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
Honeywell
MK VI MK VIII EGPWS Installation Design Guide
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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.
Honeywell
MK VI MK VIII EGPWS Installation Design Guide
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Typed names constitute approval signatures. Actual signatures are on file at Honeywell in
Redmond, WA.
DRAWN Larry Matter 14-JULY-03
CHECK
ENGR Larry Matter 14-JULY-03
MFG
QA
APVD Jim Mulkins 14-JULY-03
APVD
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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
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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
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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
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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
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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
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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
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SECTION I
GENERAL INFORMATION
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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
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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
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MK VI MK VIII EGPWS Installation Design Guide
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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
060-4267-000
Line Maintenance Manual
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
076-4610-000
MK VI / MK VIII Failures Modes, Effects, and Safety Analysis
MK VI / MK VIII Failure Modes, Effects, and Criticality Analysis
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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 965-1190-
0XX 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 965-1220-
0XX 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
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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: 1575.42 MHz
Impedance: 50 ohms
Gain: 33 dB max, 26.5 dB preferred
Power: 5 VDC
Qualification: 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 P/N 071-01553-0200 TSO-C129
Sensor Systems P/N S67-1575-52 TSO-C129, ARINC 743A
Sensor Systems P/N S67-1575-133 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.
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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
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1.6 Technical C haracteristics
MK VI / VIII EGPWS
TSO Compliance: (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
Physical size (HxWxD): 6.20” x 3.04” x 10.30”
Weight: 3.9 pounds maximum
Mounting: Standard 3 inch King Radio rack
Temperature (operational): -55°C to +70°C (F2)
Altitude range: 55,000 feet (F2)
Cooling: No cooling necessary
Shock: No shock mounting required
Power Consumption (28 VDC): 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: TSO-C151b
Physical size: 2.68” x 1.51” x 0.32” (fits Positronic connector backshell)
Weight: <1 pound with connector and backshell
Mounting: Mounts to Positronic connector backshell
Temperature (operational): same as MK VI/MK VIII EGPWS
Altitude range: same as MK VI/MK VIII EGPWS
Cooling: No cooling necessary
Shock: No shock mounting required
Power Consumption (5 VDC): 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
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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. RD50F1OJVLC-15 P2 connector, female 1 EA 440-1233-001
Honeywell 700-1710-020 Configuration Module 1 EA 700-1710-020
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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 718-1391-xxx North & South America 1 EA 718-1391-xxx
Honeywell 718-1392-xxx Europe, Africa, Asia 1 EA 718-1392-xxx
Honeywell 718-1393-xxx Asia, Australia, Pacific 1 EA 718-1393-xxx
Honeywell 402-6075-xxx Label, TDB Front Panel 1 EA 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 Vendor P/N Description QTY UM Honeywell P/N
Honeywell
Honeywell
300-1151-0061
718-1593-0012
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
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Pic Wire&Cable D5102QX Hi Temp Quadraxial A/R EA
Pic Wire&Cable D771553 MIL-STD 1553 Data Bus A/R EA
ECS
ECS
4122021
312402
ARINC 453 cable (2 shields)
ARINC 453 cable (3 shields)
A/R
A/R
EA
EA
Emteq D70-022402T-01 ARINC 453 cable A/R EA
M17/176-00002
M83536/6-022M
M12883/44-01
