J2-16 (BLU) (SPICLK) (SPIMOSI) (SPIMISO) (SPISEL_CM#) (SC_PWR) (GND) Output to Config Module Logic Low (nominal) Logic High (nominal) EMK 6/8 EMK 6/8 Clock Out 0V 5V Master Data Out 0V 5V Config Module Select 0V 5V INTERFACE OF EGPWS OUTPUTS TO CONFIGURATION MODULE 4.2.9 GPS Antenna Input A GPS input connector is available on the front of the MK VI EGPWS (965-1190-0XX only) and MK VIII EGPWS (9651220-0XX) only. Quantity 1 Cable Length/Allowed Signal Loss Not more than 8 dB, at 1575.42 MHz, for cable and connector loss from antenna to unit. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 170 Honeywell MK VI MK VIII EGPWS Installation Design Guide Connector Type Low Level DC on RF Output Pin Assignment (Signal Mnemonic): TNC +5 VDC ±5%, 50 mAmps maximum, Shield Ground. GPS ANT (COAX) 4.2.10 OAT Voltage Reference Output This output is an accurate voltage source for 500 Ω resistive temperature sensors. Quantity 1 Output Voltage 5.000 VDC ±10 mVDC (no load) Nominal Load 500 Ω Pin Assignment (Signal Mnemonic): J1-25 (OAT_REF) NOTE: This output has a source impedance of 4.42 KΩ, 0.1%. 4.2.11 Lamp Driver Outputs The MK VI and MK VIII EGPWC support two kinds of Ground/Open discrete outputs used to signal various discrete conditions. Monitor outputs are used to signal failure conditions for the MK VI and MK VIII EGPWC. Monitor outputs default to an active state when there is a failure or if power is removed from the MK VI or MK VIII EGPWC. The other Lamp Driver outputs are used to signal the alert or mode control status of the MK VI and MK VIII EGPWS. Short-term current limit protection is provided on all drivers for output shorting conditions. Ground going output discretes may be connected together to produce a “wired OR” function for the active low state of the signals. If output discretes are “wired Or’d” then diodes must be installed for isolation. 4.2.11.1 Monitor Output Characteristics Quantity Type of Output: Max. Open Circuit Voltage: Current Limit Potential Across “Closed” Switch: Pin Assignment (Signal Mnemonic): 3 Switch Closure to Ground 30 VDC 1A 2.5 VDC Max See specific output in Category 13 (MON_OUT_xx) NOTE: Intended to operate with +28VDC lamp sources and will not operate with +5VDC lamp sources. 4.2.11.2 Discrete Output Characteristics Quantity Type of Output: Max. Open Circuit Voltage: Current Limit Potential Across “Closed” Switch: Pin Assignment (Signal Mnemonic): 9 Switch Closure to Ground 30 VDC 500 mA (typical) 1 VDC Max See specific output in Category 13 (DISC_OUT_xx) NOTE: Intended to operate with +28VDC pullup external to the EGPWS. 4.2.12 Audio Outputs There are two audio outputs provided one 8-ohm output and one 600-ohm output. There are several possible volume levels available with the MKVI and MK VIII EGPWS as shown below, with maximum output being 4W (8Ω) or 100mW (600Ω). The actual audio level output by the EGPWS is dependent on several items: • Selection of nominal alert audio volume level (max, -6, -12, -18 or -24 dB) via Category 14. (Section 5.3.14) • If a ‘soft’ Glideslope alert is being issued (given 6 dB below nominal alert volume level). • If a Self Test is in progress, alerts are given 6 dB below nominal alert volume level. • Selection of Mode 6 Low Volume Discrete (lowers callout volume by 6 dB - See Section 5.3.13). 4.2.12.1 High Level (Speaker) Audio Output The 8-ohm output is capable of driving a speaker directly but can also be used to drive other devices with equal or higher impedance. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 171 Honeywell MK VI MK VIII EGPWS Installation Design Guide Quantity Maximum Power Output Nominal Output Impedance Load Impedance Number of Available Power Output Levels Pin Assignment (Signal Mnemonic): Signal (+) Return (-) 1 4 Watts Nominal 8Ω 8Ω or greater 5 selectable levels excluding the Mode 6 Audio Reduction function J1-70 J1-71 (AUD_HL_H) (AUD_HL_L) 4.2.12.2 Low Level (Interphone) Audio Output The 600-ohm output is capable of driving one 600-ohm load at the specified level (or at a reduced level). This output is primarily designed for headphones and interphone systems. Quantity 1 Nominal Output Impedance 600Ω ±10% Maximum Single Channel Power Output 100 mW Nominal Available Power Output Levels 5 selectable levels excluding the Mode 6 Audio Reduction function Pin Assignment (Signal Mnemonic): Signal (+) J1-75 (AUD_LL_H) Return (-) J1-74 (AUD_LL_L) 4.2.13 ARINC Digital Serial Output Buses 4.2.13.1 ARINC 429 Output Bus The ARINC 429 output buses are defined in the terrain display select Section 5.3.6.3, output 429 bus group. Quantity 2 Format DITS, ARINC 429 Low Speed Data Rate 12.0 KBPS to 14.5 KBPS High Speed Data Rate 100 KBPS ± 1% Direction of Information Flow Type ‘A’ broadcast for ARINC 429 Word/Frame Structure Type ‘B’ 32 bit words consisting of 8 bits label and 24 bits data/status Data definition Refer to Section 7 Pin Assignment (Signal Mnemonic): Bus #1 (A leg) J2-43 (429TX_1A) (429TX_1B) Bus #1 (B leg) J2-42 Bus #2 (A leg) Bus #2 (B leg) J2-26 J2-9 (429TX_2A) (429TX_2B) 4.2.13.2 ARINC 453 Output Bus Quantity Format Data Rate Word/Frame Structure Data definition Pin Assignment (Signal Mnemonic): Bus #1 (A leg) Bus #1 (B leg) 2 1600 bit Manchester BI-phase per ARINC 708A 1 Mb per second Refer to Section 7.2 Refer to Section 7.2 Bus #2 (A leg) Bus #2 (B leg) 4.3 J1-58 J1-59 (KCPB_1A) (KCPB_1B) J1-56 J1-57 (KCPB_2A) (KCPB_2B) Front Panel Test Interface The MK VI and MK VIII EGPWS provide a 15 pin (double density, D-Sub) test connector on the front panel, which provides interfaces for various test and maintenance functions. This connector provides the following interfaces. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 172 Honeywell MK VI MK VIII EGPWS Installation Design Guide 4.3.1 RS-232 Maintenance Port (serial port 4) One port is provided which meets the characteristics specified in RS232C. This bus can be used to read internal data from the MK VI or MK VIII EGPWS for both bench, and aircraft testing or transmitting configuration data for selected EGPWS interfaces and options. Baud Rate 19,200 Parity None Data bits 8 Stop bits 1 Maximum Recommended Cable Length 15 meters Pin Assignment (Signal Mnemonic): Transmit J3-4 (RS232TXD_MON) (RS232RXD_MON) Receive J3-3 (GND) Common J3-1 4.3.2 PCMCIA / SmartCable Port One port is provided which meets the Motorola SPI characteristics. The PCMCIA / SmartCable interface allows for both the uploading, and downloading of internal MK VI and MK VIII EGPWS information. Using this interface system, software and databases can be updated. Control of the upload/download process is accomplished by connection of the SmartCable to the MK VI or MK VIII EGPWS front panel test connector and insertion of the PCMCIA card. LEDs are provided on the SmartCable for PCMCIA interface operation. The PCMCIA / SmartCable is not intended as an on-line/inflight storage medium and must be removed after completion of the upload/download operation. Electrical Characteristics Refer to the Motorola SPI specification Data definition Refer to the Motorola SPI specification Maximum Recommended Cable Length 2 meters Pin Assignment (Signal Mnemonic): (SPICLK) J3-7 Clock (SPIMOSI) J3-9 Master Data Out J3-8 (SPIMISO) Master Data In J3-10 (SPISEL_SC#) SmartCable Select J3-6 (SC_PWR) SmartCable +5VDC SmartCable +5VDC Return J3-1 (GND) PCMCIA Card Present J3-2 (CARD_PRES#) (GND) SmartCable Ground J3-12, -13, -14 NOTE: SmartCable +5VDC Return is common with RS-232 Maintenance Port common. 4.3.3 GSE Present Discrete Input A discrete input for test and Ground Support Equipment is provided. Grounding this pin indicates to the EGPWS that test or Ground Support Equipment is connected to the computer. Active Threshold Voltage (Logic True) < 0.8 VDC Inactive Threshold Voltage (Logic False) > 2.0 VDC Input Impedance > 20 KΩ Maximum Fault Current < 500 µA Pin Assignment (Signal Mnemonic): J3-11 (GSE_PRES#) 4.4 Front Panel Status Indicators The MK VI and MK VIII EGPWC front panel provides three LEDs for indicating system and LRU status. A yellow LED labeled “EXTERNAL FAULT” is activated when a signal fault external to the MK VI or MK VIII EGPWC is detected. A green LED labeled “COMPUTER OK” is activated when the MK VI or MK VIII EGPWC itself is okay. A red LED labeled “COMPUTER FAIL” is activated when the MK VI or MK VIII EGPWC has detected an internal computer fault. Refer to Product Specification 965-1180-601 for a detailed discussion of status indications, recommended maintenance actions, Self Test activation and response. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 173 Honeywell MK VI MK VIII EGPWS Installation Design Guide 5 AIRCRAFT APPLICATION DATA This section describes the MK VI and MK VIII EGPWS interfaces for aircraft applications. Section 5.1 is a listing of the selection categories defining the various aircraft sensor interfaces and EGPWS functional options. Section 5.2 describes how the Category ID’s are selected and programmed for the interface to aircraft sensors and EGPWS functional options. Section 5.3 and its sub-sections define the specific aircraft interfaces available for the MK VI and MK VIII EGPWS. 5.1 Configuration Types The selection of the basic interfaces to the MK VI and MK VIII EGPWS can be found in the following categories: Aircraft / Mode Type Select Air Data Input Select Position Input Select Altitude Callouts Audio Menu Select Terrain Display Select Options Select Group 1 Radio Altitude Input Select Navigation Input Select Attitude Input Select Heading Input Select Windshear Input Select I / O Discretes Select Audio Output Level Future Configuration Category Future Configuration Category Future Configuration Category 5.2 Category 1 Category 2 Category 3 Category 4 Category 5 Category 6 Category 7 Category 8 Category 9 Category 10 Category 11 Category 12 Category 13 Category 14 Category 15 Category 16 Category 17 Configuration Selection Each category provides information relative to aircraft interfaces or EGPWS functional options required or used for EGPWS operation. Each category must be defined for the specific aircraft application according to the available aircraft sensors or equipment and the intended EGPWS function. The choices provided are available in each category identified by an “ID” number. The ID number is selected for each category and is used to load the selected configuration in a configuration module installed in the aircraft wiring (physically part of one of the EGPWC mating connectors). For example, selecting Category 2, ID 1 defines the Air Data Input as ARINC 429 per Table 5.3.2-1 in Category 2. With this ID programmed into the configuration module the EGPWC will look for and use the interface defined for this ID. Table 5.2 can be used to record the selected ID for each category for later reference when programming the configuration module. This programming is accomplished using a programming software tool available from Honeywell or generating a data text string and transferring this data (in either case) via the EGPWC RS-232C (see 4.3.1) to the configuration module. Once programmed, the configuration is available and read by any installed EGPWC on power up. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 174 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.2: Category ID Selection Procedure Step (Category) Signal Selection Selects: 1 2 3 a) Aircraft Type b) Mode Type Selects: a) Air Data Source Selects: a) Position Source Selects: 4 a) Altitude Callouts Menu Selects: 5 a) Audio Menu Selects: 6 a) Terrain Display Config. Instruction Ident No. Using Table 5.3.1, and any sub-tables contained within, locate the Aircraft / Mode Type. Record the Ident (ID No.) on the space available on Ident column of this table. _______ Using Table 5.3.2, 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. _______ Using Table 5.3.3, 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. _______ Using Table 5.3.4 and any sub-tables contained within, locate the desired Altitude Callout Menu. Record the Ident (ID No.) on the space available on Ident column of this table. _______ Using Table 5.3.5 and any sub-tables contained within, locate the desired Audio Menu type. Audio Menu types 2 & 3 are designed for Fixed Gear installations. Record the Ident (ID No.) on the space available on Ident column of this table. _______ Using Table 5.3.6 and any sub-tables contained within, locate the desired Terrain Display indicator type and range bus type. Record the Ident (ID No.) on the space available on Ident column of this table. _______ Using Table 5.3.7 and any sub-tables contained within, select the desired True or False condition for Steep Approach Enabled, TA&D Alternate Pop Up, Peaks Mode Enable, Obstacle Awareness Enable, Bank Angle Enable, Flap Reversal Select functions and GPS Altitude Reference type. Record the Ident (ID No.) on the space available on Ident column of this table. _______ Using Table 5.3.8, and any sub-tables contained within, locate the desired Radio Altitude signal type. Record the Ident (ID No.) on the space available on Ident column of this table. _______ Using Table 5.3.9, and any sub-tables contained within, locate the desired Navigation signal type. Record the Ident (ID No.) on the space available on Ident column of this table. _______ Using Table 5.3.10, and any sub-tables contained within, locate the desired Attitude signal type. Record the Ident (ID No.) on the space available on Ident column of this table. _______ Using Table 5.3.11, and any sub-tables contained within, locate the desired Magnetic Heading signal type. Record the Ident (ID No.) on the space available on Ident column of this table. _______ Using Table 5.3.12, select “0” NoWindshear unless you are an OEM with a defined aircraft windshear type. Record the Ident “0” (ID No.) on the space available on Ident column of this table. __0 __ ID # ID # ID # ID # ID # ID # Selects: 7 a) Steep Approach Enabled b) TA&D Alternate Pop Up c) Peaks Mode Enable d) Obstacle Awareness Enable e) Bank Angle Enable f) Flap Position Polarity g) GPS Altitude Reference Selects: 8 a) Radio Altitude Source Selects: 9 10 a) Glideslope and/or Localizer Source Selects: a) Attitude Source Selects: 11 a) Magnetic Heading Source Selects: 12 a) Windshear Input Type ID # ID # ID # ID # ID # ID # Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 175 Honeywell MK VI MK VIII EGPWS Installation Design Guide Step (Category) Signal Selection Instruction Ident No. Selects: 13 14 15 16 17 a) Input Discrete Functions b) Output Discrete Functions Selects: a) Audio Output Level Using Table 5.3.13, 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. _______ Using Table 5.3.14, 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. _______ Using Table 5.3.15, select “0” Unused. Record the Ident “0” (ID No.) on the space available on Ident column of this table. __0__ Using Table 5.3.16, select “0” Unused. Record the Ident “0” (ID No.) on the space available on Ident column of this table. __0__ Using Table 5.3.17, select “0” Unused. Record the Ident “0” (ID No.) on the space available on Ident column of this table. __0__ Selects: a) Unused Selects: b) Unused Selects: c) Unused ID # ID # ID # ID # ID # LIMITATIONS: The described use of the configuration module provides for maximum flexibility in selection of input sensors and output behavior. Every attempt has been made to avoid conflicts arising between categories and to reflect the known configurations of aircraft. However in the case of input sensors it should not be construed that all combinations are valid configurations. There may be configurations not supported by the EGPWS software configuration building process (which will cause the EGPWS to fail in an obvious manner). In general you can not have redundancy through the mixing of analog and digital sources, however redundant digital signals on different buses are permissable. As it is not practical to verify all possible sensor combinations, verification of particular sensor combinations is part of the installation certification process. If you intend to implement a sensor configuration not currently identified in Section 5, please contact Honeywell or an authorized dealer/installer. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 176 Honeywell MK VI MK VIII EGPWS Installation Design Guide 5.3 Configuration Selection Tables Configuration selection is defined by category (or group of functions or inputs). The Category number identifies the subsection where the details are defined. For example Air Data, Category 2, is defined in Section 5.3.2, and Position Input Source, Category 3, is defined in Section 5.3.3. 5.3.1 Category 1, Aircraft / Mode Type Select In this category the following parameters are defined: • Basic mode alert thresholds • Selected Mode 4B threshold • Selected airspeed expansion • Landing gear type • Aircraft category (GA Fast, GA Slow, or Bizjet) defines the expected aircraft models, which the Aircraft Type will be allocated to. It should be noted that the term “GA” when referring to GA Fast and GA Slow refers to Turboprop aircraft and slower jet aircraft. Some of the differences between aircraft types are listed below to assist the reader. Bizjet (Turbofan, MK VIII EGPWS only): • Uses Commercial GPWS modes with Bizjet optimized “Bank-Angle” callout. • A Gear stuck down fault will be indicated if the Gear are down and Airspeed exceeds 290 knots • A Flap stuck down fault will be indicated if the Flaps are down and Airspeed exceeds 250 knots • Uses either a 2000 ft and greater runway database (default) or a 3500 ft and greater runway database GA Fast (Fast Turboprop): • Uses classic MK VI GPWS modes. • A Gear stuck down fault will be indicated if the Gear are down and Airspeed exceeds 290 knots • A Flap stuck down fault will be indicated if the Flaps are down and Airspeed exceeds 250 knots GA Slow (Slow Turboprop): • Uses classic MK VI GPWS modes. • Allows use of Mode 4 Alternate Airspeed Expansion • A Gear stuck down fault will be indicated if the Gear are down and Airspeed exceeds 200 knots • A Flap stuck down fault will be indicated if the Flaps are down and Airspeed exceeds 180 knots The gear stuck and flap stuck faults activate the “GPWS INOP” and are recorded in fault history. In addition, the Mode 4 Altitude and Airspeed Expansion variables are defined as follows: • Mode 4B Altitude are described as follows: 150’ Mode 4B: The voice “Too Low Flaps” is intitiated at 150 feet above the ground. 170’ Mode 4B: The voice “Too Low Flaps” is intitiated at 170 feet above the ground. 200’ Mode 4B: The voice “Too Low Flaps” is intitiated at 200 feet above the ground. • Normal/Alternate Airspeed Expansion are described as follows: Normal Airspeed Expansion: • Above 178 knots, penetration of the Mode 4 envelope will cause a “Too Low Terrain” voice • Below 178 knots, penetration of the Mode 4 envelope will cause a “Too Low Gear” voice Alternate Airspeed Expansion: • Above 148 knots, penetration of the Mode 4 envelope will cause a “Too Low Terrain” voice • Below 148 knots, penetration of the Mode 4 envelope will cause a “Too Low Gear” voice Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 177 Honeywell MK VI MK VIII EGPWS Installation Design Guide The following table provides identification of the basic Aircraft/Mode Types and associated parameters. For purposes of selecting an ID, use the “Description” provided in Table 5.3.1 appropriate to the desired variables as given above. Table 5.3.1: Aircraft / Mode Type Select Aircraft / Mode ID Software Effectivity DESCRIPTION Type 0 0 1 1 2 2 3 3 4 4 GA Fast (Fast Turboprop, Slow Turbofan), 170’ Mode 4B, Normal Airspeed Expansion GA Fast (Fast Turboprop, Slow Turbofan), 150’ Mode 4B, Normal Airspeed Expansion GA Fast (Fast Turboprop, Slow Turbofan), 200’ Mode 4B, Normal Airspeed Expansion GA Slow (Slow Turboprop), 170’ Mode 4B, Alternate Airspeed Expansion GA Slow (Slow Turboprop), 150’ Mode 4B, Alternate Airspeed Expansion Bizjet (Turbofan), default GPWS modes with Bizjet Bank Angle Callout and 3500 ft and greater runway database. (MKVIII Only) (Note 1) Bizjet (Turbofan), default GPWS modes with Bizjet Bank 255 255 Angle Callout and 2000 ft and greater runway database. (MKVIII Only) Note 1: ID 254 is supported with terrain database 426 and later. 254 ID 0 1 2 3 4 254 255 254 Aircraft Type GA Fast GA Fast GA Fast GA Slow GA Slow Bizjet Bizjet Mode 1 Type 4 4 4 4 4 1 1 Mode 2 Type 4 4 4 5 5 1 1 Mode 3 Type 2 2 2 2 2 1 1 Mode 4 Type 6 8 5 7 9 1 1 EGPWS MKVI MKVIII -020 X X -020 X X -020 X X -020 X X -020 X X -020 N/A X -020 N/A X Mode 6 Type 1 1 1 1 1 1 1 Bank Angle Type 4 4 4 4 4 2 2 Runway Database 2000’ 2000’ 2000’ 2000’ 2000’ 3500’ 2000’ See Product Specification 965-1180-601 for a description of Mode ‘X‘ type number. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 178 Honeywell MK VI MK VIII EGPWS Installation Design Guide 5.3.2 Category 2, Air Data Input Select The following table provides identification of the Air Data source type. The entry in the Air Data Type corresponds to a table that provides detailed information on the configuration. For example, the details for Air Data Type #2 are found in Table 5.3.2-2. In this category, only the following signals are defined: • Uncorrected Barometric Altitude in analog, ARINC 575, or ARINC 429 format, and associated validity. • Temperature (Outside Air or Static Air) in analog, ARINC 575, or ARINC 429 format. • Corrected Barometric Altitude in ARINC 429 format. • Barometric Rate in ARINC 575 or ARINC 429 format. • Computed Airspeed in ARINC 575 or ARINC 429 format. TABLE 5.3.2: AIR DATA INPUT SELECT ID Air Data Type Software Effectivity Description (Table 5.3.2-x) 0 0 1 1 2 2 3 3 4 4 5 5 6 6 10 10 11 11 12 12 13 13 255 255 EGPWS MKVI Analog - Uncorrected Baro altitude and 500Ω OAT (i.e., CIC 04077) Digital - ARINC 429 (i.e., Bendix KDC 281) Digital - ARINC 575 (i.e., Collins ADC-80, 81, 82) Analog - Uncorrected Baro altitude and 500Ω OAT (i.e., Collins ADS-65) Analog - Uncorrected Baro altitude and 500Ω OAT (i.e., CIC 02702) Digital - ARINC 429 with Corrected Altitude label 204 (i.e., Bendix KDC 481T) Digital - ARINC 429 without Baro Rate label 212 (i.e., Honeywell AZ-810) Digital - ARINC 429 and 500Ω OAT (i.e. Shadin 2000) Analog - Uncorrected Baro altitude and 500Ω OAT (i.e., Honeywell AZ-241, AZ-242, AZ-648, AZ-800, AZ-810) (Note 2) Analog - Uncorrected Baro altitude without temperature (i.e., Honeywell AZ-241, AZ-242, AZ-648, AZ-800, AZ-810) (Note 2) Digital - ARINC 429 Uncorrected Altitude label 203 without temperature Digital – ARINC 429 (via dual IOC buses). (Note 1) MKVIII -020 X X -020 X X -020 X X -020 X X -020 X X -020 X X -020 X X -020 X X -020 X X -020 X X -020 X X -020 N/A X Note 1: ID 255 may only be used in conjunction with other IOC bus selections for categories 6, 8, 9, 10, 11 and 12. Note 2: The AZ-800 provides an OAT signal with reference provided by the ADC. This signal is not compatible with any current EGPWS interface. The AZ-241 does not provide an OAT interface. The installer may either add an OAT probe (ID 11) or use the internal constant (ID 12). Honeywell recommends ID 11 (added OAT probe) be used when operating in temperature extremes. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 179 Honeywell MK VI MK VIII EGPWS Installation Design Guide TABLE 5.3.2-0: AIR DATA INPUT SELECT #0 (+) = J1-62 (–) = J1-43 Outside Air Temp Total Air Temperature REFERENCE 6.1.3 6.1.4 4.2.3.5 Probe element Excitation: 5 V = J1-25 Temp Input (probe element): (+) = J1-63 (–) = J1-44 Ground GND = J1-53 SUMMARY DATA Format: DC with Validity Flag Input Type: Basic Fault Designation: BAROMETRIC ALTITUDE FAULT Validity: Barometric Alt Valid (+28V) Format: DC Input Type: Basic Fault Designation: STATIC AIR TEMPERATURE FAULT 4.2.10 J1 25 (5 V Ref) 4.42 K Ohms 63 + 44 Voat Uncorrected Barometric Altitude CONNECTION OAT PROBE ELEMENT SIGNAL Temp In 53 Chassis Gnd Note: Nominal 500 Ω Temperature Probe only. Resistance @ 0°C: 500Ω ± 0.6Ω Connection example: CIC Temperature Sensor, P/N 05257 (2 wire). Connect positive lead to both J1-25 and J1-63. Connect negative lead to both J144 and J1-53 (Chassis Ground). Other probes may have three contacts. Computed Airspeed No Connection N/A Substitute Ground Speed for Airspeed (airspeed is not available with this air data input) PIN FUNCTION CONNECTION PIN TYPE CHANNEL DESIGNATION REFERENCE Barometric Altitude Validity Discrete (+28V) J1-9 Input 28V_DISC_08 Configuration Data Derive Baro Altitude Rate Type Analog Polarity/Configuration References >+17V = Valid < +4.4V = Invalid 6.6.22 4.2.7 Summary Data Baro Altitude Rate is derived using Uncorrected Barometric Altitude. Baro Rate is not available with this air data source. TABLE 5.3.2-1: AIR DATA INPUT SELECT #1 CHANNEL 429RX_2 A = J2-39 B = J2-38 CONNECT TO: ADC #1 Format: ARINC 429 (Low Speed) Fault Designation: AIR DATA BUS Bus Type: Basic Data Uncorrected Baro. Alt Computed Airspeed Barometric Rate Static Air Temperature Label 203 206 212 213 Reference 6.2.1 6.2.39 6.2.3 6.2.2 Sig. Bits 17 14 11 11 Range ±131,072 FT ±1024 KTS ±32768 FPM 512 Degrees Signal Type Basic Basic Basic Basic Resolution 1.0 0.0625 16.0 0.25 Rate (ms) 31.3-62.5 62.5-125 31.3-62.5 250-500 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 180 Honeywell MK VI MK VIII EGPWS Installation Design Guide TABLE 5.3.2-2: AIR DATA INPUT SELECT #2 CHANNEL 429RX_2 A = J2-39 B = J2-38 CONNECT TO: ADC #1 Format: ARINC 575 (Low Speed) Fault Designation: AIR DATA BUS Bus Type: Basic Data Uncorrected Baro. Alt Computed Airspeed Barometric Rate Static Air Temperature Label 203 206 212 213 Reference 6.3.2 6.3.4 6.3.3 6.3.1 Sig. Bits 17 13 11 10 Range ±131,072 FT ±1024 KTS ±20480 FPM ±512 Degrees Signal Type Basic Basic Basic Basic Resolution 1.0 0.125 10.0 0.5 Rate (ms) 31.3-62.5 62.5-125 31.3-62.5 250-500 TABLE 5.3.2-3: AIR DATA INPUT SELECT #3 (+) = J1-62 (–) = J1-43 Outside Air Temp Total Air Temperature REFERENCE 6.1.10 6.1.4 4.2.3.5 Probe element Excitation: 5 V = J1-25 Temp Input (probe element): (+) = J1-63 (–) = J1-44 Ground GND = J1-53 SUMMARY DATA Format: DC with Validity Flag Input Type: Basic Fault Designation: BAROMETRIC ALTITUDE FAULT Validity: Barometric Alt Valid (+28V) Format: DC Input Type: Basic Fault Designation: STATIC AIR TEMPERATURE FAULT 4.2.10 J1 25 (5 V Ref) 4.42 K Ohms Voat Uncorrected Barometric Altitude CONNECTION OAT PROBE ELEMENT SIGNAL 63 + 44 Temp In 53 Chassis Gnd Note: Nominal 500 Ω Temperature Probe only. Resistance @ 0°C: 500Ω ± 0.6Ω Connection example: CIC Temperature Sensor, P/N 05257 (2 wire). Connect positive lead to both J1-25 and J1-63. Connect negative lead to both J144 and J1-53 (Chassis Ground). Other probes may have three contacts. Computed Airspeed No Connection N/A Substitute Ground Speed for Airspeed (airspeed is not available with this air data input) PIN FUNCTION CONNECTION PIN TYPE CHANNEL DESIGNATION REFERENCE Barometric Altitude Validity Discrete (+28V) J1-9 Input 28V_DISC_08 Configuration Data Derive Baro Altitude Rate Type Analog Polarity/Configuration References >+17V = Valid < +4.4V = Invalid 6.6.22 4.2.7 Summary Data Baro Altitude Rate is derived using Uncorrected Barometric Altitude. Baro Rate is not available with this air data source. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 181 Honeywell MK VI MK VIII EGPWS Installation Design Guide TABLE 5.3.2-4: AIR DATA INPUT SELECT #4 (+) = J1-62 (–) = J1-43 Outside Air Temp Total Air Temperature REFERENCE 6.1.13 6.1.4 4.2.3.5 Probe element Excitation: 5 V = J1-25 Temp Input (probe element): (+) = J1-63 (–) = J1-44 Ground GND = J1-53 SUMMARY DATA Format: DC with Validity Flag Input Type: Basic Fault Designation: BAROMETRIC ALTITUDE FAULT Validity: Barometric Alt Valid (+28V) Format: DC Input Type: Basic Fault Designation: STATIC AIR TEMPERATURE FAULT 4.2.10 J1 25 (5 V Ref) 4.42 K Ohms Voat Uncorrected Barometric Altitude CONNECTION OAT PROBE ELEMENT SIGNAL 63 + 44 Temp In 53 Chassis Gnd Note: Nominal 500 Ω Temperature Probe only. Resistance @ 0°C: 500Ω ± 0.6Ω Connection example: CIC Temperature Sensor, P/N 05257 (2 wire). Connect positive lead to both J1-25 and J1-63. Connect negative lead to both J144 and J1-53 (Chassis Ground). Other probes may have three contacts. Computed Airspeed No Connection N/A Substitute Ground Speed for Airspeed (airspeed is not available with this air data input) PIN FUNCTION CONNECTION PIN TYPE CHANNEL DESIGNATION REFERENCE Barometric Altitude Validity Discrete (+28V) J1-9 Input 28V_DISC_08 Configuration Data Derive Baro Altitude Rate Type Analog Polarity/Configuration References >+17V = Valid < +4.4V = Invalid 6.6.22 4.2.7 Summary Data Baro Altitude Rate is derived using Uncorrected Barometric Altitude. Baro Rate is not available with this air data source. TABLE 5.3.2-5: AIR DATA INPUT SELECT #5 CHANNEL 429RX_2 A = J2-39 B = J2-38 CONNECT TO: ADC #1 Format: ARINC 429 (Low Speed) Fault Designation: AIR DATA BUS Bus Type: Basic Data Uncorrected Baro. Alt Corrected Baro. Alt Computed Airspeed Barometric Rate Static Air Temperature Label 203 204 206 212 213 Reference 6.2.1 6.2.38 6.2.39 6.2.3 6.2.2 Sig. Bits 17 17 14 11 11 Range ±131,072 FT ±131,072 FT ±1024 KTS ±32678 FPM ±512 Degrees Signal Type Basic Basic Basic Basic Basic Resolution 1.0 1.0 0.0625 16.0 0.25 Rate (ms) 31.3-62.5 31.3-62.5 62.5-125 31.3-62.5 250-500 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 182 Honeywell MK VI MK VIII EGPWS Installation Design Guide TABLE 5.3.2-6: AIR DATA INPUT SELECT #6 CHANNEL 429RX_2 CONNECT TO: ADC #1 Format: ARINC 429 (Low Speed) Fault Designation: AIR DATA BUS Bus Type: Basic A = J2-39 B = J2-38 Data Uncorrected Baro. Alt Computed Airspeed Static Air Temperature Label 203 206 213 Reference 6.2.1 6.2.39 6.2.2 Configuration Data Derive Baro Altitude Rate Sig. Bits 17 14 11 Range ±131,072 FT ±1024 KTS ±512 Degrees Type Signal Type Basic Basic Basic Resolution 1.0 0.0625 0.25 Rate (ms) 31.3-62.5 62.5-125 250-500 Summary Data Baro Altitude Rate is derived using Uncorrected Barometric Altitude. Baro Rate is not available with this air data source. Digital TABLE 5.3.2-10: AIR DATA INPUT SELECT #10 Fault Designation: AIR DATA BUS Bus Type: Basic CONNECT TO: ADC #1 Format: ARINC 429 (Low Speed) Data Uncorrected Baro. Alt Corrected Baro. Alt Computed Airspeed Barometric Rate Outside Air Temp Total Air Temperature Reference 6.2.1 6.2.38 6.2.39 6.2.3 6.1.4 4.2.3.5 Probe element Excitation: 5 V = J1-25 4.2.10 Temp Input (probe element): (+) = J1-63 (–) = J1-44 Ground GND = J1-53 Label 203 204 206 212 Sig. Bits Range Signal Type Resolution 17 ±131,072 FT Basic 1.0 17 ±131,072 FT Basic 1.0 14 ±1024 KTS Basic 0.0625 11 ±32678 FPM Basic 16.0 Format: DC Input Type: Basic Fault Designation: STATIC AIR TEMPERATURE FAULT J1 25 Rate (ms) 31.3-62.5 31.3-62.5 62.5-125 31.3-62.5 (5 V Ref) 4.42 K Ohms OAT PROBE ELEMENT A = J2-39 B = J2-38 Voat CHANNEL 429RX_2 63 + 44 Temp In 53 Chassis Gnd Note: Nominal 500 Ω Temperature Probe only. Resistance @ 0°C: 500Ω ± 0.6Ω Connection example: CIC Temperature Sensor, P/N 05257 (2 wire). Connect positive lead to both J1-25 and J1-63. Connect negative lead to both J144 and J1-53 (Chassis Ground). Other probes may have three contacts. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 183 Honeywell MK VI MK VIII EGPWS Installation Design Guide TABLE 5.3.2-11: AIR DATA INPUT SELECT #11 (+) = J1-62 (–) = J1-43 Outside Air Temp Total Air Temperature REFERENCE 6.1.16 6.1.4 4.2.3.5 Probe element Excitation: 5 V = J1-25 Temp Input (probe element): (+) = J1-63 (–) = J1-44 Ground GND = J1-53 SUMMARY DATA Format: DC with Validity Flag Input Type: Basic Fault Designation: BAROMETRIC ALTITUDE FAULT Validity: Barometric Alt Valid (+28V) Format: DC Input Type: Basic Fault Designation: STATIC AIR TEMPERATURE FAULT 4.2.10 J1 25 (5 V Ref) 4.42 K Ohms Voat Uncorrected Barometric Altitude CONNECTION OAT PROBE ELEMENT SIGNAL 63 + 44 Temp In 53 Chassis Gnd Note: Nominal 500 Ω Temperature Probe only. Resistance @ 0°C: 500Ω ± 0.6Ω Connection example: CIC Temperature Sensor, P/N 05257 (2 wire). Connect positive lead to both J1-25 and J1-63. Connect negative lead to both J1-44 and J1-53 (Chassis Ground). Other probes may have three contacts. Computed Airspeed No Connection N/A Substitute Ground Speed for Airspeed (airspeed is not available with this air data input) PIN FUNCTION CONNECTION PIN TYPE CHANNEL DESIGNATION REFERENCE Barometric Altitude Validity Discrete (+28V) J1-9 Input 28V_DISC_08 Configuration Data Derive Baro Altitude Rate Type Analog Polarity/Configuration References >+17V = Valid < +4.4V = Invalid 6.6.22 4.2.7 Summary Data Baro Altitude Rate is derived using Uncorrected Barometric Altitude. Although the ADC’s provide Baro Rate, the EGPWS does not have an analog connection available. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 184 Honeywell MK VI MK VIII EGPWS Installation Design Guide TABLE 5.3.2-12: AIR DATA INPUT SELECT #12 SIGNAL CONNECTION REFERENCE SUMMARY DATA Uncorrected Barometric Altitude (+) = J1-62 (–) = J1-43 6.1.16 Format: DC with Validity Flag Input Type: Basic Fault Designation: BAROMETRIC ALTITUDE FAULT Validity: Barometric Alt Valid (+28V) Outside Air Temp No Connection N/A No temperature Computed Airspeed No Connection N/A Substitute Ground Speed for Airspeed (airspeed is not available with this air data input) PIN FUNCTION Barometric Altitude Validity Discrete (+28V) CONNECTION J1-9 PIN TYPE Input CHANNEL DESIGNATION REFERENCE 28V_DISC_08 Configuration Data Derive Baro Altitude Rate Type Analog Polarity/Configuration References >+17V = Valid 6.6.22 < +4.4V = Invalid 4.2.7 Summary Data Baro Altitude Rate is derived using Uncorrected Barometric Altitude. Although the ADC’s provide Baro Rate, the EGPWS does not have an analog connection available. TABLE 5.3.2-13: AIR DATA INPUT SELECT #13 Fault Designation: AIR DATA BUS Bus Type: Basic CHANNEL 429RX_2 CONNECT TO: ADC #1 Format: ARINC 429 (Low Speed) A = J2-39 B = J2-38 Data Reference Label Sig. Bits Range Signal Type Resolution Rate (ms) Uncorrected Baro. Alt 6.2.1 203 17 ±131,072 FT Basic 1.0 31.3-62.5 Outside Air Temp No Connection N/A No temperature Computed Airspeed No Connection N/A Substitute Ground Speed for Airspeed (airspeed is not available with this air data input) Configuration Data Derive Baro Altitude Rate Type Digital Summary Data Baro Altitude Rate is derived using Uncorrected Barometric Altitude. Baro Rate is not available with this air data source. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 185 Honeywell MK VI MK VIII EGPWS Installation Design Guide TABLE 5.3.2-255: AIR DATA INPUT SELECT #255 CHANNEL 429/422RX_1 A = J2-37 B = J2-36 CHANNEL 429RX_3 A = J2-41 B = J2-40 CONNECT TO: IOC #1 Format: ARINC 429 (High Speed) Fault Designation: IOC BUS 1 Bus Type: Basic Data Uncorrected Baro. Alt Corrected Baro. Alt Computed Airspeed True Airspeed Barometric Rate Static Air Temperature Label 203 204 206 210 212 213 Reference 6.2.1 6.2.38 6.2.39 6.2.40 6.2.3 6.2.2 Sig. Bits 17 17 14 15 11 11 Range ±131,072 FT ±131,072 FT ±1024 KTS ±2048 KTS ±32678 FPM ±512 Degrees Signal Type Basic Basic Basic Basic Basic Basic CONNECT TO: IOC #2 Format: ARINC 429 (High Speed) Fault Designation: IOC BUS 2 Bus Type: Basic Data Uncorrected Baro. Alt Corrected Baro. Alt Computed Airspeed True Airspeed Barometric Rate Static Air Temperature Label 203 204 206 210 212 213 Reference 6.2.1 6.2.38 6.2.39 6.2.40 6.2.3 6.2.2 Sig. Bits 17 17 14 15 11 11 Range ±131,072 FT ±131,072 FT ±1024 KTS ±2048 KTS ±32678 FPM ±512 Degrees Signal Type Basic Basic Basic Basic Basic Basic Resolution 1.0 1.0 0.0625 0.0625 16.0 0.25 Rate (ms) 31.3-62.5 31.3-62.5 62.5-125 62.5-125 31.3-62.5 250-500 Resolution 1.0 1.0 0.0625 0.0625 16.0 0.25 Rate (ms) 31.3-62.5 31.3-62.5 62.5-125 62.5-125 31.3-62.5 250-500 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 186 Honeywell MK VI MK VIII EGPWS Installation Design Guide 5.3.3 Category 3, Position Input Select The following table provides identification of the Position source signal. Each entry in the Position Input Type column has a corresponding table that provides detailed information on the configuration. For example, the details for Position Input Type #0 are found in Table 5.3.3-0. In this category, only the following Position signals are defined: • Altitude • Sensor Status • Date * • True Track Angle • Ground Speed • Universal Time Correlation * • Horizontal Figure of Merit (HFOM) • Vertical Figure of Merit (VFOM) • Horizontal Integrity Limit • N/S Velocity • Latitude Position • E/W Velocity • Longitude Position • Vertical Velocity * used if present Table 5.3.3: Position Input Select ID Position Input Type 0 1 2 3 4 5 (Table 5.3.3-x) 0 1 2 3 4 5 10 10 11 11 12 12 13 13 253 253 255 255 Software Effectivity Description GPS, ARINC 429 low speed, ARINC 743A format GPS, ARINC 429 low speed, ARINC 743 format GPS, Internal GPS, RS-232 GPS-PXPRESS format GPS, ARINC 429 high speed, ARINC 743A format GPS, ARINC 429 high speed, ARINC 743 format GPS, ARINC 429 low speed, ARINC 743A format No N/S-E/W velocities Note 2 GPS, ARINC 429 low speed, ARINC 743 format No N/S-E/W velocities Note 2 GPS, ARINC 429 high speed, ARINC 743A format No N/S-E/W velocities Note 2 GPS, ARINC 429 high speed, ARINC 743 format No N/S-E/W velocities Note 2 Dual IOC GPS, ARINC 429 high speed, ARINC 743A format, No N/S-E/W velocities Note 2 Dual GPS, ARINC 429 high speed, ARINC 743A format EGPWS -020 -020 -020 -020 -020 -020 MK VI X X X X X X MK VIII X X X X X X -020 X X -020 X X -020 X X -020 X X -020 X X -020 N/A X NOTE 1: The GPS Altitude Reference in Category 7, Options Select Group #1 must be properly applied for the appropriate GPS Position type. At the time of release of this document, all GPS sources except the Universal GPS1000 based systems are of MSL type. The Universal GPS1000 based GPS sources are of WGS-84 type. If the internal GPS source (ID=2) is defined, the GPS altitude reference in Category 7 must be MSL. NOTE 2: ID 10, 11, 12, 13 and 253 may only be used when pitch and roll attitude inputs are configured for use in Category 10 Attitude Input Select. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 187 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.3-0: Position Input Type 0 (Low Speed ARINC 743A GPS) CHANNEL 429RX_4 A = J2-25 B = J2-8 CONNECT TO: GPS (ARINC 743A) Format: ARINC 429 (Low Speed) Data Latitude - Normal Longitude - Normal GPS Hor. Int. Limit Altitude VFOM HFOM Ground Speed True Track Angle North/South Velocity East/West Velocity Vertical Velocity Sensor Status **UTC **Date Reference 6.2.7 6.2.8 6.2.5 6.2.4 6.2.13 6.2.10 6.2.6 6.2.9 6.2.53 6.2.54 6.2.58 6.2.16 6.2.17 6.2.18 Fault Designation: GPS BUS Bus Type: Basic Label 110 111 130 076 136 247 112 103 166 174 165 273 125 260 Sig. Bits 20 20 17 20 18 18 15 15 15 15 15 19 19 19 Range ±180 Degrees ±180 Degrees 16 nm ±131,072 FT 32768 ft 16 nm ±4096 Knots ±180 Degrees ±4096 Knots ±4096 Knots ±32768 fpm Discrete Wd Discrete Wd Discrete Wd Signal Type Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Resolution 0.00017166137695 0.00017166137695 0.00012207 0.125 0.125 0.000061035 0.125 0.0054931640625 0.125 0.125 1 n/a 0.1 min 1 day *Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 Resolution 0.00017166137695 0.00017166137695 0.00012207 0.125 0.03125 0.03125 0.125 0.0054931640625 0.125 0.125 1 n/a 0.1 min 1 day *Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 Notes: * Slowest acceptable update rate in milliseconds. ** This label is not required. Data used if present Table 5.3.3-1: Position Input Type 1 (Low Speed ARINC 743 GPS) CHANNEL 429RX_4 A = J2-25 B = J2-8 Fault Designation: GPS BUS Bus Type: Basic CONNECT TO: GPS (ARINC 743) Format: ARINC 429 (Low Speed) Data Latitude - Normal Longitude - Normal GPS Hor. Int. Limit Altitude VDOP HDOP Ground Speed True Track Angle North/South Velocity East/West Velocity Vertical Velocity Sensor Status **UTC **Date Reference 6.2.7 6.2.8 6.2.5 6.2.4 6.2.15 6.2.12 6.2.6 6.2.9 6.2.53 6.2.54 6.2.58 6.2.16 6.2.17 6.2.18 Label 110 111 130 076 102 101 112 103 166 174 165 273 125 260 Sig. Bits 20 20 17 20 15 15 15 15 15 15 15 19 19 19 Range ±180 Degrees ±180 Degrees 16 nm ±131,072 FT 1024 1024 ±4096 Knots ±180 Degrees ±4096 Knots ±4096 Knots ±32768 fpm Discrete Wd Discrete Wd Discrete Wd Signal Type Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Notes: * Slowest acceptable update rate in milliseconds. ** This label is not required. Data used if present Table 5.3.3-2: Position Input Type 2 (Internal GPS) CHANNEL Fault Designation: INTERNAL GPS Bus Type: Basic Internal GPS Data Latitude Longitude HP Error Altitude VP Error Ground Speed True Track Angle East Velocity North Velocity Vertical Velocity GPS State Integrity State Error Status Reference 6.4.1 6.4.1 6.4.1 6.4.2 6.4.2 6.4.3 6.4.3 6.4.4 6.4.4 6.4.4 6.4.5 6.4.5 6.4.5 ID/byte 15/1-4 15/5-8 15/9-12 16/1-4 16/5-8 17/1-4 17/5-8 18/1-4 18/5-8 18/9-12 1C/0 1C/1 1C/6-7 Sig. Bits 32 32 32 32 32 32 32 32 32 32 8 8 8 Range ±180 Degrees ±180 Degrees meters meters meters meters/sec 360 Degrees meters/sec meters/sec meters/sec Discrete Wd Discrete Wd Discrete Wd Signal Type Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Resolution real single-precision real single-precision real single-precision real single-precision real single-precision real single-precision real single-precision real single-precision real single-precision real single-precision n/a n/a n/a Notes: * Slowest acceptable update rate in milliseconds. 