Military Specification
Relay, 4PDT (Note 1)
Relay, Socket (Note 1)
A/R
A/R
A/R
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 071-01553-0200 KA 92 GPS Antenna (26dB) 1 EA 300-1147-001
Comant CI 405-2 KA 92 GPS Antenna (26dB) 1 EA 300-1147-001
Bendix/King 050-03318-0000 Antenna Installation Kit OPT EA 405-0432-001
Sensor Systems S67-1575-38 S67 GPS Antenna (29dB) 1 EA
Sensor Systems S67-1575-52 S67 GPS Antenna (26dB) 1 EA
Sensor Systems S67-1575-133 S67 GPS Antenna (33dB) 1 EA
Thermax M17/128-RG400 Coax Cable, RG400/U A/R EA
Coax Cable, RG-142B/U A/R EA
PIC S14293 Coax Cable A/R EA
PIC S44191 Coax Cable A/R EA
ECS 311901 Coax Cable A/R EA
ECS 311601 Coax Cable A/R EA
ECS 311201 Coax Cable A/R EA
Amp 225554-6 TNC Angle Plug, Male 1 EA 440-1239-001
Amphenol 79075 TNC Angle Plug, Male 1 EA 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
1EA
Klixon (T.I.) 7277-2-1 1 Amp Circuit Breaker, lamp
power +28
1EA
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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 GPWS BELOW G/S ALT EA
West Coast Spec. 90-81401-008 GPWS BELOW G/S (1) ALT EA
West Coast Spec. 90-81401-009 GPWS BELOW G/S (1) ALT EA
STACO 61406-003 GPWS G/S CANCEL ALT EA
STACO 61406-004 PULL UP GPWS TEST ALT EA
STACO 61406-005 GPWS GPWS TEST ALT EA
STACO 61406-006 BELOW G/S G/S CANCEL ALT EA
(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 (2) 1 EA
West Coast Spec. 90-81401-010 (3) 1 EA
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West Coast Spec. 90-81401-011 (4) 1 EA
West Coast Spec. 90-81401-012 (5) 1 EA
STACO 61406-007 GPWS FLAP OVERRIDE 1EA
(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
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 61406-001 TERRAIN DISPLAY ON 1 EA
STACO 61406-002 TERR INHIBIT ON 1 EA
STACO 61406-011 GPWS FAIL TERRAIN FAIL 1EA
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 30A05Z8 Audio Speaker 1 EA
Utah SP-3A Audio Speaker 1 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
05257
103-00157-3
103-00034
Single element, unheated
Single element, unheated
Dual element, unheated
1
1
1
EA
EA
EA
Rosemount 102CT2CB 500-ohm 1 EA
Rosemount 102AU1AF Single element, heated 1 EA
Rosemount 102AU1AG Dual element, heated 1 EA
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Rosemount 102EH2BH Dual element, heated 1 EA
Rosemount 102EH2EB Dual element, heated 1 EA
Rosemount 102JE2FG Triple element, heated 1 EA
Rosemount 129H-500 Single element, unheated 1 EA
Rosemount 129G-500 Dual element, unheated 1 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 EA 1 Positronic Ind. 9507
Hand Crimping Tool EA 1 Daniels AFM8
Hand Crimping Tool EA 1 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 EA 1 Positronic Ind. 9502-3
Contact Positioner, Socket P1 EA 1 Daniels K41 (for 22 to 28 AWG)
Contact Positioner, Socket P1 EA 1 Military M22520/2-06
Contact Positioner, Socket P2 EA 1 Positronic Ind. 9502-5
Contact Positioner, Socket P2 EA 1 Daniels K13-1 (20-24 AWG)
Contact Positioner, Socket P2 EA 1 Military M22520/2-08
Contact Positioner, Pin P3 EA 1 Positronics 9502-4
Contact Positioner, Pin P3 EA 1 Daniles 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 EA 1 Daniels DRK 95-22M
Removal Tool P1, P3 EA 1 Military M81969/8-02
Removal Tool P2 EA 1 Daniels DRK145
Insertion Tool P1, P3 EA 1 Daniels DAK 95-22M
Insertion Tool P1, P3 EA 1 Military M81969/8-01
Insertion Tool P2 EA 1 Daniels DAK145
Insertion/Removal Tool P1, P3 EA 1 Military M81969/1-04
Insertion/Removal Tool P2 EA 1 Military M81969/1-02
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1.10.4 Spare Conn ectors and Contacts - P1, P2, P3
P/N Description UM QTY Vendor Name & Part Number
440-1223-002 15 pin male with hood EA 1 Positronic Ind. DD15M10YOC-15
440-1223-003 115 pin female EA 1 Positronic Ind. DD15F10OOC-15
440-1223-004 115 pin male EA 1 Positronic Ind. DD15M10OOC-15
400-5163-002 115 pin clamp kit EA 1 AMP 745854-3
male contacts for 15 pin 22-30 AWG EA 1 Positronic Ind. MC8022D
male contacts for 15 pin 22-30 AWG EA 1 M39029/58-360
female contacts for 50 pin 20-24 AWG EA 1 Positronic Ind. FC6020D
female contacts for 50 pin 20-24 AWG EA 1 M39029/63-368
female contacts for 78 pin 22-30 AWG EA 1 Positronic Ind. FC8022D
female contacts for 78 pin 22-30 AWG EA 1 M39029/57-354
1 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
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SECTION II
INSTALLATION
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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
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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
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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.