1. "MSL" reference must be selected when an internal GPS is utilized. Refer to Table 5.3.7 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 188 *Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.3-3: Position Input Type 3 (RS232 GPS, PXpress format) CHANNEL GPS_RXA GPS_TXA J2-28 (cm) J2-29 (Rx) CONNECT TO: GPS (PXpress format) Format: RS232 (9600 baud) Data Latitude Longitude HP Error Altitude VP Error Ground Speed True Track Angle East Velocity North Velocity Vertical Velocity GPS State Integrity State Error Status Reference 6.4.1 6.4.1 6.4.1 6.4.2 6.4.2 6.4.3 6.4.3 6.4.4 6.4.4 6.4.4 6.4.5 6.4.5 6.4.5 Fault Designation: GPS BUS Bus Type: Basic ID/byte 15/1-4 15/5-8 15/9-12 16/1-4 16/5-8 17/1-4 17/5-8 18/1-4 18/5-8 18/9-12 1C/0 1C/1 1C/6-7 Sig. Bits 32 32 32 32 32 32 32 32 32 32 8 8 8 Range ±180 Degrees ±180 Degrees meters meters meters meters/sec 360 Degrees meters/sec meters/sec meters/sec Discrete Wd Discrete Wd Discrete Wd Signal Type Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Resolution real single-precision real single-precision real single-precision real single-precision real single-precision real single-precision real single-precision real single-precision real single-precision real single-precision n/a n/a n/a *Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 Notes: * Slowest acceptable update rate in milliseconds. Table 5.3.3-4: Position Input Type 4 (High Speed ARINC 743A GPS) CHANNEL 429RX_4 A = J2-25 B = J2-8 CONNECT TO: GPS (ARINC 743A) Format: ARINC 429 (High Speed) Data Latitude - Normal Longitude - Normal GPS Hor. Int. Limit Altitude VFOM HFOM Ground Speed True Track Angle North/South Velocity East/West Velocity Vertical Velocity Sensor Status **UTC **Date Reference 6.2.7 6.2.8 6.2.5 6.2.4 6.2.13 6.2.10 6.2.6 6.2.9 6.2.53 6.2.54 6.2.58 6.2.16 6.2.17 6.2.18 Fault Designation: GPS BUS Bus Type: Basic Label 110 111 130 076 136 247 112 103 166 174 165 273 125 260 Sig. Bits 20 20 17 20 18 18 15 15 15 15 15 19 19 19 Range ±180 Degrees ±180 Degrees 16 nm ±131,072 FT 32768 ft 16 nm ±4096 Knots ±180 Degrees ±4096 Knots ±4096 Knots ±32768 fpm Discrete Wd Discrete Wd Discrete Wd Signal Type Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Resolution 0.00017166137695 0.00017166137695 0.00012207 0.125 0.125 0.000061035 0.125 0.0054931640625 0.125 0.125 1 n/a 0.1 min 1 day *Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 Resolution 0.00017166137695 0.00017166137695 0.00012207 0.125 0.03125 0.03125 0.125 0.0054931640625 0.125 0.125 1 n/a 0.1 min 1 day *Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 Notes: * Slowest acceptable update rate in milliseconds. ** This label is not required. Data used if present Table 5.3.3-5: Position Input Type 5 (High Speed ARINC 743 GPS) CHANNEL 429RX_4 A = J2-25 B = J2-8 Fault Designation: GPS BUS Bus Type: Basic CONNECT TO: GPS (ARINC 743) Format: ARINC 429 (High Speed) Data Latitude - Normal Longitude - Normal GPS Hor. Int. Limit Altitude VDOP HDOP Ground Speed True Track Angle North/South Velocity East/West Velocity Vertical Velocity Sensor Status **UTC **Date Reference 6.2.7 6.2.8 6.2.5 6.2.4 6.2.15 6.2.12 6.2.6 6.2.9 6.2.53 6.2.54 6.2.58 6.2.16 6.2.17 6.2.18 Label 110 111 130 076 102 101 112 103 166 174 165 273 125 260 Sig. Bits 20 20 17 20 15 15 15 15 15 15 15 19 19 19 Range ±180 Degrees ±180 Degrees 16 nm ±131,072 FT 1024 1024 ±4096 Knots ±180 Degrees ±4096 Knots ±4096 Knots ±32768 fpm Discrete Wd Discrete Wd Discrete Wd Signal Type Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Notes: * Slowest acceptable update rate in milliseconds. ** This label is not required. Data used if present Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 189 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.3-10: Position Input Type 10 (Low Speed ARINC 743A GPS, no N/S-E/W Velocities) CHANNEL 429RX_4 A = J2-25 B = J2-8 CONNECT TO: GPS (ARINC 743A) Format: ARINC 429 (Low Speed) Data Latitude – Normal Longitude – Normal GPS Hor. Int. Limit Altitude VFOM HFOM Ground Speed True Track Angle Sensor Status **UTC **Date Reference 6.2.7 6.2.8 6.2.5 6.2.4 6.2.13 6.2.10 6.2.6 6.2.9 6.2.16 6.2.17 6.2.18 Fault Designation: GPS BUS Bus Type: Basic Label 110 111 130 076 136 247 112 103 273 125 260 Sig. Bits 20 20 17 20 18 18 15 15 19 19 19 Range ±180 Degrees ±180 Degrees 16 nm ±131,072 FT 32768 ft 16 nm ±4096 Knots ±180 Degrees Discrete Wd Discrete Wd Discrete Wd Signal Type Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Resolution 0.00017166137695 0.00017166137695 0.00012207 0.125 0.125 0.000061035 0.125 0.0054931640625 n/a 0.1 min 1 day *Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 Notes: * Slowest acceptable update rate in milliseconds. ** This label is not required. Data used if present Table 5.3.3-11: Position Input Type 11 (Low Speed ARINC 743 GPS, no N/S-E/W Velocities) CHANNEL 429RX_4 A = J2-25 B = J2-8 Fault Designation: GPS BUS Bus Type: Basic CONNECT TO: GPS (ARINC 743) Format: ARINC 429 (Low Speed) Data Latitude – Normal Longitude – Normal GPS Hor. Int. Limit Altitude VFOM HFOM Ground Speed True Track Angle Sensor Status **UTC **Date Reference 6.2.7 6.2.8 6.2.5 6.2.4 6.2.13 6.2.10 6.2.6 6.2.9 6.2.16 6.2.17 6.2.18 Label 110 111 130 076 136 247 112 103 273 125 260 Sig. Bits 20 20 17 20 15 15 15 15 19 19 19 Range ±180 Degrees ±180 Degrees 16 nm ±131,072 FT 1024 meters 1024 meters ±4096 Knots ±180 Degrees Discrete Wd Discrete Wd Discrete Wd Signal Type Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Resolution 0.00017166137695 0.00017166137695 0.00012207 0.125 0.125 0.000061035 0.125 0.0054931640625 n/a 0.1 min 1 day *Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 Notes: * Slowest acceptable update rate in milliseconds. ** This label is not required. Data used if present Table 5.3.3-12: Position Input Type 12 (High Speed ARINC 743A GPS, no N/S-E/W Velocities) CHANNEL 429RX_4 A = J2-25 B = J2-8 CONNECT TO: GPS (ARINC 743A) Format: ARINC 429 (High Speed) Data Latitude – Normal Longitude – Normal GPS Hor. Int. Limit Altitude VFOM HFOM Ground Speed True Track Angle Sensor Status **UTC **Date Reference 6.2.7 6.2.8 6.2.5 6.2.4 6.2.13 6.2.10 6.2.6 6.2.9 6.2.16 6.2.17 6.2.18 Fault Designation: GPS BUS Bus Type: Basic Label 110 111 130 076 136 247 112 103 273 125 260 Sig. Bits 20 20 17 20 18 18 15 15 19 19 19 Range ±180 Degrees ±180 Degrees 16 nm ±131,072 FT 32768 ft 16 nm ±4096 Knots ±180 Degrees Discrete Wd Discrete Wd Discrete Wd Signal Type Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Resolution 0.00017166137695 0.00017166137695 0.00012207 0.125 0.125 0.000061035 0.125 0.0054931640625 n/a 0.1 min 1 day Notes: * Slowest acceptable update rate in milliseconds. ** This label is not required. Data used if present Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 190 *Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.3-13: Position Input Type 13 (High Speed ARINC 743 GPS, no N/S-E/W Velocities) CHANNEL 429RX_4 A = J2-25 B = J2-8 Fault Designation: GPS BUS Bus Type: Basic CONNECT TO: GPS (ARINC 743) Format: ARINC 429 (High Speed) Data Latitude – Normal Longitude – Normal GPS Hor. Int. Limit Altitude VFOM HFOM Ground Speed True Track Angle Sensor Status **UTC **Date Reference 6.2.7 6.2.8 6.2.5 6.2.4 6.2.14 6.2.11 6.2.6 6.2.9 6.2.16 6.2.17 6.2.18 Label 110 111 130 076 136 247 112 103 273 125 260 Sig. Bits 20 20 17 20 15 15 15 15 19 19 19 Range ±180 Degrees ±180 Degrees 16 nm ±131,072 FT 1024 meters 1024 meters ±4096 Knots ±180 Degrees Discrete Wd Discrete Wd Discrete Wd Signal Type Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Resolution 0.00017166137695 0.00017166137695 0.00012207 0.125 0.03125 0.03125 0.125 0.0054931640625 n/a 0.1 min 1 day *Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 Notes: * Slowest acceptable update rate in milliseconds. ** This label is not required. Data used if present Table 5.3.3-253: Position Input Type 253 (Dual High Speed ARINC 743A GPS) CHANNEL 429RX_1 A = J2-37 B = J2-36 CHANNEL 429RX_3 CONNECT TO: IOC #1 (ARINC 743A-2) Format: ARINC 429 (High Speed) Fault Designation: IOC BUS 1 Bus Type: Basic Data Reference Latitude - Normal 6.2.7 Longitude - Normal 6.2.8 Latitude - Fine 6.2.59 Longitude – Fine 6.2.60 Vertical Velocity 6.2.58 GPS Hor. Int. Limit 6.2.5 Altitude 6.2.4 VFOM 6.2.13 HFOM 6.2.10 Ground Speed 6.2.6 True Track Angle 6.2.9 Sensor Status 6.2.16 **UTC 6.2.17 **Date 6.2.18 CONNECT TO: IOC #2 (ARINC 743A-2) Format: ARINC 429 (High Speed) Label 110 111 120 121 165 130 076 136 247 112 103 273 125 260 Data Latitude - Normal Longitude - Normal Latitude - Fine Longitude – Fine Vertical Velocity GPS Hor. Int. Limit Altitude VFOM HFOM Ground Speed True Track Angle Sensor Status **UTC **Date *Slowest acceptable update rate in milliseconds. **This label is not required. Data used if present A = J2-41 B = J2-40 Reference 6.2.7 6.2.8 6.2.59 6.2.60 6.2.58 6.2.5 6.2.4 6.2.13 6.2.10 6.2.6 6.2.9 6.2.16 6.2.17 6.2.18 Sig. Bits 20 20 11 11 15 17 20 18 18 15 15 19 19 19 Range ±180 Degrees ±180 Degrees ±0.000172 ±0.000172 ±32768 fpm 16 nm ±131,072 ft 32768 ft 16 nm ±4096 Knots ±180 Degrees Discrete Wd Discrete Wd Discrete Wd Signal Type Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Resolution 0.00017166137695 0.00017166137695 0.00000008381903 0.00000008381903 1 0.00012207 0.125 0.125 0.000061035 0.125 0.0054931640625 n/a 0.1 min 1 day *Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 Signal Type Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Resolution 0.00017166137695 0.00017166137695 0.00000008381903 0.00000008381903 1 0.00012207 0.125 0.125 0.000061035 0.125 0.0054931640625 n/a 0.1 min 1 day *Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 Fault Designation: IOC BUS 2 Bus Type: Basic Label 110 111 120 121 165 130 076 136 247 112 103 273 125 260 Sig. Bits 20 20 11 11 15 17 20 18 18 15 15 19 19 19 Range ±180 Degrees ±180 Degrees ±0.000172 ±0.000172 ±32768 fpm 16 nm ±131,072 ft 32768 ft 16 nm ±4096 Knots ±180 Degrees Discrete Wd Discrete Wd Discrete Wd Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 191 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.3-255: Position Input Type 255 (Dual High Speed ARINC 743A GPS) CHANNEL 429RX_4 A = J2-25 B = J2-8 CHANNEL 429RX_7 CONNECT TO: GPS #1 (ARINC 743A) Format: ARINC 429 (High Speed) Fault Designation: GPS BUS 1 Bus Type: Basic Data Reference Latitude - Normal 6.2.7 Longitude - Normal 6.2.8 GPS Hor. Int. Limit 6.2.5 Altitude 6.2.4 VFOM 6.2.13 HFOM 6.2.10 Ground Speed 6.2.6 True Track Angle 6.2.9 Sensor Status 6.2.16 **UTC 6.2.17 **Date 6.2.18 CONNECT TO: GPS #2 (ARINC 743A) Format: ARINC 429 (High Speed) Label 110 111 130 076 136 247 112 103 273 125 260 Sig. Bits 20 20 17 20 18 18 15 15 19 19 19 Range ±180 Degrees ±180 Degrees 16 nm ±131,072 FT 32768 ft 16 nm ±4096 Knots ±180 Degrees Discrete Wd Discrete Wd Discrete Wd Signal Type Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Resolution 0.00017166137695 0.00017166137695 0.00012207 0.125 0.125 0.000061035 0.125 0.0054931640625 n/a 0.1 min 1 day *Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 Fault Designation: GPS BUS 2 Bus Type: Basic Data Reference Label Sig. Bits Range Signal Type Resolution *Rate (ms) Latitude - Normal 6.2.7 110 20 ±180 Degrees Basic 0.00017166137695 1000 Longitude - Normal 6.2.8 111 20 ±180 Degrees Basic 0.00017166137695 1000 GPS Hor. Int. Limit 6.2.5 130 17 16 nm Basic 0.00012207 1000 * NOTE Altitude 6.2.4 076 20 ±131,072 FT Basic 0.125 1000 VFOM 6.2.13 136 18 32768 ft Basic 0.125 1000 HFOM 6.2.10 247 18 16 nm Basic 0.000061035 1000 Ground Speed 6.2.6 112 15 ±4096 Knots Basic 0.125 1000 True Track Angle 6.2.9 103 15 ±180 Degrees Basic 0.0054931640625 1000 Sensor Status 6.2.16 273 19 Discrete Wd Basic n/a 1000 **UTC 6.2.17 125 19 Discrete Wd Basic 0.1 min 1000 **Date 6.2.18 260 19 Discrete Wd Basic 1 day 1000 *Slowest acceptable update rate in milliseconds. **This label is not required. Data used if present NOTE: This configuration may not be selected if an AHRS configuration is required for Attitude and Heading information (refer to Category 10 type 1 and Category 11 type 1), due to the conflict with Channel 429 RX-7. A = J2-23 B = J2-6 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 192 Honeywell MK VI MK VIII EGPWS Installation Design Guide 5.3.4 Category 4, Altitude Callouts The following table provides identification of the Altitude Callouts Menu. Each entry in the ID column corresponds to a particular menu selection. The Altitude Callouts menu ID’s 0 through 12 consist of standard callouts. Selecting ID 0 – 12 will result in the callouts listed being enunciated. Smart 500 activation is reflected by a “500” callout being spoken at the end of the selected callout menu sequence in the Long Level 1 Self-Test. In addition, the Callout menu ID number and the “Smart Callout Selected” configuration message, will both be given during level 3 Self-Test and in the RS232 Present Status display. Table 5.3.4: Altitude Callouts ID MENU MINIMUMS-MINIMUMS, “Smart 500”, 200, 100, 50, 40, 30, 20 ,10 MINIMUMS-MINIMUMS, “Smart 500”, 200 MINIMUMS-MINIMUMS, “Smart 500”, 100, 50, 40, 30, 20 ,10 MINIMUMS-MINIMUMS, “Smart 500” MINIMUMS-MINIMUMS, 200, 100, 50, 40, 30, 20 ,10 MINIMUMS-MINIMUMS, 200 MINIMUMS-MINIMUMS, 100, 50, 40, 30, 20 ,10 (no callouts) 0 1 2 3 41 51 61 71 MINIMUMS-MINIMUMS 81 9 10 11 12 13 141 151 2 100 1012 MINIMUMS-MINIMUMS, 500, 200, 100, 50, 40, 30, 20 ,10 MINIMUMS-MINIMUMS, 500, 200 MINIMUMS-MINIMUMS, 500, 100, 50, 40, 30, 20 ,10 MINIMUMS-MINIMUMS, 500 MINIMUMS, 1000, 500, 400, 300, 200, 100, 50, 40, 30, 20, 10 MINIMUMS-MINIMUMS, 100 MINIMUMS-MINIMUMS, 200, 100 Above Field Callout “500” Above Field Callout “500 Above” Smart Callout Selected Software Effectivity True EGPWS MKVI MK VIII -020 X X True -020 X X True -020 X X True -020 X X False -020 X X False -020 X X False -020 X X False -020 X X False -020 X X False -020 X X False -020 X X False -020 X X False -020 X X False -020 X X False -020 X X False -020 X X False False -020 -020 X X X X 1 Compliance with TSO-C151a requires a "500" callout. These IDs cannot be used on installations requiring compliance with TSO-C151a unless there is an alternate source of the "500" callout. 2 This ID provides Above Field Callout. Geometric altitude and runway database are used to calculate the height above field. If this ID is selected TA&D and TCF must be enabled (MK VI and MK VIII installations cannot select Category 6 ID 2). Note: Selecting an Altitude Callout ID without a minimums callout can be accomplished by leaving the Decision Height (DH) input discrete open. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 193 Honeywell MK VI MK VIII EGPWS Installation Design Guide 5.3.5 Category 5, Audio Menu Select The Audio Menu Select option consists of sets of voices that are mapped to specific warning mode outputs. The Audio Menu tables list the alert/warning conditions in order of priority. The following table provides identification of the Audio Menu Type. Each entry in the Audio Menu Type column has a corresponding table that provides detailed information on the configuration. For example, the details for Audio Menu Type 0 are found in Table 5.3.5-0. Table 5.3.5: Audio Menu Type ID 0 1 2 3 Audio Menu Type (Table 5.3.5-x) 0 1 2 3 Description Basic (Caution Terrain TAD annunciation) Alternate (Terrain Ahead TAD annunciation) Basic (Caution Terrain TAD annunciation) for Fixed Gear aircraft Alternate (Terrain Ahead TAD annunciation) for Fixed Gear aircraft Software Effectivity -020 -020 -020 -020 Table 5.3.5-0: Audio Menu Type 0 (Basic) ALERT/WARNING CONDITION MODE 7 WINDSHEAR WARNING MODE 1 PULL UP MODE 2 PULL UP PREFACE MODE 2 PULL UP TERRAIN AWARENESS PREFACE TERRAIN AWARENESS WARNING OBSTACLE AWARENESS PREFACE OBSTACLE AWARENESS WARNING MODE 2 TERRAIN MODE 6 MINIMUMS TERRAIN AWARENESS CAUTION OBSTACLE AWARENESS CAUTION MODE 4 TOO LOW TERRAIN TCF TOO LOW TERRAIN MODE 6 ALTITUDE CALLOUTS MODE 4 TOO LOW GEAR MODE 4 TOO LOW FLAPS MODE 1 SINKRATE MODE 3 DON’T SINK MODE 5 GLIDESLOPE MODE 6 BANK ANGLE MODE 7 WINDSHEAR CAUTION AUDIO MENU (SIREN) WINDSHEAR-WINDSHEAR-WINDSHEAR PULL UP TERRAIN TERRAIN PULL UP TERRAIN TERRAIN PULL UP OBSTACLE OBSTACLE PULL UP TERRAIN SELECTED CALLOUTS CAUTION TERRAIN (PAUSE) CAUTION TERRAIN CAUTION OBSTACLE (PAUSE) CAUTION OBSTACLE TOO LOW TERRAIN TOO LOW TERRAIN SELECTED CALLOUTS TOO LOW GEAR TOO LOW FLAPS SINKRATE Note: The basic warning is “SINKRATE (PAUSE) SINKRATE”. However, if the Mode 1 Pullup curve is violated only a single “Sinkrate” may occur prior to the pull up voice. DON’T SINK (PAUSE) DON’T SINK GLIDESLOPE BANK ANGLE (PAUSE) BANK ANGLE, BANK ANGLE BANK ANGLE (QUIET) (or CAUTION WINDSHEAR if Caution voice Enabled) NOTES 6 1 1, 2 1 1, 2 1, 3 1, 2 1, 3 Note 1: These are the only voices that can interrupt. Note 2: The preface voices will always be given prior to the warning voice. Note 3: Voice message is continuous. Note 4: Voice message will repeat every 10 seconds. Note 5: Long Self-Test will only issue a single 'Sinkrate". Note 6: The Windshear Alerts will only be given on a MK VIII EGPWS with Windshear enabled per Category 12. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 194 4 4 5 6 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.5-1: Audio Menu Type 1 (Alternate) ALERT/WARNING CONDITION MODE 7 WINDSHEAR WARNING MODE 1 PULL UP MODE 2 PULL UP PREFACE MODE 2 PULL UP TERRAIN AWARENESS PREFACE TERRAIN AWARENESS WARNING OBSTACLE AWARENESS PREFACE OBSTACLE AWARENESS WARNING MODE 2 TERRAIN MODE 6 MINIMUMS TERRAIN AWARENESS CAUTION OBSTACLE AWARENESS CAUTION MODE 4 TOO LOW TERRAIN TCF TOO LOW TERRAIN MODE 6 ALTITUDE CALLOUTS MODE 4 TOO LOW GEAR MODE 4 TOO LOW FLAPS MODE 1 SINKRATE MODE 3 DON’T SINK MODE 5 GLIDESLOPE MODE 6 BANK ANGLE MODE 7 WINDSHEAR CAUTION AUDIO MENU NOTES (SIREN) WINDSHEAR-WINDSHEAR-WINDSHEAR 6 PULL UP 1 TERRAIN TERRAIN 1, 2 PULL UP 1 TERRAIN AHEAD 1, 2 PULL UP 1, 3 OBSTACLE AHEAD 1, 2 PULL UP 1, 3 TERRAIN SELECTED CALLOUTS TERRAIN AHEAD (PAUSE) TERRAIN AHEAD 4 OBSTACLE AHEAD (PAUSE) OBSTACLE AHEAD 4 TOO LOW TERRAIN TOO LOW TERRAIN SELECTED CALLOUTS TOO LOW GEAR TOO LOW FLAPS SINKRATE 5 Note: The basic warning is "SINKRATE (PAUSE) SINKRATE". However, if the Mode 1 Pullup curve is violated only a single "Sinkrate" may occur prior to the pull up voice. DON’T SINK (PAUSE) DON’T SINK GLIDESLOPE BANK ANGLE (PAUSE) BANK ANGLE, BANK ANGLE BANK ANGLE (Honeywell Algorithm at low altitudes) (QUIET) (or CAUTION WINDSHEAR if Caution voice Enabled) 6 Note 1: These are the only voices that can interrupt. Note 2: The preface voices will always be given prior to the warning voice. Note 3: Voice message is continuous. Note 4: Voice message will repeat every 10 seconds. Note 5: Long Self-Test will only issue a single 'Sinkrate". Note 6: The Windshear Alerts will only be given on a MK VIII EGPWS with Windshear enabled per Category 12. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 195 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.5-2: Audio Menu Type 2 (Basic for Fixed Gear Aircraft) ALERT/WARNING CONDITION MODE 7 WINDSHEAR WARNING MODE 1 PULL UP MODE 2 PULL UP PREFACE MODE 2 PULL UP TERRAIN AWARENESS PREFACE TERRAIN AWARENESS WARNING OBSTACLE AWARENESS PREFACE OBSTACLE AWARENESS WARNING MODE 2 TERRAIN MODE 6 MINIMUMS TERRAIN AWARENESS CAUTION OBSTACLE AWARENESS CAUTION MODE 4 TOO LOW TERRAIN TCF TOO LOW TERRAIN MODE 6 ALTITUDE CALLOUTS MODE 4 TOO LOW GEAR MODE 4 TOO LOW FLAPS MODE 1 SINKRATE MODE 3 DON’T SINK MODE 5 GLIDESLOPE MODE 6 BANK ANGLE MODE 7 WINDSHEAR CAUTION AUDIO MENU NOTES (SIREN) WINDSHEAR-WINDSHEAR-WINDSHEAR 6 PULL UP 1 TERRAIN TERRAIN 1, 2 PULL UP 1 TERRAIN TERRAIN 1, 2 PULL UP 1, 3 OBSTACLE OBSTACLE 1, 2 PULL UP 1, 3 TERRAIN SELECTED CALLOUTS CAUTION TERRAIN (PAUSE) CAUTION TERRAIN 4 CAUTION OBSTACLE (PAUSE) CAUTION OBSTACLE 4 TOO LOW TERRAIN TOO LOW TERRAIN SELECTED CALLOUTS TOO LOW FLAPS TOO LOW FLAPS SINKRATE 5 Note: The basic warning is “SINKRATE (PAUSE) SINKRATE”. However, if the Mode 1 Pullup curve is violated only a single “Sinkrate” may occur prior to the pull up voice. DON’T SINK (PAUSE) DON’T SINK GLIDESLOPE BANK ANGLE (PAUSE) BANK ANGLE, BANK ANGLE BANK ANGLE (Honeywell Algorithm at low altitudes) (QUIET) (or CAUTION WINDSHEAR if Caution voice Enabled) 6 Note 1: These are the only voices that can interrupt. Note 2: The preface voices will always be given prior to the warning voice. Note 3: Voice message is continuous. Note 4: Voice message will repeat every 10 seconds. Note 5: Long Self-Test will only issue a single 'Sinkrate". Note 6: The Windshear Alerts will only be given on a MK VIII EGPWS with Windshear enabled per Category 12. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 196 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.5-3: Audio Menu Type 3 (Alternate for Fixed Gear Aircraft) ALERT/WARNING CONDITION MODE 7 WINDSHEAR WARNING MODE 1 PULL UP MODE 2 PULL UP PREFACE MODE 2 PULL UP TERRAIN AWARENESS PREFACE TERRAIN AWARENESS WARNING OBSTACLE AWARENESS PREFACE OBSTACLE AWARENESS WARNING MODE 2 TERRAIN MODE 6 MINIMUMS TERRAIN AWARENESS CAUTION OBSTACLE AWARENESS CAUTION MODE 4 TOO LOW TERRAIN TCF TOO LOW TERRAIN MODE 6 ALTITUDE CALLOUTS MODE 4 TOO LOW GEAR MODE 4 TOO LOW FLAPS MODE 1 SINKRATE MODE 3 DON’T SINK MODE 5 GLIDESLOPE MODE 6 BANK ANGLE MODE 7 WINDSHEAR CAUTION AUDIO MENU NOTES (SIREN) WINDSHEAR-WINDSHEAR-WINDSHEAR 6 PULL UP 1 TERRAIN TERRAIN 1, 2 PULL UP 1 TERRAIN AHEAD 1, 2 PULL UP 1, 3 OBSTACLE AHEAD 1, 2 PULL UP 1, 3 TERRAIN SELECTED CALLOUTS TERRAIN AHEAD (PAUSE) TERRAIN AHEAD 4 OBSTACLE AHEAD (PAUSE) OBSTACLE AHEAD 4 TOO LOW TERRAIN TOO LOW TERRAIN SELECTED CALLOUTS TOO LOW FLAPS TOO LOW FLAPS SINKRATE 5 Note: The basic warning is "SINKRATE (PAUSE) SINKRATE". However, if the Mode 1 Pullup curve is violated only a single "Sinkrate" may occur prior to the pull up voice. DON’T SINK (PAUSE) DON’T SINK GLIDESLOPE BANK ANGLE (PAUSE) BANK ANGLE, BANK ANGLE BANK ANGLE (Honeywell Algorithm at low altitudes) (QUIET) (or CAUTION WINDSHEAR if Caution voice Enabled) 6 Note 1: These are the only voices that can interrupt. Note 2: The preface voices will always be given prior to the warning voice. Note 3: Voice message is continuous. Note 4: Voice message will repeat every 10 seconds. Note 5: Long Self-Test will only issue a single 'Sinkrate". Note 6: The Windshear Alerts will only be given on a MK VIII EGPWS with Windshear enabled per Category 12. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 197 Honeywell MK VI MK VIII EGPWS Installation Design Guide 5.3.6 Category 6, Terrain Display Select The following table (5.3.6) 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. The TA&D Pop Up Disable function is defined by a Boolean. The ID groups will completely identify a particular Terrain Display Interface. Table 5.3.6: Terrain Display Select ID Table 5.3.6.1 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 18 19 20 Software Effectivity Application Notes KC Picture Bus (KCPB) (Note 1) No Display (TAD and TCF Enabled) TAD / TCF Disabled Collins ProLine II (4x4) (Note 2) Honeywell/Bendix PPI-4A/4B with Auto Range (Note 3) Collins ProLine II (5x6) (Note 2) Collins ProLine II (5x4,5x5) (Note 2) Honeywell/Bendix IN182A/IN812A (RDR 2000, RDS 81/82) Honeywell/Bendix IN842A/IN862A (RDR 2100, RDS 84/86) Honeywell/Bendix EFIS 40/50 (non-Integrated) Honeywell/Bendix EFIS 40/50 (Integrated) (Note 6, 8) Collins WXI-701/711 PPI, with Auto Range Collins WXI-701/711 PPI, without Auto Range Honeywell P880/660/440, (Integrated) WXPD with SCI range Honeywell/Bendix PPI-4A/4B without Auto Range (Note 3) Honeywell P880/660/440, (Integrated) WXPD with SCI range, Aircraft symbol KC Picture Bus (KCPB) without presentation of Geometric Altitude (Note 1) KC Picture Bus (KCPB) with Digital Discrete Word (Note 1, 9) KC Picture Bus (KCPB) with Digital Discrete Word without presentation of Geometric Altitude (Note 1, 9) EGPWS MKVI MKVIII -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X -020 X X -020 -020 -020 -020 -020 N/A N/A N/A N/A N/A X X X X X -020 N/A X -020 N/A X -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 N/A N/A N/A N/A N/A N/A N/A N/A N/A N/A X X X X X X X X X X The following displays are only supported by the MK VIII 235 236 237 238 239 240 241 243 244 245 246 247 248 249 251 252 253 Collins ProLine 4 (non-Integrated) Collins ProLine 4 (Integrated) Honeywell Primus 1000 with binary Peaks Elevations and Cyan ASCII window text Honeywell Primus 1000 with binary Peaks Elevations Collins FPI-9XX (Integrated) with binary Peaks Collins ProLine 21 (Integrated) with overlay Peaks Elevation and Partial Compass Raster patch (Note 4) Collins ProLine 21 (Integrated) with binary Peaks Elevation and Full Compass Raster patch (Note 4) Honeywell EDZ802, EDZ603, EDZ803 (non-Integrated) with dual SCI range (Note 8) Honeywell EDZ806 (non-Integrated) with dual SCI range (Note 8) Honeywell EDZ806, (Integrated) with dual SCI range Honeywell/Bendix EFIS 10 (non-Integrated) (Note 7) Collins FDS-255/2000 (EGPWS controls selection) Honeywell Primus 1000 (Integrated) with overlay Peaks Elevation Honeywell Primus EPIC CDS/R with overlay Peaks Elevations Honeywell Primus EPIC CDS/R with binary Peaks Elevations Honeywell SPZ8000, EDZ605/805 with ARINC 429 range Collins FDS-255/2000 (Integrated) display controls selection Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 198 Honeywell MK VI MK VIII EGPWS Installation Design Guide ID Table 5.3.6.1 254 255 Software Effectivity Application Notes Collins ProLine 21 (Integrated) with binary Peaks Elevations and Partial Compass Raster patch (Note 4) Honeywell SPZ8000 (Integrated, older style) WXPD with SCI range (Note 5) EGPWS MKVI MKVIII -020 N/A X -020 N/A X Note 1: For a description of the KCPB features implemented in a particular software release, see Appendix B: KCPB Phased Implementation in the EGPWS Interface Methodology document 060-4303-000. Note 2: Refer to Rockwell Collins Service Information Letter, EFIS 84/85/86 SIL 2-99 Dated March 16/99 or later revision, for information describing the requirements to interface an EGPWS to the Collins Pro Line II system equipped with EFIS 84/85/86 Displays and WXR-350/840/700 or TWR-850 Weather Radar systems. This SIL provides guidance on the type and use of Collins WXA-1000 video converter, required for EGPWS installations where a WXR-350 radar is installed in the aircraft. Note 3: This configuration is applicable to RDR-4B with a mod that makes it capable of displaying blue. Note 4: This ID may only be used in conjunction with other IOC bus selections for categories 2,8,9,10,11 and 12. ID’s 240 and 254 can be selected for Pro Line 21 display configurations that provide a Partial Compass Raster patch (such as a Citation Jet). ID 241 can be selected for Pro Line 21 display configurations that provide a Full Compass Raster patch (such as a Challenger 300). Note 5: This interface only supports the SG-810 and SG-811 SPZ-8000. Note 6: SG-465 must have software level 01/14. Note 7: Requires Bendix (Honeywell) 80-series radar (i.e. RDS-86) Note 8: ID 10, 243, and 244 must have Category 7, Peaks Mode Enabled, option selected. Note 9: KCPB Digital Discrete Word supports softkey discretes for Flap Desense, Steep Approach, Glideslope Cancel and Self Test. In this category the following signals are configured by the ID number: Signal Name Signal Type KCPB* or ARINC Terrain Display Bus: ARINC 429 or RS-422 Range Bus: Boolean TA&D Alternate Pop Up *KCPB is also known as AlliedSignal Picture Bus (ASPB) Defined By Display Configuration Group Display Input Control Group Defined directly in Table Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 199 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-0 KC Picture Bus Display Configuration Group 0 Function Display Type Sweep Type Auto Pop Up Peaks Mode (Elevations via overlay) Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 CHANNEL 429_422RX_1 A = J2-37 B = J2-36 CHANNEL 429RX_3 A = J2-41 1 B = J2-40 Value KC Picture Bus (KCPB)2 Curtain (Vertical or Horizontal scan) Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On None (Display controls selection) None (Display controls selection) Controlled by display response (if selected a 10 NM range will be used) None Controlled by display KCPB Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data 4.2.13.2 7.2 CONNECT TO: Terrain Display data 4.2.13.2 7.2 Display Input Control Group 0 Fault Designation: KCPB BUS 1 Bus Type: Basic CONNECT TO: KCPB-IND Bus 1 out Format: ARINC 429 (Low Speed) Data Reference Range3 6.2.35 Query/Continuous Response 6.2.24 DSU Status Data (DSU only) 6.2.36 3 Key Press/Display Mode 6.2.25 CONNECT TO: KCPB-IND Bus 2 out Format: ARINC 429 (Low Speed) Label 271 011 350 012 Reference 6.2.35 6.2.24 6.2.36 6.2.25 Label 271 011 350 012 Data Range3 Query/Continuous Response DSU Status Data (DSU only) Key Press/Display Mode3 Channel Pins 429TX_1 (Low Speed) A = J2-43 B = J2-42 Sig. Bits 11 Discrete Discrete Discrete Range 0.5-1023.5NM N/A N/A N/A Signal Type Basic Basic Basic Basic Resolution 0.5 N/A N/A N/A Rate (ms) 250 1000 1000 250 Signal Type Basic Basic Basic Basic Resolution 0.5 N/A N/A N/A Rate (ms) 250 1000 1000 250 Fault Designation: KCPB BUS 2 Bus Type: Basic Sig. Bits 11 Discrete Discrete Discrete Range 0.5-1023.5NM N/A N/A N/A Output 429 Bus Group 0 Comments Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x , and 7.1.4.x Integration Notes: 1. When interfacing to a single display controller configuration the Display Input bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. 2. KCPB (Keyed Component Picture Bus) is also known as ASPB (AlliedSignal Picture Bus) 3. Label 012 is optional. The current fault and fault history message “RANGE” for label 271 (Range) is not shown if Range Keys are requested on label 012 (Key Press/Display Mode). 4. The Display group is configured by the Display using response labels on its ARINC 429 data bus. 5. KCPB bus types use “Inop & Warning Annunciations in same Window” therefore during EGPWS Self Test the Fail lights will not remain on throughout the test. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 200 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-1 No Display, TAD and TCF enabled No Table Table 5.3.6.1-2 No Display, TAD and TCF disabled No Table Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 201 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-3 Collins Pro-Line II, 4x4 Display Configuration Group 6 Function Display Type Sweep Type Auto Pop Up Value Collins Pro-Line II (4x4) Display Standard with +/-60 degree limit Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enabled: False Peaks Enabled: True Peaks Off Peaks On Anytime Anytime No No Yes, “TERR” located on the left side of display. Peaks Elevations located on the upper left side of Terrain image. ARINC 453 Peaks Mode (Elevations via overlay) Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 Display Input Control Group 1 CHANNEL 429_422RX_1 CONNECT TO: WX-IND Bus 1 out Format: ARINC 429 (Low Speed) Fault Designation: DISPLAY BUS 1 Bus Type: Basic A = J2-37 B = J2-36 CHANNEL 429RX_3 Reference Data Range (Display Word 2) 6.2.20 CONNECT TO: WX-IND Bus 2 out Format: ARINC 429 (Low Speed) Label 271 A = J2-41 1 B = J2-40 CONN PIN # J1-32 Data Range (Display Word 2) REFERENCE NAME GND_DISC_12 Label Sig. Bits Range 271 Discrete 5-320NM PIN FUNCTION Display Select Discrete #1 J1-31 GND_DISC_13 Reference 6.2.20 Reference 4.2.7 6.6.18 Reference 4.2.7 6.6.19 Sig. Bits Discrete Range 5-320NM Signal Type Basic Resolution N/A Rate (ms) 100 Fault Designation: DISPLAY BUS 2 Bus Type: Basic Display Select Discrete #2 Signal Type Resolution Rate (ms) Basic N/A 100 Polarity/Configuration Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 202 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-4 Honeywell/Bendix PPI-4A/4B with Auto Range Display Configuration Group 1 Function Display Type Sweep Type Auto Pop Up Value Bendix PPI-4A/4B (MAP-MODE) Standard Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On Anytime Anytime Yes 10NM No Without Peaks: “TERR” located in the lower right corner. With Peaks: Peaks numbers located in the lower right corner. ARINC 453 Peaks Mode (Elevations via overlay) Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 Display Input Control Group 1 CHANNEL 429_422RX_1 CONNECT TO: WX-IND Bus 1 out Format: ARINC 429 (Low Speed) Fault Designation: DISPLAY BUS 1 Bus Type: Basic A = J2-37 B = J2-36 CHANNEL 429RX_3 Reference Data Range (Display Word 2) 6.2.20 CONNECT TO: WX-IND Bus 2 out Format: ARINC 429 (Low Speed) Label 271 A = J2-41 1 B = J2-40 CONN PIN # J1-32 Data Range (Display Word 2) REFERENCE NAME GND_DISC_12 Label Sig. Bits Range 271 Discrete 5-320NM PIN FUNCTION Display Select Discrete #1 J1-31 GND_DISC_13 Reference 6.2.20 Reference 4.2.7 6.6.18 Reference 4.2.7 6.6.19 Sig. Bits Discrete Range 5-320NM Signal Type Basic Resolution N/A Rate (ms) 100 Fault Designation: DISPLAY BUS 2 Bus Type: Basic Display Select Discrete #2 Signal Type Resolution Rate (ms) Basic N/A 100 Polarity/Configuration Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. 2. Bendix PPI 4B with blue water capability required for Peaks display. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 203 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-5 Collins ProLine II, 5x6 Display Configuration Group 2 Function Display Type Sweep Type Auto Pop Up Value Collins ProLine II (5x6) Standard with +/-60 degree limit Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enabled: False Peaks Enabled: True Peaks Off Peaks On Anytime Anytime No No Yes, “TERR” or Peaks Elevations located on upper left side of Terrain image. ARINC 453 Peaks Mode Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 Display Input Control Group 1 CHANNEL 429_422RX_1 CONNECT TO: WX-IND Bus 1 out Format: ARINC 429 (Low Speed) Fault Designation: DISPLAY BUS 1 Bus Type: Basic A = J2-37 B = J2-36 CHANNEL 429RX_3 Reference Data Range (Display Word 2) 6.2.20 CONNECT TO: WX-IND Bus 2 out Format: ARINC 429 (Low Speed) Label 271 A = J2-41 1 B = J2-40 CONN PIN # J1-32 Data Range (Display Word 2) REFERENCE NAME GND_DISC_12 Label Sig. Bits Range 271 Discrete 5-320NM PIN FUNCTION Display Select Discrete #1 J1-31 GND_DISC_13 Reference 6.2.20 Reference 4.2.7 6.6.18 Reference 4.2.7 6.6.19 Sig. Bits Discrete Range 5-320NM Signal Type Basic Resolution N/A Rate (ms) 100 Fault Designation: DISPLAY BUS 2 Bus Type: Basic Display Select Discrete #2 Signal Type Resolution Rate (ms) Basic N/A 100 Polarity/Configuration Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 204 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-6 Collins ProLine II, 5x4, 5x5 Display Configuration Group 3 Function Display Type Sweep Type Auto Pop Up Value Collins ProLine II (5x4, 5x5) Standard with +/-60 degree limit Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enabled: False Peaks Enabled: True Peaks Off Peaks On Anytime Anytime No No Yes, “TERR” or Peaks Elevations located on upper left side of Terrain image. ARINC 453 Peaks Mode Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 Display Input Control Group 1 CHANNEL 429_422RX_1 CONNECT TO: WX-IND Bus 1 out Format: ARINC 429 (Low Speed) Fault Designation: DISPLAY BUS 1 Bus Type: Basic A = J2-37 B = J2-36 CHANNEL 429RX_3 Reference Data Range (Display Word 2) 6.2.20 CONNECT TO: WX-IND Bus 2 out Format: ARINC 429 (Low Speed) Label 271 A = J2-41 1 B = J2-40 CONN PIN # J1-32 Data Range (Display Word 2) REFERENCE NAME GND_DISC_12 Label Sig. Bits Range 271 Discrete 5-320NM PIN FUNCTION Display Select Discrete #1 J1-31 GND_DISC_13 Reference 6.2.20 Reference 4.2.7 6.6.18 Reference 4.2.7 6.6.19 Sig. Bits Discrete Range 5-320NM Signal Type Basic Resolution N/A Rate (ms) 100 Fault Designation: DISPLAY BUS 2 Bus Type: Basic Display Select Discrete #2 Signal Type Resolution Rate (ms) Basic N/A 100 Polarity/Configuration Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 205 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-7 Honeywell/Bendix IN182A/IN812A (RDR 2000, RDS 81/82) Display Configuration Group 4 Function Display Type Sweep Type Auto Pop Up Peaks Mode Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Value Bendix IN182A/IN812A color radar display RDR 2000 and RDS 81/82 radar systems Sweep range +/- 50 degrees Reference section Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up when the display is in the Never Pop Up proper mode. Category 7, Options Select Group #1 Peaks Enabled: False Peaks Enabled: True Peaks Off Peaks On Anytime WXR is on and display is in proper Mode Anytime No No Yes, “TERR” or Peaks Elevation located on upper right side of Terrain image. ARINC 453 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 Display Input Control Group 2 CHANNEL 429_422RX_1 A = J2-37 B = J2-36 CHANNEL 429RX_3 A = J2-41 1 B = J2-40 CONN PIN # J1-32 J1-31 CONNECT TO: WX-IND Bus 1 out Format: ARINC 429 (Low Speed) Fault Designation: DISPLAY BUS 1 Bus Type: Basic Data Reference Mode (Display Word 1) 6.2.26 Range (Display Word 2) 6.2.20 Discrete Word (Vertical Profile) 6.2.27 CONNECT TO: WX-IND Bus 2 out Format: ARINC 429 (Low Speed) Label 270 271 273 Data Reference Mode (Display Word 1) 6.2.26 Range (Display Word 2) 6.2.20 Discrete Word (Vertical Profile) 6.2.27 REFERENCE NAME GND_DISC_12 Reference 4.2.7 6.6.18 GND_DISC_13 Reference 4.2.7 6.6.19 Label Sig. Bits Range 270 Discrete Mode, Tilt, Gain 271 Discrete 5-320NM 273 Discrete VP Mode, Bit 11 PIN FUNCTION Display Select Discrete #1 Sig. Bits Discrete Discrete Discrete Range Mode, Tilt, Gain 5-320NM VP Mode, Bit 11 Signal Type Basic Basic Basic Resolution N/A N/A N/A Fault Designation: DISPLAY BUS 2 Bus Type: Basic Display Select Discrete #2 Signal Type Resolution Rate Basic N/A 100 ms Basic N/A 100 ms Basic N/A 100 ms Polarity/Configuration Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A Rate 100 ms 100 ms 100 ms DWG NO: 060-4314-150 REV: SHEET 206 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-8 Honeywell/Bendix IN842A/IN862A (RDR 2100, RDS 84/86) Display Configuration Group 5 Function Display Type Sweep Type Auto Pop Up Peaks Mode Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Value Bendix IN842A/IN862A color radar display RDR 2100 and RDS 84/86 radar systems Sweep range +/- 60 degrees Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up when display is in the Never Pop Up proper mode. Category 7, Options Select Group #1 Peaks Enabled: False Peaks Enabled: True Peaks Off Peaks On Anytime WXR is on and display is in proper Mode Anytime No No Yes, “TERR” or Peaks Elevation located on upper right side of Terrain image. ARINC 453 Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 Display Input Control Group 2 CHANNEL 429_422RX_1 A = J2-37 B = J2-36 CHANNEL 429RX_3 A = J2-41 1 B = J2-40 CONN PIN # J1-32 J1-31 CONNECT TO: WX-IND Bus 1 out Format: ARINC 429 (Low Speed) Fault Designation: DISPLAY BUS 1 Bus Type: Basic Data Reference Mode (Display Word 1) 6.2.26 Range (Display Word 2) 6.2.20 Discrete Word (Vertical Profile) 6.2.27 CONNECT TO: WX-IND Bus 2 out Format: ARINC 429 (Low Speed) Label 270 271 273 Data Reference Mode (Display Word 1) 6.2.26 Range (Display Word 2) 6.2.20 Discrete Word (Vertical Profile) 6.2.27 REFERENCE NAME GND_DISC_12 Reference 4.2.7 6.6.18 GND_DISC_13 Reference 4.2.7 6.6.19 Label Sig. Bits Range 270 Discrete Mode, Tilt, Gain 271 Discrete 5-320NM 273 Discrete VP Mode, Bit 11 PIN FUNCTION Display Select Discrete #1 Sig. Bits Discrete Discrete Discrete Range Mode, Tilt, Gain 5-320NM VP Mode, Bit 11 Signal Type Basic Basic Basic Resolution N/A N/A N/A Fault Designation: DISPLAY BUS 2 Bus Type: Basic Display Select Discrete #2 Signal Type Resolution Rate Basic N/A 100 ms Basic N/A 100 ms Basic N/A 100 ms Polarity/Configuration Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A Rate 100 ms 100 ms 100 ms DWG NO: 060-4314-150 REV: SHEET 207 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-9 Honeywell/Bendix EFIS 40/50 (Non-Integrated) Display Configuration Group 7 Function Display Type Sweep Type Auto Pop Up Peaks Mode (Elevations via overlay) Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Value Bendix EFIS 40/50 (Non-Integrated) Sweep range +/- 60 degrees Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up when display is in the Never Pop Up proper mode. Category 7, Options Select Group #1 Peaks Enabled: False Peaks Enabled: True Peaks Off Peaks On Anytime WXR is on and display is in proper Mode Anytime No No Yes, “TERR” at middle right of the display. Peaks Elevations located middle right of display. ARINC 453 Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 Display Input Control Group 2 CHANNEL 429_422RX_1 A = J2-37 B = J2-36 CHANNEL 429RX_3 A = J2-41 1 B = J2-40 CONN PIN # J1-32 J1-31 CONNECT TO: WX-IND Bus 1 out Format: ARINC 429 (Low Speed) Fault Designation: DISPLAY BUS 1 Bus Type: Basic Data Reference Mode (Display Word 1) 6.2.26 Range (Display Word 2) 6.2.20 Discrete Word (Vertical Profile) 6.2.27 CONNECT TO: WX-IND Bus 2 out Format: ARINC 429 (Low Speed) Label 270 271 273 Data Reference Mode (Display Word 1) 6.2.26 Range (Display Word 2) 6.2.20 Discrete Word (Vertical Profile) 6.2.27 REFERENCE NAME GND_DISC_12 Reference 4.2.7 6.6.18 GND_DISC_13 Reference 4.2.7 6.6.19 Label Sig. Bits Range 270 Discrete Mode, Tilt, Gain 271 Discrete 5-320NM 273 Discrete VP Mode, Bit 11 PIN FUNCTION Display Select Discrete #1 Sig. Bits Discrete Discrete Discrete Range Mode, Tilt, Gain 5-320NM VP Mode, Bit 11 Signal Type Basic Basic Basic Resolution N/A N/A N/A Fault Designation: DISPLAY BUS 2 Bus Type: Basic Display Select Discrete #2 Signal Type Resolution Rate Basic N/A 100 ms Basic N/A 100 ms Basic N/A 100 ms Polarity/Configuration Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A Rate 100 ms 100 ms 100 ms DWG NO: 060-4314-150 REV: SHEET 208 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-10 Honeywell/Bendix EFIS 40/50 (Integrated) Display Configuration Group 8 Function Display Type Sweep Type Auto Pop Up 2 Peaks Mode 1 Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Value Bendix EFIS 40/50 (Integrated) Sweep range +/- 90 degrees Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up on Caution or Warning. Never Pop Up Category 7, Options Select Group #1 Peaks Always Enabled (See Note 1) Anytime Anytime Yes 10 NM No No, the display supplies a “TERR” mode annunciation. ARINC 453 Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 Display Input Control Group 2 CHANNEL 429_422RX_1 A = J2-37 B = J2-36 CHANNEL 429RX_3 A = J2-41 3 B = J2-40 CONN PIN # J1-32 J1-31 CONNECT TO: WX-IND Bus 1 out Format: ARINC 429 (Low Speed) Fault Designation: DISPLAY BUS 1 Bus Type: Basic Data Reference Mode (Display Word 1) 6.2.26 Range (Display Word 2) 6.2.20 Discrete Word (Vertical Profile) 6.2.27 CONNECT TO: WX-IND Bus 2 out Format: ARINC 429 (Low Speed) Label 270 271 273 Data Reference Mode (Display Word 1) 6.2.26 Range (Display Word 2) 6.2.20 Discrete Word (Vertical Profile) 6.2.27 REFERENCE NAME GND_DISC_12 Reference 4.2.7 6.6.18 GND_DISC_13 Reference 4.2.7 6.6.19 Label Sig. Bits Range 270 Discrete Mode, Tilt, Gain 271 Discrete 5-320NM 273 Discrete VP Mode, Bit 11 PIN FUNCTION Display Select Discrete #1 Sig. Bits Discrete Discrete Discrete Range Mode, Tilt, Gain 5-320NM VP Mode, Bit 11 Signal Type Basic Basic Basic Resolution N/A N/A N/A Rate 100 ms 100 ms 100 ms Fault Designation: DISPLAY BUS 2 Bus Type: Basic Display Select Discrete #2 Signal Type Resolution Rate Basic N/A 100 ms Basic N/A 100 ms Basic N/A 100 ms Polarity/Configuration Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. 2. 3. 4. Peaks Elevations are transmitted digitally to the display via Label 025 on the ARINC 453 bus. They are then displayed as stroked characters on the bottom left or right of the display (depending on EFIS strapping). To Pop Up the Terrain display for a Terrain Caution or Warning it is necessary for the EFIS to receive two discrete signals from the EGPWS (one to indicate that the Terrain display is selected and one to indicate that selection was due to an alert). The EFIS needs to distinguish between manual selection and alert conditions so it will know when it should autorange. Both EFIS and EGPWS start to autorange on a Caution or Warning to minimize any latency problem displaying status during an alert. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. Software Level 14 required for integrated display and popup. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 209 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-11 Collins WXI-701/711 PPI, with Auto Range Display Configuration Group 9 Function Display Type Sweep Type Auto Pop Up Value Collins WXI-701/711 PPI Fan Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On Anytime Anytime Yes 10NM No Without Peaks: “TERR” located at the bottom left of display. With Peaks: Peaks numbers located at the bottom left of display. ARINC 453 Peaks Mode Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 Display Input Control Group 1 CHANNEL 429_422RX_1 CONNECT TO: WX-IND Bus 1 out Format: ARINC 429 (Low Speed) Fault Designation: DISPLAY BUS 1 Bus Type: Basic A = J2-37 B = J2-36 CHANNEL 429RX_3 Reference Data Range (Display Word 2) 6.2.20 CONNECT TO: WX-IND Bus 2 out Format: ARINC 429 (Low Speed) Label 271 A = J2-41 2 B = J2-40 CONN PIN # J1-32 Data Range (Display Word 2) REFERENCE NAME GND_DISC_12 Label Sig. Bits Range 271 Discrete 5-320NM PIN FUNCTION Display Select Discrete #1 J1-31 GND_DISC_13 Reference 6.2.20 Reference 4.2.7 6.6.18 Reference 4.2.7 6.6.19 Sig. Bits Discrete Range 5-320NM Signal Type Basic Resolution N/A Rate (ms) 100 Fault Designation: DISPLAY BUS 2 Bus Type: Basic Display Select Discrete #2 Signal Type Resolution Rate (ms) Basic N/A 100 Polarity/Configuration Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. Left/Right shift keys on the display are not to be used when displaying terrain. 2. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 210 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-12 Collins WXI-701/711 PPI, without Auto Range Display Configuration Group 10 Function Display Type Sweep Type Auto Pop Up Value Collins WXI-701/711 PPI Fan Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On Anytime Anytime No No Without Peaks: “TERR” located at the bottom left of display. With Peaks: Peaks numbers located at the bottom left of display. ARINC 453 Peaks Mode Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 Display Input Control Group 1 CHANNEL 429_422RX_1 CONNECT TO: WX-IND Bus 1 out Format: ARINC 429 (Low Speed) Fault Designation: DISPLAY BUS 1 Bus Type: Basic A = J2-37 B = J2-36 CHANNEL 429RX_3 Reference Data Range (Display Word 2) 6.2.20 CONNECT TO: WX-IND Bus 2 out Format: ARINC 429 (Low Speed) Label 271 A = J2-41 2 B = J2-40 CONN PIN # J1-32 Data Range (Display Word 2) REFERENCE NAME GND_DISC_12 Label Sig. Bits Range 271 Discrete 5-320NM PIN FUNCTION Display Select Discrete #1 J1-31 GND_DISC_13 Reference 6.2.20 Reference 4.2.7 6.6.18 Reference 4.2.7 6.6.19 Sig. Bits Discrete Range 5-320NM Signal Type Basic Resolution N/A Rate (ms) 100 Fault Designation: DISPLAY BUS 2 Bus Type: Basic Display Select Discrete #2 Signal Type Resolution Rate (ms) Basic N/A 100 Polarity/Configuration Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. Left/Right shift keys on the display are not to be used when displaying terrain. 2. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 211 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-13 Honeywell P880/660/440, WXPD with SCI range (Integrated) Display Configuration Group 11 Function Display Type Sweep Type Auto Pop Up Peaks Mode Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 Value Honeywell P880/660/440 radar displays (Integrated) Honeywell Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On Anytime Anytime No Yes (across bottom of display) Yes, for Peaks Elevations located at lower left of display Honeywell picture bus Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 CONNECT TO: Not supported for this display type Display Input Control Group 3 CHANNEL 429_422RX_1 CONNECT TO: SCI Bus 1 Format: RS-422 (12K baud) A = J2-36 B = J2-37 CHANNEL 429RX_3 Data Range (Mode/Range Word) CONNECT TO: CONN PIN # J1-32 No Connection REFERENCE NAME GND_DISC_12 Fault Designation: DISPLAY BUS 1 Bus Type: Basic Reference 6.5.1.1 Label 80 Sig. Bits 4 Discrete Range 2000NM Signal Type Basic Resolution N/A Rate (ms) 100 Fault Designation: Bus Type: Reference 4.2.7 6.6.18 PIN FUNCTION Display Select Discrete #1 Polarity/Configuration Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. Radar Indicator part number must end in –X1X. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 212 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-14 Honeywell/Bendix PPI-4A/4B without Auto Range Display Configuration Group 12 Function Display Type Sweep Type Auto Pop Up Value Bendix PPI-4A/4B (MAP-MODE) Standard Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On Anytime Anytime No No Without Peaks: “TERR” located in the lower right corner. With Peaks: Peaks numbers located in the lower right corner. ARINC 453 Peaks Mode (Elevations via overlay) Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 Display Input Control Group 1 CHANNEL 429_422RX_1 CONNECT TO: WX-IND Bus 1 out Format: ARINC 429 (Low Speed) Fault Designation: DISPLAY BUS 1 Bus Type: Basic A = J2-37 B = J2-36 CHANNEL 429RX_3 Reference Data Range (Display Word 2) 6.2.20 CONNECT TO: WX-IND Bus 2 out Format: ARINC 429 (Low Speed) Label 271 A = J2-41 1 B = J2-40 CONN PIN # J1-32 Data Range (Display Word 2) REFERENCE NAME GND_DISC_12 Label Sig. Bits Range 271 Discrete 5-320NM PIN FUNCTION Display Select Discrete #1 J1-31 GND_DISC_13 Reference 6.2.20 Reference 4.2.7 6.6.18 Reference 4.2.7 6.6.19 Sig. Bits Discrete Range 5-320NM Signal Type Basic Resolution N/A Rate (ms) 100 Fault Designation: DISPLAY BUS 2 Bus Type: Basic Display Select Discrete #2 Signal Type Resolution Rate (ms) Basic N/A 100 Polarity/Configuration Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. 2. Bendix PPI 4B with blue water capability required for Peaks display. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 213 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-15 Honeywell P880/660/440, (Integrated) WXPD with SCI range and A/C symbol Display Configuration Group 13 Function Display Type Sweep Type Auto Pop Up Peaks Mode Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 Value Honeywell P880/660/440 radar displays (Integrated) with A/C symbol Honeywell Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On Anytime Anytime No Yes (across bottom of display) Yes, for Peaks Elevations located lower left of the display Honeywell picture bus Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 CONNECT TO: Not supported for this display type Display Input Control Group 3 CHANNEL 429_422RX_1 CONNECT TO: SCI Bus 1 Format: RS-422 (12K baud) A = J2-36 B = J2-37 CHANNEL 429RX_3 Data Range (Mode/Range Word) CONNECT TO: CONN PIN # J1-32 No Connection REFERENCE NAME GND_DISC_12 Fault Designation: DISPLAY BUS 1 Bus Type: Basic Reference 6.5.1.1 Label 80 Sig. Bits 4 Discrete Range 2000NM Signal Type Basic Resolution N/A Rate (ms) 100 Fault Designation: Bus Type: Reference 4.2.7 6.6.18 PIN FUNCTION Display Select Discrete #1 Polarity/Configuration Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. Radar Indicator part number must end in -X1X. 2. This display type overlays an inverted T aircraft symbol. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 214 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-18 KC Picture Bus without presentation of Geometric Altitude Display Configuration Group 17 Function Display Type Sweep Type Auto Pop Up Peaks Mode (Elevations via overlay) Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 CHANNEL 429_422RX_1 A = J2-37 B = J2-36 CHANNEL 429RX_3 A = J2-41 B = J2-40 Value KC Picture Bus (KCPB)2 Curtain (Vertical or Horizontal scan) Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On None (Display controls selection) None (Display controls selection) Controlled by display response (if selected a 10 NM range will be used) None Controlled by display KCPB Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data 4.2.13.2 7.2 CONNECT TO: Terrain Display data 4.2.13.2 7.2 Display Input Control Group 0 Fault Designation: KCPB BUS 1 Bus Type: Basic CONNECT TO: KCPB-IND Bus 1 out Format: ARINC 429 (Low Speed) Data Reference *Range 6.2.35 Query/Continuous Response 6.2.24 DSU Status Data (DSU only) 6.2.36 *Key Press/Display Mode 6.2.25 CONNECT TO: KCPB-IND Bus 2 out Format: ARINC 429 (Low Speed) Label 271 011 350 012 Data *Range Query/Continuous Response DSU Status Data (DSU only) *Key Press/Display Mode Label 271 011 350 012 Channel Pins 429TX_1 (Low Speed) A = J2-43 B = J2-42 Reference 6.2.35 6.2.24 6.2.36 6.2.25 Sig. Bits 11 Discrete Discrete Discrete Range 0.5-1023.5NM N/A N/A N/A Signal Type Basic Basic Basic Basic Resolution 0.5 N/A N/A N/A Rate (ms) 250 1000 1000 250 Signal Type Basic Basic Basic Basic Resolution 0.5 N/A N/A N/A Rate (ms) 250 1000 1000 250 Fault Designation: KCPB BUS 2 Bus Type: Basic Sig. Bits 11 Discrete Discrete Discrete Range 0.5-1023.5NM N/A N/A N/A Output 429 Bus Group 0 Comments Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x , and 7.1.4.x 429TX_2 No Connection (No Data Output) Integration Notes: 1. When interfacing to a single display controller configuration the Display Input bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. 2. KCPB (Keyed Component Picture Bus) is also known as ASPB (AlliedSignal Picture Bus) 3. Label 012 is optional. The current fault and fault history message “RANGE” for label 271 (Range) is not shown if Range Keys are requested on label 012 (Key Press/Display Mode). 4. The Display group is configured by the Display using response labels on its ARINC 429 data bus. 5. KCPB bus types use “Inop & Warning Annunciations in same Window” therefore during EGPWS Self Test the Fail lights will not remain on throughout the test. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 215 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-19 KC Picture Bus with Soft Keys Display Configuration Group 0 Function Display Type Sweep Type Auto Pop Up Peaks Mode (Elevations via overlay) Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 CHANNEL 429_422RX_1 A = J2-37 B = J2-36 CHANNEL 429RX_3 A = J2-41 1 B = J2-40 Value KC Picture Bus (KCPB)2 Curtain (Vertical or Horizontal scan) Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On None (Display controls selection) None (Display controls selection) Controlled by display response (if selected a 10 NM range will be used) None Controlled by display KCPB Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data 4.2.13.2 7.2 CONNECT TO: Terrain Display data 4.2.13.2 7.2 Display Input Control Group 4 Fault Designation: KCPB BUS 1 Bus Type: Basic CONNECT TO: KCPB-IND Bus 1 out Format: ARINC 429 (Low Speed) Data Reference Range3 6.2.35 Query/Continuous Response 6.2.24 DSU Status Data (DSU only) 6.2.36 3 Key Press/Display Mode 6.2.25 Discrete Word 6.2.55 CONNECT TO: KCPB-IND Bus 2 out Format: ARINC 429 (Low Speed) Label 271 011 350 012 017 Data Range3 Query/Continuous Response DSU Status Data (DSU only) Key Press/Display Mode3 Discrete Word Label 271 011 350 012 017 Channel Pins 429TX_1 (Low Speed) A = J2-43 B = J2-42 Reference 6.2.35 6.2.24 6.2.36 6.2.25 6.2.55 Sig. Bits 11 Discrete Discrete Discrete Discrete Range 0.5-1023.5NM N/A N/A N/A N/A Signal Type Basic Basic Basic Basic Basic Resolution 0.5 N/A N/A N/A N/A Rate (ms) 250 1000 1000 250 200 Signal Type Basic Basic Basic Basic Basic Resolution 0.5 N/A N/A N/A N/A Rate (ms) 250 1000 1000 250 200 Fault Designation: KCPB BUS 2 Bus Type: Basic Sig. Bits 11 Discrete Discrete Discrete Discrete Range 0.5-1023.5NM N/A N/A N/A N/A Output 429 Bus Group 0 Comments Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x , and 7.1.4.x Integration Notes: 1. When interfacing to a single display controller configuration the Display Input bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. 2. KCPB (Keyed Component Picture Bus) is also known as ASPB (AlliedSignal Picture Bus) 3. Label 012 is optional. The current fault and fault history message “RANGE” for label 271 (Range) is not shown if Range Keys are requested on label 012 (Key Press/Display Mode). 4. The Display group is configured by the Display using response labels on its ARINC 429 data bus. 5. KCPB bus types use “Inop & Warning Annunciations in same Window” therefore during EGPWS Self Test the Fail lights will not remain on throughout the test. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 216 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-20 KC Picture Bus without presentation of Geometric Altitude Display Configuration Group 17 Function Display Type Sweep Type Auto Pop Up Peaks Mode (Elevations via overlay) Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 CHANNEL 429_422RX_1 A = J2-37 B = J2-36 CHANNEL 429RX_3 A = J2-41 1 B = J2-40 Value KC Picture Bus (KCPB)2 Curtain (Vertical or Horizontal scan) Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On None (Display controls selection) None (Display controls selection) Controlled by display response (if selected a 10 NM range will be used) None Controlled by display KCPB Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data 4.2.13.2 7.2 CONNECT TO: Terrain Display data 4.2.13.2 7.2 Display Input Control Group 4 Fault Designation: KCPB BUS 1 Bus Type: Basic CONNECT TO: KCPB-IND Bus 1 out Format: ARINC 429 (Low Speed) Data Reference Range3 6.2.35 Query/Continuous Response 6.2.24 DSU Status Data (DSU only) 6.2.36 3 Key Press/Display Mode 6.2.25 Discrete Word 6.2.55 CONNECT TO: KCPB-IND Bus 2 out Format: ARINC 429 (Low Speed) Label 271 011 350 012 017 Data Range3 Query/Continuous Response DSU Status Data (DSU only) Key Press/Display Mode3 Discrete Word Label 271 011 350 012 017 Channel Pins 429TX_1 (Low Speed) A = J2-43 B = J2-42 Reference 6.2.35 6.2.24 6.2.36 6.2.25 6.2.55 Sig. Bits 11 Discrete Discrete Discrete Discrete Range 0.5-1023.5NM N/A N/A N/A N/A Signal Type Basic Basic Basic Basic Basic Resolution 0.5 N/A N/A N/A N/A Rate (ms) 250 1000 1000 250 200 Signal Type Basic Basic Basic Basic Basic Resolution 0.5 N/A N/A N/A N/A Rate (ms) 250 1000 1000 250 200 Fault Designation: KCPB BUS 2 Bus Type: Basic Sig. Bits 11 Discrete Discrete Discrete Discrete Range 0.5-1023.5NM N/A N/A N/A N/A Output 429 Bus Group 0 Comments Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x , and 7.1.4.x Integration Notes: 1. When interfacing to a single display controller configuration the Display Input bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. 2. KCPB (Keyed Component Picture Bus) is also known as ASPB (AlliedSignal Picture Bus) 3. Label 012 is optional. The current fault and fault history message “RANGE” for label 271 (Range) is not shown if Range Keys are requested on label 012 (Key Press/Display Mode). 4. The Display group is configured by the Display using response labels on its ARINC 429 data bus. KCPB bus types use “Inop & Warning Annunciations in same Window” therefore during EGPWS Self Test the Fail lights will not remain on throughout the test. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 217 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-235 Collins ProLine 4 (Non-Integrated) Display Configuration Group 2 Function Display Type Sweep Type Auto Pop Up Value Collins ProLine 4 Standard with +/-60 degree limit Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enabled: False Peaks Enabled: True Peaks Off Peaks On Anytime Anytime No No Yes, “TERR” or Peaks Elevations located on upper left side of Terrain image. ARINC 453 Peaks Mode Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 Display Input Control Group 244 CHANNEL 429_422RX_1 CONNECT TO: IOC #1 Bus Format: ARINC 429 (High Speed) Fault Designation: IOC BUS 1 Bus Type: Basic A = J2-37 B = J2-36 CHANNEL 429RX_3 Reference Data Range (Mode/Range Word) 6.2.21 CONNECT TO: IOC #2 Bus Format: ARINC 429 (High Speed) Label 155 A = J2-41 1 B = J2-40 CONN PIN # J1-32 Data Range (Mode/Range Word) REFERENCE NAME GND_DISC_12 Label Sig. Bits Range 155 Discrete 5-640NM PIN FUNCTION Display Select Discrete #1 J1-31 GND_DISC_13 Reference 6.2.21 Reference 4.2.7 6.6.18 Reference 4.2.7 6.6.19 Sig. Bits Discrete Range 5-640NM Signal Type Basic Resolution N/A Rate (ms) 50 Fault Designation: IOC BUS 2 Bus Type: Basic Display Select Discrete #2 Signal Type Resolution Rate (ms) Basic N/A 50 Polarity/Configuration Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 218 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-236 Collins ProLine 4 (Integrated) Display Configuration Group 241 Function Display Type Sweep Type Auto Pop Up Peaks Mode Manual select Manual deselect Auto Range Moving Marker Overlay Page Display Priority Display bus type Terrain Mode Annunciation DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Value Collins ProLine 4 Fan Mode with +/-60 degree limit Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up controlled by display Pop Up controlled by display Category 7, Options Select Group #1 Peaks Enabled: False Peaks Enabled: True Peaks Off Peaks On Selection is controlled by display Deselection is controlled by display Yes (10 NM) controlled by display No Yes, “TERR” or Peaks Elevations located on upper left side of Terrain image. Peaks does not support sea level “blue water” Standard ARINC compatible format – Collins ProLine 4 (label 077) Standard Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 Display Input Control Group 244 CHANNEL 429_422RX_1 CONNECT TO: IOC #1 Bus Format: ARINC 429 (High Speed) Fault Designation: IOC BUS 1 Bus Type: Basic A = J2-37 B = J2-36 CHANNEL 429RX_3 Reference Data Range (Mode/Range Word) 6.2.21 CONNECT TO: IOC #2 Bus Format: ARINC 429 (High Speed) Label 155 A = J2-41 1 B = J2-40 Data Range (Mode/Range Word) Label 155 Reference 6.2.21 Sig. Bits Discrete Range 5-640NM Signal Type Basic Resolution N/A Rate (ms) 50 Signal Type Basic Resolution N/A Rate (ms) 50 Fault Designation: IOC BUS 2 Bus Type: Basic Sig. Bits Discrete Range 5-640NM Output 429 Bus Group 1 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, 7.1.4.x, and 7.1.5.x 429TX_2 (Low Speed) A = J2-26 B = J2-9 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, 7.1.4.x, and 7.1.5.x Integration Notes: When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 219 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-237 Honeywell Primus 1000 with binary Peaks Elevations and Cyan ASCII window text MK VIII Only Display Configuration Group 242 Function Display Type Sweep Type Auto Pop Up 3 Peaks Mode Manual select Manual deselect Binary Peaks Elevations Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1/#2 453TX_1 A = J1-58 B = J1-59 Value Honeywell Primus 1000 with binary Peaks Elevations Honeywell Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On Selection is controlled by display Deselection is controlled by display Yes - Data passed by ARINC 429, Labels 011 and 012 Yes 10NM Yes (Honeywell type) Yes, for Peaks Elevations only (located middle right side of display) Honeywell picture bus Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 Display Input Control Group 248 CHANNEL 429_422RX_1 CONNECT TO: IC600 #1 FDR Bus Format: ARINC 429 (High Speed) Fault Designation: FDR BUS 1 Bus Type: Basic A = J2-37 B = J2-36 Reference Data Range 6.2.23 Discrete Word 6.2.28 CONNECT TO: IC600 #2 FDR Bus Format: ARINC 429 (High Speed) Label 050 275 Reference 6.2.23 6.2.28 Label 050 275 CHANNEL 429RX_3 A = J2-41 B = J2-40 Data Range Discrete Word Sig. Bits Bits 11-14 Bit 17 Range 2000NM Discrete Signal Type Basic Basic Resolution N/A N/A Rate (ms) 100 max 500 Signal Type Basic Basic Resolution N/A N/A Rate (ms) 100 max 500 Fault Designation: FDR BUS 2 Bus Type: Basic Sig. Bits Bits 11-14 Bit 17 Range 2000NM Discrete Output 429 Bus Group 0 Channel Pins 429TX_1 (Low Speed) A = J2-43 B = J2-42 Comments Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, 7.1.4.x, and 7.1.6.x 429TX_2 No Connection (No Data Output) Integration Notes: 1. The EGPWS ARINC 429 Output Bus must be connected to the display. 2. Display channels 1 and 2 are multiplexed on ARINC 453 Bus 1. 3. The Terrain display will Pop-Up in response to EGPWS label 274, bit 28 (Left display) and bit 29 (right display). 4. The system has only one range for terrain display on MFD, therefore the range to use depends on the value of label 275, bit 17. 5. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. 6. This configuration will cause the GPWS INOP, TERRAIN INOP, and WINDSHEAR INOP lamps to turn on only at the beginning of the EGPWS Self Test. 7. At the time of this printing this configuration is not supported by Primus 1000 hardware (prior to installation contact Honeywell EGPWS group for applicability). Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 220 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-238 Honeywell Primus 1000 with binary Peaks Elevations MK VIII Only Display Configuration Group 243 Function Display Type Sweep Type Auto Pop Up Peaks Mode Manual select Manual deselect Binary Peaks Elevations Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1/#2 453TX_1 A = J1-58 B = J1-59 Value Honeywell Primus 1000 with binary Peaks Elevations Honeywell Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On Selection is controlled by display Deselection is controlled by display Yes - Data passed by ARINC 429, Labels 011 and 012 Yes 10NM Yes (Honeywell type) Yes, for Peaks Elevations only (located middle right side of display) Honeywell picture bus Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 Display Input Control Group 248 CHANNEL 429_422RX_1 CONNECT TO: IC600 #1 FDR Bus Format: ARINC 429 (High Speed) Fault Designation: FDR BUS 1 Bus Type: Basic A = J2-37 B = J2-36 Reference Data Range 6.2.23 Discrete Word 6.2.28 CONNECT TO: IC600 #2 FDR Bus Format: ARINC 429 (High Speed) Label 050 275 Reference 6.2.23 6.2.28 Label 050 275 CHANNEL 429RX_3 A = J2-41 B = J2-40 Data Range Discrete Word Sig. Bits Bits 11-14 Bit 17 Range 2000NM Discrete Signal Type Basic Basic Resolution N/A N/A Rate (ms) 100 500 Signal Type Basic Basic Resolution N/A N/A Rate (ms) 100 500 Fault Designation: FDR BUS 2 Bus Type: Basic Sig. Bits Bits 11-14 Bit 17 Range 2000NM Discrete Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, 7.1.4.x, and 7.1.6.x Integration Notes: 1. The EGPWS ARINC 429 Output Bus must be connected to the display. 2. Display channels 1 and 2 are multiplexed on ARINC 453 Bus 1. 3. The Terrain display will Pop-Up in response to EGPWS label 274, bit 28 (Left display) and bit 29 (right display). 4. The system has only one range for terrain display on MFD, therefore the range to use depends on the value of label 275, bit 17. 5. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. 6. This configuration will cause the GPWS INOP, TERRAIN INOP, and WINDSHEAR INOP lamps to turn on only at the beginning of the EGPWS Self Test. 7. At the time of this printing this configuration is not supported by Primus 1000 hardware (prior to installation contact Honeywell EGPWS group for applicability). Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 221 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-239 Collins FPI-9XX (Integrated) with binary Peaks MK VIII Only Display Configuration Group 244 Function Display Type Sweep Type Auto Pop Up Peaks Mode Binary Peaks Elevations Manual Select Manual Deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Value Collins FPI-9xx with binary Peaks Elevations Fan Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Category 7 does not affect pop up logic. The display controls pop up, therefore enable/disable of pop up is done via the display. Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On Yes - Data passed by ARINC 429, Labels 011 and 012 Selection is controlled by display Deselection is controlled by display Yes (10 NM) controlled by display No No ARINC 453 Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator #1 4.2.13.2 7.2 CONNECT TO: Terrain Display data to switching relay/Symbol Generator #2 4.2.13.2 7.2 Display Input Control Group 253 CHANNEL 429_422RX_1 CONNECT TO: WX-IND Bus 1 out Format: ARINC 429 (Low Speed) Fault Designation: DISPLAY BUS 1 Bus Type: Basic A = J2-37 B = J2-36 CHANNEL 429RX_3 Reference Data Range 6.2.20 CONNECT TO: WX-IND Bus 2 out Format: ARINC 429 (Low Speed) Label 273 A = J2-41 B = J2-40 Data Range Reference 6.2.20 Label 273 Sig. Bits N/A Range 5-320NM Signal Type Basic Resolution N/A Rate (ms) 100 Resolution N/A Rate (ms) 100 Fault Designation: DISPLAY BUS 2 Bus Type: Basic Sig. Bits N/A Range 5-320NM Signal Type Basic Output 429 Bus Group 1 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, 7.1.4.x, 7.1.5.x and 7.1.6.x 429TX_2 (Low Speed) A = J2-26 B = J2-9 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, 7.1.4.x, 7.1.5.x and 7.1.6.x Integration Notes: 1. The EGPWS ARINC 429 Output Bus must be connected to the display. 2. The FPI-9xx, when not selected, will command the display range to 10 NM and “Pop Up” to Terrain mode if there is a Terrain alert. The range does not change if Terrain Mode is already selected when there is a Terrain Alert. 3. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 222 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-240 Collins Pro Line 21 (Integrated) with overlay Peaks Elevations MK VIII Only Display Configuration Group 245 Function Display Type Sweep Type Auto Pop Up Peaks Mode Manual Select Manual Deselect Auto Range Moving Marker Overlay Page Display bus type Terrain Mode Annunciation DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Value Collins ProLine 21 Integrated, with overlay peaks elevations and partial compass raster patch Fan Mode with +/- 90 degree limit Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Category 7 does not affect pop up logic. The display controls pop up, therefore enable/disable of pop up is done via the display. Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On Selection is controlled by display Deselection is controlled by display Yes (10 NM) controlled by display No Yes, for Peaks Elevations only (located upper right side of display) ARINC Compatible Format – Collins ProLine 21 (label 077) ProLine 21 system outputs Terrain Mode annunciation, it does not use EGPWS ASCII message. Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to Primary Flight Display/Multi Function display #1 4.2.13.2 7.2 CONNECT TO: Terrain Display data to Primary Flight Display/Multi Function display #2 4.2.13.2 7.2 Display Input Control Group 254 CHANNEL 429RX_1 CONNECT TO: IOC #1 Bus Format: ARINC 429 (High Speed) Fault Designation: IOC BUS 1 Bus Type: Basic A = J2-37 B = J2-36 CHANNEL 429RX_3 Reference Data Range (Mode/Range Word) 6.2.21 CONNECT TO: IOC #2 Bus Format: ARINC 429 (High Speed) Label 176 A = J2-41 B = J2-40 Data Range (Mode/Range Word) Reference 6.2.21 Label 176 Sig. Bits Discrete Range 5-640NM Signal Type Basic Resolution N/A Rate (ms) 50 Signal Type Basic Resolution N/A Rate (ms) 50 Fault Designation: IOC BUS 2 Bus Type: Basic Sig. Bits Discrete Range 5-640NM Output 429 Bus Group 1 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, 7.1.4.x, and 7.1.6.x 429TX_2 (Low Speed) A = J2-26 B = J2-9 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, 7.1.4.x, and 7.1.6.x Integration Notes: 1. The EGPWS ARINC 429 Output Bus must be connected to the display. 2. The Terrain Display will Pop-Up in response to EGPWS label 274, bit 28 (left display) and bit 29 (right display). 3. This configuration will cause the GPWS INOP, TERRAIN INOP, and WINDSHEAR INOP lamps to turn on only at the beginning of the EGPWS Self Test. 4. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 223 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-241 Collins Pro Line 21 (Integrated) with binary Peaks Elevations and Full Compass Raster Patch MK VIII Only Display Configuration Group 247 Function Display Type Sweep Type Auto Pop Up Peaks Mode Binary Peaks Elevations Manual Select Manual Deselect Auto Range Moving Marker Overlay Page Display bus type Terrain Mode Annunciation DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Value Collins ProLine 21 Integrated, with binary peaks elevations and full compass raster patch Fan Mode with +/- 90 degree limit Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Category 7 does not affect pop up logic. The display controls pop up, therefore enable/disable of pop up is done via the display. Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On Yes - Data passed by ARINC 429, Labels 011 and 012 Selection is controlled by display Deselection is controlled by display Yes (10 NM) controlled by display No No ARINC Compatible Format – Collins ProLine 21 (label 077) ProLine 21 system outputs Terrain Mode annunciation, it does not use EGPWS ASCII message. Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to Primary Flight Display/Multi Function display #1 4.2.13.2 7.2 CONNECT TO: Terrain Display data to Primary Flight Display/Multi Function display #2 4.2.13.2 7.2 Display Input Control Group 254 CHANNEL 429RX_1 CONNECT TO: IOC #1 Bus Format: ARINC 429 (High Speed) Fault Designation: IOC BUS 1 Bus Type: Basic A = J2-37 B = J2-36 CHANNEL 429RX_3 Reference Data Range (Mode/Range Word) 6.2.21 CONNECT TO: IOC #2 Bus Format: ARINC 429 (High Speed) Label 176 A = J2-41 B = J2-40 Data Range (Mode/Range Word) Reference 6.2.21 Label 176 Sig. Bits Discrete Range 5-640NM Signal Type Basic Resolution N/A Rate (ms) 50 Signal Type Basic Resolution N/A Rate (ms) 50 Fault Designation: IOC BUS 2 Bus Type: Basic Sig. Bits Discrete Range 5-640NM Output 429 Bus Group 1 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, 7.1.4.x, 7.1.5.x and 7.1.6.x 429TX_2 (Low Speed) A = J2-26 B = J2-9 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, 7.1.4.x, 7.1.5.x and 7.1.6.x Integration Notes: 1. The EGPWS ARINC 429 Output Bus must be connected to the display. 2. The Terrain Display will Pop-Up in response to EGPWS label 274, bit 28 (left display) and bit 29 (right display). 3. This configuration will cause the GPWS INOP, TERRAIN INOP, and WINDSHEAR INOP lamps to turn on only at the beginning of the EGPWS Self Test. 4. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 224 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-243 Honeywell EDZ802, EDZ603, EDZ803 (non-Integrated) with dual SCI range MK VIII Only Display Configuration Group 238 Function Display Type Sweep Type Auto Pop Up Value Honeywell (Non-Integrated) EDZ802, EDZ603, EDZ803 Honeywell Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On Anytime except when display is in GMAP or Sector Scan mode Anytime No Yes – a magenta underline will be alternately placed and removed under the Peaks Elevations Yes for Peaks Elevations (located near the vertical center on the right edge of the Terrain image) Honeywell picture bus Peaks Mode (Elevations via overlay) Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator #1 and MFD left channel 4.2.13.2 7.2 CONNECT TO: Terrain Display data to switching relay/Symbol Generator #2 and MFD right channel 4.2.13.2 7.2 Display Input Control Group 249 CHANNEL 429_422RX_1 CONNECT TO: SCI Bus 1 Format: RS-422 (12.0K baud) A = J2-36 B = J2-37 Data Range (Mode/Range word) Status CONNECT TO: SCI Bus 2 Format: RS-422 (12.0K baud) Reference 6.5.1.1 6.5.1.2 Reference 6.5.1.1 6.5.1.2 CONN PIN # J1-32 Data Range (Mode/Range word) Status REFERENCE NAME GND_DISC_12 J1-31 GND_DISC_13 CHANNEL 429RX_3 A = J2-10 B = J2-11 Fault Designation: DISPLAY BUS 1 Bus Type: Basic Label 80 FF Sig. Bits 4 discrete Discrete Range 2000NM N/A Signal Type Basic Basic Resolution N/A N/A Rate (ms) 100 100 Fault Designation: DISPLAY BUS 2 Bus Type: Basic Reference 4.2.7 6.6.18 Reference 4.2.7 6.6.19 Label Sig. Bits Range 80 4 discrete 2000NM FF Discrete N/A PIN FUNCTION Display Select Discrete #1 Display Select Discrete #2 Signal Type Resolution Rate (ms) Basic N/A 100 Basic N/A 100 Polarity/Configuration Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. The display does not use EGPWS ARINC 429 Output Bus. 2. The display color palette is not compatible with Terrain in the GMAP mode. Peaks Elevations are outside of the scan area in Sector Scan mode. Terrain will not be allowed to display in these modes. 3. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 225 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-244 Honeywell EDZ806 (non-Integrated) with dual SCI range MK VIII Only Display Configuration Group 239 Function Display Type Sweep Type Auto Pop Up Value Honeywell (Non-Integrated) EDZ806 Honeywell Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On Anytime except when display is in GMAP or Sector Scan mode Anytime No Yes – a magenta underline will be alternately placed and removed under the Peaks Elevations Yes for Peaks Elevations (located near the vertical center on the right edge of the Terrain image) Honeywell picture bus Peaks Mode (Elevations via overlay) Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator #1 4.2.13.2 7.2 CONNECT TO: Terrain Display data to switching relay/Symbol Generator #2 4.2.13.2 7.2 Display Input Control Group 249 CHANNEL 429_422RX_1 CONNECT TO: SCI Bus 1 Format: RS-422 (12.0K baud) A = J2-36 B = J2-37 Data Range (Mode/Range word) Status CONNECT TO: SCI Bus 2 Format: RS-422 (12.0K baud) Reference 6.5.1.1 6.5.1.2 Reference 6.5.1.1 6.5.1.2 CONN PIN # J1-32 Data Range (Mode/Range word) Status REFERENCE NAME GND_DISC_12 J1-31 GND_DISC_13 CHANNEL 429RX_3 A = J2-10 B = J2-11 Fault Designation: DISPLAY BUS 1 Bus Type: Basic Label 80 FF Sig. Bits 4 discrete Discrete Range 2000NM N/A Signal Type Basic Basic Resolution N/A N/A Rate (ms) 100 100 Fault Designation: DISPLAY BUS 2 Bus Type: Basic Reference 4.2.7 6.6.18 Reference 4.2.7 6.6.19 Label Sig. Bits Range 80 4 discrete 2000NM FF Discrete N/A PIN FUNCTION Display Select Discrete #1 Display Select Discrete #2 Signal Type Resolution Rate (ms) Basic N/A 100 Basic N/A 100 Polarity/Configuration Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. The display does not use EGPWS ARINC 429 Output Bus. 2. The display color palette is not compatible with Terrain in the GMAP mode. Peaks Elevations are outside of the scan area in Sector Scan mode. Terrain will not be allowed to display in these modes. 3. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 226 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-245 Honeywell SPZ8000, EDZ806, (Integrated) with dual SCI range MK VIII Only Display Configuration Group 250 Function Display Type Sweep Type Auto Pop Up Peaks Mode Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Value Honeywell (SPZ8000 new style) every fourth display line is blanked Honeywell Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On Selection is controlled by display Deselection is controlled by display Yes 10NM Yes (Honeywell type) Yes for Peaks Elevations only (located middle right of display) Honeywell picture bus Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator #1 and MFD left channel 4.2.13.2 7.2 CONNECT TO: Terrain Display data to switching relay/Symbol Generator #1 and MFD right channel 4.2.13.2 7.2 Display Input Control Group 249 CHANNEL 429_422RX_1 CONNECT TO: SCI Bus 1 Format: RS-422 (12.0K baud) A = J2-36 B = J2-37 Data Range (Mode/Range word) Status CONNECT TO: SCI Bus 2 Format: RS-422 (12.0K baud) Reference 6.5.1.1 6.5.1.2 Data Range (Mode/Range word) Status Reference 6.5.1.1 6.5.1.2 CHANNEL 429RX_3 A = J2-10 B = J2-11 Fault Designation: DISPLAY BUS 1 Bus Type: Basic Label 80 FF Sig. Bits 4 discrete Discrete Range 2000NM N/A Signal Type Basic Basic Resolution N/A N/A Rate (ms) 100 100 Resolution N/A N/A Rate (ms) 100 100 Fault Designation: DISPLAY BUS 2 Bus Type: Basic Label 80 FF Sig. Bits 4 discrete Discrete Range 2000NM N/A Signal Type Basic Basic Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. The EGPWS ARINC 429 Output Bus must be connected to the display. 2. The ‘DISPLAY BUS’ fault will be present only if both MG inputs have failed. 3. The Honeywell EFIS SG & MG provide Terrain display relay control. 4. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. 5. The display uses the following ARINC 429 labels from the EGPWS for annunciations. The Terrain display will annunciate: “TERR” in green or cyan (depending on the program) when the Terrain is selected and valid. “TERR” in amber if Terrain is selected and any of the following conditions are TRUE: • The EGPWS ARINC 429 output bus is missing or labels 050 and 051 are absent or unreadable for 2 seconds. • EGPWS ARINC label 051 bit 13 = 0 (“Terrain Display Valid” bit FALSE). • EGPWS ARINC label 050 bit 17 = 1 (“Terrain Inhibit” bit TRUE). • EGPWS ARINC labels are valid, but the range in label 050 disagrees with the range via SCI bus label 80 (label 050 bit 11-14 contain left display bus range and bits 15-18 are the right display bus range). The display will be blanked when the amber “TERR” is present. The display will Pop Up to Terrain mode as follows: Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 227 Honeywell MK VI MK VIII EGPWS Installation Design Guide • • • • • • If all the conditions indicated for the amber “TERR” above are FALSE. If the display is in normal MFD mode (not HSI backup, or SG backup) AND if label051 bit 11 transitions from 0 to 1 (rising edge), AND Checklist is not selected on the MFD, AND TCAS Auto Pop Up is not occurring. The display will change to Map mode. The display will energize the Terrain selection relays. The display will annunciate “TERR”. The display will change to the range indicated by the EGPWS ARINC 429 label 050. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 228 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-246 Honeywell/Bendix EFIS 10, EFS 86 Radar system MK VIII Only Display Configuration Group 246 Function Display Type Sweep Type Auto Pop Up Value Bendix EFIS 10 (Non-Integrated) Normal, Sweep range +/- 90 degrees Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up on Caution or Warning.1 Never Pop Up Category 7, Options Select Group #1 Peaks Off Peaks On Anytime1 Anytime1 No No Yes; Without Peaks: “TERR” is located at the bottom left of the display. With Peaks: Peaks numbers are located at the bottom left of the display. ARINC 453 Peaks Mode Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type TERRAIN DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 TERRAIN DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator #1 4.2.13.2 7.2 CONNECT TO: Terrain Display data to switching relay/Symbol Generator #2 4.2.13.2 7.2 Display Input Control Group 246 CHANNEL 429_422RX_1 CONNECT TO: WX-IND 429 Bus 1 out Format: ARINC 429 (Low Speed) Fault Designation: DISPLAY BUS 1 Bus Type: Basic A = J2-37 B = J2-36 CHANNEL 429RX_3 Data Reference Mode (Display Word 1) 6.2.26 Range (Display Word 2) 6.2.20 CONNECT TO: WX-IND 429 Bus 2 out Format: ARINC 429 (Low Speed) Label 270 271 A = J2-412 B = J2-40 CONN PIN # J1-32 Data Mode (Display Word 1) Range (Display Word 2) REFERENCE NAME GND_DISC_12 Label Sig. Bits Range 270 Discrete Mode, Tilt, Gain 271 Discrete 5-320NM PIN FUNCTION Display Select Discrete #1 J1-31 GND_DISC_13 Reference 6.2.26 6.2.20 Reference 4.2.7 6.6.18 Reference 4.2.7 6.6.19 Sig. Bits Discrete Discrete Range Mode, Tilt, Gain 5-320NM Signal Type Basic Basic Resolution N/A N/A Rate 100 ms 100 ms Fault Designation: DISPLAY BUS 2 Bus Type: Basic Display Select Discrete #2 Signal Type Resolution Rate Basic N/A 100 ms Basic N/A 100 ms Polarity/Configuration Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. Either Weather (WX) or Weather Test pattern must be displayed before Terrain can be viewed. The white Weather annunciation “WX” will still be present when Terrain is displayed. 2. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 229 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-247 Collins FDS 255/2000 with selection controlled by the EGPWS MK VIII Only Display Configuration Group 252 Function Display Type Sweep Type Auto Pop Up Value Collins FDS 255/2000 Fan Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On Anytime Anytime No (see Integration Notes) No Yes for Peaks Elevations only (located on lower left of the display) ARINC 453 Peaks Mode Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator #1 4.2.13.2 7.2 CONNECT TO: Terrain Display data to switching relay/Symbol Generator #2 4.2.13.2 7.2 Display Input Control Group 253 CHANNEL 429_422RX_1 CONNECT TO: WX-IND 429 Bus 1 out Format: ARINC 429 (Low Speed) Fault Designation: DISPLAY BUS 1 Bus Type: Basic A = J2-37 B = J2-36 CHANNEL 429RX_3 Reference Data Range 6.2.20 CONNECT TO: WX-IND 429 Bus 2 out Format: ARINC 429 (Low Speed) Label 273 A = J2-41 B = J2-40 CONN PIN # J1-32 Data Range REFERENCE NAME GND_DISC_12 J1-31 GND_DISC_13 Reference 6.2.20 Reference 4.2.7 6.6.18 Reference 4.2.7 6.6.19 Sig. Bits N/A Range 5-320NM Signal Type Basic Resolution N/A Rate (ms) 100 Fault Designation: DISPLAY BUS 2 Bus Type: Basic Label Sig. Bits Range 273 N/A 5-320NM PIN FUNCTION Display Select Discrete #1 Display Select Discrete #2 Signal Type Resolution Rate (ms) Basic N/A 100 Polarity/Configuration Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Type 1 (Momentary) Gnd = Display Select Toggle Gnd = Normal Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. The EGPWS ARINC 429 Output Bus must be connected to the display. 2. When there is a Terrain Alert and the FDS 255/2000 is not currently displaying Terrain it will set its range to 10 NM and Pop Up to Terrain mode. The range does not change if Terrain mode is already selected when there is a Terrain Alert. 3. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 230 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-248 Honeywell Primus 1000 MK VIII Only Display Configuration Group 248 Function Display Type Sweep Type Auto Pop Up Peaks Mode Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 & #2 453TX_1 A = J1-58 B = J1-59 Value Honeywell Primus 1000 Honeywell Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On Selection is controlled by display Deselection is controlled by display Yes 10NM Yes (Honeywell type) Yes, for Peaks Elevations only (located middle right side of the display) Honeywell picture bus Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator 4.2.13.2 7.2 CONNECT TO: Not supported for this display type Display Input Control Group 248 CHANNEL 429_422RX_1 CONNECT TO: IC600 #1 FDR Bus Format: ARINC 429 (High Speed) Fault Designation: FDR BUS 1 Bus Type: Basic A = J2-37 B = J2-36 Reference Data Range 6.2.23 Discrete Word 6.2.28 CONNECT TO: IC600 #2 FDR Bus Format: ARINC 429 (High Speed) Label 050 275 Reference 6.2.23 6.2.28 Label 050 275 CHANNEL 429RX_3 A = J2-41 B = J2-40 Data Range Discrete Word Sig. Bits Bits 11-14 Bit 17 Range 2000NM Discrete Signal Type Basic Basic Resolution N/A N/A Rate (ms) 100 500 Signal Type Basic Basic Resolution N/A N/A Rate (ms) 100 500 Fault Designation: FDR BUS 2 Bus Type: Basic Sig. Bits Bits 11-14 Bit 17 Range 2000NM Discrete Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. The EGPWS ARINC 429 Output Bus must be connected to the display. 2. Display channels 1 and 2 are multiplexed on ARINC 453 bus 1. 3. The system only has one range for terrain display on MFD, therefore the range to use depends on the value of label 275, bit 17. 8. The Terrain display will Pop-Up in response to EGPWS label 274, bit 28 (Left display) and bit 29 (right display). 9. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. 10. This configuration will cause the GPWS INOP, TERRAIN INOP, and WINDSHEAR INOP lamps to turn on only at the beginning of the EGPWS Self Test. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 231 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-249 Honeywell Primus EPIC CDS/R, (Integrated) with overlay Peaks Elevations MK VIII Only Display Configuration Group 249 Function Display Type Sweep Type Auto Pop Up Peaks Mode Manual select Manual deselect Auto Range Moving Marker Overlay Page Display Priority Display bus type DISPLAY BUS #1 & #2 453TX_1 A = J1-58 B = J1-59 Value Honeywell Primus EPIC CDS/R (Control Display System/Retrofit) with overlay Peaks elevation Honeywell Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Category 7 does not affect pop up logic. The display controls pop up, therefore enable/disable of pop up is done via the display. Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On Selection is controlled by display Deselection is controlled by display Yes 10NM No Yes, for Peaks Elevations only (located on lower right side of display) Standard Honeywell picture bus Reference section 5.3.7 5.3.7 CONNECT TO: Honeywell left/right interleaved picture bus to MFD and PFD 4.2.13.2 7.2 CONNECT TO: Not supported for this display type Display Input Control Group 250 CHANNEL 429_422RX_1 CONNECT TO: IOC #1 Bus Format: ARINC 429 (High Speed) A = J2-37 B = J2-36 Data FWC & GP discrete word CHANNEL 429RX_3 CONNECT TO: IOC #2 Bus Format: ARINC 429 (High Speed) A = J2-41 B = J2-40 Data FWC & GP discrete word Fault Designation: IOC BUS 1 Bus Type: Basic Reference 6.2.48 Label 171 Sig. Bits Format 1 Bits 15-18 Bits 25-28 Range Type 1 2000NM Discrete Signal Type Basic Resolution N/A Rate (ms) 100 Signal Type Basic Resolution N/A Rate (ms) 100 Fault Designation: IOC BUS 2 Bus Type: Basic Reference 6.2.48 Label 171 Sig. Bits Format 1 Bits 15-18 Bits 25-28 Range Type 1 2000NM Discrete Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. 2. The ‘IOC BUS’ fault will be present only if both MG inputs have failed. 3. The Honeywell EFIS SG & MG provide Terrain display relay control. 4. The EGPWS ARINC 429 Output Bus must be connected to the display 5. This configuration will cause the GPWS INOP, TERRAIN INOP, and WINDSHEAR INOP lamps to turn on only at the beginning of the EGPWS Self Test. 6. Display channels 1 and 2 are multiplexed on ARINC 453 bus 1. 7. This display uses the following ARINC 429 labels from the EGPWS for annunciations: Label 050 If bits 11-14 left range output from the EGPWS does not match left MFD range (via label 171), then display white “RANGE MISMATCH” on the left PFD and MFD. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 232 Honeywell MK VI MK VIII EGPWS Installation Design Guide 8. If bits 15-18 right range output from the EGPWS does not match right MFD range (via label 171), then display white “RANGE MISMATCH” on the right PFD and MFD. Label 051 If bit 17 = 1 then display white “TERRAIN OFF” message on PFD and MFD. Labels 052-055 EGPWS ASCII characters are not used. Green “TERRAIN” on PFD and MFD by EFIS. Label 274 If bit 13 or 22 = 1 then display red “PULL UP” on left and right PFD. If bit 12 or 23 = 1 then display amber “GND PROX” on left and right PFD. If bit 14 = 1 then display white “GPWS FAIL” message on PFD. If bit 15 = 1 then display red “WIND SHR” message on PFD. If bit 17 = 1 then display white WNDSHR FAIL” message on PFD. If bit 18 = 1 then display amber “WIND SHR” message on PFD. If bit 24 = 1 then display amber “TERRAIN FAIL” message on PFD and MFD. If bit 27 = 1 then display amber “TERRAIN NA” message on PFD and MFD. If bit 28 = 1 and display configured for Pop Up on pilots side, then Pop Up Terrain on left MFD. If bit 29 = 1 and display configured for Pop Up on copilots side, then Pop Up Terrain on right MFD. If bit 14, bit 17, and bit 24 = 1 then display amber “EGPWS SYS FAIL” on PFD in lieu of “GPWS FAIL” and “WNDSHR FAIL” messages on PFD. If bits 30 and 31 = 01 (Functional Test) then display white “TERRAIN TEST” on PFD and MFD. Terrain can be displayed on the PFD and MFD. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 233 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-251 Honeywell Primus EPIC CDS/R, with binary Peaks Elevations MK VIII Only Display Configuration Group 251 Function Display Type Sweep Type Auto Pop Up Peaks Mode Binary Peaks Elevations Manual select Manual deselect Auto Range Moving Marker Overlay Page Display Priority Display bus type DISPLAY BUS #1 & #2 453TX_1 A = J1-58 B = J1-59 Value Honeywell Integrated Primus Epic CDS/R (Control Display System/Retrofit), with binary peaks elevations Honeywell Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Category 7 does not affect pop up logic. The display controls pop up, therefore enable/disable of pop up is done via the display. Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On Yes - Data passed by ARINC 429, Labels 011 and 012 Selection is controlled by display Deselection is controlled by display Yes 10NM No No Standard Honeywell picture bus Reference section 5.3.7 5.3.7 CONNECT TO: Honeywell left/right interleaved picture bus to MFD and PFD 4.2.13.2 7.2 CONNECT TO: Not supported for this display type Display Input Control Group 250 CHANNEL 429_422RX_1 CONNECT TO: IOC #1 Bus Format: ARINC 429 (High Speed) A = J2-37 B = J2-36 Data FWC & GP discrete word CHANNEL 429RX_3 CONNECT TO: IOC #2 Bus Format: ARINC 429 (High Speed) A = J2-41 B = J2-40 Data FWC & GP discrete word Fault Designation: IOC BUS 1 Bus Type: Basic Reference 6.2.48 Label 171 Sig. Bits Format 1 Bits 15-18 Bits 25-28 Range Type 1 2000NM Discrete Signal Type Basic Resolution N/A Rate (ms) 100 Signal Type Basic Resolution N/A Rate (ms) 100 Fault Designation: IOC BUS 2 Bus Type: Basic Reference 6.2.48 Label 171 Sig. Bits Format 1 Bits 15-18 Bits 25-28 Range Type 1 2000NM Discrete Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, 7.1.4.x, 7.1.5.x, and 7.1.6.x 429TX_2 (Low Speed) A = J2-26 B = J2-9 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, 7.1.4.x, 7.1.5.x, and 7.1.6.x Integration Notes: 1. The EGPWS ARINC 429 Output Bus must be connected to the display. 2. Display channels 1 and 2 are multiplexed on ARINC 453 Bus 1. 3. This configuration will cause the GPWS INOP, TERRAIN INOP, and WINDSHEAR INOP lamps to turn on only at the beginning of the EGPWS Self Test. 4. This display uses the following ARINC 429 labels from the EGPWS for annunciation’s: Label 011/012 Label 050 Upper/Lower Peaks Elevations – “xxx/xxx” on PFD and MFD. If bits 11-14 left range output from EGPWS does not match left MFD range (via label 171), then display white “RANGE MISMATCH” on left PFD and MFD. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 234 Honeywell MK VI MK VIII EGPWS Installation Design Guide Label 051 Labels 052-055 Label 274 If bits 15-18 right range output from EGPWS does not match right MFD range (via label 171), then display white “RANGE MISMATCH” on right PFD and MFD. If Bit 17 = 1 then display white “TERRAIN OFF” message on PFD and MFD and Terrain window will be cleared by EPIC. EGPWS ASCII characters are not used. Green TERRAIN on PFD and MFD by EFIS. If Bit 13 or 22 =1 then display red “PULL UP” on left and right PFD. If Bit 12 or 23 =1 then display amber “GND PROX” on left and right PFD. If Bit 14 = 1 then display white “GPWS FAIL” message on PFD. If Bit 15 = 1 then display red “WIND SHR” message on PFD. If Bit 17 = 1 then display white “WNDSHR FAIL” message on PFD. If Bit 18 = 1 then display amber “WIND SHR” message on PFD. If Bit 24 = 1 then display amber “TERRAIN FAIL” message on PFD and MFD (Terrain window cleared by Epic). If Bit 27 = 1 then display amber “TERRAIN NA” message on PFD and MFD (Terrain window cleared by Epic). If Bit 28 = 1 and display configured for pop up on Pilots side, then Pop Up Terrain on left MFD. If Bit 29 = 1 and display configured for pop up on CoPilots side, then Pop Up Terrain on right MFD. If Bit 14, Bit 17, and Bit 24 = 1 then display amber “EGPWS SYS FAIL” on PFD in lieu of “GPWS FAIL” and “WNDSHR FAIL” messages on the PFD. If bits 30 and 31 = 01 (functional test) then display white “TERRAIN TEST” on PFD and MFD. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 235 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-252 Honeywell SPZ8000, EDZ605, EDZ805 and EDZ806, with ARINC 429 Range MK VIII Only Display Configuration Group 250 Function Display Type Sweep Type Auto Pop Up Peaks Mode Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Value Honeywell (SPZ8000 new style) dual ARINC 429 Range Honeywell Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On Selection is controlled by display Deselection is controlled by display Yes 10NM Yes (Honeywell type) Yes for Peaks Elevations only (located middle right side of display) Honeywell picture bus Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator #1 and MFD left channel 4.2.13.2 7.2 CONNECT TO: Terrain Display data to switching relay/Symbol Generator #1 and MFD right channel 4.2.13.2 7.2 Display Input Control Group 252 CHANNEL 429_422RX_1 CONNECT TO: MG/SG Left Bus Format: ARINC 429 (Low Speed) A = J2-37 B = J2-36 Reference Data Range 6.2.23 (Both ranges on one word) CONNECT TO: MG/SG Right Bus Format: ARINC 429 (Low Speed) CHANNEL 429RX_3 A = J2-41 B = J2-40 Data Range (Both ranges on one word) Fault Designation: EFIS BUS 1 Bus Type: Basic Reference 6.2.23 Note: Provides range unless MG is not backing up right side (see channel 3) Label Sig. Bits Range Signal Type Resolution Rate (ms) 050 4/4 2000NM discrete TA&D N/A 100 Fault Designation: EFIS BUS 2 Bus Type: Basic Note: Only provides range if MG is backing up right side, MG input on channel 1 is primary input Label Sig. Bits Range Signal Type Resolution Rate (ms) 050 4/4 2000NM discrete TA&D N/A 100 Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. The EGPWS ARINC 429 Output Bus must be connected to the display. 2. The ‘EFIS BUS’ fault will be present only if both MG inputs have failed. 3. The Honeywell EFIS SG & MG provide Terrain display relay control. 4. The display uses the following ARINC 429 labels from the EGPWS for annunciations. The Terrain display will annunciate: “TERR” in green or cyan (depending on the program) when the Terrain is selected and valid. “TERR” in amber if Terrain is selected and any of the following conditions are TRUE: • The EGPWS ARINC 429 output bus is missing or labels 050 and 051, or are absent or unreadable for 2 seconds. • EGPWS ARINC label 051 bit 13 = 0 (“Terrain Display Valid” bit FALSE). • EGPWS ARINC label 050 bit 17 = 1 (“Terrain Inhibit” bit TRUE). • EGPWS ARINC labels are valid, but the range in label 050 disagrees with the range via SCI bus label 80 (label 050 bit 11-14 contain left display bus range and bits 15-18 are the right display bus range). Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 236 Honeywell MK VI MK VIII EGPWS Installation Design Guide The display will be blanked when the amber “TERR” is present. The display will Pop Up to Terrain mode as follows: • If all the conditions indicated for the amber “TERR” above are FALSE. • If the display is in normal MFD mode (not HSI backup, or SG backup) AND if label 051 bit 11 transitions from 0 to 1 (rising edge), AND Checklist is not selected on the MFD, AND TCAS Auto Pop Up is not occurring. • The display will change to Map mode. • The display will energize the Terrain selection relays. • The display will annunciate “TERR”. • The display will change to the range indicated by the EGPWS ARINC 429 label 050. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 237 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-253 Collins FDS 255/2000 with selection controlled by the display MK VIII Only Display Configuration Group 253 Function Display Type Sweep Type Auto Pop Up Peaks Mode Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Value Collins FDS 255/2000 Fan Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Category 7 does not affect pop up logic. The display controls pop up, therefore enable/disable of pop up is done via the display. Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On Selection controlled by display Deselection controlled by display No (see Integration Notes) No Yes for Peaks Elevations only (located on lower left of the display) Standard Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator #1 4.2.13.2 7.2 CONNECT TO: Terrain Display data to switching relay/Symbol Generator #2 4.2.13.2 7.2 Display Input Control Group 253 CHANNEL 429_422RX_1 CONNECT TO: WX-IND 429 Bus 1 out Format: ARINC 429 (Low Speed) Fault Designation: DISPLAY BUS 1 Bus Type: Basic A = J2-37 B = J2-36 CHANNEL 429RX_3 Reference Data Range 6.2.20 CONNECT TO: WX-IND 429 Bus 2 out Format: ARINC 429 (Low Speed) Label 273 A = J2-41 B = J2-40 Data Range Reference 6.2.20 Label 273 Sig. Bits N/A Range 5-320NM Signal Type Basic Resolution N/A Rate (ms) 100 Resolution N/A Rate (ms) 100 Fault Designation: DISPLAY BUS 2 Bus Type: Basic Sig. Bits N/A Range 5-320NM Signal Type Basic Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. The EGPWS ARINC 429 Output Bus must be connected to the display. 2. When there is a Terrain Alert and the FDS 255/2000 is not currently displaying Terrain it will set its range to 10 NM and Pop Up to Terrain mode. The range does not change if Terrain mode is already selected when there is a Terrain Alert. 3. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 238 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-254 Collins ProLine 21 (Integrated) MK VIII Only Display Configuration Group 254 Function Display Type Sweep Type Auto Pop Up Peaks Mode Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type Terrain Mode Annunciation DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Value Collins ProLine 21, Integrated with binary peaks elevation, with partial compass raster patch Fan Mode with +/- 90 degree limit Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Category 7 does not affect pop up logic. The display controls pop up, therefore enable/disable of pop up is done via the display. Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On Selection is controlled by display Deselection is controlled by display Yes (10NM) – Controlled by ProLine 21 system No No ARINC compatible format – Collins ProLine 21 (label 077) ProLine 21 system outputs Terrain Mode annunciation, it does not use EGPWS ASCII message. Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to Primary Flight Display/Multi Function Display #1 4.2.13.2 7.2 CONNECT TO: Terrain Display data to Primary Flight Display/Multi Function Display #2 4.2.13.2 7.2 Display Input Control Group 254 CHANNEL 429RX_1 CONNECT TO: IOC #1 Bus Format: ARINC 429 (High Speed) Fault Designation: IOC BUS 1 Bus Type: Basic A = J2-37 B = J2-36 CHANNEL 429RX_3 Reference Data Range (Mode/Range Word) 6.2.21 CONNECT TO: IOC #2 Bus Format: ARINC 429 (High Speed) Label 176 A = J2-41 B = J2-40 Data Range (Mode/Range Word) Reference 6.2.21 Label 176 Sig. Bits Discrete Range 5-640NM Signal Type Basic Resolution N/A Rate (ms) 50 Signal Type Basic Resolution N/A Rate (ms) 50 Fault Designation: IOC BUS 2 Bus Type: Basic Sig. Bits Discrete Range 5-640NM Output 429 Bus Group 1 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, 7.1.4.x, 7.1.5.x and 7.1.6.x 429TX_2 (Low Speed) A = J2-26 B = J2-9 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, 7.1.4.x, 7.1.5.x and 7.1.6.x Integration Notes: 1. The EGPWS ARINC 429 Output Bus must be connected to the display. 2. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel. 3. The Peaks mode will support ‘blue water’ on displays that can support blue. 4. This configuration will cause the GPWS INOP, TERRAIN INOP, and WINDSHEAR INOP lamps to turn on only at the beginning of the EGPWS Self Test. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 239 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.6.1-255 Honeywell SPZ8000 older style MK VIII Only Display Configuration Group 255 Function Display Type Sweep Type Auto Pop Up Peaks Mode (Elevations via overlay) Manual select Manual deselect Auto Range Moving Marker Overlay Page Display bus type DISPLAY BUS #1 453TX_1 A = J1-58 B = J1-59 DISPLAY BUS #2 453TX_2 A = J1-56 B = J1-57 Value Honeywell (5x6) SPZ8000 older style; does not blank every fourth weather radar display line. This interface supports SG-810 and SG-811 SPZ8000 systems only. Honeywell Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True Pop Up On Caution or Warning Never Pop Up Category 7, Options Select Group #1 Peaks Enable: False Peaks Enable: True Peaks Off Peaks On Selection is controlled by display Deselection is controlled by display Yes (10 NM) Yes (Honeywell type) Yes for Peaks Elevations only (located on lower right side) Honeywell picture bus Reference section 5.3.7 5.3.7 CONNECT TO: Terrain Display data to switching relay/Symbol Generator #1 4.2.13.2 7.2 CONNECT TO: Terrain Display data to switching relay/Symbol Generator #2 Note: Range setting always follows Display Bus #1 4.2.13.2 7.2 Display Input Control Group 255 CHANNEL 429_422RX_1 CONNECT TO: SCI Bus 1 Format: RS-422 (12K baud) A = J2-36 B = J2-37 Data Range (Mode/Range Word) Fault Designation: DISPLAY BUS 1 Bus Type: Basic Reference 6.5.1.1 Label 80 Sig. Bits 4 discrete Range 2000NM Signal Type Basic Resolution N/A Rate (ms) 100 Output 429 Bus Group 0 Channel Pins Comments 429TX_1 (Low Speed) A = J2-43 B = J2-42 Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, and 7.1.4.x Integration Notes: 1. The EGPWS ARINC 429 Output Bus must be connected to the SPZ8000 display. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 240 Honeywell MK VI MK VIII EGPWS Installation Design Guide 5.3.7 Category 7, Options Select Group #1 The following table provides identification of the Options Select Group #1. Each entry in the ID column corresponds to a particular combination of TA&D Alternate Pop Up, Obstacle Awareness Enabled, Peaks Mode Enabled, Bank Angle Enable, Steep Approach Enabled, Flap Reversal and GPS Altitude Reference selection. Refer to section 7.5 for configuration messages that will be present for each option selected. Table 5.3.7: Options Select Group #1 ID 0 1 2 3 4 5 6 7 8 9 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 Steep Approach Enabled 1 False False False False False False False False False False False False False False False False False False False False False False False False False False False False False False False False False False False False TA&D Alternate Pop Up False False False False False False False False False False False False False False False False False False False False False False False False False False False False False False False False True True True True Peaks Mode Enabled 2 False False False False False False False False False False False False False False False False True True True True True True True True True True True True True True True True False False False False Obstacle Awareness Enabled False False False False False False False False True True True True True True True True False False False False False False False False True True True True True True True True False False False False Bank Angle Enable Flap Reversal GPS Altitude Reference 3 Software Effectivity False False False False True True True True False False False False True True True True False False False False True True True True False False False False True True True True False False False False False False True True False False True True False False True True False False True True False False True True False False True True False False True True False False True True False False True True WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 1 TRUE enables steep approach selection via Steep Approach Select Discrete (see Section 5.3.13 and 6.6.25). Enables PEAKS mode display if display supports (see display configuration group Section 5.3.6) 3 "MSL" reference must be selected when an internal GPS is utilized (Refer to Table 5.3.3-2). 2 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 241 Honeywell MK VI MK VIII EGPWS Installation Design Guide ID 36 37 38 39 40 41 42 43 44 45 46 47 48 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 Steep Approach Enabled 1 False False False False False False False False False False False False False False False False False False False False False False False False False False False False True True True True True True True True True True True True True True True True True True True True True True TA&D Alternate Pop Up True True True True True True True True True True True True True True True True True True True True True True True True True True True True False False False False False False False False False False False False False False False False False False False False False False Peaks Mode Enabled 2 False False False False False False False False False False False False True True True True True True True True True True True True True True True True False False False False False False False False False False False False False False False False True True True True True True Obstacle Awareness Enabled False False False False True True True True True True True True False False False False False False False False True True True True True True True True False False False False False False False False True True True True True True True True False False False False False False Bank Angle Enable Flap Reversal GPS Altitude Reference 3 Software Effectivity True True True True False False False False True True True True False False False False True True True True False False False False True True True True False False False False True True True True False False False False True True True True False False False False True True False False True True False False True True False False True True False False True True False False True True False False True True False False True True False False True True False False True True False False True True False False True True False False True True False False WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 242 Honeywell MK VI MK VIII EGPWS Installation Design Guide ID 86 87 88 89 90 91 92 93 94 95 96 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 Steep Approach Enabled 1 True True True True True True True True True True True True True True True True True True True True True True True True True True True True True True True True True True True True True True True True True True TA&D Alternate Pop Up False False False False False False False False False False True True True True True True True True True True True True True True True True True True True True True True True True True True True True True True True True Peaks Mode Enabled 2 True True True True True True True True True True False False False False False False False False False False False False False False False False True True True True True True True True True True True True True True True True Obstacle Awareness Enabled False False True True True True True True True True False False False False False False False False True True True True True True True True False False False False False False False False True True True True True True True True Bank Angle Enable Flap Reversal GPS Altitude Reference 3 Software Effectivity True True False False False False True True True True False False False False True True True True False False False False True True True True False False False False True True True True False False False False True True True True True True False False True True False False True True False False True True False False True True False False True True False False True True False False True True False False True True False False True True False False True True WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL WGS-84 MSL -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 -020 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 243 Honeywell MK VI MK VIII EGPWS Installation Design Guide 5.3.8 Category 8, Radio Altitude Input Select The following table provides identification of the Radio Altitude type. The entry in the Radio Altitude Type corresponds to a table that provides detailed information on the configuration. For example, the details for Radio Altitude Type #1 are found in Table 5.3.8-1. ARINC 552, ALT 55 and digital ARINC 429 compatible Radio Altimeters are supported. ALT50 Radio Altimeters are not recommended due to the maximum 2000-foot operation. GPWS TSO-C92c requires Mode 1 alert thresholds up to 2450 feet radio altitude. In this category, only the following signals are defined: • Radio Altitude source selection, input scaling, and associated validities. Table 5.3.8: Radio Altitude Input Select ID 0 1 2 3 4 Radio Altitude Type Software Effectivity Description (Table 5.3.8-x) 0 1 2 3 4 Analog Radio Altitude (ARINC 552) Analog Radio Altitude (ALT 55) Digital Radio Altitude (ARINC 429) Analog Radio Altitude (RT-200/300) Analog Radio Altitude (KRA 405) EGPWS Effectivity MKVI MKVIII X X X X X X X X X X -020 -020 -020 -020 -020 Digital Radio Altitude (ARINC 429 via dual IOC -020 N/A X buses with DH/MDA) (Note 1,3) Digital Radio Altitude (ARINC 429 via dual IOC 252 252 -020 N/A X buses) (Note 1,3) Digital Radio Altitude (ARINC 429 via dual IOC -020 N/A X 253 253 buses with DH discrete) (Note 1) Digital Radio Altitude and MDA (ARINC 429 254 254 -020 N/A X via dual IOC buses) (Notes 1, 2, 3) Digital Radio Altitude (ARINC 429 via dual IOC 255 255 -020 N/A X buses) (Note 1, 3) Note 1: ID 251 - 255 may only be used in conjunction with other IOC bus selections for categories 2,6,9,10,11 and 12. Note 2: ID 254 must be used in conjunction with Category 9 ID 254, since this provides Label 163 which determines from bits 19-21 whether MDA or DH is displayed. Note 3: ID 251, 252, 254 and 255 must not be used in conjunction with Category 4, ID 100 or 101 Altitude Callouts types. 251 251 Table 5.3.8-0: Radio Altitude Input Select Type 0 (ARINC 552) SIGNAL Radio Altimeter #1 PIN FUNCTION Radio Altitude Validity Discrete #1 (+28V) DH Discrete (Gnd) CONNECTION REFERENCE (+) = J1-64 (-) = J1-45 6.1.1 4.2.3.1 CONNECTION PIN TYPE J1-29 Input J1-33 Input SUMMARY DATA Format: ARINC 552 with Validity Flag Input Type: Basic Fault Designation: RADIO ALTIMETER FAULT Validity: Radio Altitude Valid Discrete #1 (+28V) CHANNEL DESIGNATION Polarity/Configuration REFERENCE 28V_DISC_07 >+17V = Valid <+4.4V = Invalid GND_DISC_11 Gnd = Below DH Gnd = Above DH References 6.6.1 4.2.7 6.6.14 4.2.7 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 244 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.8-1: Radio Altitude Input Select Type 1 (ALT 55) SIGNAL Radio Altimeter #1 PIN FUNCTION CONNECTION REFERENCE (+) = J1-64 (-) = J1-45 6.1.2 4.2.3.1 CONNECTION Radio Altitude Validity Discrete #1 (+28V) DH Discrete (Gnd) PIN TYPE J1-29 Input J1-33 Input SUMMARY DATA Format: Alt 55 with Validity Flag Input Type: Basic Fault Designation: RADIO ALTIMETER FAULT Validity: Radio Altitude Valid Discrete #1 (+28V) CHANNEL DESIGNATION Polarity/Configuration REFERENCE 28V_DISC_07 >+17V = Valid <+4.4V = Invalid GND_DISC_11 Gnd = Below DH Gnd = Above DH References 6.6.1 4.2.7 6.6.14 4.2.7 Table 5.3.8-2: Radio Altitude Input Select Type 2 (ARINC 429) CHANNEL 429RX_5 A = J2-21 B = J2-4 PIN FUNCTION DH Discrete (Gnd) CONNECT TO: Left LRRA Format: ARINC 429 (Low Speed) Data Radio Altitude CONNECTION Reference 6.2.29 PIN TYPE Input J1-33 Fault Designation: RADIO ALTIMETER BUS Bus Type: Basic Label Sig. Bits Range 164 16 ±8192 FT CHANNEL DESIGNATION REFERENCE GND_DISC_11 Signal Type Resolution Basic 0.125 Polarity/Configuration Gnd = Below DH Gnd = Above DH Rate (ms) 25-50 References 6.6.14 4.2.7 Table 5.3.8-3: Radio Altitude Input Select Type 3 (RT-200/300) SIGNAL Radio Altimeter #1 PIN FUNCTION Radio Altitude Validity Discrete #1 (+28V) DH Discrete (Gnd) CONNECTION (+) = J1-64 (-) = J1-45 REFERENCE 6.1.11 4.2.3.1 CONNECTION PIN TYPE J1-29 Input J1-33 Input SUMMARY DATA Format: DC with Validity Flag (RT-200/300 Precision Output) Input Type: Basic Fault Designation: RADIO ALTIMETER FAULT Validity: Radio Altitude Valid Discrete #1 (+28V) CHANNEL DESIGNATION Polarity/Configuration REFERENCE 28V_DISC_07 >+17V = Valid <+4.4V = Invalid GND_DISC_11 Gnd = Below DH Gnd = Above DH References 6.6.1 4.2.7 6.6.14 4.2.7 Table 5.3.8-4: Radio Altitude Input Select Type 4 (KRA 405) SIGNAL Radio Altimeter #1 PIN FUNCTION Radio Altitude Validity Discrete #1 (+28V) DH Discrete (Gnd) CONNECTION REFERENCE (+) = J1-64 (-) = J1-45 6.1.2 4.2.3.1 CONNECTION PIN TYPE J1-29 Input J1-33 Input SUMMARY DATA Format: Alt 55 with Validity Flag (KRA-405 Auxiliary Output #1) Input Type: Basic Fault Designation: RADIO ALTIMETER FAULT Validity: Radio Altitude Valid Discrete #1 (+28V) CHANNEL DESIGNATION Polarity/Configuration References REFERENCE 28V_DISC_07 >+17V = Valid 6.6.1 <+4.4V = Invalid 4.2.7 GND_DISC_11 Gnd = Below DH 6.6.14 Gnd = Above DH 4.2.7 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 245 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.8-251: Radio Altitude Input Select Type 251 (ARINC 429 via dual IOC buses with DH/MDA) Fault Designation: IOC BUS 1 Bus Type: Basic CHANNEL 429RX_1 CONNECT TO: IOC #1 Format: ARINC 429 (High Speed) A = J2-37 B = J2-36 CHANNEL 429RX_3 Data Reference Radio Altitude 6.2.29 Decision Height/MDA 6.2.62 CONNECT TO: IOC #2 Format: ARINC 429 (High Speed) Data Radio Altitude Decision Height/MDA A = J2-41 B = J2-40 Reference 6.2.29 6.2.62 Label 164 170 Sig. Bits 16 12 / 14 Range ±8192 FT 4096/16384 Signal Type Basic Basic Resolution 0.125 1.0 Rate (ms) 25-50 1000 Resolution 0.125 1.0 Rate (ms) 25-50 1000 Fault Designation: IOC BUS 2 Bus Type: Basic Label 164 170 Sig. Bits 16 12 / 14 Range ±8192 FT 4096/16384 Signal Type Basic Basic Table 5.3.8-252: Radio Altitude Input Select Type 252 (ARINC 429 via dual IOC buses with DH discrete) Fault Designation: IOC BUS 1 Bus Type: Basic CHANNEL 429RX_1 CONNECT TO: IOC #1 Format: ARINC 429 (High Speed) A = J2-37 B = J2-36 CHANNEL 429RX_3 Data Reference Radio Altitude 6.2.29 Decision Height (format 1) 6.2.41 CONNECT TO: IOC #2 Format: ARINC 429 (High Speed) Data Radio Altitude Decision Height (format 1) A = J2-41 B = J2-40 Reference 6.2.29 6.2.41 Label 164 370 Sig. Bits 16 16 Range ±8192 FT ±8192 FT Signal Type Basic Basic Resolution 0.125 0.125 Rate (ms) 25-50 100-200 Resolution 0.125 0.125 Rate (ms) 25-50 100-200 Fault Designation: IOC BUS 2 Bus Type: Basic Label 164 370 Sig. Bits 16 16 Range ±8192 FT ±8192 FT Signal Type Basic Basic Table 5.3.8-253: Radio Altitude Input Select Type 253 (ARINC 429 via dual IOC buses with DH discrete) CHANNEL 429RX_1 A = J2-37 B = J2-36 CHANNEL 429RX_3 Fault Designation: IOC BUS 1 Bus Type: Basic CONNECT TO: IOC #1 Format: ARINC 429 (High Speed) Data Radio Altitude Reference 6.2.29 CONNECT TO: IOC #2 Format: ARINC 429 (High Speed) A = J2-41 B = J2-40 PIN FUNCTION DH Discrete (Gnd) Data Radio Altitude J1-33 Sig. Bits 16 Range ±8192 FT Signal Type Basic Resolution 0.125 Rate (ms) 25-50 Resolution 0.125 Rate (ms) 25-50 Fault Designation: IOC BUS 2 Bus Type: Basic Reference 6.2.29 CONNECTION Label 164 PIN TYPE Input Label 164 Sig. Bits 16 Range ±8192 FT CHANNEL DESIGNATION REFERENCE GND_DISC_11 Signal Type Basic Polarity/Configuration Gnd = Below DH Gnd = Above DH References 6.6.14 4.2.7 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 246 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.8-254: Radio Altitude Input Select Type 254 (ARINC 429 via dual IOC buses) CHANNEL 429RX_1 A = J2-37 B = J2-36 CHANNEL 429RX_3 A = J2-41 B = J2-40 Fault Designation: IOC BUS 1 Bus Type: Basic CONNECT TO: IOC #1 Format: ARINC 429 (High Speed) Data Reference Radio Altitude 6.2.29 Decision Height (format 3) 6.2.41 MDA (format 3) 6.2.51 CONNECT TO: IOC #2 Format: ARINC 429 (High Speed) Data Radio Altitude Decision Height (format 3) MDA (format 3) Reference 6.2.29 6.2.41 6.2.51 Label 164 370 170 Sig. Bits 16 16 16 Range ±8192 FT ±8192 FT ±65536 FT Signal Type Basic Basic Basic Resolution 0.125 0.125 1.0 Rate (ms) 25-50 100-200 200 Resolution 0.125 0.125 1.0 Rate (ms) 25-50 100-200 200 Fault Designation: IOC BUS 2 Bus Type: Basic Label 164 370 170 Sig. Bits 16 16 16 Range ±8192 FT ±8192 FT ±65536 FT Signal Type Basic Basic Basic Table 5.3.8-255: Radio Altitude Input Select Type 255 (ARINC 429 via dual IOC buses) Fault Designation: IOC BUS 1 Bus Type: Basic CHANNEL 429RX_1 CONNECT TO: IOC #1 Format: ARINC 429 (High Speed) A = J2-37 B = J2-36 CHANNEL 429RX_3 Data Reference Radio Altitude 6.2.29 Decision Height (format 1) 6.2.41 CONNECT TO: IOC #2 Format: ARINC 429 (High Speed) A = J2-41 B = J2-40 Data Radio Altitude Decision Height (format 1) Reference 6.2.29 6.2.41 Label 164 370 Sig. Bits 16 16 Range ±8192 FT ±8192 FT Signal Type Basic Basic Resolution 0.125 0.125 Rate (ms) 25-50 100-200 Resolution 0.125 0.125 Rate (ms) 25-50 100-200 Fault Designation: IOC BUS 2 Bus Type: Basic Label 164 370 Sig. Bits 16 16 Range ±8192 FT ±8192 FT Signal Type Basic Basic Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 247 Honeywell MK VI MK VIII EGPWS Installation Design Guide 5.3.9 Category 9, Navigation Input Select The following table provides identification of the Navigation type. The entry in the Navigation Type corresponds to a table that provides detailed information on the configuration. For example, the details for Navigation Type #1 are found in Table 5.3.9-1. In this category, only the following signals are defined: • • • • Glideslope source selection. Localizer source selection. PFD Mode Select Word Selected Course Note: Numerous (but not all) Envelope Modulation cases require a localizer input. Therefore, a NAV ID that supplies both Glideslope and Localizer should be selected in this category, if possible. However, due to hardware limitations, use of Localizer for installations that can only provide low level GS validity is not supported. In these cases, only ID #1 can be selected. Envelope Modulation will still function for those locations which do not require a Localizer input, but not for those that require Localizer. TABLE 5.3.9: NAVIGATION INPUT SELECT ID Navigation Inputs Select Software Effectivity Description (Table 5.3.9-x) Analog Glideslope (ARINC 547) with +28V Validity Flag Analog Glideslope (ARINC 547) with Low Level Validity EGPWS Effectivity MKVI MK VIII -020 X X -020 X X 0 0 1 1 2 2 Digital Glideslope (ARINC 429) -020 X X 3 3 Digital Glideslope and Localizer (ARINC 429) -020 X X 4 4 Digital KN40 Glideslope and Localizer (ARINC 429) -020 X X 5 5 Analog Glideslope/Localizer (ARINC 547) with +28V Validity Flag -020 X X Digital Glideslope, Localizer, PFD Word and Selected -020 N/A X Course (ARINC 429 via dual IOC buses) (Note 1) Digital Glideslope, Localizer and Selected Course 251 251 -020 N/A X (ARINC 429 via dual IOC buses) (Note 2) Digital Glideslope and Localizer – Alternate Input 252 252 -020 N/A X Channels (ARINC 429 via dual IOC buses) (Note 2) Digital Glideslope and Localizer (ARINC 429 via 253 253 -020 N/A X dual IOC buses) (Note 2) Digital Glideslope, Localizer and PFD Word (ARINC 254 254 -020 N/A X 429 via dual IOC buses) (Note 1) Digital Glideslope and Localizer – Alternate Labels 255 255 -020 N/A X (ARINC 429 via dual IOC buses) (Note 2) Note 1: ID 250 and 254 may only be used in conjunction with other IOC bus selections for categories 2,6,8,10,11 and 12. The use of either the left or right source is based on the displayed source provided on label 163. Note 2: ID 251, 252, 253, and 255 may only be used in conjunction with other IOC bus selections for categories 2,6,8,10,11 and 12. 250 250 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 248 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.9-0: Navigation Inputs Select 0 SIGNAL CONNECTION (+) = J1-65 (-) = J1-46 Glideslope Deviation PIN FUNCTION Glideslope Validity Discrete #1 +28V ILS Tuned Discrete #1 GND ILS Tuned Discrete #1 REFERENCE 6.1.6 4.2.3.2 CONNECTION PIN TYPE J1-11 Input J1-39 Input J1-20 Input SUMMARY DATA Format: ARINC 547 with Validity Flag & ILS Select Input Type: Basic Fault Designation: GLIDESLOPE FAULT Validity: Glideslope Validity Discrete #1 (+28V) CHANNEL DESIGNATION Polarity/Configuration REFERENCE 28V_DISC_06 >+17V = Valid < +4.4V = Not Valid 28V_DISC_01 >+17V = ILS Tuned < +4.4V = ILS Not Tuned GND_DISC_01 Gnd = ILS Tuned Gnd = ILS Not Tuned Reference 6.6.10 4.2.7 6.6.9 4.2.7 6.6.8 4.2.7 Table 5.3.9-1: Navigation Inputs Select 1 SIGNAL CONNECTION REFERENCE Glideslope Deviation (+) = J1-65 (-) = J1-46 6.1.7 4.2.3.2 Low Level Glideslope Deviation Validity (+) = J1-30 (-) = J1-10 6.1.14 4.2.3.3 PIN FUNCTION +28V ILS Tuned Discrete #1 GND ILS Tuned Discrete #1 CONNECTION PIN TYPE J1-39 Input J1-20 Input SUMMARY DATA Format: ARINC 547 with Low Level Validity & ILS Select Input Type: Basic Fault Designation: GLIDESLOPE FAULT Validity: Low Level Glideslope Deviation Validity Format: DC Input Type: Basic Fault Designation: GLIDESLOPE LOW LEVEL VALIDITY FAULT > 0.145V = Valid (typical active range is 0.16V to 0.84V) <= 0.145V = Invalid CHANNEL DESIGNATION Polarity/Configuration REFERENCE 28V_DISC_01 >+17V = ILS Tuned < +4.4V = ILS Not Tuned GND_DISC_01 Gnd = ILS Tuned Gnd = ILS Not Tuned Reference 6.6.9 4.2.7 6.6.8 4.2.7 Table 5.3.9-2: Navigation Inputs Select 2 CHANNEL 429RX_6 A = J2-22 B = J2-5 Fault Designation: ILS BUS Bus Type: Basic CONNECT TO: ILS #1 Format: ARINC 429 (Low Speed) Data Glideslope Reference 6.2.30 Label 174 Sig. Bits 12 Range ±0.8 DDM Signal Type Basic Resolution 0.0001953125 Rate (ms) 33.3-66.6 Resolution 0.0001953125 0.00009765625 Rate (ms) 33.3-66.6 33.3-66.6 Resolution 0.0001953125 0.00009765625 Bit 14 = ILS Rate (ms) 33.3-66.6 33.3-66.6 167-333 Table 5.3.9-3: Navigation Inputs Select 3 CHANNEL 429RX_6 A = J2-22 B = J2-5 Fault Designation: ILS BUS Bus Type: Basic CONNECT TO: ILS #1 Format: ARINC 429 (Low Speed) Data Glideslope Localizer Reference 6.2.30 6.2.33 Label 174 173 Sig. Bits 12 12 Range ±0.8 DDM ±0.4 DDM Signal Type Basic Basic Table 5.3.9-4: Navigation Inputs Select 4 CHANNEL 429RX_6 A = J2-22 B = J2-5 Fault Designation: ILS BUS Bus Type: Basic CONNECT TO: ILS #1 Format: ARINC 429 (Low Speed) Data Glideslope Localizer ILS Select (VOR/ILS Freq) Reference 6.2.30 6.2.33 6.2.46 Configuration Data KN40 Nav Source Label 174 173 034 Sig. Bits 12 12 Discrete Range ±0.8 DDM ±0.4 DDM n/a Signal Type Basic Basic Basic Type Reference Section True Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 249 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.9-5: Navigation Inputs Select 5 SIGNAL CONNECTION REFERENCE Glideslope Deviation (+) = J1-65 (-) = J1-46 6.1.6 4.2.3.2 Localizer Deviation (+) = J1-30 (-) = J1-10 6.1.17 4.2.3.3 PIN FUNCTION Localizer Validity Discrete #1 Glideslope Validity Discrete #1 +28V ILS Tuned Discrete #1 GND ILS Tuned Discrete #1 CONNECTION PIN TYPE J1-48 Input J1-11 Input J1-39 Input J1-20 Input SUMMARY DATA Format: ARINC 547 with Validity Flag & ILS Select Input Type: Basic Fault Designation: GLIDESLOPE FAULT Validity: Glideslope Validity Discrete #1 (+28V) Format: ARINC 547 with Validity Flag & ILS Select Input Type: Basic Fault Designation: LOCALIZER FAULT Validity: Glideslope Validity Discrete #1 (+28V) CHANNEL DESIGNATION Polarity/Configuration REFERENCE 28V_DISC_11 >+17V = Valid < +4.4V = Not Valid 28V_DISC_06 >+17V = Valid < +4.4V = Not Valid 28V_DISC_01 >+17V = ILS Tuned < +4.4V = ILS Not Tuned GND_DISC_01 Gnd = ILS Tuned Gnd = ILS Not Tuned Reference 6.6.28 4.2.7 6.6.10 4.2.7 6.6.9 4.2.7 6.6.8 4.2.7 Table 5.3.9-250: Navigation Inputs Select 250 CHANNEL 429/422RX_1 A = J2-37 B = J2-36 CHANNEL 429RX_3 A = J2-41 B = J2-40 CONNECT TO: IOC #1 Format: ARINC 429 (High Speed) Fault Designation: IOC BUS 1 Bus Type: Basic Data Reference Glideslope 6.2.30 Localizer 6.2.33 PFD Mode Select Word 6.2.44 Selected Course 6.2.61 CONNECT TO: IOC #2 Format: ARINC 429 (High Speed) Label 174 173 163 100 Data Glideslope Localizer PFD Mode Select Word Selected Course Reference 6.2.30 6.2.33 6.2.44 6.2.61 Sig. Bits 12 12 Discrete 11 Range ±0.8 DDM ±0.4 DDM Type 4 ±180 degrees Signal Type Basic Basic Basic Basic Resolution 0.0001953125 0.00009765625 n/a 0.087890625 Rate (ms) 33.3-66.6 33.3-66.6 250 200 Signal Type Basic Basic Basic Basic Resolution 0.0001953125 0.00009765625 n/a 0.087890625 Rate (ms) 33.3-66.6 33.3-66.6 250 200 Signal Type Basic Basic Basic Resolution 0.0001953125 0.00009765625 0.087890625 Rate (ms) 33.3-100 33.3-100 33.3-100 Signal Type Basic Basic Basic Resolution 0.0001953125 0.00009765625 0.087890625 Rate (ms) 33.3-100 33.3-100 33.3-100 Fault Designation: IOC BUS 2 Bus Type: Basic Label 174 173 163 100 Sig. Bits 12 12 Discrete 11 Range ±0.8 DDM ±0.4 DDM Type 4 ±180 degrees Table 5.3.9-251: Navigation Inputs Select 251 CHANNEL 429/422RX_1 A = J2-37 B = J2-36 CHANNEL 429RX_3 A = J2-41 B = J2-40 CONNECT TO: IOC #1 Format: ARINC 429 (High Speed) Fault Designation: IOC BUS 1 Bus Type: Basic Data Reference Glideslope 6.2.30 Localizer 6.2.33 Selected Course 6.2.61 CONNECT TO: IOC #2 Format: ARINC 429 (High Speed) Label 174 173 100 Data Glideslope Localizer Selected Course Reference 6.2.30 6.2.33 6.2.61 Sig. Bits 12 12 11 Range ±0.8 DDM ±0.4 DDM ±180 degrees Fault Designation: IOC BUS 2 Bus Type: Basic Label 174 173 100 Sig. Bits 12 12 11 Range ±0.8 DDM ±0.4 DDM ±180 degrees Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 250 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.9-252: Navigation Inputs Select 252 CHANNEL 429/422RX_1 A = J2-39 B = J2-38 CHANNEL 429RX_3 A = J2-21 B = J2-04 CONNECT TO: IOC #1 Format: ARINC 429 (High Speed) Fault Designation: IOC BUS 1 Bus Type: Basic Data Reference Glideslope 6.2.30 Localizer 6.2.33 CONNECT TO: IOC #2 Format: ARINC 429 (High Speed) Label 174 173 Data Glideslope Localizer Reference 6.2.30 6.2.33 Sig. Bits 12 12 Range ±0.8 DDM ±0.4 DDM Signal Type Basic Basic Resolution 0.0001953125 0.00009765625 Rate (ms) 33.3-66.6 33.3-66.6 Signal Type Basic Basic Resolution 0.0001953125 0.00009765625 Rate (ms) 33.3-66.6 33.3-66.6 Signal Type Basic Basic Resolution 0.0001953125 0.00009765625 Rate (ms) 33.3-66.6 33.3-66.6 Signal Type Basic Basic Resolution 0.0001953125 0.00009765625 Rate (ms) 33.3-66.6 33.3-66.6 Signal Type Basic Basic Basic Resolution 0.0001953125 0.00009765625 n/a Rate (ms) 33.3-66.6 33.3-66.6 250 Signal Type Basic Basic Basic Resolution 0.0001953125 0.00009765625 n/a Rate (ms) 33.3-66.6 33.3-66.6 250 Signal Type Basic Basic Resolution 0.0001953125 0.00009765625 Rate (ms) 33.3-66.6 33.3-66.6 Signal Type Basic Basic Resolution 0.0001953125 0.00009765625 Rate (ms) 33.3-66.6 33.3-66.6 Fault Designation: IOC BUS 2 Bus Type: Basic Label 174 173 Sig. Bits 12 12 Range ±0.8 DDM ±0.4 DDM Table 5.3.9-253: Navigation Inputs Select 253 CHANNEL 429/422RX_1 A = J2-37 B = J2-36 CHANNEL 429RX_3 A = J2-41 B = J2-40 CONNECT TO: IOC #1 Format: ARINC 429 (High Speed) Fault Designation: IOC BUS 1 Bus Type: Basic Data Reference Glideslope 6.2.30 Localizer 6.2.33 CONNECT TO: IOC #2 Format: ARINC 429 (High Speed) Label 174 173 Data Glideslope Localizer Reference 6.2.30 6.2.33 Sig. Bits 12 12 Range ±0.8 DDM ±0.4 DDM Fault Designation: IOC BUS 2 Bus Type: Basic Label 174 173 Sig. Bits 12 12 Range ±0.8 DDM ±0.4 DDM Table 5.3.9-254: Navigation Inputs Select 254 CHANNEL 429/422RX_1 A = J2-37 B = J2-36 CHANNEL 429RX_3 A = J2-41 B = J2-40 CONNECT TO: IOC #1 Format: ARINC 429 (High Speed) Fault Designation: IOC BUS 1 Bus Type: Basic Data Reference Glideslope 6.2.30 Localizer 6.2.33 PFD Mode Select Word 6.2.44 CONNECT TO: IOC #2 Format: ARINC 429 (High Speed) Label 174 173 163 Data Glideslope Localizer PFD Mode Select Word Reference 6.2.30 6.2.33 6.2.44 Sig. Bits 12 12 Discrete Range ±0.8 DDM ±0.4 DDM Type 4 Fault Designation: IOC BUS 2 Bus Type: Basic Label 174 173 163 Sig. Bits 12 12 Discrete Range ±0.8 DDM ±0.4 DDM Type 4 Table 5.3.9-255: Navigation Inputs Select 255 CHANNEL 429/422RX_1 A = J2-37 B = J2-36 CHANNEL 429RX_3 A = J2-41 B = J2-40 CONNECT TO: IOC #1 Format: ARINC 429 (High Speed) Fault Designation: IOC BUS 1 Bus Type: Basic Data Reference Glideslope 6.2.30 Localizer 6.2.33 CONNECT TO: IOC #2 Format: ARINC 429 (High Speed) Label 117 116 Data Glideslope Localizer Reference 6.2.30 6.2.33 Sig. Bits 12 12 Range ±0.8 DDM ±0.4 DDM Fault Designation: IOC BUS 2 Bus Type: Basic Label 117 116 Sig. Bits 12 12 Range ±0.8 DDM ±0.4 DDM Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 251 Honeywell MK VI MK VIII EGPWS Installation Design Guide 5.3.10 Category 10, Attitude Input Select The following table provides identification of the Attitude Roll Angle type. The entry in the Attitude Input Select corresponds to a table that provides detailed information on the configuration. For example, the details for Attitude Input Select #2 are found in 5.3.10-2. In this category, only the following signals are defined: • • • • • • • • Roll Attitude. Pitch Attitude Roll Rate Pitch Rate Normal Acceleration Longitudinal Acceleration Inertial Vertical Speed Inertial Altitude Table 5.3.10: Attitude Input Select ID 0 1 2 3 4 Attitude Input Select (Table 5.3.10-x) 0 Software Effectivity Description EGPWS Effectivity MKVI MKVIII Analog Roll without validity (3-Wire Synchro) -020 X X 2 Analog Pitch and Roll (3-Wire Synchro) -020 X X 4 Analog Roll with validity (3-Wire Synchro) Digital Pitch and Roll (ARINC 429 High Speed) (Note 2) Digital Pitch, Roll, and Vertical Speed (ARINC 429 High Speed) (Note 2) -020 X X -020 X X -020 X X 5 5 6 6 Digital Pitch, Roll, Vertical Speed and Altitude -020 N/A X (ARINC 429 via dual IOC buses) (Note 1) Digital Roll and Acceleration 255 255 -020 N/A X (ARINC 429 via dual IOC buses) (Note 1) Note 1: ID 253 and 255 may only be used in conjunction with other IOC bus selections for categories 2,6,8,9,11 and 12. Note 2: Category 10 and Category 11 use the same ARINC 429 receiver if a digital source is selected. 