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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 700-
1710-001). 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 P2 pin #
Violet P2-17
Blue P2-16
Orange P2-33
Black P2-50
White P2-49
Red P2-32
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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
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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
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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
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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
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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
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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
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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
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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
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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.
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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
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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 -Optional-
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 GPWS and BELOW G/S lights and/or other EGPWS
annunciators.
GPWS CANCLD -Optional-
If 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.
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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.
Figure 2.3
PULLUP
GPWS
PULLUP
GPWS
TERR
ON
TERR
INHB
TERR
FAIL
The above picture is an example of lamp location and
does not restrict lamp location or format
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FIGURE 2-2 MK VI/MK VIII EGPWS OUTLINE
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FIGURE 2-3 MK VI/MK VIII EGPWS MOUNTING TRAY
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THIS PAGE INTENTIONALLY LEFT BLANK
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SECTION III
SYSTEM PLANNING
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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
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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
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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
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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
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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.
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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.
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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
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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
Boundaries Mode 4
Aircraft type /
Alternate Mode 4B
Mode 4A Gear Down
at 500 ft, < X knots
Mode 4B Flaps Down
feet / < X knots
Mode 4 A/B
Maximum
A/B
Type
GA Fast, Normal Mode 4B 178 knots 170 ft / 150 knots 750 ft 6
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 1750 ft 7
GA Slow, Alternate Mode 4B 148 knots 150 ft / 118 knots 1750 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
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°
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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.
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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.
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62
43
9
25
63
44
53
J1
Altitude Out
Signal Common
BIT Out
Analog Air Data ComputerEGPWS MK VI / MK VIII
(+)
(-)
Uncorrected
Barometric
Altitude
Baro Altitude Valid +28V
(+)
(-)
Temp. Input
Chassis Ground
+5V Excitation
500 ohm
Temperature
Probe
Analog-ADC.vsd
Cat 2 Uncorrected Baro Altitude 1
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 11/122J1A-63 J1A-11 (CGND) J1A-12
Honeywell AZ-242 411/122J1B-174J1A-11 (CGND) J1A-12
Honeywell AZ-648 11/122J1-J J1-G J1-U
Honeywell AZ-800311/122J1A-78 J1A-10 (CGND) J1A-34
Honeywell AZ-810311/122J1A-78 J1A-10 (CGND) J1A-34
Honeywell AZ-252 11/122J1A-17 J1A-10 (CGND) J1A-34
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.
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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.
39
38
A
B
J2 ARINC 429 Air Data
ARINC 429 Bus - Hi
ARINC 429 Bus - Lo
EGPWS MK VI / MK VIII
A
B
ARINC 429 Low Speed
Air Data Bus
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
(s/w mod 71.73.01)
5* J1-40 J1-22
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.
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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.
39
38
A
B
J2 ARINC 575 Air Data
ARINC 575 Bus - Hi
ARINC 575 Bus - Lo
EGPWS MK VI / MK VIII
A
B
ARINC 575
Air Data Bus
ARINC575-ADC.vsd
Cat 2 Bus 1 Bus 2
Vendor Model ID A B A B
Collins ADC-80( )
Collins ADC-82A
2 P3-35 P3-36
B&D 90004 2 J1-27 J1-9
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.
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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.
39
38
A
B
J2 ARINC 429 Air Data
ARINC 429 Bus - Hi
ARINC 429 Bus - Lo
EGPWS MK VI / MK VIII
A
B
A
RINC 429 Low Speed
Air Data Bus
(+)
(-)
Temp. Input
Chassis Ground
+5V Excitation
500 ohm
Temperature
Probe
25
63
44
53
J1
Shadin2000.vsd
Cat 2 Bus 1 Bus 2
Vendor PN ID A B A B
962830-1,2,3 10 J2-7 J2-8
962830A-1,2,3
962830A-X-S-4
962830A-X-S-5
10
J1-40 J1-22
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.
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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.
37
36
A
B
J2 IOC Buses
IOC Bus 1
EGPWS MK VI / MK VIII
A
B
ARINC 429
High Speed
41
40
A
B
IOC Bus 2
A
B
ARINC 429
High Speed
ARINC429-IOC.vsd
Cat 2 IOC Bus 1 IOC Bus 2
Vendor Model ID A B A B
BD-100
CJ-1/CJ-2
255
255
A4P1-1
P1-1
A4P1-2
P1-2
A4P101-1
P101-1
A4P101-2
P101-2
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.