253 253 Table 5.3.10-0: Attitude Input Select Type 0 SIGNAL Roll Attitude CONNECTION (X) = J1-1 (Y) = J1-21 (Z) = J1-2 REFERENCE 6.1.8 SUMMARY DATA Format: 3 Wire Synchro Input Type: Basic Fault Designation: ROLL FAULT Validity: None Reference: None Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 252 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.10-2: Attitude Input Select Type 2 SIGNAL CONNECTION REFERENCE Roll Attitude (X) = J1-1 (Y) = J1-21 (Z) = J1-2 6.1.15 Pitch Attitude (X) = J1-5 (Y) = J1-7 (Z) = J1-6 6.1.12 PIN FUNCTION CONNECTION PIN TYPE J1-68 Input Attitude Validity Discrete #1 SUMMARY DATA Format: 3 Wire Synchro with Validity Flag Input Type: Basic Fault Designation: ROLL FAULT Validity: Attitude Validity Discrete #1 Reference: None Format: 3 Wire Synchro with Validity Flag Input Type: Basic Fault Designation: PITCH FAULT Validity: Attitude Validity Discrete #1 Reference: None CHANNEL DESIGNATION Polarity/ REFERENCE Configuration 28V_DISC_12 >+17V = Valid <+4.4V = Invalid References 6.6.24 4.2.7 Table 5.3.10-4: Attitude Input Select Type 4 SIGNAL CONNECTION (X) = J1-1 (Y) = J1-21 (Z) = J1-2 Roll Attitude PIN FUNCTION REFERENCE 6.1.15 CONNECTION PIN TYPE J1-68 Input Attitude Validity Discrete #1 SUMMARY DATA Format: 3 Wire Synchro with Validity Flag Input Type: Basic Fault Designation: ROLL FAULT Validity: Attitude Validity Discrete #1 Reference: None CHANNEL DESIGNATION Polarity/ REFERENCE Configuration 28V_DISC_12 >+17V = Valid <+4.4V = Invalid Summary Data 6.6.24 4.2.7 Table 5.3.10-5: Attitude Input Select Type 5 CHANNEL 429RX_7 A = J2-23 B = J2-6 Fault Designation: AHRS BUS Bus Type: Basic CONNECT TO: AHRS Format: ARINC 429 (High Speed) Data Roll Angle Pitch Angle Reference 6.2.31 6.2.34 Label 325 324 Sig. Bits 14 14 Range ±180 degrees ±180 degrees Signal Type Basic Basic Resolution 0.010986328125 0.010986328125 Rate (ms) 10-20 10-20 Resolution 0.010986328125 0.010986328125 0.01562500 0.01562500 1.0 Rate (ms) 10-20 10-20 10-20 10-20 20-40 Table 5.3.10-6: Attitude Input Select Type 6 CHANNEL 429RX_7 A = J2-23 B = J2-6 Fault Designation: AHRS BUS Bus Type: Basic CONNECT TO: AHRS Format: ARINC 429 (High Speed) Data Roll Angle Pitch Angle Body Roll Rate Body Pitch Rate Inertial Vertical Speed Reference 6.2.31 6.2.34 6.2.50 6.2.49 6.2.56 Label 325 324 327 326 365 Sig. Bits 14 14 13 13 15 Range ±180 degrees ±180 degrees ±128 deg/sec ±128 deg/sec ±32,768 fpm Signal Type Basic Basic Basic Basic Basic Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 253 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.10-253: Attitude Input Select Type 253 CHANNEL 429RX_7 A = J2-37 B = J2-36 Data Roll Angle Pitch Angle Body Roll Rate Body Pitch Rate Inertial Vertical Speed Inertial Altitude CHANNEL 429RX_7 A = J2-41 B = J2-40 Fault Designation: IOC BUS 1 Bus Type: Basic CONNECT TO: IOC #1 Format: ARINC 429 (High Speed) Reference 6.2.31 6.2.34 6.2.50 6.2.49 6.2.56 6.2.57 Label 325 324 327 326 365 361 Range ±180 degrees ±180 degrees ±128 deg/sec ±128 deg/sec ±32,768 fpm ±131,072 ft Signal Type Basic Basic Basic Basic Basic Basic Resolution 0.010986328125 0.010986328125 0.01562500 0.01562500 1.0 0.125 Rate (ms) 10-20 10-20 10-20 10-20 20-40 20-40 Resolution 0.010986328125 0.010986328125 0.01562500 0.01562500 1.0 0.125 Rate (ms) 10-20 10-20 10-20 10-20 20-40 20-40 Fault Designation: IOC BUS 2 Bus Type: Basic CONNECT TO: IOC #2 Format: ARINC 429 (High Speed) Data Roll Angle Pitch Angle Body Roll Rate Body Pitch Rate Inertial Vertical Speed Inertial Altitude Sig. Bits 14 14 13 13 15 20 Reference 6.2.31 6.2.34 6.2.50 6.2.49 6.2.56 6.2.57 Label 325 324 327 326 365 361 Sig. Bits 14 14 13 13 15 20 Range ±180 degrees ±180 degrees ±128 deg/sec ±128 deg/sec ±32,768 fpm ±131,072 ft Signal Type Basic Basic Basic Basic Basic Basic Note: ID 253 may only be used with Category 2 ‘digital’ Barometric Altitude Rate sources, analog sources are not compatible with Inertial Vertical Speed. Table 5.3.10-255: Attitude Input Select Type 255 CHANNEL 429/422RX_1 Fault Designation: IOC BUS 1 Bus Type: Basic CONNECT TO: IOC #1 Format: ARINC 429 (High Speed) Data Reference Roll Angle 6.2.31 Pitch Angle 6.2.34 Normal Acceleration 6.2.42 Longitudinal Acceleration 6.2.43 CHANNEL CONNECT TO: IOC #2 429RX_3 Format: ARINC 429 (High Speed) Label 325 324 333 331 Data Roll Angle Pitch Angle Normal Acceleration Longitudinal Acceleration Label 325 324 333 331 A = J2-37 B = J2-36 A = J2-41 B = J2-40 Reference 6.2.31 6.2.34 6.2.42 6.2.43 Sig. Bits 14 14 12 12 Range ±180 degrees ±180 degrees ±4 g’s ±4 g’s Signal Type Basic Basic Basic Basic Resolution 0.010986328125 0.010986328125 0.000977 g’s 0.000977 g’s Rate (ms) 10-20 10-20 10-20 10-20 Resolution 0.010986328125 0.010986328125 0.000977 g’s 0.000977 g’s Rate (ms) 10-20 10-20 10-20 10-20 Fault Designation: IOC BUS 2 Bus Type: Basic Sig. Bits 14 14 12 12 Range ±180 degrees ±180 degrees ±4 g’s ±4 g’s Signal Type Basic Basic Basic Basic Note: The output for Normal Acceleration reads 0 g’s nominal when aircraft is on the ground, or during unaccelerated level flight. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 254 Honeywell MK VI MK VIII EGPWS Installation Design Guide 5.3.11 Category 11, Heading Input Select The following table provides identification of the Heading type. The entry in the Heading Input Select corresponds to a table that provides detailed information on the configuration. For example, the details for Magnetic Heading Input Select #0 are found in Table 5.3.11-0. In this category, only the following signals are defined: • • Magnetic Heading True Heading Table 5.3.11: Heading Input Select ID Heading Input Select Software Effectivity Description EGPWS Effectivity (Table 5.3.11-x) 0 Analog Magnetic Heading (3-Wire Synchro with reference and validity discrete) 0 MKVI MK VIII -020 X X -020 X X -020 X X 1 2 2 3 3 Digital Magnetic Heading (High Speed ARINC 429) (Note 2) Digital Magnetic Heading and True Heading (High Speed ARINC 429) (Note 2) Digital True Heading -020 N/A X (ARINC 429 via dual IOC buses) (Note 1) Digital Magnetic Heading 255 255 -020 N/A X (ARINC 429 via dual IOC buses) (Note 1) Note 1: ID 254 and 255 may only be used in conjunction with other IOC bus selections for categories 2,6,8,9,10 and 12. Note 2: Category 10 and Category 11 use the same ARINC 429 receiver if a digital source is selected. 254 254 Table 5.3.11-0: Heading Input Select 0 SIGNAL CONNECTION (X) = J1-22 (Y) = J1-23 (Z) = J1-3 Reference (H) = J1-4 (C) = J1-24 CONNECTION Magnetic Heading PIN FUNCTION Magnetic Heading Validity Discrete REFERENCE 6.1.9 4.2.4.2 4.2.4.4 CHANNEL DESIGNATION REFERENCE 28V_DISC_10 PIN TYPE J1-28 SUMMARY DATA Format: 5 Wire Synchro with Validity Flag Input Type: Basic Fault Designation: MAGNETIC HEADING FAULT Validity: Magnetic Heading Validity Discrete (+28V) Reference: Nominal 26 VAC Input Polarity/Configuration References >+17V = Valid < +4.4V = Invalid 6.6.23 4.2.7 Table 5.3.11-2: Heading Input Select Type 2 CHANNEL 429RX_7 A = J2-23 B = J2-6 Fault Designation: AHRS BUS Bus Type: Basic CONNECT TO: AHRS Format: ARINC 429 (High Speed) Data Magnetic Heading Reference 6.2.32 Label 320 Sig. Bits 15 Range ±180 degrees Signal Type Basic Resolution 0.0054931640625 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 255 Rate (ms) 10-20 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.11-3: Heading Input Select Type 3 CHANNEL 429RX_7 A = J2-23 B = J2-6 Fault Designation: AHRS BUS Bus Type: Basic CONNECT TO: AHRS Format: ARINC 429 (High Speed) Data Magnetic Heading True Heading Reference 6.2.32 6.2.37 Label 320 314 Sig. Bits 15 15 Range ±180 degrees ±180 degrees Signal Type Basic Basic Resolution 0.0054931640625 0.0054931640625 Rate (ms) 10-20 25-50 Table 5.3.11-254: Heading Input Select 254 CHANNEL 429/422RX_1 A = J2-37 B = J2-36 CHANNEL 429RX_3 A = J2-41 B = J2-40 CONNECT TO: IOC #1 Format: ARINC 429 (High Speed) Data True Heading Reference 6.2.32 CONNECT TO: IOC #2 Format: ARINC 429 (High Speed) Data True Heading Reference 6.2.32 Fault Designation: IOC BUS 1 Bus Type: Basic Label 314 Sig. Bits 15 Range ±180 degrees Signal Type Basic Resolution 0.0054931640625 Rate (ms) 25-50 Signal Type Basic Resolution 0.0054931640625 Rate (ms) 25-50 Signal Type Basic Resolution 0.0054931640625 Rate (ms) 25-50 Signal Type Basic Resolution 0.0054931640625 Rate (ms) 25-50 Fault Designation: IOC BUS 2 Bus Type: Basic Label 314 Sig. Bits 15 Range ±180 degrees Table 5.3.11-255: Heading Input Select 255 CHANNEL 429/422RX_1 A = J2-37 B = J2-36 CHANNEL 429RX_3 A = J2-41 B = J2-40 CONNECT TO: IOC #1 Format: ARINC 429 (High Speed) Data Magnetic Heading Reference 6.2.32 CONNECT TO: IOC #2 Format: ARINC 429 (High Speed) Data Magnetic Heading Reference 6.2.32 Fault Designation: IOC BUS 1 Bus Type: Basic Label 320 Sig. Bits 15 Range ±180 degrees Fault Designation: IOC BUS 2 Bus Type: Basic Label 320 Sig. Bits 15 Range ±180 degrees Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 256 Honeywell MK VI MK VIII EGPWS Installation Design Guide 5.3.12 Category 12, Windshear Input Select The following table provides identification of the Windshear Input Type. The entry in the Windshear Input Type corresponds to a table that provides detailed information on the configuration. For example, the details for Windshear Input Type #255 are found in 5.3.12-255. In this category, only the following signals are to be defined: • • Body Angle of Attack (AOA) in ARINC 429 format Normalized Angle of Attack (AOA) in ARINC 429 format Table 5.3.12: Windshear Input Select ID Windshear Input Type 0 N/A 253 255 254 255 255 255 Description No Windshear Digital – ARINC 429 AOA (via Dual IOC buses). (Note 1) Digital – ARINC 429 AOA (via Dual IOC buses). (Note 1) Digital – ARINC 429 AOA (via Dual IOC buses). (Note 1) Windshear Disable Windshear INOP Disable Windshear Caution TRUE TRUE FALSE Software Effectivity Disable Windshear Caution Voice Disable EGPWS Effectivity MKVI MKVIII TRUE TRUE -020 X X FALSE TRUE TRUE -020 N/A X FALSE FALSE FALSE TRUE -020 N/A X FALSE FALSE FALSE FALSE -020 N/A X Note 1: IDs 253, 254, and 255 may only be used in conjunction with other IOC bus selections for categories 2, 6, 8, 9, 10, and 11. Table 5.3.12-255: Windshear Input Type 255 CHANNEL 429RX_1 CONNECT TO: IOC #1 Bus Format: ARINC 429 (High Speed) Fault Designation: IOC BUS 1 Bus Type: Basic A = J2-37 B = J2-36 CHANNEL 429RX_3 Data Reference Left Angle of Attack Body 6.2.44 Normal Angle of Attack 6.2.52 CONNECT TO: IOC #2 Bus Format: ARINC 429 (High Speed) Label 224 236 A = J2-41 B = J2-40 Data Right Angle of Attack Body Normal Angle of Attack Reference 6.2.45 6.2.52 Sig. Bits 12 15 Range ±180 degrees 0 to 1 Signal Type Basic Basic Resolution 0.0439453125 deg 0.00003051757812 Rate (ms) 100 80 Signal Type Basic Basic Resolution 0.0439453125 deg 0.00003051757812 Rate (ms) 100 80 Fault Designation: IOC BUS 2 Bus Type: Basic Label 225 236 Sig. Bits 12 15 Range ±180 degrees 0 to 1 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 257 Honeywell MK VI MK VIII EGPWS Installation Design Guide 5.3.13 Category 13, Input / Output Discrete Type Select The following table provides identification of the Input/Output Discrete Type. Each entry in the Input/Output Discrete Type column has a corresponding table that provides detailed information on the configuration. For example, the details for Input/Output Discrete Type #0 are found in Table 5.3.13-0. Table 5.3.13: Input/Output Discrete Type Select ID Input/Output Discrete Type (Table 5.3.13-x) 0 0 1 1 2 2 3 3 4 4 5 5 6 6 7 7 254 254 255 255 Software Effectivity Description Input / Output discrete definitions (Lamp format 1) Input / Output discrete definitions (Lamp format 2) Input / Output discrete definitions (Lamp format 1) with GPWS Inhibit Input / Output discrete definitions (Lamp format 2) with GPWS Inhibit Input / Output discrete definitions (Lamp format 1, Flashing lamps) with GPWS Inhibit. Input / Output discrete definitions (Lamp format 2, Flashing lamps) with GPWS Inhibit. Input / Output discrete definitions (Lamp format 1) with GPWS Inhibit and Mom. Steep Approach Select. Input / Output discrete definitions (Lamp format 2) with GPWS Inhibit and Mom. Steep Approach Select. Windshear Input / Output discrete definitions (Lamp Format 1). Windshear Input / Output discrete definitions (Lamp Format 2). EGPWS Effectivity MKVI MKVIII -020 X X -020 X X -020 X X -020 X X -020 X X -020 X X -020 X X -020 X X -020 N/A X -020 N/A X Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 258 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.13-0: Input/Output Discrete Type 0 CONN PIN # CHANNEL DESIGNATION REFERENCE PIN TYPE J1-38 28V_DISC_02 Input +28V Glideslope Inhibit Discrete 6.6.12 J1-19 GND_DISC_02 Input GND Glideslope Inhibit Discrete 6.6.11 J1-37 28V_DISC_03 Input +28V Landing Flaps Discrete 6.6.5 J1-18 GND_DISC_03 Input GND Landing Flaps Discrete 6.6.4 J1-36 28V_DISC_04 Input +28V Audio Inhibit Discrete 6.6.17 J1-17 GND_DISC_04 Input GND Audio Inhibit Discrete 6.6.16 J1-35 28V_DISC_05 Input +28V Landing Gear Discrete 6.6.3 J1-16 GND_DISC_05 Input GND Landing Gear Discrete 6.6.2 J1-15 GND_DISC_06 Input Glideslope Cancel Discrete (Note 1,4) 6.6.13 J1-14 GND_DISC_07 Input Momentary Flap Override Discrete (Note 1,4) 6.6.6 J1-13 GND_DISC_08 Input Mode 6 Low Volume Discrete 6.6.15 J1-8 28V_DISC_09 Input Autopilot Engaged Discrete #1 6.6.21 J1-12 GND_DISC_09 Input Terrain Awareness & TCF Inhibit Discrete (Note 2,4) 6.6.20 J1-34 GND_DISC_10 Input Self-Test Discrete (Note 1,4) 6.6.7 J2-31 GND_DISC_15 Input J1-72 MON_OUT_1 Output PIN FUNCTION Steep Approach Discrete #2 (Note 2) (alternate action) GPWS INOP Discrete TAD INOP Discrete Terrain Not Available GPWS Warning Discrete Terrain Awareness Caution or Warning Obstacle Awareness Caution or Warning Ref 6.6.25 MON_OUT_2 Output J1-78 DISC_OUT_1 Output J1-77 DISC_OUT_2 Output GPWS Alert Discrete (Glideslope Only) 7.4.1 J1-76 DISC_OUT_3 Output Glideslope Cancel Discrete 7.4.6 J1-73 DISC_OUT_4 Output Flap Override Discrete 7.4.5 J1-69 DISC_OUT_5 Output Audio On Discrete 7.4.2 J1-54 DISC_OUT_6 Output Terrain Display Select #1 Discrete 7.4.4 DISC_OUT_8 Output J1-49 DISC_OUT_9 Output J1-48 J2-15 J1-50 J1-52 28V_DISC_11 28V_DISC_13 MON_OUT_3 DISC_OUT_7 Input Input Output Output Not Defined in this ID. (Note 3) Not Defined in this ID. (Note 3) Not Defined in this ID. (Note 3) Not Defined in this ID. (Note 3) J1-51 Configuration Data Lamp Format Flashing Lamps >+17V = Inhibit <+4.4V = Not Inhibit Gnd = Inhibit Gnd = Not Inhibit >+17V = Flaps Up <+4.4V = Not Flaps Up Gnd = Flaps Up Gnd = Not Flaps Up >+17V = Inhibit <+4.4V = Not Inhibit Gnd = Inhibit Gnd = Not Inhibit >+17V = Gear Down <+4.4V = Gear Up Gnd = Gear Down Gnd = Gear Up Gnd = Cancel Toggle Gnd = Normal Gnd = Flap Override Toggle Gnd = Normal Gnd = Low Volume Gnd = Normal >+17V = Engaged <+4.4V = Not Engaged Gnd = Inhibit Gnd = Not Inhibit Gnd = Self-Test Toggle Gnd = Normal Gnd = Selected Gnd = Not Selected 7.4.3 J1-55 Terrain Awareness Caution or Warning Obstacle Awareness Caution or Warning Terrain Display Select #2 Discrete Polarity/Configuration 7.4.3 7.4.1 7.4.7.1 7.4.7.2 7.4.7.3 Gnd = Terrain Pop Up 7.4.4 Possible States Type 1,Type 2 True, False State Type 1 False Note 1: Provided by Momentary cockpit switch (non-latching) Note 2: Provided by Alternate cockpit switch (Latching) with guard if inhibiting. Note 3: This discrete may be used in another category. Note 4: Function is provided as an OR operation of the physical discrete and the 429 discrete word bit, if configured by the display type. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 259 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.13-1: Input/Output Discrete Type 1 CONN PIN # CHANNEL DESIGNATION REFERENCE PIN TYPE J1-38 28V_DISC_02 Input +28V Glideslope Inhibit Discrete 6.6.12 J1-19 GND_DISC_02 Input GND Glideslope Inhibit Discrete 6.6.11 J1-37 28V_DISC_03 Input +28V Landing Flaps Discrete 6.6.5 J1-18 GND_DISC_03 Input GND Landing Flaps Discrete 6.6.4 J1-36 28V_DISC_04 Input +28V Audio Inhibit Discrete 6.6.17 J1-17 GND_DISC_04 Input GND Audio Inhibit Discrete 6.6.16 J1-35 28V_DISC_05 Input +28V Landing Gear Discrete 6.6.3 J1-16 GND_DISC_05 Input GND Landing Gear Discrete 6.6.2 J1-15 GND_DISC_06 Input Glideslope Cancel Discrete (Note 1,4) 6.6.13 J1-14 GND_DISC_07 Input Momentary Flap Override Discrete (Note 1,4) 6.6.6 J1-13 GND_DISC_08 Input Mode 6 Low Volume Discrete 6.6.15 J1-8 28V_DISC_09 Input Autopilot Engaged Discrete #1 6.6.21 J1-12 GND_DISC_09 Input Terrain Awareness & TCF Inhibit Discrete (Note 2,4) 6.6.20 J1-34 GND_DISC_10 Input Self-Test Discrete (Note 1,4) 6.6.7 J2-31 GND_DISC_15 Input Steep Approach Discrete #2 (Note 2) (alternate action) 6.6.25 J1-72 MON_OUT_1 Output J1-55 MON_OUT_2 Output J1-78 DISC_OUT_1 Output J1-77 DISC_OUT_2 Output PIN FUNCTION Ref J1-76 DISC_OUT_3 Output GPWS INOP Discrete TAD INOP Discrete Terrain Not Available GPWS Warning Discrete Terrain Awareness Warning Obstacle Awareness Warning GPWS Alert Discrete Terrain Awareness Caution Obstacle Awareness Caution Glideslope Cancel Discrete J1-73 DISC_OUT_4 Output Flap Override Discrete J1-69 DISC_OUT_5 Output Audio On Discrete 7.4.2 J1-54 DISC_OUT_6 Output 7.4.4 J1-51 DISC_OUT_8 Output J1-49 J1-48 J2-15 J1-50 J1-52 DISC_OUT_9 28V_DISC_11 28V_DISC_13 MON_OUT_3 DISC_OUT_7 Output Input Input Output Output Terrain Display Select #1 Discrete Terrain Awareness Caution or Warning Obstacle Awareness Caution or Warning Terrain Display Select #2 Discrete Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). Configuration Data Lamp Format Flashing Lamps Polarity/Configuration >+17V = Inhibit <+4.4V = Not Inhibit Gnd = Inhibit Gnd = Not Inhibit >+17V = Flaps Up <+4.4V = Not Flaps Up Gnd = Flaps Up Gnd = Not Flaps Up >+17V = Inhibit <+4.4V = Not Inhibit Gnd = Inhibit Gnd = Not Inhibit >+17V = Gear Down <+4.4V = Gear Up Gnd = Gear Down Gnd = Gear Up Gnd = Cancel Toggle Gnd = Normal Gnd = Flap Override Toggle Gnd = Normal Gnd = Low Volume Gnd = Normal >+17V = Engaged <+4.4V = Not Engaged Gnd = Inhibit Gnd = Not Inhibit Gnd = Self-Test Toggle Gnd = Normal Gnd = Selected Gnd = Not Selected 7.4.3 7.4.3 7.4.1 7.4.7.2 7.4.1 7.4.7.1 7.4.6 7.4.5 7.4.7.3 Gnd = Terrain Pop Up 7.4.4 Possible States Type 1,Type 2 True, False State Type 2 False Note 1: Provided by Momentary cockpit switch (non-latching) Note 2: Provided by Alternate cockpit switch (Latching) with guard if inhibiting. Note 3: This discrete may be used in another category. Note 4: Function is provided as an OR operation of the physical discrete and the 429 discrete word bit, if configured by the display type. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 260 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.13-2: Input/Output Discrete Type 2 CONN PIN # CHANNEL DESIGNATION REFERENCE PIN TYPE J1-38 28V_DISC_02 Input +28V Glideslope Inhibit Discrete 6.6.12 J1-19 GND_DISC_02 Input GND Glideslope Inhibit Discrete 6.6.11 J1-37 28V_DISC_03 Input +28V Landing Flaps Discrete 6.6.5 J1-18 GND_DISC_03 Input GND Landing Flaps Discrete 6.6.4 J1-36 28V_DISC_04 Input +28V Audio Inhibit Discrete 6.6.17 J1-17 GND_DISC_04 Input GND Audio Inhibit Discrete 6.6.16 J1-35 28V_DISC_05 Input +28V Landing Gear Discrete 6.6.3 J1-16 GND_DISC_05 Input GND Landing Gear Discrete 6.6.2 J1-15 GND_DISC_06 Input Glideslope Cancel Discrete (Note 1,4) 6.6.13 J1-14 GND_DISC_07 Input Momentary Flap Override Discrete (Note 1,4) 6.6.6 J1-13 GND_DISC_08 Input Mode 6 Low Volume Discrete 6.6.15 J1-8 28V_DISC_09 Input Autopilot Engaged Discrete #1 6.6.21 J1-12 GND_DISC_09 Input Terrain Awareness & TCF Inhibit Discrete (Note 2,4) 6.6.20 J1-34 GND_DISC_10 Input Self-Test Discrete (Note 1,4) 6.6.7 J1-67 GND_DISC_14 Input GPWS Inhibit Discrete 6.6.27 J2-31 GND_DISC_15 Input Steep Approach Discrete #2 (Note 2) (alternate action) 6.6.25 J1-72 MON_OUT_1 Output J1-55 MON_OUT_2 Output J1-78 DISC_OUT_1 Output J1-77 DISC_OUT_2 Output PIN FUNCTION GPWS INOP Discrete TAD INOP Discrete Terrain Not Available GPWS Warning Discrete Terrain Awareness Caution or Warning Obstacle Awareness Caution or Warning Ref >+17V = Inhibit <+4.4V = Not Inhibit Gnd = Inhibit Gnd = Not Inhibit >+17V = Flaps Up <+4.4V = Not Flaps Up Gnd = Flaps Up Gnd = Not Flaps Up >+17V = Inhibit <+4.4V = Not Inhibit Gnd = Inhibit Gnd = Not Inhibit >+17V = Gear Down <+4.4V = Gear Up Gnd = Gear Down Gnd = Gear Up Gnd = Cancel Toggle Gnd = Normal Gnd = Flap Override Toggle Gnd = Normal Gnd = Low Volume Gnd = Normal >+17V = Engaged <+4.4V = Not Engaged Gnd = Inhibit Gnd = Not Inhibit Gnd = Self-Test Toggle Gnd = Normal Gnd = Inhibit Gnd = Not Inhibit Gnd = Selected Gnd = Not Selected 7.4.3 7.4.3 7.4.1 7.4.7.1 7.4.7.2 GPWS Alert Discrete (Glideslope Only) 7.4.1 J1-76 DISC_OUT_3 Output Glideslope Cancel Discrete 7.4.6 J1-73 DISC_OUT_4 Output Flap Override Discrete 7.4.5 J1-69 DISC_OUT_5 Output Audio On Discrete 7.4.2 J1-54 DISC_OUT_6 Output 7.4.4 J1-51 DISC_OUT_8 Output J1-49 J1-48 J2-15 J1-50 J1-52 DISC_OUT_9 28V_DISC_11 28V_DISC_13 MON_OUT_3 DISC_OUT_7 Output Input Input Output Output Terrain Display Select #1 Discrete Terrain Awareness Caution or Warning Obstacle Awareness Caution or Warning Terrain Display Select #2 Discrete Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). Configuration Data Lamp Format Flashing Lamps Polarity/Configuration 7.4.7.3 Gnd = Terrain Pop Up 7.4.4 Possible States Type 1,Type 2 True, False State Type 1 False Note 1: Provided by Momentary cockpit switch (non-latching) Note 2: Provided by Alternate cockpit switch (Latching) with guard if inhibiting. Note 3: This discrete may be used in another category. Note 4: Function is provided as an OR operation of the physical discrete and the 429 discrete word bit, if configured by the display type. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 261 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.13-3: Input/Output Discrete Type 3 CONN PIN # CHANNEL DESIGNATION REFERENCE PIN TYPE PIN FUNCTION Ref J1-38 28V_DISC_02 Input +28V Glideslope Inhibit Discrete 6.6.12 J1-19 GND_DISC_02 Input GND Glideslope Inhibit Discrete 6.6.11 J1-37 28V_DISC_03 Input +28V Landing Flaps Discrete 6.6.5 J1-18 GND_DISC_03 Input GND Landing Flaps Discrete 6.6.4 J1-36 28V_DISC_04 Input +28V Audio Inhibit Discrete 6.6.17 J1-17 GND_DISC_04 Input GND Audio Inhibit Discrete 6.6.16 J1-35 28V_DISC_05 Input +28V Landing Gear Discrete 6.6.3 J1-16 GND_DISC_05 Input GND Landing Gear Discrete 6.6.2 J1-15 GND_DISC_06 Input Glideslope Cancel Discrete (Note 1,4) 6.6.13 J1-14 GND_DISC_07 Input Momentary Flap Override Discrete (Note 1,4) 6.6.6 J1-13 GND_DISC_08 Input Mode 6 Low Volume Discrete 6.6.15 J1-8 28V_DISC_09 Input Autopilot Engaged Discrete #1 6.6.21 J1-12 GND_DISC_09 Input Terrain Awareness & TCF Inhibit Discrete (Note 2) 6.6.20 J1-34 GND_DISC_10 Input Self-Test Discrete (Note 1,4) 6.6.7 J1-67 GND_DISC_14 Input GPWS Inhibit Discrete 6.6.27 J2-31 GND_DISC_15 Input Steep Approach Discrete #2 (Note 2) (alternate action) 6.6.25 J1-72 MON_OUT_1 Output J1-55 MON_OUT_2 Output J1-78 DISC_OUT_1 Output J1-77 DISC_OUT_2 Output J1-76 DISC_OUT_3 J1-73 J1-69 Output GPWS INOP Discrete TAD INOP Discrete Terrain Not Available GPWS Warning Discrete Terrain Awareness Warning Obstacle Awareness Warning GPWS Alert Discrete Terrain Awareness Caution Obstacle Awareness Caution Glideslope Cancel Discrete 7.4.6 DISC_OUT_4 Output Flap Override Discrete 7.4.5 DISC_OUT_5 Output Audio On Discrete 7.4.2 J1-54 DISC_OUT_6 Output 7.4.4 J1-51 DISC_OUT_8 Output J1-49 J1-48 J2-15 J1-50 J1-52 DISC_OUT_9 28V_DISC_11 28V_DISC_13 MON_OUT_3 DISC_OUT_7 Output Input Input Output Output Terrain Display Select #1 Discrete Terrain Awareness Caution or Warning Obstacle Awareness Caution or Warning Terrain Display Select #2 Discrete Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). Configuration Data Lamp Format Flashing Lamps Polarity/Configuration >+17V = Inhibit <+4.4V = Not Inhibit Gnd = Inhibit Gnd = Not Inhibit >+17V = Flaps Up <+4.4V = Not Flaps Up Gnd = Flaps Up Gnd = Not Flaps Up >+17V = Inhibit <+4.4V = Not Inhibit Gnd = Inhibit Gnd = Not Inhibit >+17V = Gear Down <+4.4V = Gear Up Gnd = Gear Down Gnd = Gear Up Gnd = Cancel Toggle Gnd = Normal Gnd = Flap Override Toggle Gnd = Normal Gnd = Low Volume Gnd = Normal >+17V = Engaged <+4.4V = Not Engaged Gnd = Inhibit Gnd = Not Inhibit Gnd = Self-Test Toggle Gnd = Normal Gnd = Inhibit Gnd = Not Inhibit Gnd = Selected Gnd = Not Selected 7.4.3 7.4.3 7.4.1 7.4.7.2 7.4.1 7.4.7.1 7.4.7.3 Gnd = Terrain Pop Up 7.4.4 Possible States Type 1,Type 2 True, False State Type 2 False Note 1: Provided by Momentary cockpit switch (non-latching) Note 2: Provided by Alternate cockpit switch (Latching) with guard if inhibiting Note 3: This discrete may be used in another category. Note 4: Function is provided as an OR operation of the physical discrete and the 429 discrete word bit, if configured by the display type. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 262 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.13-4: Input/Output Discrete Type 4 CONN PIN # CHANNEL DESIGNATION REFERENCE PIN TYPE J1-38 28V_DISC_02 Input +28V Glideslope Inhibit Discrete 6.6.12 J1-19 GND_DISC_02 Input GND Glideslope Inhibit Discrete 6.6.11 J1-37 28V_DISC_03 Input +28V Landing Flaps Discrete 6.6.5 J1-18 GND_DISC_03 Input GND Landing Flaps Discrete 6.6.4 J1-36 28V_DISC_04 Input +28V Audio Inhibit Discrete 6.6.17 J1-17 GND_DISC_04 Input GND Audio Inhibit Discrete 6.6.16 J1-35 28V_DISC_05 Input +28V Landing Gear Discrete 6.6.3 J1-16 GND_DISC_05 Input GND Landing Gear Discrete 6.6.2 J1-15 GND_DISC_06 Input Glideslope Cancel Discrete (Note 1,4) 6.6.13 J1-14 GND_DISC_07 Input Momentary Flap Override Discrete (Note 1,4) 6.6.6 J1-13 GND_DISC_08 Input Mode 6 Low Volume Discrete 6.6.15 J1-8 28V_DISC_09 Input Autopilot Engaged Discrete #1 6.6.21 J1-12 GND_DISC_09 Input Terrain Awareness & TCF Inhibit Discrete (Note 2,4) 6.6.20 J1-34 GND_DISC_10 Input Self-Test Discrete (Note 1,4) 6.6.7 J1-67 GND_DISC_14 Input GPWS Inhibit Discrete 6.6.27 J2-31 GND_DISC_15 Input Steep Approach Discrete #2 (Note 2) (alternate action) 6.6.25 J1-72 MON_OUT_1 Output J1-55 MON_OUT_2 Output J1-76 DISC_OUT_3 J1-73 J1-69 PIN FUNCTION Ref Output GPWS INOP Discrete TAD INOP Discrete Terrain Not Available Glideslope Cancel Discrete 7.4.6 DISC_OUT_4 Output Flap Override Discrete 7.4.5 DISC_OUT_5 Output Audio On Discrete 7.4.2 J1-54 DISC_OUT_6 Output 7.4.4 J1-51 DISC_OUT_8 Output J1-49 J1-48 J2-15 J1-50 J1-52 DISC_OUT_9 28V_DISC_11 28V_DISC_13 MON_OUT_3 DISC_OUT_7 Output Input Input Output Output Terrain Display Select #1 Discrete Terrain Awareness Caution or Warning Obstacle Awareness Caution or Warning Terrain Display Select #2 Discrete Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). GPWS Warning Discrete (Flashing) Terrain Awareness Caution or Warning (Flashing) Obstacle Awareness Caution or Warning (Flashing) GPWS Alert Discrete (Glideslope Only) (Flashing) 7.4.1 7.4.7.1 7.4.7.2 7.4.1 J1-78 J1-77 DISC_OUT_1 Output DISC_OUT_2 Output Configuration Data Lamp Format Flashing Lamps Polarity/Configuration >+17V = Inhibit <+4.4V = Not Inhibit Gnd = Inhibit Gnd = Not Inhibit >+17V = Flaps Up <+4.4V = Not Flaps Up Gnd = Flaps Up Gnd = Not Flaps Up >+17V = Inhibit <+4.4V = Not Inhibit Gnd = Inhibit Gnd = Not Inhibit >+17V = Gear Down <+4.4V = Gear Up Gnd = Gear Down Gnd = Gear Up Gnd = Cancel Toggle Gnd = Normal Gnd = Flap Override Toggle Gnd = Normal Gnd = Low Volume Gnd = Normal >+17V = Engaged <+4.4V = Not Engaged Gnd = Inhibit Gnd = Not Inhibit Gnd = Self-Test Toggle Gnd = Normal Gnd = Inhibit Gnd = Not Inhibit Gnd = Selected Gnd = Not Selected 7.4.3 7.4.3 7.4.7.3 Gnd = Terrain Pop Up 7.4.4 Flashing Lamps Yes Yes Yes Yes Possible States Type 1,Type 2 True, False State Type 1 True Note 1: Provided by Momentary cockpit switch (non-latching) Note 2: Provided by Alternate cockpit switch (Latching) with guard if inhibiting. Note 3: This discrete may be used in another category. Note 4: Function is provided as an OR operation of the physical discrete and the 429 discrete word bit, if configured by the display type. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 263 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.13-5: Input/Output Discrete Type 5 CONN PIN # CHANNEL DESIGNATION REFERENCE PIN TYPE J1-38 28V_DISC_02 Input +28V Glideslope Inhibit Discrete 6.6.12 J1-19 GND_DISC_02 Input GND Glideslope Inhibit Discrete 6.6.11 J1-37 28V_DISC_03 Input +28V Landing Flaps Discrete 6.6.5 J1-18 GND_DISC_03 Input GND Landing Flaps Discrete 6.6.4 J1-36 28V_DISC_04 Input +28V Audio Inhibit Discrete 6.6.17 J1-17 GND_DISC_04 Input GND Audio Inhibit Discrete 6.6.16 J1-35 28V_DISC_05 Input +28V Landing Gear Discrete 6.6.3 J1-16 GND_DISC_05 Input GND Landing Gear Discrete 6.6.2 J1-15 GND_DISC_06 Input Glideslope Cancel Discrete (Note 1,4) 6.6.13 J1-14 GND_DISC_07 Input Momentary Flap Override Discrete (Note 1,4) 6.6.6 J1-13 GND_DISC_08 Input Mode 6 Low Volume Discrete 6.6.15 J1-8 28V_DISC_09 Input Autopilot Engaged Discrete #1 6.6.21 J1-12 GND_DISC_09 Input Terrain Awareness & TCF Inhibit Discrete (Note 2,4) 6.6.20 J1-34 GND_DISC_10 Input Self-Test Discrete (Note 1,4) 6.6.7 J1-67 GND_DISC_14 Input GPWS Inhibit Discrete 6.6.27 J2-31 GND_DISC_15 Input Steep Approach Discrete #2 (Note 2) (alternate action) 6.6.25 J1-72 MON_OUT_1 Output J1-55 MON_OUT_2 Output J1-76 DISC_OUT_3 J1-73 J1-69 PIN FUNCTION Ref Output GPWS INOP Discrete TAD INOP Discrete Terrain Not Available Glideslope Cancel Discrete 7.4.6 DISC_OUT_4 Output Flap Override Discrete 7.4.5 DISC_OUT_5 Output Audio On Discrete 7.4.2 J1-54 DISC_OUT_6 Output 7.4.4 J1-51 DISC_OUT_8 Output J1-49 J1-48 J2-15 J1-50 J1-52 DISC_OUT_9 28V_DISC_11 28V_DISC_13 MON_OUT_3 DISC_OUT_7 Output Input Input Output Output Terrain Display Select #1 Discrete Terrain Awareness Caution or Warning Obstacle Awareness Caution or Warning Terrain Display Select #2 Discrete Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). Polarity/Configuration >+17V = Inhibit <+4.4V = Not Inhibit Gnd = Inhibit Gnd = Not Inhibit >+17V = Flaps Up <+4.4V = Not Flaps Up Gnd = Flaps Up Gnd = Not Flaps Up >+17V = Inhibit <+4.4V = Not Inhibit Gnd = Inhibit Gnd = Not Inhibit >+17V = Gear Down <+4.4V = Gear Up Gnd = Gear Down Gnd = Gear Up Gnd = Cancel Toggle Gnd = Normal Gnd = Flap Override Toggle Gnd = Normal Gnd = Low Volume Gnd = Normal >+17V = Engaged <+4.4V = Not Engaged Gnd = Inhibit Gnd = Not Inhibit Gnd = Self-Test Toggle Gnd = Normal Gnd = Inhibit Gnd = Not Inhibit Gnd = Selected Gnd = Not Selected 7.4.3 7.4.3 7.4.7.3 Gnd = Terrain Pop Up 7.4.4 Flashing Lamps J1-78 DISC_OUT_1 Output J1-77 DISC_OUT_2 Output GPWS Warning Discrete Terrain Awareness Warning Obstacle Awareness Warning GPWS Alert Discrete Terrain Awareness Caution Obstacle Awareness Caution Configuration Data Lamp Format Flashing Lamps 7.4.1 7.4.7.2 7.4.1 7.4.7.1 Yes Yes Yes Yes Yes Yes Possible States Type 1,Type 2 True, False State Type 2 True Note 1: Provided by Momentary cockpit switch (non-latching) Note 2: Provided by Alternate cockpit switch (Latching) with guard if inhibiting Note 3: This discrete may be used in another category. Note 4: Function is provided as an OR operation of the physical discrete and the 429 discrete word bit, if configured by the display type. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 264 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.13-6: Input/Output Discrete Type 6 CONN PIN # CHANNEL DESIGNATION REFERENCE PIN TYPE J1-38 28V_DISC_02 Input +28V Glideslope Inhibit Discrete 6.6.12 J1-19 GND_DISC_02 Input GND Glideslope Inhibit Discrete 6.6.11 J1-37 28V_DISC_03 Input +28V Landing Flaps Discrete 6.6.5 J1-18 GND_DISC_03 Input GND Landing Flaps Discrete 6.6.4 J1-36 28V_DISC_04 Input +28V Audio Inhibit Discrete 6.6.17 J1-17 GND_DISC_04 Input GND Audio Inhibit Discrete 6.6.16 J1-35 28V_DISC_05 Input +28V Landing Gear Discrete 6.6.3 J1-16 GND_DISC_05 Input GND Landing Gear Discrete 6.6.2 J1-15 GND_DISC_06 Input Glideslope Cancel Discrete (Note 1,4) 6.6.13 J1-14 GND_DISC_07 Input Momentary Flap Override Discrete (Note 1,4) 6.6.6 J1-13 GND_DISC_08 Input Mode 6 Low Volume Discrete 6.6.15 J1-8 28V_DISC_09 Input Autopilot Engaged Discrete #1 6.6.21 J1-12 GND_DISC_09 Input Terrain Awareness & TCF Inhibit Discrete (Note 2,4) 6.6.20 J1-34 GND_DISC_10 Input Self-Test Discrete (Note 1,4) 6.6.7 J1-67 GND_DISC_14 Input GPWS Inhibit Discrete 6.6.27 J2-31 GND_DISC_15 Input Steep Approach Discrete #2 (Note 1,4) (momentary) 6.6.25 J1-72 MON_OUT_1 Output J1-55 MON_OUT_2 Output J1-78 DISC_OUT_1 Output J1-77 DISC_OUT_2 Output PIN FUNCTION GPWS INOP Discrete TAD INOP Discrete Terrain Not Available GPWS Warning Discrete Terrain Awareness Caution or Warning Obstacle Awareness Caution or Warning Ref 7.4.3 7.4.1 7.4.7.1 7.4.7.2 7.4.1 J1-76 DISC_OUT_3 Output Glideslope Cancel Discrete 7.4.6 J1-73 DISC_OUT_4 Output Flap Override Discrete 7.4.5 J1-69 DISC_OUT_5 Output Audio On Discrete 7.4.2 J1-54 DISC_OUT_6 Output 7.4.4 J1-51 DISC_OUT_8 Output 7.4.14 J1-49 DISC_OUT_9 Output J1-52 J1-48 J2-15 J1-50 DISC_OUT_7 28V_DISC_11 28V_DISC_13 MON_OUT_3 Output Input Input Output Steep Approach Discrete Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). Configuration Data Lamp Format Flashing Lamps >+17V = Inhibit <+4.4V = Not Inhibit Gnd = Inhibit Gnd = Not Inhibit >+17V = Flaps Up <+4.4V = Not Flaps Up Gnd = Flaps Up Gnd = Not Flaps Up >+17V = Inhibit <+4.4V = Not Inhibit Gnd = Inhibit Gnd = Not Inhibit >+17V = Gear Down <+4.4V = Gear Up Gnd = Gear Down Gnd = Gear Up Gnd = Cancel Toggle Gnd = Normal Gnd = Flap Override Toggle Gnd = Normal Gnd = Low Volume Gnd = Normal >+17V = Engaged <+4.4V = Not Engaged Gnd = Inhibit Gnd = Not Inhibit Gnd = Self-Test Toggle Gnd = Normal Gnd = Inhibit Gnd = Not Inhibit Gnd = Toggle on/off Gnd = Normal 7.4.3 GPWS Alert Discrete (Glideslope Only) Terrain Display Select #1 Discrete Terrain Awareness Caution or Warning Obstacle Awareness Caution or Warning Terrain Display Select #2 Discrete Polarity/Configuration 7.4.7.3 Gnd = Terrain Pop Up 7.4.4 Possible States Type 1,Type 2 True, False State Type 1 False Note 1: Provided by Momentary cockpit switch (non-latching) Note 2: Provided by Alternate cockpit switch (Latching) with guard if inhibiting. Note 3: This discrete may be used in another category. Note 4: Function is provided as an OR operation of the physical discrete and the 429 discrete word bit, if configured by the display type. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 265 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.13-7: Input/Output Discrete Type 7 CONN PIN # CHANNEL DESIGNATION REFERENCE PIN TYPE J1-38 28V_DISC_02 Input +28V Glideslope Inhibit Discrete 6.6.12 J1-19 GND_DISC_02 Input GND Glideslope Inhibit Discrete 6.6.11 J1-37 28V_DISC_03 Input +28V Landing Flaps Discrete 6.6.5 J1-18 GND_DISC_03 Input GND Landing Flaps Discrete 6.6.4 J1-36 28V_DISC_04 Input +28V Audio Inhibit Discrete 6.6.17 J1-17 GND_DISC_04 Input GND Audio Inhibit Discrete 6.6.16 J1-35 28V_DISC_05 Input +28V Landing Gear Discrete 6.6.3 J1-16 GND_DISC_05 Input GND Landing Gear Discrete 6.6.2 J1-15 GND_DISC_06 Input Glideslope Cancel Discrete (Note 1,4) 6.6.13 J1-14 GND_DISC_07 Input Momentary Flap Override Discrete (Note 1,4) 6.6.6 J1-13 GND_DISC_08 Input Mode 6 Low Volume Discrete 6.6.15 J1-8 28V_DISC_09 Input Autopilot Engaged Discrete #1 6.6.21 J1-12 GND_DISC_09 Input Terrain Awareness & TCF Inhibit Discrete (Note 2,4) 6.6.20 J1-34 GND_DISC_10 Input Self-Test Discrete (Note 1,4) 6.6.7 J1-67 GND_DISC_14 Input GPWS Inhibit Discrete 6.6.27 J2-31 GND_DISC_15 Input Steep Approach Discrete #2 (Note 1,4) (momentary) 6.6.25 J1-72 MON_OUT_1 Output J1-55 MON_OUT_2 Output J1-78 DISC_OUT_1 Output J1-77 DISC_OUT_2 Output J1-76 DISC_OUT_3 J1-73 J1-69 PIN FUNCTION Ref Output GPWS INOP Discrete TAD INOP Discrete Terrain Not Available GPWS Warning Discrete Terrain Awareness Warning Obstacle Awareness Warning GPWS Alert Discrete Terrain Awareness Caution Obstacle Awareness Caution Glideslope Cancel Discrete 7.4.6 DISC_OUT_4 Output Flap Override Discrete 7.4.5 DISC_OUT_5 Output Audio On Discrete 7.4.2 J1-54 DISC_OUT_6 Output 7.4.4 J1-51 DISC_OUT_8 Output J1-49 DISC_OUT_9 Output Terrain Display Select #1 Discrete Terrain Awareness Caution or Warning Obstacle Awareness Caution or Warning Terrain Display Select #2 Discrete J1-52 J1-48 J2-15 J1-50 DISC_OUT_7 28V_DISC_11 28V_DISC_13 MON_OUT_3 Output Input Input Output Steep Approach Discrete Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). 7.4.14 Configuration Data Lamp Format Flashing Lamps Polarity/Configuration >+17V = Inhibit <+4.4V = Not Inhibit Gnd = Inhibit Gnd = Not Inhibit >+17V = Flaps Up <+4.4V = Not Flaps Up Gnd = Flaps Up Gnd = Not Flaps Up >+17V = Inhibit <+4.4V = Not Inhibit Gnd = Inhibit Gnd = Not Inhibit >+17V = Gear Down <+4.4V = Gear Up Gnd = Gear Down Gnd = Gear Up Gnd = Cancel Toggle Gnd = Normal Gnd = Flap Override Toggle Gnd = Normal Gnd = Low Volume Gnd = Normal >+17V = Engaged <+4.4V = Not Engaged Gnd = Inhibit Gnd = Not Inhibit Gnd = Self-Test Toggle Gnd = Normal Gnd = Inhibit Gnd = Not Inhibit Gnd = Toggle on/off Gnd = Normal 7.4.3 7.4.3 7.4.1 7.4.7.2 7.4.1 7.4.7.1 7.4.7.3 Gnd = Terrain Pop Up 7.4.4 Possible States Type 1,Type 2 True, False State Type 2 False Note 1: Provided by Momentary cockpit switch (non-latching) Note 2: Provided by Alternate cockpit switch (Latching) with guard if inhibiting Note 3: This discrete may be used in another category. Note 4: Function is provided as an OR operation of the physical discrete and the 429 discrete word bit, if configured by the display type. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 266 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.13-254: Input/Output Discrete Type 254 CONN PIN # CHANNEL DESIGNATION REFERENCE PIN TYPE J1-38 28V_DISC_02 Input J1-19 GND_DISC_02 Input PIN FUNCTION Ref +28V Glideslope Inhibit Discrete 6.6.12 GND Glideslope Inhibit Discrete 6.6.11 +28V Landing Flaps Discrete/ Flap Override Switch (non-momentary) GND Landing Flaps Discrete/ Flap Override Switch (non-momentary) J1-37 28V_DISC_03 Input J1-18 GND_DISC_03 Input J1-36 28V_DISC_04 Input +28V Audio Inhibit Discrete 6.6.17 J1-17 GND_DISC_04 Input GND Audio Inhibit Discrete 6.6.16 J1-35 28V_DISC_05 Input +28V Landing Gear Discrete 6.6.3 J1-16 GND_DISC_05 Input GND Landing Gear Discrete 6.6.2 J1-15 GND_DISC_06 Input Glideslope Cancel Discrete (Note 1) 6.6.13 J1-13 GND_DISC_08 Input Mode 6 Low Volume Discrete 6.6.15 J1-8 28V_DISC_09 Input Autopilot Engaged Discrete #1 6.6.21 J1-12 GND_DISC_09 Input Terrain Awareness & TCF Inhibit Discrete (Note 2) 6.6.20 J1-34 GND_DISC_10 Input Self-Test Discrete 6.6.7 J1-67 GND_DISC_14 Input GPWS Inhibit Discrete 6.6.27 J2-31 GND_DISC_15 Input Steep Approach Discrete #2 (Note 2) (alternate action) 6.6.25 J1-72 MON_OUT_1 Output J1-55 MON_OUT_2 Output J1-50 MON_OUT_3 Output J1-78 DISC_OUT_1 Output J1-77 DISC_OUT_2 Output 6.6.5 6.6.4 GPWS INOP Discrete TAD INOP Discrete Terrain Not Available Windshear INOP GPWS Warning Discrete Terrain Awareness Caution or Warning Obstacle Awareness Caution or Warning GPWS Alert Discrete (Glideslope Only) 7.4.9 7.4.1 7.4.7.1 7.4.7.2 7.4.1 >+17V = Inhibit <+4.4V = Not Inhibit Gnd = Inhibit Gnd = Not Inhibit >+17V = Flaps Up <+4.4V = Not Flaps Up Gnd = Flaps Up Gnd = Not Flaps Up >+17V = Inhibit <+4.4V = Not Inhibit Gnd = Inhibit Gnd = Not Inhibit >+17V = Gear Down <+4.4V = Gear Up Gnd = Gear Down Gnd = Gear Up Gnd = Cancel Toggle Gnd = Normal Gnd = Low Volume Gnd = Normal >+17V = Engaged <+4.4V = Not Engaged Gnd = Inhibit Gnd = Not Inhibit Gnd = Self-Test Toggle Gnd = Normal Gnd = Inhibit Gnd = Not Inhibit Gnd = Selected Gnd = Not Selected 7.4.3 7.4.3 J1-76 DISC_OUT_3 Output Glideslope Cancel Discrete 7.4.6 J1-73 DISC_OUT_4 Output Windshear Warning Discrete 7.4.10 J1-52 DISC_OUT_7 Output Windshear Caution Discrete 7.4.11 J1-69 DISC_OUT_5 Output Audio On Discrete 7.4.2 J1-54 DISC_OUT_6 Output 7.4.4 J1-51 DISC_OUT_8 Output J1-49 J1-48 J1-14 J2-15 DISC_OUT_9 28V_DISC_11 GND_DISC_07 28V_DISC_13 Output Input Input Input Terrain Display Select #1 Discrete Terrain Awareness Caution or Warning Obstacle Awareness Caution or Warning Terrain Display Select #2 Discrete Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). Configuration Data Lamp Format Flashing Lamps Polarity/Configuration 7.4.7.3 Gnd = Terrain Pop Up 7.4.4 Possible States Type 1,Type 2 True, False State Type 1 False Note 1: Provided by Momentary cockpit switch (non-latching) Note 2: Provided by Alternate cockpit switch (Latching) with guard if inhibiting Note 3: This discrete may be used in another category. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 267 Honeywell MK VI MK VIII EGPWS Installation Design Guide Table 5.3.13-255: Input/Output Discrete Type 255 CONN PIN # CHANNEL DESIGNATION REFERENCE PIN TYPE J1-38 28V_DISC_02 Input J1-19 GND_DISC_02 Input PIN FUNCTION Ref +28V Glideslope Inhibit Discrete 6.6.12 GND Glideslope Inhibit Discrete 6.6.11 +28V Landing Flaps Discrete/ Flap Override Switch (non-momentary) GND Landing Flaps Discrete/ Flap Override Switch (non-momentary) J1-37 28V_DISC_03 Input J1-18 GND_DISC_03 Input J1-36 28V_DISC_04 Input +28V Audio Inhibit Discrete 6.6.17 J1-17 GND_DISC_04 Input GND Audio Inhibit Discrete 6.6.16 J1-35 28V_DISC_05 Input +28V Landing Gear Discrete 6.6.3 J1-16 GND_DISC_05 Input GND Landing Gear Discrete 6.6.2 J1-15 GND_DISC_06 Input Glideslope Cancel Discrete (Note 1) 6.6.13 J1-13 GND_DISC_08 Input Mode 6 Low Volume Discrete 6.6.15 J1-8 28V_DISC_09 Input Autopilot Engaged Discrete #1 6.6.21 J1-12 GND_DISC_09 Input Terrain Awareness & TCF Inhibit Discrete (Note 2) 6.6.20 J1-34 GND_DISC_10 Input Self-Test Discrete (Note 1) 6.6.7 J1-67 GND_DISC_14 Input GPWS Inhibit Discrete 6.6.27 J2-31 GND_DISC_15 Input Steep Approach Discrete #2 (Note 2) 6.6.25 J1-72 MON_OUT_1 Output 7.4.3 J1-55 MON_OUT_2 Output J1-50 MON_OUT_3 Output J1-78 DISC_OUT_1 Output J1-77 DISC_OUT_2 Output 7.4.6 6.6.5 6.6.4 J1-76 DISC_OUT_3 Output GPWS INOP Discrete TAD INOP Discrete Terrain Not Available Windshear INOP GPWS Warning Discrete Terrain Awareness Warning Obstacle Awareness Warning GPWS Alert Discrete Terrain Awareness Caution Obstacle Awareness Caution Glideslope Cancel Discrete J1-73 DISC_OUT_4 Output Windshear Warning Discrete 7.4.10 J1-52 DISC_OUT_7 Output Windshear Caution Discrete 7.4.11 J1-69 DISC_OUT_5 Output Audio On Discrete 7.4.2 J1-54 DISC_OUT_6 Output 7.4.4 J1-51 DISC_OUT_8 Output Terrain Display Select #1 Discrete Terrain Awareness Caution or Warning Obstacle Awareness Caution or Warning J1-49 J1-48 J1-14 J2-15 DISC_OUT_9 28V_DISC_11 GND_DISC_07 28V_DISC_13 Output Input Input Input Terrain Display Select #2 Discrete Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). Not Defined in this ID (Note 3). 