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.
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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, RS-
232, 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.
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3.5.4 ARINC 429 BUS (Cat. 3 ID 0,1,4,5,10-13)
25
8
A
B
J2 ARINC 429 GPS
ARINC 429 Bus - Hi
ARINC 429 Bus - Lo
EGPWS MK VI / MK VIII
A
B
ARINC 429
GPS Bus
ARINC429-GPS.vsd
Cat 3 429 GPS Alt ARINC Bus 1 Bus 2
Vendor Model ID Speed Ref. 743/743A A B A B
Collins GNLU-910A Note 5 High MSL 743A LMP-2J LMP-2K
Collins GPS-4000 0/42H/L2MSL 743A MP-11A MP-11B
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
(1017-3X-XXX) or
(1017-4X-XXX)
1 Low WGS-84 743 P1-a P1-b
UNS-1D
(1192-00-1111XX) or
(1192-30-1111XX)
1 Low WGS-84 743 MP-10J MP-10K
UNS-1F, -1E, -1L
(2192-00-11110X)
0 Low MSL 743A MP-10J MP-10K MP-4J MP-4K
UNS-1K
(1116-3X-111X) or
(1116-4X-111X)
1 Low WGS-84 743 MP-4C MP-4D
UNS-1M
(1013-4X-XXX)
1 Low WGS-84 743 P2-K P2-L
GNS-XLS
(17960-0203-) SM04
(17960-0102-) SM07
0 Low MSL 743A J101-N5 1J101-N6 1
GNS-XL
(18355-) SM06
0 Low MSL 743A J101-N5 1J101-N6 1
GNS-X / CDU-XLS
(14141-0624-) SM04
0 Low MSL 743A JA-A01 JA-A02
HG2021GBXX 1/5 2H/L2MSL 743 J1-38 J1-39 J1-24 J1-25
HG2021GC/GDXX 0/4 2H/L2MSL 743A J1-38 J1-39 J1-24 J1-25
HT1000/HT9100 10/12 H/L WGS-84 743A MP-C02 MP-C01
FreeFlight (Trimble)
2101 I/O Approach Plus
(81440-XX software ver. 241F)
0 Low MSL 743A J1-16 J1-23 J1-58 J1-57
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 Enhanced GNS-XLS ARINC 429 bus also contains Range label
2 HG2021G: Pin 21 open = high speed; Pin 21 GND = Low speed; GPS-4000:
3 North/South Velocity (label 166) and East/West Velocity (label 174) are required in MK VI / MK VIII -008 software and on.
4 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
5 Check manufacturer for compatibility with North-South, East-West Velocities.
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3.5.5 RS-232 Tra nsmit-Receive, 9600 baud (Cat. 3 ID 3)
45
29
J2 RS-232 GPS
RX – Receive In
TX – Transmit Out
EGPWS MK VI / MK VIII
TX
RX
RS – 232
GPS Bus
28CM
GND
NC
RS232-GPS.vsd
GPS Alt ARINC NS3RS-232
Vendor Model Ref. 743/743A EW RX TX GND
GARMIN GNS430/5302
Software Version 2.21
MSL N/A Note 3 P4001-56 Chassis
KLN 900
066-04034-0104 or
066-04034-0204
MSL N/A OK P9002-13 Chassis
KLN 94 MSL N/A OK P941-6 Chassis
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.
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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.
25
8
A
B
J2 ARINC 429 GPS
ARINC 429 Bus 1
Lo
EGPWS MK VI / MK VIII
A
B
ARINC 429
GPS Bus
23
6
A
B
A
B
ARINC 429
GPS Bus
Hi
ARINC 429 Bus 2
Lo
Hi
ARINC429-DualGPS.vsd
Cat 3 429 GPS Alt ARINC Bus 1 Bus 2
Aircraft Model ID Speed Ref. 743/743A A B A B
253 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: 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 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.
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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.
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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. DGAC-
registered 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
CONDITION Retractable Gear
(Type 0 and 1)
Fixed Gear
(Type 2 and 3)
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.
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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).
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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
False or True in Category 7. If False,
Pop Up behavior for the terrain
display is described here.
The TA&D Alternate Pop Up is set to
False or True in Category 7. If True,
Pop Up behavior for the terrain
display is described here.
Peaks Mode Category 7, Options Select Group #1
See Note 1 Peaks Enable: False Peaks Enable: True
Peaks Enable is set to False or True
in Category 7. The effect of setting it
to False is described here.
Peaks Enable is set to False or True
in Category 7. The effect of setting it
to True is described here.
Manual select Describes if/when terrain display(s) can be manually selected
Manual deselect Describes if/when terrain display(s) can be manually deselected
Auto Range Defines if the display data is automatically scaled and, if so, the scale used
(such as 10 nautical miles)
Moving Marker Indicates whether or not a moving marker is provided
Overlay Page Describes where “TERR” and Peaks Elevations overlays will be located on the
display screen.
Display bus type Defines the display bus type ‘KC Picture Bus’ (KCPB was ASPB), ‘Honeywell
Picture Bus’ or ‘ARINC 453’.
CHANNEL
TX453-1 CONNECT TO:
A = J1-58
B = J1-59 Indicates the correct connection for these pins
CHANNEL
TX453-2 CONNECT TO:
A = J1-56
B = J1-57 Indicates the correct connection for these pins
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
CONNECT TO:
WXR Output 429 bus 1
Fault Designation: DISPLAY BUS 1
Bus Type: Basic
A = J2-37
B = J2-36
Data
Range
Status
Reference Label Sig. Bits Range Signal Type Resolution Rate (ms)
CHANNEL
429RX_3
CONNECT TO:
WXR Output 429 bus 1
Fault Designation: DISPLAY BUS 2
Bus Type: Basic
A = J2-41
B = J2-40
Data
Range
Status
Reference Label Sig. Bits Range Signal Type Resolution Rate (ms)
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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 Polarity/Configuration
J1-32 GND_DISC_12
Reference
6.6.18 Display Select Discrete #1
Type 1 (Momentary)
Gnd = Display Select Toggle
<not> Gnd = Normal
J1-31 GND_DISC_13
Reference
6.6.19 Display Select Discrete #2
Type 1 (Momentary)
Gnd = Display Select Toggle
<not> 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.
Output 429 Bus Group
Channel Pins Comments
429TX_1 A = J2-43
B = J2-42
Transmits Label sets: (Section 7)
429TX_2 A = J2-26
B = J2-9
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
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Honeywell GNS-XLS
J2
J1
J101
N5
N6
Q4
Q6
37
36
25
8
41
40
58
59
56
57
TERR
INHIB
TERR
INOP
Lamp Test
28V Lamp Dimming Bus
Alternate Action
12
55
EGPWS GNS-XLS
A
B
ARINC 429 Range #1 In
A
B
ARINC 429 GPS In
A
B
ARINC 429 Range #2 In
A
B
KCPB Video #1 Out
A
B
KCPB Video #2 Out
Terrain Inhibit (in)
Terrain INOP (out)
MK VI 965-11X0-020 or later.
MK VIII 965-12X0-020 or later.
A
B
A
B
Range & GPS out
KCPB Video in (H)
17960-0203-XXXX
SM04
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
GNS-XLS-1.vsd
70-ohm termination
Q5 KCPB Video in (L)
No connection
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Honeywell KMD 540/
550/850
J2
J1
J3001
29
30
11
12
13
31
37
36
41
40
58
59
56
57
TERR
INHIB
TERR
INOP
Lamp Test
28V Lamp Dimming Bus
Alternate Action
12
55
EGPWS KMD 540/550/850
A
B
ARINC 429 Range #1 In
A
B
ARINC 429 Range #2 In
A
B
KCPB Video #1 Out
A
B
KCPB Video #2 Out
Terrain Inhibit (in)
Terrain INOP (out)
A
B
A
B
429 Out
KCPB Video in
(No termination)
Note:
For interface and operation of the Honeywell KMD 540/550/850
see Honeywell Installation Manual P/N 006-10608-0001
KMD540-1.vsd
No connection
MK VI 965-11X0-020 or later.
MK VIII 965-12X0-020 or later.