7.4.4 Configuration Data Lamp Format Flashing Lamps Polarity/Configuration >+17V = Inhibit <+4.4V = Not Inhibit Gnd = Inhibit Gnd = Not Inhibit >+17V = Flaps Up <+4.4V = Not Flaps Up Gnd = Flaps Up Gnd = Not Flaps Up >+17V = Inhibit <+4.4V = Not Inhibit Gnd = Inhibit Gnd = Not Inhibit >+17V = Gear Down <+4.4V = Gear Up Gnd = Gear Down Gnd = Gear Up Gnd = Cancel Toggle Gnd = Normal Gnd = Low Volume Gnd = Normal >+17V = Engaged <+4.4V = Not Engaged Gnd = Inhibit Gnd = Not Inhibit Gnd = Self-Test Toggle Gnd = Normal Gnd = Inhibit Gnd = Not Inhibit Gnd = Selected Gnd = Not Selected 7.4.3 7.4.9 7.4.1 7.4.7.2 7.4.1 7.4.7.1 7.4.7.3 Possible States Type 1,Type 2 True, False Gnd = Terrain Pop Up State Type 2 False Note 1: Provided by Momentary cockpit switch (non-latching) Note 2: Provided by Alternate cockpit switch (Latching) with guard if inhibiting Note 3: This discrete may be used in another category. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 268 Honeywell MK VI MK VIII EGPWS Installation Design Guide 5.3.14 Category 14, Audio Output Level The following table provides identification of the Audio Output Level Select. Each entry in the ID column corresponds to a particular nominal alert output level selection (Max, -6 dB, -12 dB, -18dB and –24dB). The nominal “Max” output is 4 W(rms) for the 8-ohm output and 100 mW(rms) for the 600-ohm output. The Audio Output Level can be additionally reduced by 6dB with the Mode 6 Low Volume discrete (see Category 13). The output power level will be the nominal maximum output (4W or 100mW) reduced by the volume selection from Table 5.3.14 and the Mode 6 Low Volume discrete. Table 5.3.14: Audio Output Level ID 0 1 2 3 4 Software Effectivity Volume Select -020 -020 -020 -020 -020 Nominal (Equivalent to classic MK VI MAX) -6 dB -12 dB -18 dB -24 dB 5.3.15 Category 15, Undefined for this software release The following table provides identification for a future undefined input select category. The entry in the following undefined Type corresponds to a table that will provide detailed information on the configuration. The details for Undefined Type #0 are not detailed. Table 5.3.15: Undefined Type ID Undefined Type 0 N/A Description Software Effectivity -020 EGPWS MKVI MKVIII X X 5.3.16 Category 16, Undefined for this software release The following table provides identification for a future undefined input select category. The entry in the following undefined Type corresponds to a table that will provide detailed information on the configuration. The details for Undefined Type #0 are not detailed. Table 5.3.16: Undefined Type ID Undefined Type 0 N/A Description Software Effectivity -020 EGPWS MKVI MKVIII X X 5.3.17 Category 17, Undefined for this software release The following table provides identification for a future undefined input select category. The entry in the following undefined Type corresponds to a table that will provide detailed information on the configuration. The details for Undefined Type #0 are not detailed. Table 5.3.17: Undefined Type ID 0 Undefined Type Description Software Effectivity N/A -020 EGPWS MKVI MKVIII X X Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 269 Honeywell MK VI MK VIII EGPWS Installation Design Guide 6 CONFIGURABLE INPUT DATA DEFINITION This section defines the EGPWS input signal characteristics or data word formats for input signals commonly used in MK VI and VIII EGPWS applications. See Section 5 for specific information on signal usage. 6.1 Analog Input Data 6.1.1 ARINC 552 Radio Altimeter Data Item Signal Name: AIC Algorithm: Signal Dynamic Range: Signal Reasonable Range: Signal Open Wire Threshold Reference Dynamic Range: Reference Reasonable Range: Scale: Value Radio Altitude, ARINC 552 ARINC 552A Radio Altitude –100 to +3566 Feet –30 to +2800 Feet –50 Feet None None For Radio Altitude ≤ 480 feet: Voltsin = (0.02 * RALT (ft)) + 0.4 For Radio Altitude > 480 feet: Voltsin = 10 × (1 + Ln ( Input Signal Connection: Input Reference Connection: AIC Name: External Validity Flag Connection: AIC LSB: AIC Status Mask: External Validity Type: RALT (ft) + 20 500 )) (+) = J1-64, (–) = J1-45 None D1 (DC1) J1-29 0.25 Feet 0000200C Discrete Validity 6.1.2 ALT 55 Radio Altimeter Data Item Signal Name: AIC Algorithm: Signal Dynamic Range: Signal Reasonable Range: Signal Open Wire Threshold Reference Dynamic Range: Reference Reasonable Range: Scale: Input Signal Connection: Input Reference Connection: AIC Name: External Validity Flag Connection: AIC LSB: AIC Status Mask: External Validity Type: Value Radio Altitude, ALT 55 DC Absolute –100 to +3200 Feet –30 to +2800 Feet –50 Feet None None For Radio Altitude ≤ 500 Feet (≤ 10.4 VDC): Voltsin = (0.02 * RALT) + 0.4 or RALT (ft) = 50 ft/VDC * Voltsin – 20 ft For Radio Altitude > 500 feet (> 10.4 VDC): Voltsin = 0.003 * (RALT –500) + 10.4 or RALT (ft) = 333.3333 ft/VDC * Voltsin – 2966.7 (+) = J1-64, (–) = J1-45 None D1 (DC1) J1-29 0.25 Feet 0000200C Discrete Validity Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 270 Honeywell MK VI MK VIII EGPWS Installation Design Guide 6.1.3 Uncorrected Barometric Altitude Data Item Signal Name: AIC Algorithm: Signal Dynamic Range: Signal Reasonable Range: Signal Open Wire Threshold Reference Dynamic Range: Reference Reasonable Range: Scale: Input Signal Connection: Input Reference Connection: AIC Name: External Validity Flag Connection: AIC LSB: AIC Status Mask: External Validity Type: Value Uncorrected Baro Altitude, DC Voltage DC Absolute –19,334 to +31,166 Feet –1500 to +30,000 Feet –3000 Feet None None Altitude (Feet) = 3150 Feet/VDC * Volts – 17250 Feet (+) = J1-62, (–) = J1-43 None D2 (DC2) J1-9 2 Feet 0000200F Discrete Validity 6.1.4 Outside Air Temperature (500 ohm probe) Data Item Signal Name: AIC Algorithm: Signal Dynamic Range: Signal Reasonable Range: Signal Open Wire Threshold Reference Dynamic Range: Reference Reasonable Range: Scale: Input Signal Connection: Input Reference Connection: AIC Name: External Validity Flag Connection: AIC LSB: AIC Status Mask: External Validity Type: Value Outside Air Temperature, DC Signal DC Absolute –85 to +60 °C –70 to +60 °C –80 °C None None VOAT OAT (in °C) < 0.43448 525.50676* VOAT – 268.805 >= 0.43448 and < 0.49212 545.64369* VOAT – 277.560 >= 0.49212 and < 0.54816 566.02357* VOAT – 287.594 >= 0.54816 581.96990* VOAT – 296.270 (+) = J1-63, (–) = J1-44 (see section 5.3.2 for hookup) None D5 (DC5) None 0.03125 °C 0000200F None 6.1.5 Outside Air Temperature (Internal Constant) Data Item Signal Name: AIC Algorithm: Signal Dynamic Range: Signal Reasonable Range: Signal Open Wire Threshold Reference Dynamic Range: Reference Reasonable Range: Scale: Input Signal Connection: Input Reference Connection: AIC Name: Value Outside Air Temperature, DC Signal DC Absolute Constant, no external connection Constant, no external connection None None None OAT (in °C) = 25°C Constant (no external connection) None None Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 271 Honeywell MK VI MK VIII EGPWS Installation Design Guide External Validity Flag Connection: AIC LSB: AIC Status Mask: External Validity Type: None 0.03125 °C 00000000 None 6.1.6 ARINC 547/578-4 Low Level Glideslope Deviation with Discrete Valid Data Item Signal Name: AIC Algorithm: Signal Dynamic Range: Signal Reasonable Range: Signal Open Wire Threshold Reference Dynamic Range: Reference Reasonable Range: Scale: Input Signal Connection: Input Reference Connection: AIC Name: External Validity Flag Connection: AIC LSB: AIC Status Mask: External Validity Type: Value Low Level Glideslope Deviation, DC Signal DC Absolute ±16 Dots ±12 Dots –15 Dots None None GS Deviation (Dots) = 13.333333 Dots/VDC * Voltsin – (Positive = Fly Down) (75 mV per DOT, 0 Volts = 0 DOT) NOTE: To be consistent with the ARINC 429 definition G/S scaling inverts sign of input signal such that positive numbers are fly down. (+) = J1-65 (above beam), (–) = J1-46 (below beam) None D3 (DC3) J1-11 (+28 VDC discrete) 0.00048828 Dots 0000200C Discrete Validity 6.1.7 ARINC 547/578-4 Low Level Glideslope Deviation with Low Level Valid Data Item Signal Name: AIC Algorithm: Signal Dynamic Range: Signal Reasonable Range: Signal Open Wire Threshold Reference Dynamic Range: Reference Reasonable Range: Scale: Input Signal Connection: Input Reference Connection: AIC Name: External Validity Flag Connection: AIC LSB: AIC Status Mask: External Validity Type: Value Low Level Glideslope Deviation, DC Signal DC Absolute ±16 Dots ±12 Dots –15 Dots None None GS Deviation (Dots) = 13.333333 Dots/VDC * Voltsin – (Positive = Fly Down) (75 mV per DOT, 0 Volts = 0 DOT) NOTE: To be consistent with the ARINC 429 definition G/S scaling inverts sign of input signal such that positive numbers are fly down. (+) = J1-65 (above beam), (–) = J1-46 (below beam) None D3 (DC3) (+) = J1-30, (–) = J1-10 (GS low level validity see 6.1.21) 0.00048828 Dots 0000200C Low Level Validity 6.1.8 Roll Attitude, 3 Wire Synchro (11.8 VAC ) Data Item Signal Name: AIC Algorithm: Signal Dynamic Range: Signal Reasonable Range: Value Roll Attitude, 3 Wire Synchro 3 Wire Synchro (11.8 VAC) ±90° Synchro Angle (15.5 VAC max) ±80° Synchro Angle Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 272 Honeywell MK VI MK VIII EGPWS Installation Design Guide Signal Open Wire Threshold Reference Dynamic Range: Reference Reasonable Range: Scale: Input Signal Connection: Input Reference Connection: AIC Name: External Validity Flag Connection: AIC FIFO LSB: AIC Status Mask: External Validity Type: None None None Roll Angle (deg) = 1 deg/deg (X) = J1-1, (Y) = J1-21, (Z) = J1-2 None S1 (Synchro #1) None 0.00549316° 0000010F None 6.1.9 Magnetic Heading, 5 Wire Synchro The Magnetic Heading will be corrected with the internal Magnetic Variable Table. Data Item Value Signal Name: Magnetic Heading, 5 Wire Synchro AIC Algorithm: 5 Wire Synchro (11.8V) Signal Dynamic Range: ±180° Synchro Angle (15.5 VAC max) Signal Reasonable Range: ±180° Signal Open Wire Threshold None Reference Dynamic Range: 17 - 34 VAC Reference Reasonable Range: None Scale: Mag Hdg (deg) = 1 deg/deg Input Signal Connection: (X) = J1-22, (Y) = J1-23, (Z) = J1-3 Input Reference Connection: (H) = J1-4, (C) = J1-24 AIC Name: S2 (Synchro #2) External Validity Flag Connection: J1-28 AIC FIFO LSB: 0.00549316° AIC Status Mask: 0000070F External Validity Type: Discrete Validity, +28VDC 6.1.10 Uncorrected Barometric Altitude (ADS-65) Data Item Signal Name: AIC Algorithm: Signal Dynamic Range: Signal Reasonable Range: Signal Open Wire Threshold Reference Dynamic Range: Reference Reasonable Range: Scale: Input Signal Connection: Input Reference Connection: AIC Name: External Validity Flag Connection: AIC LSB: AIC Status Mask: External Validity Type: Value Uncorrected Baro Altitude, DC Voltage DC Absolute –5514 to +128,080 Feet –1500 to +46,000 Feet –3000 Feet None None Altitude (Feet) = 8333.33 Feet/VDC * Volts (+) = J1-62, (–) = J1-43 None D2 (DC2) J1-9 2 Feet 0000200F Discrete Validity 6.1.11 RT-221/300 Radio Altimeter Data Item Signal Name: AIC Algorithm: Value Radio Altitude, RT-221/300 DC Absolute Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 273 Honeywell MK VI MK VIII EGPWS Installation Design Guide Signal Dynamic Range: Signal Reasonable Range: Signal Open Wire Threshold Reference Dynamic Range: Reference Reasonable Range: Scale: Input Signal Connection: Input Reference Connection: AIC Name: External Validity Flag Connection: AIC LSB: AIC Status Mask: External Validity Type: –100 to +3200 Feet –30 to +2800 Feet –50 Feet None None RALT (ft) = 250 ft/VDC * Voltsin (+) = J1-64, (–) = J1-45 None D1 (DC1) J1-29 0.25 Feet 0000200C Discrete Validity 6.1.12 Pitch Synchro Attitude, 3 Wire Synchro (11.8 VAC ) Data Item Signal Name: AIC Algorithm: Signal Dynamic Range: Signal Reasonable Range: Signal Open Wire Threshold Reference Dynamic Range: Reference Reasonable Range: Scale: Input Signal Connection: Input Reference Connection: AIC Name: External Validity Flag Connection: AIC FIFO LSB: AIC Status Mask: External Validity Type: Value Pitch Attitude, 3 Wire Synchro 3 Wire Synchro (11.8 VAC) ±90° Synchro Angle (15.5 VAC max) ±80° Synchro Angle None None None Pitch Angle (deg) = 1 deg/deg (X) = J1-5, (Y) = J1-7, (Z) = J1-6 None S3 (Synchro #3) J1-68 (Common Validity with Roll Attitude 6.1.15) 0.00549316° 0000010F Discrete Validity 6.1.13 Uncorrected Barometric Altitude (CIC 02702) Data Item Signal Name: AIC Algorithm: Signal Dynamic Range: Signal Reasonable Range: Signal Open Wire Threshold Reference Dynamic Range: Reference Reasonable Range: Scale: Input Signal Connection: AIC Name: Input Reference Connection: External Validity Flag Connection: AIC LSB: AIC Status Mask: External Validity Type: Value Uncorrected Baro Altitude, DC Voltage DC Absolute –3713 to +62,017 Feet –1000 to +40,000 Feet –3000 Feet None None Altitude (Feet) = 4100 Feet/VDC * Volts – 1000 Feet (+) = J1-62, (–) = J1-43 D2 (DC2) None J1-9 2 Feet 0000200F Discrete Validity Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 274 Honeywell MK VI MK VIII EGPWS Installation Design Guide 6.1.14 ARINC 547/578-4 Low Level Glideslope Deviation Validity Data Item Signal Name: AIC Algorithm: Signal Dynamic Range: Signal Reasonable Range: Signal Open Wire Threshold Reference Dynamic Range: Reference Reasonable Range: Scale: Input Signal Connection: Input Reference Connection: AIC Name: External Validity Flag Connection: AIC LSB: AIC Status Mask: External Validity Type: Value Low Level Glideslope Validity, DC Signal DC Absolute –1.1 to +1.5 VDC –0.5 to +1.5 VDC –1 VDC None None GS Validity (VDC) = Voltsin (+) = J1-30, (–) = J1-10 None D4 (DC4) None 0.0012207 VDC 0000200C None 6.1.15 Roll Attitude, 3 Wire Synchro (11.8 VAC ) with Validity Data Item Signal Name: AIC Algorithm: Signal Dynamic Range: Signal Reasonable Range: Signal Open Wire Threshold Reference Dynamic Range: Reference Reasonable Range: Scale: Input Signal Connection: Input Reference Connection: AIC Name: External Validity Flag Connection: AIC FIFO LSB: AIC Status Mask: External Validity Type: Value Roll Attitude, 3 Wire Synchro 3 Wire Synchro (11.8 VAC) ±90° Synchro Angle (15.5 VAC max) ±80° Synchro Angle None None None Roll Angle (deg) = 1 deg/deg (X) = J1-1, (Y) = J1-21, (Z) = J1-2 None S1 (Synchro #1) J1-68 0.00549316° 0000010F Discrete Validity 6.1.16 Uncorrected Barometric Altitude (AZ-241, AZ-800) Data Item Signal Name: AIC Algorithm: Signal Dynamic Range: Signal Reasonable Range: Signal Open Wire Threshold Reference Dynamic Range: Reference Reasonable Range: Scale: Input Signal Connection: AIC Name: Input Reference Connection: External Validity Flag Connection: Value Uncorrected Baro Altitude, DC Voltage DC Absolute –3750 to +52,750 Feet (0.0 Vdc to +11.30 Vdc) –1000 to +50,000 Feet (+0.55 Vdc to +10.75 Vdc) –1950 Feet (+0.36 Vdc) None None Altitude (Feet) = 5000 Feet/VDC * Volts – 3750 (0.2 mVdc/foot, 0.75 Vdc = 0 feet) (+) = J1-62, (–) = J1-43 D2 (DC2) None J1-9 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 275 Honeywell MK VI MK VIII EGPWS Installation Design Guide AIC LSB: AIC Status Mask: External Validity Type: 2 Feet 0000200F Discrete Validity, 28V 6.1.17 ARINC 547 Localizer Deviation with Discrete Valid Data Item Signal Name: AIC Algorithm: Signal Dynamic Range: Signal Reasonable Range: Signal Open Wire Threshold Reference Dynamic Range: Reference Reasonable Range: Scale: Input Signal Connection: Input Reference Connection: AIC Name: External Validity Flag Connection: AIC LSB: AIC Status Mask: External Validity Type: Value LocalizerDeviation, DC Signal DC Absolute ±16 Dots ±12 Dots –15 Dots None None Loc Deviation (Dots) = 13.333333 Dots/VDC * Voltsin Positive = Fly Right 75 mV per DOT, 0 Volts = 0 DOT (+) = J1-30 (fly right), (–) = J1-10 (fly left) None D4 (DC4) J1-48 (+28 VDC discrete) 0.00126 Dots 0000200C Discrete Validity 6.2 Digital Input Data, ARINC 429 The MK VI/VIII EGPWC supports 8 ARINC 429 digital receivers used to monitor broadcast data from other LRUs and to support interactive protocols. Each receiver channel follows the characteristics of reference document Digital Information Transfer System (DITS), ARINC Characteristic 429. Transmission System Interconnect. Each 429 receiver shall be connected to an ARINC 429 transmitter by means of a single twisted and shielded pair of wires. The shield shall be grounded at both ends and at all production breaks in the cable to an aircraft ground close to the rack connector. Receiver Bus Frequency. Receivers are capable of operating at both Low and High speed and are determined by configuration selection. The following table identifies the bus speed characteristics. Bus Speed High Low Bus Frequency 100 KBPS +/- 1% 12.0 KBPS to 14.5 KBPS ARINC Receiver Bus Identification. Each ARINC Receiver Channel is identified with two identifiers, one for each leg of the twisted wire pair. The identifier is formed as follows: 429RX[Channel Id][Leg] where Channel Id ranges [1-8], and Leg is A for the positive leg and B for the negative leg (see channel 1 exception in following paragraph). An example of a channel identifier would be 429RX-2A, which identifies leg A of ARINC 429 channel 2. In addition, one of the ARINC 429 channels is connected to an UART to provision for RS422 operation. In this case the channel identifier has been defined as 429_422RX_1A and 429_422RX_1B SIGN/STATUS Matrix The number of BITS, and the meaning of these BITS, varies depending on the type of data in the ARINC word. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 276 Honeywell MK VI MK VIII EGPWS Installation Design Guide BIT 31 0 0 1 1 BINARY (BNR) DATA DEFINITION Failure Warning No Computed Data (NCD) Functional Test Normal Operation BIT 30 0 1 0 1 BIT 29 DEFINITION Plus, North, East, Right, To, Above Minus, South, West, Left, From, Below 0 1 BINARY CODED DECIMAL (BCD) DATA BIT 30 DEFINITION 0 Plus, North, East, Right, To, Above 1 No Computed Data (NCD) 0 Functional Test 1 Minus, South, West, Left, From, Below BIT 31 0 0 1 1 Unless identified as using the Honeywell Discrete definition all data indicated as ‘Discrete’ uses the following SSM definition. (Note that PWS uses a non-standard SSM format as described in section 6.2.21) BIT 31 0 0 1 1 DISCRETE DATA BIT 30 DEFINITION 0 Normal Operation 1 No Computed Data NCD 0 Functional Test 1 Not Used Data identified as Honeywell Discrete uses the SSM definition below. HONEYWELL DISCRETE DATA BIT 31 BIT 30 DEFINITION 0 0 Normal Operation 0 1 No Computed Data NCD 1 0 Functional Test 1 1 Failure Warning ISO 5 ALPHABET Some ARINC 429 labels transmit data using the ISO 5 alphabet as defined in the following table. B4 0 B3 0 B2 0 B1 0 0 0 0 NUL 0 0 1 0 1 0 SP 0 1 1 0 1 0 0 1 0 1 P 0 0 0 0 0 0 0 0 0 1 1 1 0 1 1 0 0 1 1 0 1 0 1 0 CNTRL STX ETX EOT ENQ ACK DC1 DC2 DC3 DC4 NAK SYN ! “ # % & 1 2 3 4 5 6 A B C D E F Q R S T U V 0 1 1 1 ‘ 7 G W 1 0 0 0 CLEAR ( 8 H X 1 1 0 0 0 1 1 0 EVENT ) * 9 : I J Y Z LOGOFF 1 1 0 MCDU MENU PROG PERF INIT DATA FPLN RAD NAV FUEL PRED SEL F-PLN SPARE 1 1 1 SEL1 SEL2 SEL3 SEL4 SEL5 SEL6 NEXT PAGE SER1 SER2 SER3 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 277 Honeywell MK VI MK VIII EGPWS Installation Design Guide B4 1 1 B3 0 1 B2 1 0 B1 1 0 0 0 0 0 0 1 1 1 1 1 0 1 1 0 DEGREE SYMBOL BOX ↓ 1 1 1 1 0 1 0 + , 0 1 1 ; < 1 0 0 K L 1 0 1 [ \ . = > M N ] ↑ / ? O ← → 1 1 0 1 1 1 SER4 SER5 SER6 TRIANGLE DIAMOND 6.2.1 Uncorrected Barometric Altitude (203) Source: ARINC 706 DADC or IOC UNCORRECTED BAROMETRIC ALTITUDE LABEL (Octal) 203 Units: Feet Approx. LSB: 1 Foot Max. Range: ± 131,072 Feet Data Bits: 12 to 28 = 17 + = Above Sea Level (ASL) Sign Bit: 29 Pad Bits: 11 Transmit Interval (mSec): 31.3 to 62.5 Data Type: 2’s Complement Binary SDI Bits: 9, 10 (50 if DAU) 6.2.2 Static Air Temperature (213) Source: ARINC 706 DADC or IOC STATIC AIR TEMPERATURE LABEL (Octal) 213 Units: Degrees Celsius Max. Range: 512 Degrees C. Approx. LSB: 0.25 Degree Data Bits: 18 to 28 = 11 + = Above ZERO Sign Bit: 29 Pad Bits: 11 to 17 Transmit Interval (mSec): 250 to 500 Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.3 Barometric Altitude Rate (212) Source: ARINC 706 DADC or IOC BAROMETRIC ALTITUDE RATE LABEL (Octal) 212 Units: Feet/Minute Approx. LSB: 16 Ft/Min Max. Range: ± 32,768 Ft/Min Data Bits: 18 to 28 = 11 + = Ascent Sign Bit: 29 Pad Bits: 11 to 17 Transmit Interval (mSec): 31.3 to 62.5 Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.4 Altitude (076) - GPS (MSL) ALTITUDE – GPS (MSL) LABEL (Octal) 076 Units: Feet Data Bits: 9 to 28 = 20 + = Up Transmit Interval (mSec): 1000 Maximum Source: ARINC 743(A) GPSSU Max. Range: 131,072 Feet Approx. LSB: 0.125 Foot Sign Bit: 29 Pad Bits: None Data Type: 2’s Complement Binary SDI Bits: None 6.2.5 Horizontal Integrity Limit (130) - GPS Source: ARINC 743(A) GPS GPS Horizontal Integrity Limit LABEL (Octal) 130 Units: Nautical Miles Max. Range: 16 Approx. LSB: 0.00012207 Data Bit: 12 - 28 (see table below) = 17 + = always positive Sign Bit: N/A Pad Bits: N/A Transmit Interval (mSec): 1000 ms Data Type: BNR + discrete SDI Bits: 9, 10 Bit 11 12 – 28 BIT ASSIGNMENT GPS HIL Definition Set to 1 whenever the receivers RAIM detects a non-isolatable satellite failure (NISF), set to 0 otherwise Integrity limit in nautical miles 6.2.6 Ground Speed (112) - GPS Source: ARINC 743(A) GPSSU Ground Speed – GPS LABEL (Octal) 112 Units: Knots Max. Range: 4,096 Knots Approx. LSB: 0.125 Knot Data Bits: 14 to 28 = 15 + = Forward Sign Bit: 29 Pad Bits: 11 to 13 Transmit Interval (mSec): 1000 Maximum Data Type: 2’s Complement Binary SDI Bits: 9, 10 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 278 Honeywell MK VI MK VIII EGPWS Installation Design Guide 6.2.7 Latitude (110) - GPS Source: ARINC 743(A) GPSSU LATITUDE – GPS LABEL (Octal) 110 Units: Degrees Approx. LSB: 0.000172 Deg Max. Range: ± 180 Degrees Data Bits: 9 to 28 = 20 + = North Sign Bit: 29 Pad Bits: None Transmit Interval (mSec): 1000 Maximum Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.8 Longitude (111) - GPS Source: ARINC 743(A) GPSSU LONGITUDE – GPS LABEL (Octal) 111 Units: Degrees Approx. LSB: 0.000172 Deg Max. Range: ± 180 Degrees Data Bits: 9 to 28 = 20 + = East Sign Bit: 29 Pad Bits: None Transmit Interval (mSec): 1000 Maximum Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.9 Track Angle (103) - GPS Source: ARINC 743(A) GPSSU TRACK ANGLE – GPS LABEL (Octal) 103 Units: Degrees Approx. LSB: 0.0055 Deg. Max. Range: ± 180 Degrees Data Bits: 15 to 29 = 15 + = Clockwise from North Sign Bit: 29 Pad Bits: 11 to 14 Transmit Interval (mSec): 1000 Maximum Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.10 Horizontal Figure Of Merit (247) – GPS (ARINC 743A) Source: ARINC 743A GPSSU HORIZONTAL FIGURE OF MERIT - GPS LABEL (Octal) 247 Units: Nautical Miles Max. Range: 16 NM’s Approx. LSB: 0.000061035 Data Bits: 11 to 28 = 18 + = N/A Sign Bit: 29 Pad Bits: N/A Transmit Interval (mSec): 1000 Maximum Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.11 Horizontal Figure Of Merit (247) – GPS (ARINC 743) Source: ARINC 743 GPSSU HORIZONTAL FIGURE OF MERIT - GPS LABEL (Octal) 247 Units: Meters Max. Range: 1,024 Approx. LSB: 0.03125 Data Bits: 14 to 28 = 15 + = N/A Sign Bit: 29 Pad Bits: 11 to 13 Transmit Interval (mSec): 1000 Maximum Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.12 Horizontal Figure Of Merit from HDOP (101) – GPS (ARINC 743) Source: ARINC 743 GPSSU HORIZONTAL FIGURE OF MERIT – GPS LABEL (Octal) 101 Units: Meters Max. Range: 16,384* Approx. LSB: 0.5* Data Bits: 14 to 28 = 15 + = N/A Sign Bit: 29 Pad Bits: 11 to 13 Transmit Interval (mSec): 1000 Maximum Data Type: 2’s Complement Binary SDI Bits: 9, 10 * The HDOP scaling is multiplied by 16 to produce HFOM values required by the EGPWS 6.2.13 Vertical Figure Of Merit (136) – GPS (ARINC 743A) Source: ARINC 743A GPSSU VERTICAL FIGURE OF MERIT – GPS LABEL (Octal) 136 Units: Feet Max. Range: 32,768 ft Approx. LSB: 0.125 Data Bits: 11 to 28 = 18 + = N/A Sign Bit: 29 Pad Bits: N/A Transmit Interval (mSec): 1000 Maximum Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.14 Vertical Figure Of Merit (136) – GPS (ARINC 743) Source: ARINC 743 GPSSU VERTICAL FIGURE OF MERIT – GPS LABEL (Octal) 136 Units: Meters Max. Range: 1,024 Approx. LSB: 0.03125 Data Bits: 14 to 28 = 15 + = N/A Sign Bit: 29 Pad Bits: 11 to 13 Transmit Interval (mSec): 1000 Maximum Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.15 Vertical Figure Of Merit from VDOP (102) – GPS (ARINC 743) Source: ARINC 743 GPSSU VERTICAL FIGURE OF MERIT – GPS LABEL (Octal) 102 Units: Meters Max. Range: 16,384* Approx. LSB: 0.5* Data Bits: 14 to 28 = 15 + = N/A Sign Bit: 29 Pad Bits: 11 to 13 Transmit Interval (mSec): 1000 Maximum Data Type: 2’s Complement Binary SDI Bits: 9, 10 * The VDOP scaling is multiplied by 16 to produce VFOM values required by the EGPWS Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 279 Honeywell MK VI MK VIII EGPWS Installation Design Guide 6.2.16 Sensor Status (273) - GPS Source: ARINC 743(A) GPSSU SENSOR STATUS – GPS LABEL (Octal) 273 Units: N/A Max. Range: N/A Approx. LSB: N/A Data Bits: 11 to 29 = 19 See TABLE + = N/A Sign Bit: N/A Pad Bits: N/A Transmit Interval (mSec): 1000 Maximum Data Type: Discrete SDI Bits: 9, 10 SENSOR STATUS BIT ASSIGNMENTS DEFINITION MSB of Satellites Visible (16 to 31) DADS Status (*) Present = ‘0’ Not Present = ‘1’ DADS Source (*) Primary = ‘0’ Secondary = ‘1’ IRS/FMS Status Present = ‘0’ Not Present = ‘1’ IRS/FMS Source Primary = ‘0’ Secondary = ‘1’ Number of Satellites Visible (0 to 15) Number of Satellites Tracked (0 to 15) Current System in Use 00 = GPS 10 = GLONASS 11 = GPS/GLONASS 01 = Spare 26 - 28 Operational Mode 000 = Self Test Mode 001 = Initialization Mode 010 = Acquisition Mode 011 = Navigation Mode 100 = Altitude/Clock Aiding Mode 101 = Differential Mode 110 = Direction/Speed Aiding Mode 111 = Fault 29 MSB of Satellites Tracked (16 to 31) DADS Input is NOT required if ALTITUDE Data to GPSSU Sensor is Received from IRS/FMS Inputs. Bit No. 11 12 13 14 15 16 - 19 20 - 23 24 - 25 (*) = 6.2.17 Universal Time Correlation (125) - GPS Source: ARINC 743(A) GPSSU UNIVERSAL TIME CORRELATION (UTC) (BCD) LABEL (Octal) 125 Units: Hours:Minutes Max. Range: See NOTE 1 Approx. LSB: 0.1 Minute Data Bits: See NOTE 2 + = N/A Sign Bit: N/A Pad Bits: N/A Transmit Interval (mSec): 1000 Maximum Data Type: BCD SDI Bits: 9, 10 NOTE 1: Maximum value = 23:59.9 NOTE 2: BCD BIT Assignments per Table below: BIT NO. 11 - 14 15 - 18 19 - 22 23 - 26 27 - 29 UNIVERSAL TIME CORRELATION BIT ASSIGNMENTS DEFINITION (CFDS/GPS) DEFINITION (CAIMS) Tenths of Minutes UNITS of Minutes UNITS of Minutes TENS of Minutes TENS of Minutes UNITS of Hours UNITS of Hours TENS of Hours TENS of Hours N/A 6.2.18 Date (260) - GPS Source: [AIRBUS] - ARINC 604 CFDS/ CMC/ [GPS] - ARINC 743(A) GPSSU DATE LABEL (Octal) 260 Units: Day:Month:Year Max. Range: N/A Approx. LSB: 1 Day Data Bits: 11 to 29 = 19 See NOTE 1 + = N/A Sign Bit: N/A Pad Bits: N/A Transmit Interval (mSec): 1000 Maximum Data Type: BCD SDI Bits: 9, 10 NOTE 1: BITS 11 to 14 (4) = UNITS of the YEAR (0 to 9) BITS 15 to 18 (4) = TENS of the YEAR (0 to 9) BITS 19 to 22 (4) = UNITS of the MONTH (0 to 9) Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 280 Honeywell MK VI MK VIII EGPWS Installation Design Guide BIT 23 (1) = TENS of the MONTH (0 or 1) BITS 24 to 27 (4) = UNITS of the DAY (0 to 9) BITS 28 to 29 (2) = TENS of the DAY (0 to 3) 6.2.19 Control Word (154) - MFD CONTROL WORD – MFD LABEL (Octal) 154 Units: N/A Data Bits: Discrete word, see below Transmit Interval (mSec): 50 ms Bit No. 11 – 13 14 15 – 29 Source: MFD Max. Range: N/A + = N/A Data Type: Discrete Approx. LSB: N/A Sign Bit: N/A Pad Bits: 9, 10 SDI Bits: N/A DAU WORD BIT ASSIGNMENTS DEFINITION Not Used by EGPWC Terrain Display Overlay Active Not Used by EGPWC 6.2.20 Control Word 2 (271/273) Source: WXR Control Panel/Nav Display CONTROL WORD 2 – WXR DISPLAY WD 1 – NAV DISPLAY BUS LABEL (Octal) 271 Units: N/A Max. Range: N/A Approx. LSB: N/A For FDS-255 display the label is 273. Data Bits: Discrete word, see below + = N/A Sign Bit: N/A Pad Bits: 9, 10 Transmit Interval (mSec): 100 to 120 ms Data Type: Discrete SDI Bits: N/A Bit No. 11 12 13 14 – 23 24 – 29 CONTROL WORD 2 BIT ASSIGNMENTS DEFINITION Special Function, Not Used by EGPWC Anticlutter, Not Used by EGPWC Windshear, Not Used by EGPWC Spares Display Range as specified in the table below BITS 24 to 29 = Display Range (5 to 320NM, format as follows) Bit 29 Bit 28 Bit 27 Bit 26 Bit 25 Bit 24 RANGE 0 0 0 0 0 0 320 NM 0 0 0 0 0 1 5 NM 0 0 0 0 1 0 10 NM 0 0 0 1 0 0 20 NM 0 0 1 0 0 0 40 NM 0 1 0 0 0 0 80 NM 1 0 0 0 0 0 160 NM Note: The range bits are additive; e.g., if bits 24 and 26 = 1 then the range would be 25 NM. 6.2.20.1 Control Word 2 (271/273) Type 2 Source: IOC Bus CONTROL WORD 2 – WXR (Type 2) DISPLAY WD 1 – NAV DISPLAY BUS LABEL (Octal) 271 Units: N/A Max. Range: N/A Approx. LSB: N/A For FDS-255 display the label is 273. Data Bits: Discrete word, see below + = N/A Sign Bit: N/A Pad Bits: 9, 10 Transmit Interval (mSec): 100 ms Data Type: Discrete SDI Bits: N/A Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 281 Honeywell MK VI MK VIII EGPWS Installation Design Guide Bit No. 11–22 23 24 – 29 CONTROL WORD 2 BIT ASSIGNMENTS DEFINITION Spares Display Range Divide by 20 Display Range as specified in the table below BITS 24 to 29 = Display Range (5 to 320NM, format as follows) Bit 29 Bit 28 Bit 27 Bit 26 Bit 25 Bit 24 RANGE 0 0 0 0 0 0 320 NM 0 0 0 0 0 1 5 NM 0 0 0 0 1 0 10 NM 0 0 0 1 0 0 20 NM 0 0 1 0 0 0 40 NM 0 1 0 0 0 0 80 NM 1 0 0 0 0 0 160 NM Note: The range bits are additive; e.g., if bits 24 and 26 = 1 then the range would be 25 NM. 6.2.21 Discrete Word (155 or 176) - MFD Source: MFD or IOC #1 & IOC #2 DISCRETE WORD – MFD LABEL (Octal) 155 or 176 Units: N/A Max. Range: N/A Approx. LSB: N/A Data Bits: Discrete word, see below + = N/A Sign Bit: N/A Pad Bits: 9, 10 Transmit Interval (mSec): 50 ms Data Type: Discrete SDI Bits: N/A Bit No. 11 - 17 18 - 24 25 - 29 DAU WORD BIT ASSIGNMENTS DEFINITION Not Used by EGPWC Terrain Display Range as specified in the table below Not Used by EGPWC BITS 18 to 24 = Display Range (5 to 640 NM, Format as follows) DISPLAY RANGE BIT ASSIGNMENTS Bits 24-18 DEFINITION Bits 24-18 All 7 bits zero: 640 NM Bit 21 set: Bit 18 set: 5 NM Bit 22 set: Bit 19 set: 10 NM Bit 23 set: Bit 20 set: 20 NM Bit 24 set: DEFINITION 40 NM 80 NM 160 NM 320 NM 6.2.22 Hazard Range Output (077) Hazard Range Output - Wx RADAR LABEL (Octal) 077 Units: N/A Data Bits: Discrete word, see below Transmit Interval (mSec): 20 ms Bit No. 11 12 13 14 15 Source: Wx Radar Max. Range: N/A Approx. LSB: N/A + = N/A Sign Bit: N/A Pad Bits: 9, 10 Data Type: Discrete (non-standard SSM, see below) SDI Bits: N/A HAZARD RANGE OUTPUT BIT ASSIGNMENTS DEFINITION Event Number LSB, Not Used by EGPWC Event Number, Not Used by EGPWC Event Number MSB, Not Used by EGPWC Range (Start), 0.0625 NM, Not Used by EGPWC Range (Start), 0.125 NM, Not Used by EGPWC Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 282 Honeywell MK VI MK VIII EGPWS Installation Design Guide 16 17 18 19 20 21 22 23 24 25 26 27 28 29 Range (Start), 0.25 NM, Not Used by EGPWC Range (Start), 0.5 NM, Not Used by EGPWC Range (Start), 1 NM, Not Used by EGPWC Range (Start), 2 NM, Not Used by EGPWC Range (Start), 4 NM, Not Used by EGPWC Range (End), 0.0625 NM, Not Used by EGPWC Range (End), 0.125 NM, Not Used by EGPWC Range (End), 0.25 NM, Not Used by EGPWC Range (End), 0.5 NM, Not Used by EGPWC Range (End), 1 NM, Not Used by EGPWC Range (End), 2 NM, Not Used by EGPWC Range (End), 4 NM, Not Used by EGPWC Alert level Alert level BITS 28 & 29 = Alert Level, format as follows Bit 28 Bits 29 DEFINITION 0 0 No Alert 1 0 Level 1 (Advisory) 0 1 Level 2 (Caution) 1 1 Level 3 (Warning) BITS 30 & 31 = SSM as follows BIT 31 BIT 30 DEFINITION 0 0 Normal Operation 0 1 Invalid (fault) 1 0 Functional Test 1 1 NCD 6.2.23 Range (050) - Multifunction Signal Generator (MG) or IC600 RANGE – MG LABEL (Octal) 050 Units: N/A Data Bits: Discrete word containing both left and right ranges, see below Transmit Interval (mSec): 100 ms Source: MG Max. Range: N/A + = N/A Approx. LSB: N/A Sign Bit: N/A Pad Bits: 9, 10 Data Type: Discrete SDI Bits: N/A Note: Data format identical to EPGWC output label 050. BITS 11 to 14 = Left Terrain Display Range (0.5 to 2000NM, Format as follows) BITS 15 to 18 = Right Terrain Display Range (0.5 to 2000NM, Format as follows) MG Note: Range is on one of two buses depending on whether MG is backing up right side. Bits 14-11 Bits 18-15 0000 0001 0010 0011 0100 0101 0110 0111 DISPLAY RANGE BIT ASSIGNMENTS DEFINITION Bits 14-11 Bits 18-15 0.5 NM 1000 1.0 NM 1001 2.5 NM 1010 5.0 NM 1011 10 NM 1100 25 NM 1101 50 NM 1110 100 NM 1111 DEFINITION 150 NM 200 NM 300 NM 500 NM 1000 NM 2000 NM 600 NM 6.2.24 Query / Continuous Response (011) - KCPB QUERY / CONTINUOUS RESPONSE LABEL (Octal) 011 Units: N/A Data Bits: Discrete word Transmit Interval: Prompted Response or Continuous Response, 2-30 words/sec Max. Range: N/A + = N/A Data Type: Discrete Source: KCPB Display Approx. LSB: N/A Sign Bit: N/A Pad Bits: None SDI Bits: N/A Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 283 Honeywell MK VI MK VIII EGPWS Installation Design Guide Label 011 communicates the response to the KCPB Query / Setup Label (KCPB Label 027) or on a continuous basis. For a detailed description of the Query / Continuous Response Label 011 definition see the EGPWS Interface Methodology, 060-4303-000. 6.2.25 Key Press Data (012) – KCPB KEY PRESS DATA LABEL (Octal) 012 Units: N/A Data Bits: Discrete word Transmit Interval (mSec): 180 Source: Honeywell TDU/FMS Max. Range: N/A + = N/A Data Type: Discrete Approx. LSB: N/A Sign Bit: N/A Pad Bits: None SDI Bits: 0 TDU/FMS key press data will be transmitted using Label 012. The state of the front panel keys will be transmitted nominally every 180 ms. Keys which are being pressed will be represented as logic “1” in the appropriate bit while non pressed keys will be registered as logic “0”. For a detailed description of the Key Press / Display Mode Label 012 definition see the EGPWS Interface Methodology, 060-4303-000. KEY PRESS DATA LABEL (Octal) 012 Units: N/A Max. Range: N/A Data Bits: Discrete word + = N/A Transmit Interval (mSec): at least 200 msec Data Type: Discrete Source: KCPB Display Approx. LSB: N/A Sign Bit: N/A Pad Bits: None SDI Bits: 0 Key press / Display Mode data will be transmitted using Label 012. This is an optional label for KCPB displays. The state of the front panel keys will be transmitted nominally every 200 ms. Keys which are being pressed will be represented as logic “1” in the appropriate bit while non pressed keys will be registered as logic “0”. For a detailed description of the Key Press / Display Mode Label 012 definition see the EGPWS Interface Methodology, 060-4303-000. 6.2.26 Control Word 1 (270) CONTROL WORD 1 – WXR LABEL (Octal) 270 Units: N/A Data Bits: Discrete word, see below Transmit Interval (mSec): 100 ms Bit No. 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 Max. Range: N/A + = N/A Data Type: Discrete Source: WXR Control Panel Approx. LSB: N/A Sign Bit: N/A Pad Bits: 9, 10 SDI Bits: N/A CONTROL WORD 1 BIT ASSIGNMENTS DEFINITION Scan, Not Used by EGPWC Anticlutter, Not Used by EGPWC Stabilization, Not Used by EGPWC Mode Mode Mode Tilt, +0.25 degrees Tilt, +0.5 degrees Tilt, +1.0 degrees Tilt, +2.0 degrees Tilt, +4.0 degrees Tilt, +8.0 degrees Tilt, -16.0 degrees (sign) Gain, Bit –1 Gain, Bit –2 Gain, Bit –4 Gain, Bit –8 Gain, Bit –16 Gain, Bit –32 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 284 Honeywell MK VI MK VIII EGPWS Installation Design Guide Bits 14 to 16 = Mode, format as follows Bit 16 Bit 15 0 0 0 0 0 1 0 1 1 0 1 0 1 1 1 1 Bit 14 0 1 0 1 0 1 0 1 MODE Standby Weather Only Map Only Windshear Hazard Factor Test Windshear and Turbulence Weather and Turbulence Windshear Icon 6.2.27 Discrete Word (273) – Bendix Weather Radar Vertical Profile Mode Source: EFIS/Weather Radar Discrete Word LABEL (Octal) 273 Units: N/A Max. Range: N/A Approx. LSB: N/A Data Bit: 11 + = N/A Sign Bit: N/A Pad Bits: N/A Transmit Interval (mSec): 100 ms Data Type: Discrete SDI Bits: 9, 10 Some display systems support a vertical profile WXR display where the radar scans up and down. This mode can not support a terrain display. Therefore when this mode bit is set (indicating that the profile mode is active) the EGPWS is to treat this as a non-displayable mode. Mode bit 11 Displayable Vertical Profile On 1 No Vertical Profile Off 0 Yes 6.2.28 Discrete Word (275) – IC600 only Source: IC Discrete Word - (IC600 Packed Discrete Word 4) LABEL (Octal) 275 Units: N/A Max. Range: N/A Approx. LSB: N/A Data Bits: Bit 17: See TABLE + = N/A Sign Bit: N/A Pad Bits: N/A Transmit Interval (mSec): 500 ms Data Type: Discrete SDI Bits: 9, 10 BIT ASSIGNMENTS Discrete Data Bit Definition IC outputting MFD format Bit 17 = 1: IC Driving Display (its range is displayed) Bit 17 = 0: IC not Driving Display 6.2.29 Radio Altitude (164) Source: ARINC 707 LRRA or IOC RADIO ALTITUDE LABEL (Octal) 164 Units: Feet Approx. LSB: 0.125 Foot Max. Range: ± 8,192 Feet Data Bits: 13 to 28 = 16 + = Above Ground Level (AGL) Sign Bit: 29 Pad Bits: 11, 12 Transmit Interval (mSec): 25 to 50 Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.30 Glideslope Deviation (174 or 117) Source: ARINC 710 ILS or IOC GLIDESLOPE DEVIATION LABEL (Octal) 174 or 117 Units: See NOTE Max. Range: ± 0.8 DDM Approx. LSB: 0.000195 DDM Data Bits: 17 to 28 = 12 + = Fly Down = Above Beam C/L Sign Bit: 29 Pad Bits: 11 to 16 Transmit Interval (mSec): 33.3 to 66.6 Data Type: 2’s Complement Binary SDI Bits: 9, 10 NOTE: Units = Difference in Depth of Modulation (DDM) 0.0875 DDM = 1 ‘Dot’. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 285 Honeywell MK VI MK VIII EGPWS Installation Design Guide 6.2.31 Roll Angle (325) Source: ARINC 704 INU / IRS/ AHRS / FMS or IOC ROLL ANGLE LABEL (Octal) 325 Units: Degrees/180 Approx. LSB: 0.01099 Deg Max. Range: ± 180 Degrees Data Bits: 15 to 28 = 14 + = Right Wing Down Sign Bit: 29 Pad Bits: 11 to 14 Transmit Interval (mSec): 10 to 36 Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.32 Magnetic Heading (320) Source: ARINC 704 INU / IRS / AHRS / FMS or IOC MAGNETIC HEADING LABEL (Octal) 320 Units: Degrees/180 Approx. LSB: 0.00549 Degrees Max. Range: ± 180 Degrees Data Bits: 14 to 28 = 15 + = Clockwise from North Sign Bit: 29 Pad Bits: 11 to 13 Transmit Interval (mSec): 10 to 50 Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.33 Localizer Deviation (173 or 116) Source: ARINC 710 ILS or IOC LOCALIZER DEVIATION LABEL (Octal) 173 or 116 Units: See NOTE Max. Range: ± 0.4 DDM Approx. LSB: 0.0000977 DDM Data Bits: 17 to 28 = 12 + = Fly RIGHT = Left of Beam C/L Sign Bit: 29 Pad Bits: 11 to 16 Transmit Interval (mSec): 33.3 to 66.6 Data Type: 2’s Complement Binary SDI Bits: 9, 10 115 ms max for IAC 100 ms max for IOC NOTE: Units = Difference in Depth of Modulation (DDM) 0.0775 DDM = 1 ‘Dot’. 6.2.34 Pitch Angle (324) Source: ARINC 704 INU / IRS/ AHRS / FMS or IOC PITCH ANGLE LABEL (Octal) 324 Units: Degrees/180 Approx. LSB: 0.01099 Deg Max. Range: ± 180 Degrees Data Bits: 15 to 28 = 14 + = Nose Up Sign Bit: 29 Pad Bits: 11 to 14 Transmit Interval (mSec): 10 to 36 Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.35 Range (271) - KCPB Source: KCPB Display RANGE LABEL (Octal) 271 Units: NM Max. Range: 1023.5 Approx. LSB: 0.5 Data Bits: 19 to 29 = 11 + = N/A Sign Bit: N/A Pad Bits: 11-18 Transmit Interval (mSec): at least 200 msec. Data Type: Binary SDI Bits: 9,10 6.2.36 DSU Status Word (350) Source: DSU DSU STATUS WORD LABEL (Octal) 350 Units: N/A Max. Range: N/A Approx. LSB: N/A Data Bits: Discrete word, see below + = N/A Sign Bit: N/A Pad Bits: N/A Transmit Interval (mSec): 1000 maximum Data Type: Discrete SDI Bits: 9,10 Bit No. 11 12 13 15-14 16 17 18 DSU STATUS WORD BIT ASSIGNMENTS DEFINITION Power Up Program Memory Test (ROM_FAIL) Power Up External RAM Test (RAM_FAIL) Power Up UDI Video Dual Port RAM Test (UDIVM_FAIL) Unused (always 0) Continuous ARINC 453 Inactive Test (A453INACT_FAIL) Continuous Display Range Validity Test (DISPRING_FAIL) Continuous Unused Interrupts Test (UNUSEDINT_FAIL) Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 286 Honeywell MK VI MK VIII EGPWS Installation Design Guide 23-19 24 25 26 27 28 29 Unused (always 0) Program Pin A Status Program Pin B Status Program Pin C Status Program Pin D Status Program Pin E Status Unused (always 0) 6.2.37 True Heading (314) Source: IRS/AHRS/IOC TRUE HEADING LABEL (Octal) 314 Units: Degrees/180 Max. Range: +/- 180 Degrees Approx. LSB: 0.00549 Degrees Data Bits: 14 to 28 = 15 + = Clockwise from North Sign Bit: 29 Pad Bits: 11 to 13 Transmit Interval (mSec): 25 to 50 Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.38 Corrected Barometric Altitude (204) Source: ARINC 706 DADC or IOC CORRECTED BAROMETRIC ALTITUDE LABEL (Octal) 204 Units: Feet Max. Range: 131,072 Feet Approx. LSB: 1 Foot Data Bits: 12 to 28 = 17 + = Above Sea Level (ASL) Sign Bit: 29 Pad Bits: 11 Transmit Interval (mSec): 31.3 to 62.5 Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.39 Computed Airspeed (206) Source: ARINC 706 DADC or IOC Max. Range: 1,024 Knots Approx. LSB: 0.0625 Knot Sign Bit: 29 Pad Bits: 11 to 14 Data Type: 2’s Complement Binary SDI Bits: 9, 10 COMPUTED AIRSPEED LABEL (Octal) 206 Units: Knots Data Bits: 15 to 28 = 14 + = Forward Transmit Interval (mSec): 62.5 to 125(100 if DAU) 6.2.40 True Airspeed (210) Source: IOC Max. Range: 2,048 Knots Approx. LSB: 0.0625 Knot Sign Bit: 29 Pad Bits: 11 to 13 Data Type: 2’s Complement Binary SDI Bits: 9, 10 TRUE AIRSPEED LABEL (Octal) 210 Units: Knots Data Bits: 14 to 28 = 15 + = Forward Transmit Interval (mSec): 62.5 to 125 6.2.41 Decision Height (370) – IOC Scaling DECISION HEIGHT LABEL (Octal) 370 Units: Feet Source: IOC Max. Range: ±8192 FT See NOTE 1 Approx. LSB: 0.125 Foot Data Bits: 13 to 28 = 16 + = Above Ground Level (AGL) Sign Bit: 29 Pad Bits: 11,12 Transmit Interval (mSec): 100 to 200 Data Type: 2’s Complement Binary SDI Bits: 9, 10 NOTE 1: Some IOC configurations may only provide positive ranges (0 to 8192 Feet), however the EGPWS supports both positive and negative ranges (+/- 8192 Feet) for all configurations. NOTE 2: This label may be provided in a configuration with a single DH input or in conjunction with a selected MDA input. For those configurations which provide DH and MDA on separate labels, Format 3 applies (Format 1 is 0/0 SDI, Format 2 is Left SDI used and Format 3 is No SDI.) 6.2.42 Normal Acceleration (333) Source: IOC NORMAL ACCELERATION LABEL (Octal) 333 Units: g’s Max. Range: +/-4.0 g’s Approx. LSB: 0.000977 g’s Data Bits: 17 to 28 = 12 + = Up See NOTE Sign Bit: 29 Pad Bits: 11 to 16 Transmit Interval (mSec): 10 to 20 Data Type: 2’s Complement Binary SDI Bits: 9, 10 NOTE: Output reads 0 g’s nominal when aircraft is on the ground, or during unaccelerated flight. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 287 Honeywell MK VI MK VIII EGPWS Installation Design Guide 6.2.43 Longitudinal Acceleration (331) Source: IOC LONGITUDINAL ACCELERATION LABEL (Octal) 331 Units: g’s Max. Range: +/-4.0 g’s Approx. LSB: 0.000977 g’s Data Bits: 17 to 28 = 12 + = Forward Sign Bit: 29 Pad Bits: 11 to 16 Transmit Interval (mSec): 10 to 20 Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.44 Left Body Angle of Attack (224) Source: IOC Body Angle of Attack LABEL (Octal) 224 Units: degrees Max. Range: +/-180 degrees Approx. LSB: 0.0439 degrees Data Bits: 17 to 28 = 12 + = Nose Up Sign Bit: 29 Pad Bits: 11 to 16 Transmit Interval (mSec): 50 to 100 Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.45 Right Body Angle of Attack (225) Source: IOC Body Angle of Attack LABEL (Octal) 225 Units: degrees Max. Range: +/-180 degrees Approx. LSB: 0.0439 degrees Data Bits: 17 to 28 = 12 + = Nose Up Sign Bit: 29 Pad Bits: 11 to 16 Transmit Interval (mSec): 50 to 100 Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.46 VOR/ILS Frequency (034) Source: ARINC 710 ILS VOR/ILS Frequency LABEL (Octal) 034 Units: MHz Max. Range: 108 - 117.95MHz Approx. LSB: 10 kHz Data Bits: See NOTE + = N/A Sign Bit: N/A Pad Bits: N/A Transmit Interval (mSec): 167 to 333 Data Type: Binary Coded Decimal (BCD) SDI Bits: 9, 10 NOTE: This input is used to indicate if the VOR/ILS receiver is tuned to an ILS frequency, or to a VOR frequency. BIT #14 will be set to a ‘0’ for all VOR frequencies, and to a ‘1’ for all ILS frequencies, by the tuning information source. 6.2.47 PFD Mode Select Word (163) Source: PFD via IOC PFD MODE SELECT WORD – Type 4 LABEL (Octal) 163 Units: N/A Max. Range: N/A Approx. LSB: N/A Data Bits: See NOTE 2 and 3 + = N/A Sign Bit: N/A Pad Bits: N/A Transmit Interval (mSec): See NOTE 1 Data Type: Discrete SDI Bits: N/A NOTE 1: Transmit Interval for data from PFD via IOC is 250 mSec Maximum. NOTE 2: BITS 25 to 28 contain Binary Code for Displayed Data Source, as listed below. NOTE 3: BITS 19/20 indicate MDA selection status and BIT 21 indicates DH selection status, as listed below. BIT NO. 19, 20 21 PFD Mode Select Word DEFINITION MDA Display Selection Bit 19 Bit 20 0 0 MDA not selected 1 0 MDA selected X 1 Not used DH Display Selection 0 DH Not Selected 1 DH Selected Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 288 Honeywell MK VI MK VIII EGPWS Installation Design Guide 25 – 28 Navigation data source currently displayed on the Primary Flight Display (PFD). The table below show decimal values with bit 25 the LSB * = Values currently used by EGPWC 00 = Not Used * 08 = MLS #1 01 = Not Used * 09 = MLS #2 * 02 = VOR/LOC #1 * 10 = ILS #1 * 03 = VOR/LOC #2 * 11 = ILS #2 04 = FMS #1 12 = NOTE 1 05 = FMS #2 13 = NOTE 1 06 = FMS #3 14 = Not Used 07 = Not Used 15 = Not Used NOTE 1: Code 12 and Code 13 are currently assigned to TACAN Data source. Neither of these states are used by the EGPWC to select or evaluate input data. 6.2.48 FWC & GP Discrete Word (171) Source: FWC or GP (#1 & #2) DISCRETE WORD – FWC & GP Max. Range: N/A LABEL (Octal) 171 Units: N/A Approx. LSB: N/A Data Bits: Discrete word, see below + = N/A Sign Bit: N/A Pad Bits: none Transmit Interval (mSec): 100 Data Type: Discrete SDI Bits: 9, 10 See below Note: Several formats exist for this label. Format 1: is the default format. Format 2: will be specified if required in the Display Input Control Group. FWC or GP WORD BIT ASSIGNMENTS (Format 1) Bit No. DEFINITION Note: Not all of the following bits are necessarily used on a given aircraft, but all will be processed. The usage depends on the aircraft avionics. For example, Steep Approach is only supported in a limited number of installations, however, the bits for Steep Approach are always monitored. 9, 10 SDI: 1/0 = Left Display Range; 0/1 = Right Display Range; 0/0 & 1/1 = No Range 11-14 Self Test command codes BIT 11 12 13 14 0 0 0 0 = No Test command 0 0 1 0 = Short Level 1 Test command 0 1 0 0 = Long Level 1 Test command 0 1 1 0 = Level 2 Test command 1 0 0 0 = Level 3 Test command 1 0 1 0 = Level 4 Test command 1 1 0 0 = Level 5 Test command 1 1 1 0 = Level 6 Test command 0 0 0 1 = Self Test Cancel command 0 0 1 1 = Skip command 15 Glideslope Cancel (momentary) 16 Flap Override (alternate action) 17 Terrain Awareness & TCF Inhibit 18 Auto Range confirm (alternate action) 19 Landing Gear Down 20 Weight on Wheels 21 Low Altitude (momentary) Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 289 Honeywell MK VI MK VIII EGPWS Installation Design Guide 22 23 24 25-28 29 Timed Audio Inhibit (momentary) Reserved for EGPWS Test command Bit Steep Approach activated (alternate action) Terrain Display Range (as specified in the table below) Not Used BITS 25 to 28 = Terrain Display Range (0.5 to 2000 NM) format as follows: DISPLAY RANGE BIT ASSIGNMENTS Bits 28-25 DEFINITION Bits 28-25 DEFINITION 0000 0.5 NM 1000 150 NM 0001 1.0 NM 1001 200 NM 0010 2.5 NM 1010 300 NM 0011 5.0 NM 1011 500 NM 0100 10 NM 1100 1000 NM 0101 25 NM 1101 2000 NM 0110 50 NM 1110 600 NM 0111 100 NM 1111 1200 NM 6.2.49 Body Pitch Rate (326) Source: AHRS / IOC Body Pitch Rate LABEL (Octal) 326 Units: Deg/Sec Max. Range: +/-128 Degrees/Sec Approx. LSB: 0.0156 Deg/Sec Data Bits: 16 to 28 = 13 + = Nose Up Sign Bit: 29 Pad Bits: 11 to 15 Transmit Interval (mSec): 10 to 20 Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.50 Body Roll Rate (327) Source: AHRS / IOC Body Roll Rate LABEL (Octal) 327 Units: Deg/Sec Max. Range: +/-128 Degrees/Sec Approx. LSB: 0.0156 Deg/Sec Data Bits: 16 to 28 = 13 + = Right Wing Down Sign Bit: 29 Pad Bits: 11 to 15 Transmit Interval (mSec): 10 to 20 Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.51 Minimum Descent Altitude (170) – IOC Scaling Source: IOC Minimum Descent Altitude LABEL (Octal) 170 Units: Feet Approx. LSB: 1 Foot Max. Range: ± 65,536 Feet 1 Data Bits: 13 to 28 = 16 + = Above Sea Level (ASL) Sign Bit: 29 Pad Bits: 9 to 12 Transmit Interval (mSec): 200 Data Type: 2’s Complement Binary SDI Bits: N/A 2 Note 1: Some IOC configurations may only provide positive ranges (0 to 65536 feet), however the EGPWS supports both positive and negative ranges (±65,536 feet) for all configurations. Note 2: This label may be provided in a configuration with a single DH input or in conjunction with a selected MDA input. For those configurations which provide DH and MDA on separate labels format 3 applies (Format 1 is 0/0 SDI, Format 2 is Left SDI used and Format 3 is no SDI.) 6.2.52 Normal Angle of Attack (236) Source: IOC Normal Angle of Attack LABEL (Octal) 236 Units: N/A Max. Range: 0 to 1 Approx. LSB: 0.000031 Data Bits: 14 to 28 = 15 + = N/A Sign Bit: N/A Pad Bits: 11 to 13, 29 Transmit Interval (mSec): 80 Data Type: 2’s Complement Binary SDI Bits: 9, 10 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 290 Honeywell MK VI MK VIII EGPWS Installation Design Guide 6.2.53 North/South Velocity (166) - GPS Source: ARINC 743(A) GPSSU NORTH/SOUTH VELOCITY – GPS LABEL (Octal) 166 Units: Knots Approx. LSB: 0.125 Knots Max. Range: ± 4,096 Knots Data Bits: 14 to 28 = 15 + = North Sign Bit: 29 Pad Bits: 11 to 13 Transmit Interval (mSec): 1000 Maximum Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.54 East/West Velocity (174) - GPS Source: ARINC 743(A) GPSSU EAST/WEST VELOCITY – GPS LABEL (Octal) 174 Units: Knots Approx. LSB: 0.125 Knots Max. Range: ± 4,096 Knots Data Bits: 14 to 28 = 15 + = East Sign Bit: 29 Pad Bits: 11 to 13 Transmit Interval (mSec): 1000 Maximum Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.55 Discrete Word (017) - KMD 550/850 Source: KMD 550/850 display Discrete Word LABEL (Octal) 017 Units: N/A Max. Range: N/A Approx. LSB: N/A Data Bits: 11 + = N/A Sign Bit: N/A Pad Bits: N/A Transmit Interval (mSec): 200 Data Type: Discrete SDI Bits: 9, 10 BIT NO. 11 - 16 17 18 19 20 21 22 23 24 - 29 DISCRETE WORD BIT ASSIGNMENTS DEFINITION COMMENTS Spares Self Test Momentary Terrain Awareness Inhibit Latched Low Altitude Mode Select Momentary Timed Audio Inhibit Momentary G/S Cancel Momentary Steep Approach Momentary Flap Override Momentary Spares 6.2.56 Inertial Vertical Speed (365) Source: ARINC 704 IRS/AHRS Inertial Vertical Speed LABEL (Octal) 365 Units: FPM Max. Range: +/-32768 FPM Approx. LSB: 1 FPM Data Bits: 14 to 28 = 15 + = Ascent Sign Bit: 29 Pad Bits: 11 to 13 Transmit Interval (mSec): 20 to 40 Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.57 Inertial Altitude (361) Source: ARINC 704 IRS/AHRS Inertial Altitude LABEL (Octal) 361 Units: Feet Max. Range: +/-131,072 feet Approx. LSB: 0.125 feet Data Bits: 9 to 28 = 20 + = Above Sea Level (ASL) Sign Bit: 29 Pad Bits: None Transmit Interval (mSec): 20 to 40 Data Type: 2’s Complement Binary SDI Bits: None 6.2.58 Vertical Velocity (165) - GPS Source: ARINC 743A GPSSU Vertical Velocity – GPS LABEL (Octal) 165 Units: FPM Max. Range: +/-32,768 FPM Approx. LSB: 1 FPM Data Bits: 14 to 28 = 15 + = Ascent Sign Bit: 29 Pad Bits: 11 to 13 Transmit Interval (mSec): 1000 Maximum Data Type: 2’s Complement Binary SDI Bits: 9, 10 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 291 Honeywell MK VI MK VIII EGPWS Installation Design Guide 6.2.59 Latitude Fine (120) - GPS Source: ARINC 743(A) GPSSU Latitude Fine - GPS LABEL (Octal) 120 Units: Degrees Max. Range: +/-0.000172 Deg Approx. LSB: 8.38E-8 Deg Data Bits: 18 to 28 = 11 + = N/A Sign Bit: 29 Pad Bits: 11 to 17 Transmit Interval (mSec): 1000 Maximum Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.60 Longitude Fine (121) - GPS Source: ARINC 743(A) GPSSU Longitude Fine - GPS LABEL (Octal) 121 Units: Degrees Max. Range: +/-0.000172 Deg Approx. LSB: 8.38E-8 Deg Data Bits: 18 to 28 = 11 + = N/A Sign Bit: 29 Pad Bits: 11 to 17 Transmit Interval (mSec): 1000 Maximum Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.61 Selected Course (100) - IOC Source: IOC Selected Course (BNR) LABEL (Octal) 100 Units: Degrees/180 Max. Range: +/-180 Degrees Approx. LSB: 0.8789 Degrees Data Bits: 18 to 28 = 11 + = Clockwise from North Sign Bit: 29 Pad Bits: 11 to 17 Transmit Interval (mSec): 100 to 500 Data Type: 2’s Complement Binary SDI Bits: 9, 10 6.2.62 DH/MDA Selected (170) – DAU Scaling Source: DAU Max. Range (for DH): Max. Range (for MDA): Approx. LSB: 1 foot +/-4096 feet +/-16384 feet Data Bits (for DH): Data Bits (for MDA): + = Above Ground Level (ASL) Sign Bit: 29 Pad Bits: 11 17 to 28 = 12 15 to 28 = 14 Transmit Interval (mSec): 1000 Data Type: 2’s Complement Binary / Discrete SDI Bits: 9, 10 Note: If Signal Displayed bit 13=1, MDA Selected is mapped to bit 14. SSM for this word uses the discrete word format. DH/MDA Selected LABEL (Octal) 170 Units: Feet 6.3 Digital Data, ARINC 575 ARINC 575 data is very similar to the low speed ARINC 429 data described in the previous sections, but is one generation earlier in the aircraft serial data definition. As such, there is NO SDI Field, and the SIGN/STATUS Matrix for 2’s Complement Binary data is different, and is given below for reference. SIGN/STATUS Matrix: The number of BITS, and the meaning of these BITS, varies depending on the type of data in the ARINC 575 word. ARINC 575 BINARY (BNR) DATA BIT 31 0 0 1 1 BIT 30 0 1 0 1 DEFINITION Plus, North, East, Right, To, Above Failure Warning No Computed Data (NCD) Minus, South, West, Left, From, Below 6.3.1 Static Air Temperature (213) Source: ARINC 575 ADC STATIC AIR TEMPERATURE LABEL (Octal) 213 Units: Degrees Celsius Max. Range: 512 Degrees C. Approx. LSB: 0.5 Degree Data Bits: 20 to 29 = 10 + = Above ZERO Sign Bit: Part of SSM Pad Bits: 9 to 19 Transmit Interval (mSec): 500 Maximum Data Type: 2’s Complement Binary SDI Bits: N/A Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 292 Honeywell MK VI MK VIII EGPWS Installation Design Guide 6.3.2 Uncorrected Barometric Altitude (203) Source: ARINC 575 ADC UNCORRECTED BAROMETRIC ALTITUDE LABEL (Octal) 203 Units: Feet Approx. LSB: 1 Foot Max. Range: ± 131,072 Feet Data Bits: 13 to 29 = 17 + = Above Sea Level (ASL) Sign Bit: Part of SSM Pad Bits: 9 to 17 Transmit Interval (mSec): 62.5 Maximum Data Type: 2’s Complement Binary SDI Bits: N/A 6.3.3 Barometric Altitude Rate (212) Source: ARINC 575 ADC BAROMETRIC ALTITUDE RATE LABEL (Octal) 212 Units: Feet/Minute Approx. LSB: 10 Ft/Min Max. Range: ± 20,480 Ft/Min Data Bits: 19 to 29 = 11 + = Ascent Sign Bit: Part of SSM Pad Bits: 9 to 18 Transmit Interval (mSec): 62.5 Maximum Data Type: 2’s Complement Binary SDI Bits: N/A 6.3.4 Computed Airspeed (206) Source: ARINC 575 ADC COMPUTED AIRSPEED LABEL (Octal) 206 Units: Knots Approx. LSB: 0.125 Knot Max. Range: ± 1024 Knots Data Bits: 17 to 29 = 13 + = Forward Sign Bit: Part of SSM Pad Bits: 9 to 16 Transmit Interval (mSec): 125 Maximum Data Type: 2’s Complement Binary SDI Bits: N/A 6.4 Digital Data, RS-232 RS-232 data can be received and transmitted from an internal GPS Pxpress card in a TTL voltage level for use as a GPS source. This data can also be received from a simulator in a TIA/EIA RS-232 format, which will be emulating the GPS data format of the GPS Pxpress card. The characteristics of the GPS Pxpress data is 9600 baud, 1 stop bit, 8 bit data, odd parity. 6.4.1 Xpress GPS Packets ID 15: Lat/Lon/Estimated Horizontal Position Error Byte Data Type Units 0 Valid Flag Byte Valid = 1, Invalid = 0 1-4 Latitude Real Radians (WGS 84) 5-8 Longitude Real Radians (WGS 84) 9-12 Horizontal Position Error (*) Real Meters (*) Horizontal position error = 2 * standard deviation of horizontal position. 6.4.2 Xpress GPS Packets ID 16: Altitude/Estimated Vertical Position Error Byte Data Type Units 0 Valid Flag Byte Valid = 1, Invalid = 0 1-4 Altitude (*) Real Meters (MSL = WGS 84 - Geoid) 5-8 Vertical Position Error (**) Real Meters (*) Altitude is MSL Altitude, which is computed from WGS 84 altitude by adding the geoid correction. (**) Vertical position error = 2 * standard deviation of vertical position. 6.4.3 Xpress GPS Packets ID 17: Ground Speed/Track Angle Byte 0 1-4 5-8 Data Valid Flag Ground Speed Track Angle Type Byte Real Real Units Valid = 1, Invalid = 0 Meters/Second Degrees (0..360) Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 293 Honeywell MK VI MK VIII EGPWS Installation Design Guide 6.4.4 Xpress GPS Packets ID 18: East/North/Up Velocity Byte 0 1-4 5-8 9-12 Data Valid Flag East Velocity North Velocity Up Velocity Type Byte Real Real Real Units Valid = 1, Invalid = 0 Meters/Second Meters/Second Meters/Second 6.4.5 Xpress GPS Packets ID 1C: GPS State This packet contains information concerning the current state of the receiver subsystem. Byte Data Type Units 0 State Byte Discrete (*) 1 Integrity State Byte Bit Field (**) 2 Masked Integrity Warning Byte True = 1, False = 0 (***) 3 Bad Coverage Byte True = 1, False = 0 (****) 4 Altitude Aiding In Use Byte True = 1, False = 0 5 Nav Mode Byte Discrete (*****) 6-7 Error Status Integer Bit Field (******) (*) State (binary) 00 initialization 01 search the sky 02 acquisition 03 transition 04 navigation 05 navigation with possible data collection 06 navigation with position degradation 07 dead reckoning (**) Integrity State (true if set; false otherwise) 0 HDOP > 4.0 Set in approach mode when RAIM is not available and the computed HDOP exceeds 4.0 1 RAIM unavailable Set when RAIM is not available in the current navigation mode 2 integrity warning Set when a RAIM error is detected 3 RAIM unavailable (masked) Set when RAIM is not available in the current navigation mode and a turn is not in progress 4 approach RAIM unavailable Set when RAIM is unavailable in approach mode. This flag allows a "host" to do a crosscheck on the RAIM prediction result before it switches into approach mode. However, if the system is not currently using altitude aiding, this flag could be unnecessarily set and contradict with the RAIM prediction result, which may assume altitude aiding. Consequently, the “host” should disregard this flag when the predicted approach RAIM is available, the current NAV mode is not approach, altitude aiding is not in effect, and all satellites in the XPRESS visibility list are in a tracking state. 5 FDE unavailable Set when FDE is not available in the current navigation mode. If the FDE becomes unavailable because of shading during a turn, it will be masked for the duration of the turn. 6 FE active Set when FDE excludes a tracking satellite. 7 Pseudo integrity warning Set when a RAIM error is detected whether or not RAIM is available in the current navigation mode. (***) Masked Integrity Warning True when there is a RAIM detected error or when RAIM is not available and a turn is not in progress (****) Bad Coverage True when there is insufficient satellite coverage for RAIM or NAV Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 294 Honeywell MK VI MK VIII EGPWS Installation Design Guide (*****) NAV Mode (binary) 0 en route 1 terminal 2 approach 3 oceanic (******) Error Status (true if set; false otherwise) 0 not used 1 ROM failure 2 RAM failure 3 Nonvolatile RAM lost 4 RF failure 5 not used 6 not used 7 BaseBand ASIC failure 8 BaseBand ASIC timeout 9 not used 10 RS-232 channel 1 receiver timeout 11 EEPROM failure 12 RS-232 channel 2 fail 13 1 millisecond underflow 14 not used 15 1 millisecond overflow 6.5 Digital Data, RS-422 The MK VI and MK VIII EGPWC supports up to 3 RS-422 digital receivers (with 2 receivers having transmit capability also) used to monitor broadcast data from other LRUs and to support interactive protocols. Each receiver channel follows the characteristics of reference document EIA 422. Transmission System Interconnect. Each RS-422 receiver shall be connected to an RS-422 transmitter by means of a single twisted and shielded pair of wires. The shield shall be grounded at both ends and at all production breaks in the cable to an aircraft ground close to the rack connector. Receiver Bus Frequency. Receivers are capable of operating up to 38.4K baud and are determined by configuration selection. 6.5.1 Honeywell RS-422 Serial Control Interface (SCI) Mode/Range Word The Serial Control Interface is transmitted on an RS-422 data bus. The data stream consists of 13 words (a label byte followed by two data bytes) transmitted within 47 milliseconds. Each character consists of one bit (Low), 8 data bits with least significant bit first; an ODD parity bit and one stop bit (high). The most significant bit of the character is a label or data flag bit. The data rate of the SCI bus is 12 KBS ±0.01%. Channel 429_422RX_1 (J2-36/37) and 422RX_2 (J2-10/11) can be configured for this input. Only two of the words on the bus are decoded, Label 80 Mode/Range Word 1 and Label FF Status Word 1. 6.5.1.1 Serial Control Interface (SCI) Mode/Range Word 1 (80) Mode/Range Word 1 LABEL (Hex) 80 Units: N/A Data Bit: 1 – 8 Transmit Interval (mSec): See above Max. Range: N/A + = N/A Data Type: Discrete Source: Map Electronics Unit (MEU) Approx. LSB: N/A Sign Bit: N/A Pad Bits: N/A SDI Bits: N/A Note this is an RS-422 serial data stream not ARINC 429 so SDI and SSM for this word are not applicable. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 295 Honeywell MK VI MK VIII EGPWS Installation Design Guide DISPLAY RANGE BIT ASSIGNMENTS Bits 4 - 7 Range Bits 4 - 7 Range 0100 0.5 NM 0110 150 NM 0010 1.0 NM 1100 200 NM 1111 2.5 NM 1010 300 NM 1011 5.0 NM 0001 500 NM 1101 10 NM 0101 1000 NM 1001 25 NM 0011 2000 NM 1110 50 NM 0000 spare 1000 100 NM 0111 spare DISPLAY MODE BIT ASSIGNMENTS 1 Bits 1-3 Display Mode Displayable 000 STBY NO 001 WX YES 010 MAP NO 011 FLIGHT PLAN NO 100 TEST NO 101 WX/T YES 110 CYC NO 111 TRB NO 1 Display Mode used for “bolt-on” EDZ displays only. 6.5.1.2 Serial Control Interface (SCI) Status Word 1 (FF) Status Word 1 LABEL (Hex) FF Units: N/A Data Bit: 1 – 8 Transmit Interval (mSec): See above Max. Range: N/A + = N/A Data Type: Discrete Source: Map Electronics Unit (MEU) Approx. LSB: N/A Sign Bit: N/A Pad Bits: N/A SDI Bits: N/A STATUS WORD BIT ASSIGNMENTS BIT DEFINITION 1 SECTOR SCAN * 2 TARGET ENABLE 3 P-450 4 ERASE 5 VAR GAIN 6 SLAVE 7 RIGHT 8 0 (Always zero in data word) * Sector Scan used for “bolt-on” EDZ displays only. 6.5.2 Honeywell RS-232 Serial Control Interface for DC811 Up/Down Range The DC811 controller transmits a 6 byte data packet with spacing between bytes of 16.67 mSec. Each byte consists of one start bit (low), 8 data bits with least significant bit (LSB) first; an EVEN parity bit and one stop bit (high). The LSB of the first packet byte is set to 1 to indicate the start of the packet (the other 5 bytes will have the LSB set to 0). The data rate for this bus is 7.8125 KBS ± 0.01%. Depressing the Up or Down Range button will cause an Up or Down Range bit to be set for 1 packet period (approximately 100 mSec). After an Up or Down transition no additional changes will be allowed for approximately ½ second. EGPWS Up/Down Ranges Supported DC811 Data Packet in Nautical Miles 2.5 BYTE BIT DESCRIPTION 1 0 1=Start of packet flag 5 2 10 3 25* 4 6 1=Range increment 50 5 1 1=Range decrement 100 6 * (default on power up) Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 296 Honeywell MK VI MK VIII EGPWS Installation Design Guide 6.6 Discrete Inputs This section contains a brief description of each input discrete is used in the EGPWS. There are 28 possible discrete inputs each have one of the following input characteristics 1) 15 Open/Ground two state discretes 2) 13 Open/28VDC two state discretes The EGPWS supports the following inputs in discrete form. The Level 6 audio information specifies the voice issued when a state change occurs on the input discrete during level 6 self test. Refer to the Product Specification for self test description. 6.6.1 Analog Radio Altitude Validity Flags A Radio Altitude Validity Flag is used by the EGPWS for analog Radio Altimeter inputs. Type: Validity from ARINC 552, ALT 55 Radio Altimeter or RT-200/300 (analog). Signal Status: Valid or Invalid Level 6 Audio readout Valid => “Radio Altimeter 1 Valid” Invalid => “Radio Altimeter 1 Invalid” Radio Altitude Validity Discrete #1 6.6.2 GND Landing Gear Discrete Type: Supplied by landing gear or landing gear selector handle position-sensitive switch. This input can be paralleled with, or used exclusively by a Gear Override Switch if an alternate source of Gear Position is used. Signal Status: Landing Gear Down or Landing Gear Up Fault monitoring: Indication of landing gear selected for more than 60 seconds at airspeeds above 290 (200 for GA Slow) knots will result in a gear switch fault which will cause a GPW INOP indication. Note: This can be caused by either a gear switch fault or by the Gear Override switch being left in the on position. Level 6 Audio readout Landing Gear Down => “Landing Gear Down” Landing Gear Up => “Landing Gear Up” Landing Gear Discrete or Gear Override 6.6.3 +28V Landing Gear Discrete Type: Supplied by landing gear or landing gear selector handle position-sensitive switch. This input can be paralleled with, or used exclusively by a Gear Override Switch if an alternate source of Gear Position is used. Signal Status: Landing Gear Down or Landing Gear Up Fault monitoring: Indication of landing gear selected for more than 60 seconds at airspeeds above 290 (200 for GA Slow) knots will result in a gear switch fault which will cause a GPW INOP indication. Note: This can be caused by either a gear switch fault or by the Gear Override switch being left in the on position. +28 V Landing Gear Discrete Level 6 Audio readout Landing Gear Down => “28 Volts Landing Gear Down” Landing Gear Up => “28 Volts Landing Gear Up” Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 297 Honeywell MK VI MK VIII EGPWS Installation Design Guide 6.6.4 GND Landing Flap Discrete Type: Supplied by Flap or Flap selector handle switch. Signal Status: Landing Flaps or Not Landing Flaps Fault monitoring: Indication of landing flaps selected for more than 60 seconds at airspeeds above 250 (180 for GA Slow) knots will result in a flap switch fault which will cause a GPW INOP indication. Note: This can be caused by either a flap switch fault or by the Flap Override switch being left in the on position. Level 6 Audio readout Landing Flaps => “Landing Flaps” Not Landing Flaps => “Not Landing Flaps” GND Landing Flaps Discrete or Flap Override 6.6.5 +28V Landing Flap Discrete Type: Supplied by Flap or Flap selector handle switch. Signal Status: Landing Flaps or Not Landing Flaps Fault monitoring: Indication of landing flaps selected for more than 60 seconds at airspeeds above 250 (180 for GA Slow) knots will result in a flap switch fault which will cause a GPW INOP indication. Note: This can be caused by either a flap switch fault or by the Flap Override switch being left in the on position. Level 6 Audio readout Landing Flaps => “Landing Flaps” Not Landing Flaps => “Not Landing Flaps” +28 V Landing Flaps Discrete or Flap Override 6.6.6 Momentary Flap Override Discrete Type: Supplied by a momentarily actuated cockpit switch. Signal Status: Fault Monitoring: Flap Override activated if not active or Flap Override canceled if currently active. Activation of this input continuously for more than 15 seconds will result in the ‘Momentary Flap Override Invalid” fault which will cause a GPW INOP indication. Level 6 Audio readout Flap Override Selected => “Flap Override” Flap Override Not Selected => “Not Flap Override” Momentary Flap Override 6.6.7 Self-Test Discrete Type: Supplied by a momentarily actuated cockpit self-test switch. Signal Status: Fault Monitoring: Self Test or Normal Activation of this input continuously for more than 60 seconds will result in the ‘Self Test Invalid” fault which will cause a GPW INOP indication. Note: This input is used to start and stop the Level 6 self test, there is no audio output for this discrete in Level 6. 6.6.8 GND ILS Tuned Discrete #1 Type: Supplied by ILS/VOR Mode Selector. Signal Status: ILS tuned or VOR tuned GND ILS Tuned Discrete #1 Level 6 Audio readout ILS Tuned => “ILS 1 Tuned” ILS Not Tuned => “ILS 1 Not Tuned” Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 298 Honeywell MK VI MK VIII EGPWS Installation Design Guide 6.6.9 +28V ILS Tuned Discrete #1 Type: Supplied by ILS/VOR Mode Selector. Signal Status: ILS tuned or VOR tuned +28 V ILS Tuned Discrete #1 Level 6 Audio readout ILS Tuned => “28 Volts ILS 1 Tuned” ILS Not Tuned => “28 Volts ILS 1 Not Tuned” 6.6.10 Glideslope Validity Discrete #1 A Glideslope Validity Discrete may be used by EGPWS, for the ARINC 547 Glideslope Receiver input. Type: Validity from ARINC 547 Glideslope receiver. Signal Status: Valid or Invalid Note: Analog Glideslope monitoring requires that this input discrete (or the Analog Low Level Glideslope Validity Discrete) is always true whenever ILS is not tuned . In other words that the flag is biased out of view. Level 6 Audio readout Valid => “Glideslope 1 Valid” Invalid => “Glideslope 1 Invalid” Glideslope Validity Discrete #1 6.6.11 GND Glideslope Inhibit Discrete Type: Switch for inhibit of Glideslope mode Signal Status: Glideslope Inhibit or Not Inhibit Mode 5 will be disabled and “Glideslope” will not be enunciated during cockpit Self Test and the long vocabulary test if inhibited. Level 6 Audio readout Inhibit => “Glideslope Inhibit True” Not Inhibit => “Glideslope Inhibit False” Glideslope Inhibit Discrete 6.6.12 +28 V Glideslope Inhibit Discrete Type: Supplied by an alternate action latching cockpit switch for inhibit of Glideslope mode. Signal Status: Glideslope Inhibit or Not Inhibit Mode 5 will be inhibited and “Glideslope” will not be enunciated during cockpit Self Test and the long vocabulary test if inhibited. Level 6 Audio readout Inhibit => “28 Volts Glideslope Inhibit True” Not Inhibit => “28 Volts Glideslope Inhibit False” +28V Glideslope Inhibit Discrete 6.6.13 Glideslope Cancel Discrete Type: Supplied by a momentary actuated cockpit Glideslope mode manual inhibit switch. Signal Status: Glideslope is canceled if Glideslope function is active Fault monitoring: Activation of this input for more than 15 seconds will result in the ‘Glideslope Cancel Invalid’ fault which will cause a GPW INOP indication. Typically the Glideslope cancel can only be selected below 2000 feet AGL. Level 6 Audio readout Cancel => “Glideslope Canceled” Normal => “Glideslope Enabled” Glideslope Cancel Discrete Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 299 Honeywell MK VI MK VIII EGPWS Installation Design Guide 6.6.14 Decision Height Discrete Type: Decision Height Bug switch Signal Status: Less than Decision Height or Greater than Decision Height Level 6 Audio readout Less Than DH => “Below DH” Greater Than DH => “Above DH” DH Discrete 6.6.15 Mode 6 Low Volume Discrete Type: Mode 6 low volume select switch Signal Status: Low Volume Select or Normal Volume “Low Volume” in this case refers to the -6db volume level used during Self-Test. “Normal Volume” refers to the audio output level selected per Category 14 (5.3.14). Level 6 Audio readout Low Volume => “Mode 6 Low Volume” Normal => “Mode 6 Normal Volume” Mode 6 Low Volume Discrete 6.6.16 GND Audio Inhibit Discrete Type: Analog discrete input from a flight deck mounted switch Signal Status: Audio Suppress enabled or disabled/All Modes Inhibit enable or disable Fault Monitoring: Activation of this input will result in the “External EGPWS Inhibited”. Level 6 Audio readout Inhibit => “Audio Inhibit” Not Inhibit => “Audio Not Inhibit” GND Audio Inhibit Discrete 6.6.17 +28V Audio Inhibit Discrete Type: Analog discrete input from a flight deck mounted switch Signal Status: Audio Suppress enabled or disabled/All Modes Inhibit enable or disable Fault Monitoring: Activation of this input will result in the “External EGPWS Inhibited”. Level 6 Audio readout Inhibit => “28 Volts Audio Inhibit” Not Inhibit => “28 Volts Audio Not Inhibit” +28V Audio Inhibit Discrete 6.6.18 Display Select Discrete #1 Type: Supplied by momentarily actuated cockpit manual switch. Signal Status: Terrain Awareness Display (TAD) activated if not active or TAD canceled if currently active. Level 6 Audio readout True => “Display Discrete 1 True” False => “Display Discrete 1 False” Display Select Discrete #1 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 300 Honeywell MK VI MK VIII EGPWS Installation Design Guide 6.6.19 Display Select Discrete #2 Type: Supplied by momentarily actuated cockpit manual switch. Signal Status: Terrain Awareness Display (TAD) activated if not active or TAD canceled if currently active. Level 6 Audio readout True => “Display Discrete 2 True” False => “Display Discrete 2 False” Display Select Discrete #2 6.6.20 Terrain Awareness & TCF Inhibit Discrete Type: Supplied by an alternate action (latching) and self indicating cockpit switch for inhibit of Terrain Awareness & TCF functions Signal Status: Terrain Awareness & TCF Inhibit or Not Inhibit “Terrain Inhibited” will be enunciated during cockpit Self Test if inhibited. Level 6 Audio readout Inhibit => “Terrain Off” Not Inhibit => “Terrain On” Terrain Awareness & TCF Inhibit 6.6.21 Autopilot Engaged Discrete #1 An Autopilot Engaged Discrete may be used by EGPWS for the Bank Angle mode computation. Type: Discrete from the Autopilot system. Signal Status: Engaged or Not Engaged Level 6 Audio readout Engaged => “Autopilot On” Not Engaged => “Autopilot Off” Autopilot Engaged Discrete 6.6.22 Barometric Altitude Validity Discrete A Barometric Altitude Validity Discretes may be used by EGPWS for the barometric rate sensor. Type: Validity from barometric altitude sensor. Signal Status: Valid or Invalid Valid => Invalid => Barometric Altitude Validity Discrete Level 6 Audio readout “Altitude Valid” “Altitude Invalid” 6.6.23 Magnetic Heading Validity Discrete A Magnetic Heading Validity Discrete may be used by EGPWS for the Mag Heading sensor. Type: Validity from Magnetic Heading sensor. Signal Status: Valid or Invalid Level 6 Audio readout Valid => “Magnetic Heading Valid” Invalid => “Magnetic Heading Invalid” Magnetic Heading Validity Discrete 6.6.24 Attitude Validity Discrete A Attitude Validity Discretes may be used by EGPWS for the Pitch and Roll signals. Type: Validity from vertical gyro or attitude computer. Signal Status: Valid or Invalid Valid => Invalid => Attitude Validity Discrete Level 6 Audio readout “Attitude Valid” “Attitude Invalid” Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 301 Honeywell MK VI MK VIII EGPWS Installation Design Guide 6.6.25 Steep Approach Discrete #2 Activates steep approach biasing if Steep Approach Enabled is true (see Category 7, Section 5.3.7). Alt. Action Type: Supplied by an alternate action (latching) and self indicating cockpit switch . Momentary Type: Supplied by a momentary (non-latching) switch with switch lamp driven by EGPWS Steep Approach Discrete output. Signal Status: Steep Approach Selected or not Selected Fault monitoring: None if Steep Approach Enabled is false. EGPWS Self-Test is inhibited if Steep Approach Enabled is true and Steep Approach Discrete #2 is “Selected” on the ground. For momentary switch inputs, activation of this switch input for more than 15 seconds will result in the “Steep Approach Invalid” fault which will cause a GPWS INOP indication. Level 6 Audio readout Selected => “Steep Approach Selected” Not Selected => “Steep Approach Not Selected” Steep Approach Discrete #2 6.6.26 Timed Audio Inhibit Discrete Type: Supplied by a momentary action (internally latching) and indicating cockpit switch for inhibit of audio functions. Signal Status: Audio Inhibit or not Inhibit Fault monitoring: The Audio Inhibit function does not inhibit Self Test, therefore, “Timed Audio Inhibited Fault” will be enunciated during cockpit Level 2 Self Test. Level 6 Audio readout Selected => “Timed Audio Inhibit” Not Selected => “Timed Audio Not Inhibit” Timed Audio Inhibit Discrete 6.6.27 GPWS Inhibit Discrete This discrete inhibits all audio and visual except for Windshear, Terrain Awareness and TCF. Type: Supplied by an alternate action (latching) and self indicating cockpit switch. Signal Status: GPWS enabled or disabled Fault monitoring: Activation of this input for more than 5 seconds will result in the ‘GPWS Inhibit’ fault which will cause a GPWS INOP indication. Level 6 Audio readout Selected => “GPWS Inhibit” Not Selected => “GPWS Not Inhibit” GPWS Inhibit Discrete 6.6.28 Localizer Validity Discrete #1 A Localizer Validity discrete may be used by the EGPWS for localizer input from an ARINC 547 Nav Receiver. Type: Validity from ARINC 547 Nav Receiver Signal Status: Valid or Invalid Level 6 Audio readout Valid => “Localizer 1 Valid” Invalid => “Localizer 1 Invalid” Localizer Validity Discrete #1 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 302 Honeywell MK VI MK VIII EGPWS Installation Design Guide 7 OUTPUT DATA DEFINITION 7.1 ARINC 429 Output Data The MK VI and VIII EGPWC provides one or two ARINC 429 low or high-speed output channels per section 5.3.6.3. The output consist of internal parameters that can be used for display selection, test purposes, and discrete outputs that can be used for discrete outputs, test and recording. During LRU Self-Test the SSM of each output label is set to the Functional Test status code. The output types can be summarized as follows. 1) Internal data: Some internal data is output for test purposes only such as Radio Altitude, Computed Airspeed, Geometric Altitude, etc. 2) Alert status: Each type of Voice and Lamp activity is mapped to a specific label/BIT. This can be used to provide inputs to display systems and flight recorders. 3) Internal Mode status: Various internal EGPWC mode logic is transmitted for test purposes. 4) Terrain Display messages for TAD cockpit integration. The ARINC 429 bus transmits both discrete and BNR labels. In the event of catastrophic computer failure, or 429 transmitter failure, outputs will not be transmitted. During Self-Test, the SSM will be set to functional test on all outputs (bits 31/30 = 1/0). During all other conditions of computer or input failures, the 429 outputs will continue to be transmitted as actual valid data. For valid status the standard discrete SSM format is used (00) except for data indicated as being in 2’s complement format where the standard BNR SSM format is used (11). The SDI bits (9/10) will always be set to “00”. Note: Label 067 includes an indication of parameter inaccuracy that is not tied to the above discussion of SSM settings. The following table identifies those outputs that are transmitted. Note that the outputs are segregated by functional groups. Refer to the subsections following the table for specific format information for each output. The subsections are in the same order as the table. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 303 Honeywell MK VI MK VIII EGPWS Installation Design Guide TABLE 7.1-1: ARINC 429 DITS OUTPUTS 270 271 272 273 274 300 7.1.1.1 7.1.1.2 7.1.1.3 7.1.1.4 7.1.1.5 7.1.1.6 135 164 261 067 310 311 223 224 242 331 332 362 364 375 376 7.1.2.1 7.1.2.2 7.1.2.3 7.1.2.4 7.1.2.5 7.1.2.6 7.1.2.7 7.1.2.8 7.1.2.9 7.1.2.10 7.1.2.11 7.1.2.12 7.1.2.13 7.1.2.14 7.1.2.15 OPERATIONAL OUTPUTS NAME DESCRIPTION DISCRETE OUTPUT WORDS EGPWS ALERT DISCRETE #1 EGPWS ALERT INDICATION EGPWC LOGIC DISCRETES INTERNAL LOGIC BOOLEANS MODE 6 CALLOUTS DISCRETE #1 MODE 6 CALLOUT INDICATION #1 MODE 6 CALLOUTS DISCRETE #2 MODE 6 CALLOUT INDICATION #2 EGPWS ALERT DISCRETE #2 LAMP OUTPUT WORD EGPWC ALERT DISCRETE #3 INOP INDICATIONS OF THE MK VI AND VIII EGPWC FUNCTIONS The internal data output labels are lowest priority. INTERNAL DATA OUTPUTS GEOMETRIC ALTITUDE VFOM COMPUTED GEOMETRIC ALTITUDE VFOM TERRAIN CLEARANCE RADIO ALTITUDE FILTERED BY MK VI AND VIII EGPWC GEOMETRIC ALTITUDE COMPUTED GEOMETRIC ALTITUDE COMPUTED TERRAIN CLEARANCE TERRAIN CLEARANCE COMPUTED BY EGPWS LATITUDE PRESENT POSITION EGPWS SELECTED LATITUDE LONGITUDE PRESENT POSITION EGPWS SELECTED LONGITUDE BODY ANGLE OF ATTACK – RIGHT COMPUTED BODY ANGLE OF ATTACK – RIGHT VANE BODY ANGLE OF ATTACK – LEFT COMPUTED BODY ANGLE OF ATTACK – LEFT VANE CORRECTED AIRSPEED COMPUTED CORRECTED AIRSPEED WINDSHEAR WARNING THRESHOLD WINDSHEAR WARNING THRESHOLD COMPUTED BY EGPWS CORRECTED LONGITUDINAL ACCELERATION COMPUTED CORRECTED LONGITUDINAL ACCELERATION RAW TOTAL SHEAR RAW TOTAL SHEAR COMPUTED BY EGPWS CORRECTED NORMAL ACCELERATION COMPUTED CORRECTED NORMAL ACCELERATION CORRECTED FLIGHT PATH ANGLE COMPUTED CORRECTED FLIGHT PATH ANGLE SCALED TOTAL SHEAR SCALED TOTAL SHEAR COMPUTED BY EGPWS 050 051 052 053 054 055 7.1.3.1 7.1.3.2 7.1.3.3 7.1.3.4 7.1.3.5 7.1.3.6 TERRAIN DISPLAY OUTPUTS DISPLAYED RANGE TERRAIN DISPLAY STATUS WORD MESSAGE WORD #1 MESSAGE WORD #2 MESSAGE WORD #3 MESSAGE WORD #4 TERRAIN DISPLAY #1 AND #2 RANGE TERRAIN DISPLAY STATUS INFORMATION COLOR OF DISPLAY MESSAGE FIRST TWO CHARACTERS OF DISPLAY MESSAGE SECOND TWO CHARACTERS OF DISPLAY MESSAGE LAST TWO CHARACTERS OF DISPLAY MESSAGE 2,4 2,4 2,4 2,4 2,4 2,4 377 7.1.4.1 EQUIPMENT ID EQUIPMENT IDENTIFICATION PROVIDES ARINC 429 DEFINED EQUIPMENT ID NO. (023) 3 350 351 355 7.1.5.1 7.1.5.2 7.1.5.3 FAULT SUMMARY WORDS FAULT DIAGNOSTIC WORD #1 FAULT DIAGNOSTIC WORD #2 FAULT DIAGNOSTIC WORD #3 PROVIDES FAULT STATUS PROVIDES FAULT STATUS PROVIDES FAULT STATUS 5 5 5 011 012 7.1.6.1 7.1.6.2 PEAKS ELEVATION BINARY PEAKS UPPER ELEVATION PEAKS LOWER ELEVATION UPPER ELEVATION VALUE AND COLOR LOWER ELEVATION VALUE AND COLOR 6,7,8 6,7,8 LABEL Reference NOTES: NOTES 1 1 1 1 1 1 5 1 5 5,6 5, 5, 9 9 9 9 9 9 9 9 9 1) Update rate 100 ms ± 10% 2) Update rate 200 ms ± 10% 3) Update rate 500 ms ± 10% 4) Transmitted only if Terrain Awareness function enabled 5) Update rate 1000 ms ± 10% 6) NCD and Failure Warning Indications Provided 7) Transmitted only if Peaks enabled 8) Update rate 500 ms ± 10% for each SDI 9) Update rate 100 ms ± 20% (Labels only used for testing) Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 304 Honeywell MK VI MK VIII EGPWS Installation Design Guide 7.1.1 Discrete Output Words The discrete output words transmit the status of all MK VI, and VIII EGPWC discrete and audio outputs. Label 274 is typically used to drive EFIS and/or EICAS displays. The other discrete labels are typically only used for flight recording and test purposes. 7.1.1.1 EGPWS Alert Discrete #1 (270) Data: Discrete Label: 270 Octal Significant Bits: (see table below) Sign Bit: N/A Transmit Interval: 100 msec ± 10% Bit No. ASSIGNED WARNING MESSAGE (1 = voice on) 11 SINKRATE-PAUSE-SINKRATE 12 PULL UP 13 TERRAIN OR TERRAIN-TERRAIN 14 DONT SINK-PAUSE-DONT SINK 15 TOO LOW GEAR 16 TOO LOW FLAPS 17 TOO LOW TERRAIN 18 GLIDESLOPE 19 MINIMUMS MINIMUMS * 20 TERRAIN PULLUP 21 CAUTION TERRAIN * 22 TERRAIN AHEAD PULL UP or OBSTACLE AHEAD PULL UP * 23 (SIREN) WINDSHEAR WINDSHEAR WINDSHEAR * 24 CAUTION WINDSHEAR * 25 ENGINE FAIL * 26 VEE ONE * 27 CAUTION TERRAIN or TERRAIN AHEAD 28 CAUTION OBSTACLE or OBSTACLE AHEAD 29 OBSTACLE OBSTACLE NOTE (*): Bits 23 through 26 will be set to zero when unsupported. Bit 22, This bit is used for the alternate terrain and obstacle warning voice message. The basic terrain warning message is mapped to bits 13 and 12 and obstacle warning voice mapped to bits 29 and 12. Bits 23 & 24, are supported by MKVIII EGPWS only, provided that WS is included in configuration. Bits 20, 25 & 26, are Not supported. Bit 27, is the alternate Terrain Caution voice. 7.1.1.2 EGPWC Logic Discretes (271) Data: Discrete Label: 271 Octal Significant Bits: (see table below) Sign Bit: N/A Transmit Interval: 100 msec ± 10% BIT No. DEFINITION * 11 GPW INHIBIT (by Windshear) * 12 WS ALERT INHIBIT 13 TERRAIN CLEARANCE FLOOR ALERT 14 ENVELOPE MOD IN PROGRESS 15 ENVELOPE MOD SNAPSHOT LATCH SET * 16 WINDSHEAR TAKE-OFF * 17 WINDSHEAR MASTER VALID 18 TAKE-OFF MODE 19 MODE 1 SINKRATE 20 MODE 1 PULL UP 21 MODE 2 TERRAIN 22 MODE 2 PULL UP 23 MODE 3 VISUAL 24 MODE 4 VISUAL 25 MODE 5 VISUAL * 26 MODE 7 VISUAL ALERT 27 TERRAIN AWARENESS CAUTION 28 TERRAIN AWARENESS WARNING * 29 MODE 7 VISUAL WARNING NOTE (*): Bits 11, 12, 16, 17, 26 and 29 will be set to zero when Not Supported. Supported by MKVIII EGPWS only, provided that WS is included in configuration. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 305 Honeywell MK VI MK VIII EGPWS Installation Design Guide 7.1.1.3 Mode 6 Callouts Discrete #1 (272) Data: Discrete Label: 272 Octal Significant Bits: (see table below) Sign Bit: N/A Transmit Interval: 100 msec ± 10% BIT NO WARNING MESSAGE (1 = voice on) 11 MINIMUMS * 12 DECISION HEIGHT * 13 APPROACHING MINIMUMS * 14 APPROACHING DECISION HEIGHT * 15 ZERO (Not supported) 16 TEN 17 TWENTY 18 THIRTY 19 FORTY 20 FIFTY * 21 SIXTY * 22 EIGHTY 23 ONE HUNDRED 24 TWO HUNDRED 25 THREE HUNDRED * 26 MINIMUM * 27 PLUS HUNDRED * 28 DECIDE * 29 FIFTY ABOVE NOTE (*): Bits 12 - 15, 21, 22 and 26 - 29 will be set to zero, Not supported. 7.1.1.4 Mode 6 Callouts Discrete #2 (273) Data: Discrete Label: 273 Octal Significant Bits: (see table below) Sign Bit: N/A Transmit Interval: 100 msec ± 10% BIT NO DEFINITION (1 = voice on) 11 FOUR HUNDRED 12 FIVE HUNDRED (NORMAL, SMART or ABOVE FIELD) 13 ONE THOUSAND * 14 700 HZ TONE * 15 960 HZ TONE * 16 1400 HZ TONE * 17 2800 HZ TONE 18 BANK ANGLE (pause) BANK ANGLE * 19 THIRTY FIVE * 20 TWENTY FIVE HUNDRED * 21 RADIO ALTIMETER * 22 FIVE 23 FIVE HUNDRED ABOVE (ABOVE FIELD) * 24 (SPARE) * 25 (SPARE) * 26 (SPARE) * 27 FLAPS (pause) FLAPS * 28 AUTOPILOT * 29 SPEED BRAKE (pause) SPEED BRAKE NOTE (*): Bits 14 - 17, 19 – 22, and 24 - 29 will be set to zero. Not supported. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 306 Honeywell MK VI MK VIII EGPWS Installation Design Guide 7.1.1.5 EGPWS Alert Discrete #2 (274) Data: Discrete Label: 274 Octal Significant Bits: (see table below) Sign Bit: N/A Transmit Interval: 50 to 100 msec Bit No. ASSOCIATED DISCRETE PIN DEFINITION (1 = ON) 11 J1-76 (TYPICALLY GLIDESLOPE CANCEL) 12 J1-77 GPWS ALERT 13 J1-78 GPWS WARNING 14 ---GPWS INOP * 15 ---WINDSHEAR WARNING 16 J1-69 AUDIO ON * 17 ---WINDSHEAR INOP * 18 ---WINDSHEAR CAUTION * 19 ---CALLOUTS INOP * 20 ---VEE ONE INOP * 21 ---ENGINE FAIL INOP 22 ---TERRAIN AWARENESS WARNING or OBSTACLE AWARENESS WARNING 23 ---TERRAIN AWARENESS CAUTION or OBSTACLE AWARENESS CAUTION 24 ---TERRAIN AWARENESS INOP 25 FRONT PANEL LED EXTERNAL FAULT 26 FRONT PANEL LED COMPUTER FAIL 27 ---TERRAIN AWARENESS NOT AVAILABLE 28 J1-54 TERRAIN DISPLAY DISCRETE #1 * 29 J1-49 TERRAIN DISPLAY DISCRETE #2 NOTE (*): Bits 15, 17- 21 and 29 will be set to zero when Not Supported. Bits 15, 17, & 18 are supported by MKVIII EGPWS only, provided that WS is included in configuration. Bits 20 & 21 are Not supported. 7.1.1.6 EGPWC Alert Discrete #3 (300) Data: Discrete Label: 300 Octal Significant Bits: (see table below) Sign Bit: N/A Transmit Interval: 50 to 100 msec BIT No. DEFINITION 11 MODES 1-4 INOP 12 MODE 5 INOP 13 MODE 6 INOP 14 BANK ANGLE INOP * 15 MODE 7 INOP 16 TERRAIN CLEARANCE FLOOR INOP or RUNWAY FIELD CLEARANCE FLOOR INOP 17 TERRAIN AWARENESS INOP 18 ENVELOPE MODULATION INOP * 19 SPEED BRAKE INHIBIT * 20 SPEED BRAKE ALERT * 21 TCAS INHIBIT * 22 (SPARE) * 23 (SPARE) * 24 (SPARE) * 25 (SPARE) * 26 (SPARE) * 27 FLAP OVERRIDE LATCH 28 OBSTACLE AWARENESS CAUTION 29 OBSTACLE AWARENESS WARNING NOTE (*): Bits 15 and 19 - 27 will be set to zero when Not Supported. Bit 15 is supported by MKVIII EGPWS only, provided that WS is included in configuration. Bits 19 - 27 are Not supported. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 307 Honeywell MK VI MK VIII EGPWS Installation Design Guide 7.1.2 Internal Data Outputs Internal data outputs are only used for test purposes. Tables 7.1.2.1 through 7.1.2.6 are available for both MKVI and MKVIII EGPWS. Tables 7.1.2.7 through 7.1.2.15 are are only output when the Honeywell Windshear Algorithm is enabled (available only on the MKVIII EGPWS) and are only used for test purposes. 7.1.2.1 Geometric Altitude VFOM (135) LABEL (Octal) 135 Units: Feet Max. Range: 32,768 Ft Approx. LSB: 0.125 Foot Data Bits: 11 to 28 = 18 + = N/A Sign Bit: 29 Pad Bits: N/A Data Type: 2’s Compliment Binary SDI Bits: 9, 10 Transmit Interval (msec): 1000 ± 10% 7.1.2.2 Terrain Clearance (164) LABEL (Octal) 164 Units: Feet Approx. LSB: 1.0 Foot Max. Range: ± 8,192 Feet Data Bits: 16 to 28 = 13 + = Above Ground Level (AGL) Sign Bit: 29 Pad Bits: 11 to 15 Data Type: 2’s Compliment Binary SDI Bits: 9, 10 Transmit Interval (mSec): 100 ± 10% 7.1.2.3 Geometric Altitude (261) LABEL (Octal) 261 Units: Feet Approx. LSB: 0.125 Foot Max. Range: ± 131,072 Ft Data Bits: 9 to 28 = 20 + = Above Sea Level (ASL) Sign Bit: 29 Pad Bits: N/A Data Type: 2’s Compliment Binary SDI Bits: N/A Transmit Interval (msec): 1000 ± 10% 7.1.2.4 Computed Terrain Clearance (067) LABEL (Octal) 067 Units: Feet Approx. LSB: 1.0 Foot Max. Range: ±131,072 Ft Data Bits: 12 to 28 = 17 + = Above Ground Level (AGL) Sign Bit: 29 Pad Bits: N/A Data Type: 2’s Compliment Binary SDI Bits: N/A Transmit Interval (msec): 1000 ± 10% Bit 11 12 -28 Definitions Set to 1 when Computed Terrain Clearance low accuracy is indicated Computed Terrain Clearance 7.1.2.5 Latitude – Selected EGPWS (310) LABEL (Octal) 310 Units: Degrees LSB: 0.00017166137695 Max. Range: ± 180 Degrees Data Bits: 9 to 28 = 20 + = North Sign Bit: 29 Pad Bits: N/A Data Type: 2’s Compliment Binary SDI Bits: used for data Transmit Interval (mSec): 1000 ± 10% 7.1.2.6 Longitude – Selected EGPWS (311) LABEL (Octal) 311 Units: Degrees LSB: 0.00017166137695 Max. Range: ± 180 Degrees Data Bits: 9 to 28 = 20 + = East Sign Bit: 29 Pad Bits: N/A Data Type: 2’s Compliment Binary SDI Bits: used for data Transmit Interval (mSec): 1000 ± 10% 7.1.2.7 Body Angle of Attack—Right (223) – MKVIII EGPWS w/ Windshear only Units: Degrees/180 LABEL (Octal) 223 Approx. LSB: 0.00549 Degree Max. Range: ± 180 Degrees Data Bits: 14 to 28 = 15 + = Nose Up Sign Bit: 29 Pad Bits: 11 to 13 Data Type: 2’s Compliment Binary SDI Bits: 9, 10 Transmit Interval (mSec): 100 ± 20% Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 308 Honeywell MK VI MK VIII EGPWS Installation Design Guide 7.1.2.8 Body Angle of Attack—Left (224) – MKVIII EGPWS w/ Windshear only Units: Degrees/180 Approx. LSB: 0.00549 Degree LABEL (Octal) 224 Max. Range: ± 180 Degrees Data Bits: 14 to 28 = 15 + = Nose Up Sign Bit: 29 Pad Bits: 11 to 13 Data Type: 2’s Compliment Binary SDI Bits: 9, 10 Transmit Interval (mSec): 100 ± 20% 7.1.2.9 Corrected Airspeed (242) – MKVIII EGPWS w/ Windshear only Units: Feet/Second LABEL (Octal) 242 Max. Range: 2048 Ft/Sec Approx. LSB: 0.0625 Ft/Sec Data Bits: 14 to 28 = 15 + = Forward Sign Bit: 29 Pad Bits: 11 to 13 Data Type: 2’s Compliment Binary SDI Bits: 9, 10 Transmit Interval (mSec): 100 ± 20% 7.1.2.10 Windshear Warning Threshold (331) – MKVIII EGPWS w/ Windshear only Units: g’s LABEL (Octal) 331 Max. Range: 0.0 40 -4.0 g’s Approx. LSB: 0.00012207 g’s Data Bits: 14 to 28 = 15 + = N/A (always negative) Sign Bit: 29 Pad Bits: 11 to 13 Data Type: 2’s Compliment Binary SDI Bits: 9, 10 Transmit Interval (mSec): 100 ± 20% 7.1.2.11 Corrected Longitudinal Acceleration (332) – MKVIII EGPWS w/ Windshear only Units: g’s LABEL (Octal) 332 Approx. LSB: 0.00012207 g’s Max. Range: ± 4.0 g’s Data Bits: 14 to 28 = 15 + = Forward Sign Bit: 29 Pad Bits: 11 to 13 Data Type: 2’s Compliment Binary SDI Bits: 9, 10 Transmit Interval (mSec): 100 ± 20% Note: Longitudinal Acceleration is corrected by Cosine of Body Angle of Attack. 7.1.2.12 Raw Total Shear (362) – MKVIII EGPWS w/ Windshear only Units: g’s Approx. LSB: 0.00012207 g’s LABEL (Octal) 362 Max. Range: ± 4.0 g’s Data Bits: 14 to 28 = 15 + = Headwind/Updraft Sign Bit: 29 Pad Bits: 11 to 13 Data Type: 2’s Compliment Binary SDI Bits: 9, 10 Transmit Interval (mSec): 100 ± 20% 7.1.2.13 Corrected Normal Acceleration (364) – MKVIII EGPWS w/ Windshear only Units: g’s LABEL (Octal) 364 Approx. LSB: 0.00012207 g’s Max. Range: ± 4.0 g’s Data Bits: 14 to 28 = 15 + = Up Sign Bit: 29 Pad Bits: 11 to 13 Data Type: 2’s Compliment Binary SDI Bits: 9, 10 Transmit Interval (mSec): 100 ± 20% Note: Normal Acceleration is corrected by Sine of Body Angle of Attack. 7.1.2.14 Computed Flight Path Angle (375) – MKVIII EGPWS w/ Windshear only Units: Radians LABEL (Octal) 375 Approx. LSB: 0.00012207 Radians Max. Range: ± 4.0 Radians Data Bits: 14 to 28 = 15 + = Nose Up Sign Bit: 29 Pad Bits: 11 to 13 Data Type: 2’s Compliment Binary SDI Bits: 9, 10 Transmit Interval (mSec): 100 ± 20% 7.1.2.15 Scaled Total Shear (376) – MKVIII EGPWS w/ Windshear only Units: g’s Approx. LSB: 0.00012207 g’s LABEL (Octal) 376 Max. Range: ± 4.0 g’s Data Bits: 14 to 28 = 15 + = Headwind/Updraft Sign Bit: 29 Pad Bits: 11 to 13 Data Type: 2’s Compliment Binary SDI Bits: 9, 10 Transmit Interval (mSec): 100 ± 20% Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 309 Honeywell MK VI MK VIII EGPWS Installation Design Guide 7.1.3 Terrain Display Outputs The following ARINC 429 outputs support the Terrain Display function. 7.1.3.1 Displayed Range (050) Data: Discrete BIT NO 11 – 14 15 – 18 19 - 29 Label (Octal): 050 Transmit Interval: 200 msec ± 10% DEFINITION TERRAIN DISPLAY RANGE #1 (0.5 to 2000 NM format) TERRAIN DISPLAY RANGE #2 (0.5 to 2000 NM format) UNDEFINED NOTE: Bits contain left and right side Terrain Display Ranges (0.5 to 2000 NM, format as follows) (Bits 14-11) & (Bits 18-15) 0000 0001 0010 0011 0100 0101 0110 0111 DISPLAY RANGE BIT ASSIGNMENTS DEFINITION (Bits 14-11) & (Bits 18-15) 0.5 NM 1000 1.0 NM 1001 2.5 NM 1010 5.0 NM 1011 10 NM 25 NM 50 NM 100 NM 1100 1101 1110 1111 DEFINITION 150 NM 200 NM 300 NM 500 NM 1000 NM 2000 NM 600 NM 1200 NM 7.1.3.2 Terrain Display Status Word (051) Data: Discrete Label (Octal): 051 Transmit Interval: 200 msec ± 10% BIT NO DEFINITION 11 POP UP BOOLEAN #1 12 POP UP BOOLEAN #2 13 TERRAIN DISPLAY VALID (cleared when TERRAIN AWARENESS NOT AVAILABLE or TERRAIN AWARENESS INOP are true) 14 SPARE 15 SPARE 16 17 18 19 20 21 22 FLAP OVERRIDE (Only from ARINC 429 FWC discrete word label 171, not from discrete switch) TERRAIN AWARENESS & TCF INHIBIT SPARE SPARE SPARE SPARE SPARE 23 24 25 26 27 28 SPARE SPARE SPARE TERRAIN DISPLAY CAUTION TERRAIN DISPLAY WARNING STEEP APPROACH ACTIVATED 29 SPARE Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 310 Honeywell MK VI MK VIII EGPWS Installation Design Guide 7.1.3.3 Message Word #1 (052) This label contains the color to be displayed on the 6-character terrain display window. Data: Discrete BIT NO 9 - 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 Label (Octal): 052 DEFINITION SDI (00) Spare Spare Spare Spare Spare Spare Spare Spare Spare Spare Spare Spare Character Color Character Color Character Color Character Color Character Color Character Color Character Color Transmit Interval: 200 msec ± 10% BIT Coding COLOR Code (Hex) LSB (7 bit Hex) 000 0001 = Red 000 0010 = Amber 000 0011 = Yellow 000 0100 = Green 000 0101 = Cyan 000 0110 = Magenta 000 0111 = White MSB (7 bit Hex) 7.1.3.4 Message Word #2 (053) This label contains the first 2 characters to be displayed on the 6-character terrain display window. Data: Discrete BIT NO 9,10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 Label (Octal): 053 DEFINITION SDI (00) Spare Spare Spare Spare Spare Character Code - Left Most of Set 1 of 6 Character Code - Left Most of Set 1 of 6 Character Code - Left Most of Set 1 of 6 Character Code - Left Most of Set 1 of 6 Character Code - Left Most of Set 1 of 6 Character Code - Left Most of Set 1 of 6 Character Code - Left Most of Set 1 of 6 Character Code - Next Most of Set 2 of 6 Character Code - Next Most of Set 2 of 6 Character Code - Next Most of Set 2 of 6 Character Code - Next Most of Set 2 of 6 Character Code - Next Most of Set 2 of 6 Character Code - Next Most of Set 2 of 6 Character Code - Next Most of Set 2 of 6 Transmit Interval: 200 msec ± 10% BIT Coding LSB (7 bit Hex) MSB (7 bit Hex) LSB (7 bit Hex) TEXT Code (Hex) TEXT Code (Hex) 20 = (space) 21 = ! 22 = “ 23 = # 24 = % 25 = $ 26 = & 27 = ‘ 28 = ( 29 = ) 2A = * 2B = + 2C = , 2D = 2E = . 2F = / 30 = 0 31 = 1 32 = 2 33 = 3 34 = 4 35 = 5 36 = 6 37 = 7 38 = 8 39 = 9 3A = : 3B = ; 3C = < 3D = = 3E = > 3F = ? Continued at LABEL 054 Below MSB (7 bit Hex) Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 311 Honeywell MK VI MK VIII EGPWS Installation Design Guide 7.1.3.5 Message Word #3 (054) This label contains the second 2 characters to be displayed on the 6 character terrain display window. Data: Discrete BIT NO 9,10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 Label (Octal): 054 DEFINITION SDI (00) Spare Spare Spare Spare Spare Character Code - Next Most of Set 3 of 6 Character Code - Next Most of Set 3 of 6 Character Code - Next Most of Set 3 of 6 Character Code - Next Most of Set 3 of 6 Character Code - Next Most of Set 3 of 6 Character Code - Next Most of Set 3 of 6 Character Code - Next Most of Set 3 of 6 Character Code - Next Most of Set 4 of 6 Character Code - Next Most of Set 4 of 6 Character Code - Next Most of Set 4 of 6 Character Code - Next Most of Set 4 of 6 Character Code - Next Most of Set 4 of 6 Character Code - Next Most of Set 4 of 6 Character Code - Next Most of Set 4 of 6 Transmit Interval: 200 msec ± 10% BIT Coding TEXT Code (Hex) TEXT Code (Hex) Continued from LABEL 053 Above 40 = ° (Deg Sign) 41 = A 42 = B 43 = C 44 = D 45 = E 46 = F 47 = G 48 = H 49 = I 4A = J 4B = K 4C = L 4D = M 4E = N 4F = O LSB (7 bit Hex) MSB (7 bit Hex) LSB (7 bit Hex) MSB (7 bit Hex) 50 = P 51 = Q 52 = R 53 = S 54 = T 55 = U 56 = V 57 = W 58 = X 59 = Y 5A = Z 5B = [ 5C = \ 5D = ] 5E = ^ 5F = _ (underscore) 00 = (Null) NOTE: Text code for degree sign is non-standard ASCII for 40HEX. 7.1.3.6 Message Word #4 (055) This label contains the last 2 characters to be displayed on the 6-character terrain display window. Data: Discrete BIT NO 9,10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 Label (Octal): 055 DEFINITION SDI (00) Spare Spare Spare Spare Spare Character Code - Next Most of Set 5 of 6 Character Code - Next Most of Set 5 of 6 Character Code - Next Most of Set 5 of 6 Character Code - Next Most of Set 5 of 6 Character Code - Next Most of Set 5 of 6 Character Code - Next Most of Set 5 of 6 Character Code - Next Most of Set 5 of 6 Character Code - Right Most of Set 6 of 6 Character Code - Right Most of Set 6 of 6 Character Code - Right Most of Set 6 of 6 Character Code - Right Most of Set 6 of 6 Character Code - Right Most of Set 6 of 6 Character Code - Right Most of Set 6 of 6 Character Code - Right Most of Set 6 of 6 Transmit Interval: 200 msec ± 10% BIT Coding LSB (7 bit Hex) MSB (7 bit Hex) LSB (7 bit Hex) MSB (7 bit Hex) Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 312 Honeywell MK VI MK VIII EGPWS Installation Design Guide 7.1.4 Equipment Identification Provides equipment identification for maintenance reporting. 7.1.4.1 Equipment Identification Word (377) Data: Discrete Label (Octal): 377 BIT NO DEFINITION 11 - 22 ID Code 23 - 29 Spare (set to zero) Transmit Interval: 500 msec ± 10% Equipment ID code = 023 Hex for EGPWC. 7.1.5 Fault Summary Words (for Proline 4/21) Provides fault diagnosis information. 7.1.5.1 Fault Diagnostic Word #1 (350) Data: Discrete BIT NO 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 Label (Octal): 350 DEFINITION (1= Failed) ARINC 429 INPUT #1 FAILED ARINC 429 INPUT #2 FAILED ARINC 429 INPUT #3 FAILED ARINC 429 INPUT #4 FAILED ARINC 429 INPUT #5 FAILED ARINC 429 INPUT #6 FAILED ARINC 429 INPUT #7 FAILED ARINC 429 INPUT #8 FAILED ANALOG DC INPUT #1 FAILED ANALOG DC INPUT #2 FAILED ANALOG DC INPUT #3 FAILED ANALOG DC INPUT #4 FAILED ANALOG DC INPUT #5 FAILED ANALOG DC INPUT #6 FAILED ANALOG DC INPUT #7 FAILED ANALOG SYNCHRO INPUT #1 FAILED ANALOG SYNCHRO INPUT #2 FAILED ANALOG SYNCHRO INPUT #3 FAILED ANALOG SYNCHRO INPUT #4 FAILED Transmit Interval: 1000 msec ± 10% (future) (future) (future) (future) (future) (future) (future) (future) (future) (future) (future) 7.1.5.2 Fault Diagnostic Word #2 (351) Data: Discrete BIT NO 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 Label (Octal): 351 DEFINITION (1= Failed) ANALOG SYNCHRO INPUT #5 FAILED AC REFERENCE #1 FAILED AC REFERENCE #2 FAILED DC REFERENCE #1 FAILED ADC RS232/RS422 INPUT FAILED ADC RS232/RS422 OUTPUT FAILED GPS RS232/RS422 INPUT FAILED GPS RS232/RS422 OUTPUT FAILED SUPPORT TASK FAILED NVM FAULT WATCHDOG TIMER FAULT A/D FAIL FAULT VOICE FAIL DITS OUTPUT FAIL TERRAIN DATABASE FAULT FLASH FILE SYSTEM WRITE FAULT DITS INPUT FAIL VOICE DATABASE FAULT SYSTEM OR MODE TASK FAULT Transmit Interval: 1000 msec ± 10% (future) (future) (future) (future) (future) (future) (future) (future) Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 313 Honeywell MK VI MK VIII EGPWS Installation Design Guide 7.1.5.3 Fault Diagnostic Word #3 (355) Data: Discrete BIT NO 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 Label (Octal): 355 Transmit Interval: 1000 msec ± 10% DEFINITION (1= Failed) ENVELOPE MODULATION DATABASE FAULT EXCESSIVE WATCHDOG TIMEOUTS FAILURE AIRCRAFT DATABASE FAULT ‘OR’ CRC FAULT IMAGE DSP FAULT INTERNAL GPS FAULT CONFIGURATION MODULE FAILED GLIDESLOPE CANCEL DISCRETE FAILED AUDIO INHIBIT DISCRETE INPUT FAILED SELF TEST DISCRETE INPUT FAILED FLAP INPUT FAILED GEAR INPUT FAILED Spare Spare Spare Spare Spare Spare Spare Spare 7.1.6 Peak Binary Labels The following ARINC 429 outputs are used to provide Peak Elevations and color information for integrated displays where the EFIS outputs stroke written Peaks Elevation information on the display. This label set consists of 2 labels containing upper and lower elevation, color, and display blanking data. Each label is transmitted with two different SDI values for the captain’s and first officer’s display values. 7.1.6.1 Peaks Upper Elevation (011) Data: See Below BIT NO 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 Label (Octal): 011 Transmit Interval: 500 msec ± 10% DEFINITION SDI 0 Not Used 1 Captain 0 F/O 1 Not Used SDI 0 0 1 1 COLOR BIT 1 0 1 0 1 0 1 0 COLOR BIT 2 0 Black 0 Green 1 Yellow 1 Red 0 Magenta 0 Blue 1 Cyan COLOR BIT 3 0 0 0 0 1 1 1 BLANK PEAKS ELEVATION DISPLAY 0 Normal Display 1 Blank Display DASH PEAKS ELEVATION DISPLAY 0 Normal Display 1 Display Dashes SPARE SPARE SPARE SPARE 100 Ft 200 Ft NOTE: Elevation bits are 400 Ft additive; e.g., bits 20 & 21 = 1 800 Ft indicates 300 Ft. 1600 Ft Upper Peaks Elevation 3200 Ft 6400 Ft 12800 Ft 25600 Ft SIGN 0 = 0 (Plus) 1 = - 51200 Ft SSM 0 Failure 1 No Computed SSM 0 Warning 0 Data PARITY (Odd) 0 Functional Test 1 1 1 White 1 1 Normal 1 Operation Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 314 Honeywell MK VI MK VIII EGPWS Installation Design Guide 7.1.6.2 Peaks Lower Elevation (012) Data: See Below BIT NO 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 Label (Octal): 012 Transmit Interval: 500 msec ± 10% DEFINITION SDI 0 Not Used 1 Captain 0 F/O 1 Not Used SDI 0 0 1 1 COLOR BIT 1 0 1 0 1 0 1 0 COLOR BIT 2 0 Black 0 Green 1 Yellow 1 Red 0 Magenta 0 Blue 1 Cyan COLOR BIT 3 0 0 0 0 1 1 1 BLANK PEAKS ELEVATION DISPLAY 0 Normal Display 1 Blank Display DASH PEAKS ELEVATION DISPLAY 0 Normal Display 1 Display Dashes SPARE SPARE SPARE SPARE 100 Ft 200 Ft NOTE: Elevation bits are 400 Ft additive; e.g., bits 20 & 21 = 1 800 Ft indicates 300 Ft. 1600 Ft Lower Peaks Elevation 3200 Ft 6400 Ft 12800 Ft 25600 Ft SIGN 0 = 0 (Plus) 1 = - 51200 Ft SSM 0 Failure 1 No Computed SSM 0 Warning 0 Data PARITY (Odd) 0 Functional Test 1 1 1 White 1 1 Normal 1 Operation 7.2 ARINC 708A Output Two channels of ARINC 708A or KCPB (453) data is provided to drive terrain displays for installations that use the Terrain Awareness display function. Refer to document 060-4303-000, EGPWS Interface Methodology for further KCPB information. See Category 6 for more details on individual displays. 7.3 Audio Output Mode computation outputs generally result in an audio voice alert unless inputs are invalid or one of the audio suppression discretes is active. The actual output message, or intended message during audio suppression, is sent to the alert lamp logic for proper output activation. The audio outputs consist of an 8 ohm amplifier and a transformer isolated 600 ohm output. Additional automatic volume control lowers both outputs a fixed 6 dB below the nominal level on command. Refer to section 4.2.12 and Category 14 for information on volume levels. Selectable sets of voice alert messages can be defined. Each set is selected by the Voice Menu option in Category 5. 7.4 Discrete Outputs Outputs from the various alert mode computations are first processed to determine which lamp outputs to produce. All of the lamp outputs are driven by solid state switches to ground. These outputs can also be used as discrete drivers for other devices. All monitor lamp outputs are normally a steady state switch to ground. Various formats of discrete outputs can be provided as defined in Category 13. 7.4.1 Ground Proximity Alerts Discrete (Lamp) Outputs Two Lamp formats are defined as a function of the selected I/O Discrete Type of section 5.3.13. For Lamp Format type 1, only Mode 5 “Glideslope” message will activate the alert lamp output (amber). All other messages will activate the warning lamp output (red). Note that Mode 6 does not activate any lamp outputs, only voices. With Lamp Format 2, only the messages containing the phrase “Pull Up” will activate the warning lamp output (red). All other messages will activate the alert lamp output (amber). The Glideslope Cancel Input Discrete controls the output of the Mode 5 “Glideslope” message. If the Glideslope Cancel Input Discrete is activated then the caution lamp (amber) and the voice annunciation will be inhibited for the Mode 5 “Glideslope” message. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 315 Honeywell MK VI MK VIII EGPWS Installation Design Guide 7.4.2 Audio On Discrete The Audio On discrete goes true whenever any voice message is being enunciated. It will stay true until the voice is completed. This output can be used to inhibit other audio systems (e.g., TCAS) during EGPWS audio or used to drive the audio key line input provided on some aircraft audio systems. 7.4.3 Monitor Discretes (GPWS INOP & Terrain INOP or Terrain Not Available) The EGPWC produces two discrete monitor outputs. These discretes reflect the GPWS INOP and Terrain INOP / Terrain Not Available functions. These discretes activate with loss of EGPWC power. The status of these two discretes is also contained on an ARINC 429 output word. Note: Some display systems provide one message area for both warning and associated INOP annunciation. There are conditions where GPW INOP and a GPWS warning can exist at the same time (e.g., Sinkrate warning can occur even if a Ground Airspeed input fault exists.) For these installations a configuration item INOP & Warning Annunciation in Same Window is provided which causes the INOP annunciation to extinguish whenever a valid warning annunciation is required. Various formats of monitor outputs can be provided as defined in Category 13. 7.4.4 Terrain Display Switching Discretes (WxR/EGPWS Display Select) The EGPWC produces two discrete outputs for controlling the terrain display(s). They can be used either to control picture bus switching relay(s) or connected directly to the symbol generator(s). 7.4.5 Flap Override Discrete The MK VI EGPWC Flap Override function can be selected by the pilot to desensitize the alert and warning modes. The Flap Override discrete output is active (Gnd) whenever the Flap Override has been selected and is typically used to drive a lamp. 7.4.6 Glideslope Cancel Discrete The Glideslope Cancel discrete is active whenever Glideslope Cancel has been selected and is typically used to drive a lamp in the Glideslope Cancel switch. 7.4.7 Terrain / Obstacle Awareness Alert Discretes Terrain Awareness provides discrete alert outputs for Terrain / Obstacle Cautions and Warnings. These outputs can drive cockpit lamps or act as discrete inputs to other aircraft systems. 7.4.7.1 Terrain / Obstacle Caution Terrain and Obstacle Cautions can be configured to activate any of the discrete outputs. Depending on configuration, the Caution discretes will typically activate either the GPWS Warn Lamp, the GPSW Alert Lamp, or will drive their own output lamps. 7.4.7.2 Terrain / Obstacle Warning Terrain and Obstacle Warnings can be configured to activate any of the discrete outputs. Depending on configuration, the Warning discretes will typically activate either the GPWS Warn Lamp or will drive their own output lamps. 7.4.8 Terrain Pop Up The Terrain and Obstacle Caution and Warning are combined (Or’d) on one discrete to make a Terrain Pop Up indication for an integrated display system. The Pop Up discrete can be used by a display system to differentiate between a manual selection or one due to a Terrain/Obstacle Caution or Warning event. 7.4.9 Windshear INOP Monitor Discretes The MK VIII EGPWC also produces an additional discrete monitor output for Windshear. This discrete reflects the WINDSHEAR INOP functions. The status of this discrete is also contained on an ARINC 429 output word. 7.4.10 Windshear Warning The MK VIII EGPWC Windshear Warnings can be configured to activate any of the discrete outputs. Depending on configuration, the Warning discrete will typically drive its own output lamp or provide a discrete output to other aircraft systems. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 316 Honeywell MK VI MK VIII EGPWS Installation Design Guide 7.4.11 Windshear Caution The MK VIII EGPWC Windshear Cautions can be configured to activate any of the discrete outputs. Depending on configuration, the Caution discrete will typically drive its own output lamp or provide a discrete output to other aircraft systems. 7.4.12 Steep Approach Discrete The Steep Approach discrete is active whenever Steep Approach has been selected via the pilot (or an Envelope Modulation steep approach case is active) and is typically used to drive a lamp in the Steep Approach switch. For standard steep approach selection method (alternate action switch) this discrete is not provided as the switch must be self lighting. For Discrete I/O category IDs that supply a momentary Steep Approach Switch this lamp driver output is provided to light the switch. 7.5 System Configuration Status The EGPWC indicates the current hardware, software, databases, Category states and input discretes detected by the system. Each configuration item has an associated configuration message. This is the message that will be read out during Present Status on the RS-232 interface or voice output during Self Test Level 3 to inform the user of the current configuration. TABLE 7.5-1: CONFIGURATION OPTIONS AND MESSAGES Selected Option/Condition Category 4 (Smart Callout Selected) Category 6 (TA&D Disable) Category 7 (Flap Reversal Select) Category 7 (Bank Angle Enable) Category 7 (TA&D Alternate Pop Up) Category 7 (Obstacle Awareness Enabled) Category 7 (Peaks Mode Enabled) Category 7 (WGS84 Reference Selected) Category 7 (MSL Reference Selected) Category 7 (Steep Approach Enabled) Alternate Action Steep Approach Discrete #2 input discrete activated Category 7 (Steep Approach Enabled) AND Alternate Action Steep Approach Discrete #2 input discrete activated Category 7 (Steep Approach Enabled) AND Momentary Steep Approach switch configured and Steep Approach (latch) activated Glideslope Inhibit input discrete activated Mode 6 Volume Control Discrete Selected GND Audio Suppress (Inhibit)/All Modes Inhibit Discrete Selected OR +28 V Audio Suppress (Inhibit)/All Modes Inhibit Discrete Selected Terrain Awareness & TCF Inhibit input discrete activated GPWS Inhibit input discrete activated Configuration Message SMART CALLOUT SELECTED TERRAIN AWARENESS DISABLED TERRAIN CLEARANCE FLOOR DISABLED FLAP WOW REVERSAL SELECTED BANK ANGLE SELECTED ALTERNATE POP UP SELECTED OBSTACLE AWARENESS ENABLED PEAKS MODE ENABLED GPS ALTITUDE REFERENCE WGS 84 SELECTED GPS ALTITUDE REFERENCE MSL SELECTED STEEP APPROACH ENABLED STEEP APPROACH SELECTED STEEP APPROACH ACTIVATED STEEP APPROACH ACTIVATED GLIDESLOPE INHIBITED MODE 6 LOW VOLUME SELECTED EXTERNAL EGPWS INHIBITED Note: Will only occur for present status as this condition inhibits self tests TERRAIN AWARENESS AND TCF DISABLED GPWS INHIBITED Note: Will only occur for present status as this condition inhibits self tests Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 317 Honeywell MK VI MK VIII EGPWS Installation Design Guide 7.5.1 System Status Messages System Status Messages provide additional information beyond Internal and External Current Faults in order to help isolate the reason for certain EGPWC INOP situations. These messages will be read out during Present Status on the RS-232 interface or voice output during Self-Test Level 2. The table below defines the System Status Messages. TABLE 7.5.1-1: EGPWC SYSTEM STATUS MESSAGES System Level Event Bank Angle INOP Envelope Mod INOP Mode 1 INOP Mode 2 INOP Mode 3 INOP Mode 4 INOP Mode 5 INOP Mode 6 INOP TAD Deselected 1 Terrain Awareness INOP 2 Terrain Clearance Floor INOP 3 Terrain Not Available 4 Windshear INOP 5 INTERNAL INDICATIONS BAINOP TRUE EMINOP Exists and set TRUE M1INOP TRUE M2INOP TRUE M3INOP TRUE M4INOP TRUE M5GPWINOP TRUE M6INOP TRUE System Status Message Bank Angle INOP Envelope Modulation INOP Mode 1 INOP Mode 2 INOP Mode 3 INOP Mode 4 INOP Mode 5 INOP Mode 6 INOP Terrain Awareness – No Valid Latitude Terrain Awareness - No Valid Longitude Terrain Awareness - No Valid True Heading Terrain Awareness - No Valid Corrected Altitude Terrain Awareness - No Valid Altitude Rate Terrain Awareness - No Valid Roll Terrain Awareness - Display Mode 1 Invalid Terrain Awareness - Display Mode 2 Invalid Terrain Awareness - Range 1 Invalid Terrain Awareness - Range 2 Invalid Terrain Awareness - No Valid Runway Terrain Awareness: No Valid Obstacle Terrain Awareness INOP Latitude Invalid Longitude Invalid True Heading Invalid Corrected Altitude Invalid Barometric Altitude Rate Invalid Roll Invalid Wx Mode 1 Invalid Wx Mode 2 Invalid Range 1 Invalid Range 2 Invalid Runway Distance invalid Obstacle Database Invalid TAINOP TRUE TCFINOP TRUE (Always Created) Terrain Clearance Floor INOP Position Error AND TCFINOP TRUE TAD Position Error AND TAINOP FALSE Terrain Clearance Floor - Position Error Terrain Awareness - Position Error Outside Regional Database TRUE (MK VI ONLY) WSINOP TRUE Terrain Awareness – Outside Regional Terrain Database Windshear INOP 1 The following preconditions apply: a) The signal must not be faulted since if faulted, signal fault message will exist, b) TAD/TCF Inhibit Discrete is NOT selected, c) TAD Disable program pin is NOT selected, d) The signal condition must NOT be masked via the configuration database and both On-Ground and In-Air masks must be taken into account, e) The associated input signal must exist for the current aircraft configuration. 2 TAD INOP Preconditions: a) TAD/TCF Inhibit Discrete NOT selected, and b) TAD Disable configuration NOT selected. 3 TCF INOP Precond itions: a) TCF Disable configuration NOT selected (TRUE causes TCF INOP). 4 TAD INOP Preconditions: a) TAD/TCF Inhibit Discrete NOT selected, and b) TAD Disable configuration NOT selected. 5 Windshear INOP Precondition: The windshear algorithm has been defined within the current aircraft configuration Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 318 Honeywell MK VI MK VIII EGPWS Installation Design Guide 8 CONNECTOR INTERFACE 8.1 Pinout for Front Connectors sorted by pin number Table 8.1-1: Pin Assignment For Front Connectors Sorted by Pin Number Connector Pin Channel Designation Reference J1-01 J1-02 J1-03 J1-04 J1-05 J1-06 J1-07 J1-08 J1-09 J1-10 SYN_1X SYN_1Z SYN_2Z 26REF_1H SYN_3X SYN_3Z SYN_3Y 28V_DISC_09 28V_DISC_08 J1-11 J1-12 J1-13 J1-14 J1-15 J1-16 J1-17 J1-18 J1-19 J1-20 J1-21 J1-22 J1-23 J1-24 J1-25 J1-26 J1-27 J1-28 J1-29 J1-30 28V_DISC_06 GND_DISC_09 GND_DISC_08 GND_DISC_07 GND_DISC_06 GND_DISC_05 GND_DISC_04 GND_DISC_03 GND_DISC_02 GND_DISC_01 SYN_1Y SYN_2X SYN_2Y 26REF_1L OAT_REF J1-31 J1-32 J1-33 J1-34 J1-35 J1-36 J1-37 J1-38 J1-39 J1-40 J1-41 J1-42 J1-43 J1-44 J1-45 J1-46 J1-47 J1-48 GND_DISC_13 GND_DISC_12 GND_DISC_11 GND_DISC_10 28V_DISC_05 28V_DISC_04 28V_DISC_03 28V_DISC_02 28V_DISC_01 PWR_H PWR_L GND ALT_L OAT_L RALT_L GSDEV_L GS_VAL_L 28V_DISC_10 28V_DISC_07 GS_VAL_H 28V_DISC_11 Signal Usage Summary Roll Attitude Synchro (X leg) Roll Attitude Synchro (Z leg) Magnetic Heading Synchro (Z leg) 26VAC Reference #1 (H) Pitch Synchro (X leg) Pitch Synchro (Z leg) Pitch Synchro (Y leg) Autopilot Engaged Discrete (+28VDC) Barometric Altitude Validity Discrete (+28VDC) Glideslope Deviation Low Level Validity (-) or Localizer Deviation (+ left) Glideslope Validity Discrete (+28VDC) Terrain Awareness and TCF Inhibit Discrete (Ground) Mode 6 Low Volume Discrete (Ground) Flap Override Discrete (Ground) Glideslope Cancel Discrete (Ground) Landing Gear Discrete (Ground) Audio Inhibit Discrete (Ground) Landing Flaps Discrete (Ground) Glideslope Inhibit Discrete (Ground) ILS Tuned Discrete (Ground) Roll Attitude Synchro (Y leg) Magnetic Heading Synchro (X leg) Magnetic Heading Synchro (Y leg) 26VAC Reference #1 (L) Air Temperature Reference (+5VDC) (Spare) (Spare) Magnetic Heading Validity Discrete (+28VDC) Radio Altitude Validity Discrete (+28VDC) Glideslope Deviation Low Level Validity (+) or Localizer Deviation (+ right) Display Selected Discrete #2 (Ground) Display Selected Discrete #1 (Ground) DH Discrete (Ground) Self Test Discrete (Ground) Landing Gear Discrete (+28VDC) Audio Inhibit Discrete (+28VDC) Landing Flaps Discrete (+28VDC) Glideslope Inhibit Discrete (+28VDC) ILS 1 Tuned Discrete (+28VDC) Power Input: 28 VDC (+) Power Input: 28 VDC (return) Chassis Ground Barometric Altitude (-) Air Temperature (-) Radio Altitude: ARINC 552 or ALT 55 (-) Glideslope Deviation - Low Level (+ down) (Spare) Localizer Validity Discrete (+28VDC) Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 319 Honeywell MK VI MK VIII EGPWS Installation Design Guide Connector Pin J1-49 J1-50 J1-51 J1-52 Channel Designation Reference DISC_OUT_9 MON_OUT_3 DISC_OUT_8 DISC_OUT_7 J1-53 J1-54 J1-55 J1-56 J1-57 J1-58 J1-59 J1-60 J1-61 J1-62 J1-63 J1-64 J1-65 J1-66 J1-67 J1-68 J1-69 J1-70 J1-71 J1-72 J1-73 GND DISC_OUT_6 MON_OUT_2 453TX_2A 453TX_2B 453TX_1A 453TX_1B PWR_H PWR_L ALT_H OAT_H RALT_H GSDEV_H J1-74 J1-75 J1-76 J1-77 J1-78 AUD_LL_L AUD_LL_H DISC_OUT_3 DISC_OUT_2 DISC_OUT_1 J2-01 J2-02 J2-03 J2-04 J2-05 J2-06 SYN_4X SYN_4Y SYN_5Z 429RX_5B 429RX_6B 429RX_7B J2-07 J2-08 J2-09 J2-10 J2-11 J2-12 J2-13 J2-14 J2-15 J2-16 J2-17 J2-18 J2-19 J2-20 J2-21 J2-22 429RX_8B 429RX_4B 429TX_2B ADC_RXB ADC_RXA GPS_RXB 429TX_GPS_B GND 28V_DISC_13 GND SC_PWR SYN_4Z SYN_5X SYN_5Y 429RX_5A 429RX_6A GND_DISC_14 28V_DISC_12 DISC_OUT_5 AUD_HL_H AUD_HL_L MON_OUT_1 DISC_OUT_4 Signal Usage Summary Terrain Select Relay Output #2 Windshear INOP Lamp Output (monitor) Spare Lamp Output Steep Approach (momentary) Lamp Output or Windshear Caution Lamp Output Temperature Probe GND Terrain Select Relay Output #1 TAD / TCF INOP Output (monitor) Terrain Display Output Data #2 (A leg) Terrain Display Output Data #2 (B leg) Terrain Display Output Data #1 (A leg) Terrain Display Output Data #1 (B leg) Power Input: 28 VDC (+) Power Input: 28 VDC (return) Barometric Altitude (+) Air Temperature (+) Radio Altitude: ARINC 552 or ALT 55 (+) Glideslope Deviation - Low Level (+ up) (Spare) GPWS Inhibit Discrete (Ground) Attitude Validity Discrete (+28VDC) Audio On (GND) Output High Level Audio Output - 8Ω (+) High Level Audio Output - 8Ω (-) GPWS INOP Output (monitor) Flap Override Output (Gnd) or Windshear Warning Output Low Level Audio Output - 600Ω (-) Low Level Audio Output - 600Ω (+) Glideslope Cancel Output Glideslope Alert Output GPWS Warning Output Configurable Synchro #1 (X leg) Configurable Synchro #1 (Y leg) Configurable Synchro #2 (Z leg) Radio Altitude ARINC 429 Input (B leg) ILS ARINC 429 Input (B leg) AHRS ARINC 429 Input B leg GPS #2 ARINC 429 Input B leg Spare ARINC 429 Input (B leg) GPS ARINC 429 Input (B leg) EGPWS ARINC 429 Output #2 (B leg) SCI Display Range #2 RS-422 Receive B leg (port 2) SCI Display Range #2 RS-422 Receive A leg (port 2) GPS RS-422 Receive B leg (port 3) Spare Discrete Input Configuration Module Power Return (Ground) Configuration Module Power (+5VDC) Configurable Synchro #1 (Z leg) Configurable Synchro #2 (X leg) Configurable Synchro #2 (Y leg) Radio Altitude ARINC 429 Input (A leg) ILS ARINC 429 Input (A leg) Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 320 Honeywell MK VI MK VIII EGPWS Installation Design Guide Connector Pin Channel Designation Reference J2-23 429RX_7A J2-24 J2-25 J2-26 J2-27 429RX_8A 429RX_4A 429TX_2A ADC_TXA J2-28 J2-29 GND GPS_RXA J2-30 J2-31 J2-32 J2-33 J2-34 J2-35 J2-36 429TX_GPS_A GND_DISC_15 SPICLK SPIMISO 26REF_2H 26REF_2L 429/422RX_1B J2-37 429/422RX_1A J2-38 J2-39 J2-40 429RX_2B 429RX_2A Signal Usage Summary AHRS ARINC 429 Input A leg GPS #2 ARINC 429 Input A leg Spare ARINC 429 Input (A leg) GPS ARINC 429 Input (A leg) EGPWS ARINC 429 Output #2 (A leg) RS-232 Transmit (port 2) RS-422 Transmit A leg (port 2) GPS RS-232 Common (port 2&3) GPS RS-232 Receive (port 3) GPS RS-422 Receive (A leg) (port 3) J2-42 J2-43 J2-44 J2-45 429TX_1B 429TX_1A ADC_TXB GPS_TXA J2-46 J2-47 J2-48 J2-49 J2-50 GPS_TXB Steep Approach Discrete #2 (Ground) Configuration Module Serial Clock Configuration Module Serial Input 26VAC Reference #2 (H) 26VAC Reference #2 (L) Display Range #1 ARINC 429 Input B leg SCI Display Range #1 RS-422 Input A leg (port 1) IOC #1 ARINC 429 Input B leg Display Range #1 ARINC 429 Input A leg SCI Display Range #1 RS-422 Input B leg (port 1) IOC #1 ARINC 429 Input A leg Air Data ARINC 429 Input (B leg) Air Data ARINC 429 Input (A leg) Display Range #2 ARINC 429 Input B leg IOC #2 ARINC 429 Input B leg Display Range #2 ARINC 429 Input A leg IOC #2 ARINC 429 Input A leg EGPWS ARINC 429 Output #1 (B leg) EGPWS ARINC 429 Output #1 (A leg) RS-422 Transmit B leg (port 2) GPS RS-232 Transmit (port 3) RS-422 Transmit (A leg) (port 3) RS-422 Transmit (B leg) (port 3) SPISEL_CM# SPIMOSI Configuration Module Serial Select Configuration Module Serial Output J3-01 J3-02 J3-03 J3-04 J3-05 J3-06 J3-07 J3-08 J3-09 J3-10 J3-11 J3-12 J3-13 J3-14 J3-15 GND CARD_PRES# RS232RXD_MON RS232TXD_MON SmartCable Power Return (Ground) PCMCIA Card Present EGPWS Monitor Port (RS232 Receive) EGPWS Monitor Port (RS232 Transmit) Reserved SmartCable Power (+5VDC) SmartCable Serial Clock SmartCable Serial Input SmartCable Serial Output SmartCable Serial Select GSE Present Ground Ground Ground Reserved J2-41 GPS ANT 429RX_3B 429RX_3A SC_PWR SPICLK SPIMISO SPIMOSI SPISEL_SC# GSE_PRES# GND GND GND COAX GPS COAX connection Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 321 Honeywell MK VI MK VIII EGPWS Installation Design Guide Figure 8.1-1, Front Panel Connector Orientation - J1, J2, J3, GPS ANT Note: The GPS ANT connector only applies to the 965-1190-0xx and the 965-1220-0xx. MK VI EGPWS shown. Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 322 Honeywell MK VI MK VIII EGPWS Installation Design Guide Figure 8.1-2, Connector Pin References - J1, J2, J3 Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 323 Honeywell MK VI MK VIII EGPWS Installation Design Guide 9 DEFINITIONS The following acronyms are provided for use with this document: Acronym Interpretation AAAS ADC ADS AGC AGL AHRS AIC AIMS ASA AOA ASL ATP BCD BIST BIT BITE BNR C/O CAA CAIMS CFDS CFIT CFM CISRD CMC COTS CP CRS CW DAA DADC DAU DC DDM DEVN DH DITS DME DO DSP DSU DSWC EEPROM EFCP EFIS EGPWC EGPWD EGPWS EICAS EMI ENB EPROM F/T F/W Alternate Audio Alert Select Air Data Computer Air Data System Automatic Gain Control Above Ground Level Attitude Heading Reference System Analog Input Controller Airplane Information Management System AlliedSignal Aerospace Angle of Attack Above Sea Level Acceptance Test Procedure Binary Coded Decimal Built in Self Test Built In Test Built In Test Equipment Binary Callouts Civil Aviation Authority Central Aircraft Information/Maintenance System Centralized Fault Display System Controlled Flight Into Terrain Cubic Feet per Minute CFDS Interface System Requirements Document Central Maintenance Computer Commercial Off the Shelf Control Panel Course Clockwise Digital/Analog Adapter Digital Air Data Computer Data Acquisition Unit Digital Command Difference in Depth of Modulation Deviation Decision Height Digital Information Transfer System Distance Measuring Equipment Discrete Output Digital Signal Processor Display Switching Unit Digital Stall Warning Computer Electrically Erasable Programmable Read Only Memory EFIS Control Panel Electronic Flight Instrument System Enhanced Ground Proximity Warning Computer Enhanced Ground Proximity Warning Display Enhanced Ground Proximity Warning System Engine Indication and Crew Alert System Electromagnetic Interference Enabled Erasable Programmable Read Only Memory Functional test Fail/Warning Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 324 Honeywell MK VI MK VIII EGPWS Installation Design Guide Acronym Interpretation FAA FCC FDR FIAS FMC FMS FPM FSEU FWC G/S GMT GPS GPW GPWS GT H/W HDG HDOP HFOM HSID I/O IAC ICD ILS INOP IOC IRS ISO IVS KT KTS LED LRRA LRU LSB LT MCP MDA MFD MKII MKV MKVI MKVII MKVIII MLS MMU MSB MSL N/A NCD ND NVM OMS P/N PAR PC PCMCIA PFD Federal Aviation Administration Flight Control Computer Flight Data Recorder Flight Inspection Aircraft System Flight Management Computer Flight Management System Feet per Minute Flaps/Slats Electronic Unit Fault Warning Computer Glideslope Greenwich Mean Time Global Position System Ground Proximity Warning Ground Proximity Warning System Greater Than Hardware Heading Horizontal Dilution of Position Horizontal Figure of Merit Hardware/Software Interface Document Input/Output Integrated Avionics Computer Interface Control Document Instrument Landing System Inoperative Input/Output Concentrator Inertial Reference System International Standards Organization Inertial Vertical Speed Knots Knots Light Emitting Diode Low Range Radio Altimeter Line Replaceable Unit Least Significant Bit Less Than Mode Control Panel Minimum Barometric Altitude Multi-Functional Display Mark Two Warning Computer Mark Five Warning Computer Mark Six Warning Computer Mark Seven Warning Computer Mark Eight Warning Computer Microwave Landing System Memory Management Unit Most Significant Bit Mean Sea Level Not Applicable No Computed Data Navigation Display Non Volatile Memory Onboard Maintenance System Part Number Parity Personal Computer Personal Computer Memory Card Industry Association Primary Flight Display Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 325 Honeywell MK VI MK VIII EGPWS Installation Design Guide Acronym Interpretation PMAT PP PVM PWS QFE QNH RA RAM RDOP ROM RTCA RTS RWY S/T S/W SDI SDRD SIG SPC SRD SSM ST SWC TA&D TACAN TAD TBD TCAS TCF TERPS TK TLB TSO TTL UART USM UTC UUT VDC VDOP VFOM VHF VLSI VOR W/S WC WGS-84 WX Portable Maintanence Access Terminal Program Pin Processor/Voice/Memory Predictive Windshear System Corrected Baro Alt relative to field elevation Corrected Baro Alt relative to sea level Radio Altitude Random Access Memory Radar Display Output Processing Read Only Memory Requirements and Technical Concepts for Aviation Ready to Transmit Signal Runway Self Test Software Source/Destination Identifier Software Design Requirements Document Significant Stall Protection Computer System Requirements Document Sign Status Matrix Self Test Stall Warning Computer Terrain Awareness & Display Tactical Air Navigation Terrain Awareness Display To Be Determined Traffic Collision Avoidance System Terrain Clearance Floor United States’ Standards for Terminal Instrument Procedures Track Translation Lookaside Buffer Technical Standing Order Tuned To Localizer Universal Asynchronous Receiver Transmitter Unsigned Magnitude Universal Time Correlation Unit Under Test Volts, DC Vertical Dilution of Precision Vertical Figure of Merit Very High Frequency Very Large Scale Integrated Circuit VHF Omni-directional Range Windshear Warning Computer World Geodetic System 1984 (ICAO Standard) Weather Radar Proprietary notice on title page applies CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-150 REV: SHEET 326
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File Type : PDF File Type Extension : pdf MIME Type : application/pdf PDF Version : 1.3 Linearized : No Encryption : Standard V1.2 (40-bit) User Access : Print, Copy, Annotate, Fill forms, Extract, Assemble, Print high-res Modify Date : 2003:07:17 10:54:52-06:00 Subject : MK VI / MK VIII EGPWS Class A TAWS Create Date : 2003:07:14 05:37:54Z Page Count : 326 Creation Date : 2003:07:14 05:37:54Z Mod Date : 2003:07:17 10:54:52-06:00 Producer : Acrobat Distiller 5.0 (Windows) Author : L. Matter Metadata Date : 2003:07:17 10:54:52-06:00 Creator : L. Matter Title : INSTALLATION DESIGN GUIDE -020 Description : MK VI / MK VIII EGPWS Class A TAWS Page Mode : UseOutlines Has XFA : NoEXIF Metadata provided by EXIF.tools