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Honeywell Grimes
TRA-45A
J2
J1
J1
J1
28
13
1
3
28
13
1
3
37
36
41
40
58
59
56
57
TERR
INHIB
TERR
INOP
Lamp Test
28V Lamp Dimming Bus
Alternate Action
12
55
EGPWS TRA-45A
TRA-45A
A
B
ARINC 429 Range #1 In
A
B
ARINC 429 Range #2 In
A
B
KCPB Video #1 Out
A
B
KCPB Video #2 Out
Terrain Inhibit (in)
Terrain INOP (out)
MK VI 965-11X0-020 or later.
MK VIII 965-12X0-020 or later.
A
B
A
B
A
B
A
B
Range out
KCPB Video in
70-ohm termination
Range out
KCPB Video in
70-ohm termination
80-5145-X-2
Note:
For interface and operation of the Honeywell Grimes TRA-45A see
Honeywell TRA-45A Equipment Installation Manual P/N 34-40-01
80-5145-X-2
TRA45.vsd
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AVTECH DSU
Primus WXR UDI
J2
J1
J1
8
9
47
48
37
36
41
40
58
59
56
57
TERR
INHIB
TERR
INOP
Lamp Test
28V Lamp Dimming Bus
Alternate Action
12
55
EGPWS
AVTECH DSU
A
B
ARINC 429 Range #1 In
A
B
ARINC 429 Range #2 In
A
B
KCPB Video #1 Out
A
B
KCPB Video #2 Out
Terrain Inhibit (in)
Terrain INOP (out)
MK VI 965-11X0-020 or later.
MK VIII 965-12X0-020 or later.
A
B
A
B
Range out
KCPB Video in
Note:
For interface and operation of the Avtech 6001 DSU see Avtech
DSU Installation and Operation Procedure P/N 6001-1680
P/N 6001-1
PrimusUDI-1.vsd
PRIMUS SERIES
90, 100, 200, 300,
300SL, 400, 500, AVQ30
450, 650 w/o Lightning,
800
440, 650 w/ Lightning,
660, 700, 870, 880 219
13
6
18
9
3
16
12
10
4
8
15
11
17
14
5
7
219
13
6
18
9
3
16
12
10
4
8
15
11
17
NC
5
7
1
NJESUTDHR MKLA PCVBGF
49
open
7
2
TERR
ON
momentary 32
Display Invalid
Terrain Select
Terrain Status
J2
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Integrated
Primus 440/660/880
J2
J1
F
G
M
L
37
36
41
40
58
59
56
57
TERR
INHIB
TERR
INOP
Lamp Test
28V Lamp Dimming Bus
Alternate Action
12
55
EGPWS
Honeywell
Radar Indicator
A
B
RS-422 Serial Range #1 In
A
B
Range #2 In
A
B
ARINC 453 Video #1 Out
A
B
ARINC 453 Video #2 Out
Terrain Inhibit (in)
Terrain INOP (out)
MK VI 965-11X6-004 or later.
MK VIII 965-12X6-004 or later.
P
N
P
N
SCI Bus
WXPD Bus
Note:
For interface and operation of the Honeywell Weather Radar Indicator
WI-440, 660, 880 see Honeywell Service Bulletin 7007700-34-15
WI-440, 660, 880
7007700-X1X
IntP880.vsd
NC
NC
Honeywell WRX R/T
WU-440, 660, 880
71 72 3 4
TERR
ON
momentary
32
54
Terrain Display Select (in)
Terrain Display Select (out)
28V EGPWS PWR Bus
XEGPWS Selected
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Honeywell Primus
1000
J2
J1
12
25
41
42
37
36
43
42
58
59
TERR
INHIB
Lamp Test
28V Lamp Dimming Bus
Alternate Action
12
EGPWS Integrated Avionics
Computer IC-600
A
B
ARINC 429 Range #1 In
A
B
ARINC 429 Range #2 In A
B
ARINC 429
Control Bus Out
A
B
ARINC 453 Symbol
Generator Out
Terrain Inhibit (in)
MK VIII 965-12X0-020 or later.
A
B
A
B
429 Out
EGPWS Cont
7017000
Primus1000.vsd
41
40
41
42
12
25
Integrated Avionics
Computer IC-600
A
B
A
B
EGPWS Cont
429 Out
7017000
PILOT
CO-PILOT
Display Unit DU-870
7014300
74
75
A
B453 Bus In
Display Unit DU-870
7014300
74
75
A
B453 Bus In
61
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Honeywell / Bendix
RDR 2000 / IN182A
J2
J1
27
2
1
20
37
36
41
40
58
59
56
57
TERR
INHIB
TERR
INOP
Lamp Test
28V Lamp Dimming Bus
Alternate Action
12
55
EGPWS
Honeywell
Radar Indicator
A
B
ARINC 429 Range #1 In
A
B
ARINC 429 Range #2 In
A
B
ARINC 453 Video #1 Out
A
B
ARINC 453 Video #2 Out
Terrain Inhibit (in)
Terrain INOP (out)
MK VI 965-11X0-020 or later.
MK VIII 965-12X0-020 or later.
H
C
Control Bus A
T/R Data Bus
Note:
For interface and operation of the Honeywell RDR 2000 Color Weather
Radar system see Honeywell Installation Manual 006-00643-0000
IN182A
066-3084-XX
RDR2000.vsd
NC
Honeywell WRX R/T
ART 2000
2342 43
TERR
ON
momentary
32
54
Terrain Display Select (in)
Terrain Display Select (out)
28V EGPWS PWR Bus
31 RT On/Off 1
31
A
B
Honeywell
MK VI MK VIII EGPWS Installation Design Guide
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Honeywell / Bendix
PPI-4B
J2
J1
10
11
5
12
37
36
41
40
58
59
56
57
TERR
INHIB
TERR
INOP
Lamp Test
28V Lamp Dimming Bus
Alternate Action
12
55
EGPWS
Honeywell
Radar Indicator
A
B
ARINC 429 Range #1 In
A
B
ARINC 429 Range #2 In
A
B
ARINC 453 Video #1 Out
A
B
ARINC 453 Video #2 Out
Terrain Inhibit (in)
Terrain INOP (out)
MK VI 965-11X0-020 or later.
MK VIII 965-12X0-020 or later.
H
C
Control Bus A
T/R Data Bus
PPI-4B
2041222-XXXX
PPI4A4B.vsd
NC
Honeywell WRX R/T
RTA-4B
3B 4B 2D 3D
TERR
ON
momentary
32
54
Terrain Display Select (in)
Terrain Display Select (out)
28V EGPWS PWR Bus
15 RT On/Off 1
6BBP
A
B
5L
T/R Data Bus
70-ohm termination
Honeywell
MK VI MK VIII EGPWS Installation Design Guide
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453 DATA BUS A OUT
BENDIX/KING
WEATHER RADAR R/T
429 CONTROL BUS 1A IN
453 DATA BUS B OUT
SEE NOTE 2.
429 CONTROL BUS 1B IN
MARK VI/VIII ENHANCED GROUND
PROXIMITY WARNING COMPUTER
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
SEE NOTE 3.
37
J2
41
40
36
KCPB B OUT
KCPB A OUT
TERRAIN POP-UP OUT
58
J1
59
51
SEE NOTE 1.
SEE NOTE 1.
SEE NOTE 1.
SEE NOTE 1.
SEE NOTE 1.
22 R/T TRANSMITTER 429 A OUT
P465
2BBENDIX/KING SG 465
SYMBOL GENERATOR #1
49
SEE NOTE 1.
SEE NOTE 1.
R/T TRANSMITTER 429 B OUT
68
81
P465
22
49
1B
P465
2B
SEE NOTE 1.
R/T TRANSMITTER 429 A OUT
R/T TRANSMITTER 429 B OUT
BENDIX/KING SG 465
MFD SYMBOL GENERATOR
453 DATA BUS B IN
453 DATA BUS A IN
PRESS-TO-TEST
+28VDC POWER IN
+28VDC POWER IN
40
60
TERRAIN SELECT RELAY OUT54
TERRAIN INOP55
TERRAIN SELECT SWITCH IN
TERRAIN INHIBIT SWITCH IN12
32
PRESS-TO-TEST
TERRAIN INHIBIT
POWER
+28VDC AVIONICS
EGPWS
ANNUNCIATOR DIMMER
ANNUNCIATOR
BUS
EGPWS FAIL
NORMAL
NORMAL
STANDBY
DISPLAY DOWN
TERRAIN
ON
ANNUNCIATOR DIMMER
(ALTERNATE ACTION)
(MOMENTARY)
BUS
ANNUNCIATOR
USE M17/176-0002 SHIELDED WIRE OR 024-00064-0000
QUADRAX CABLE FOR THE 453 DATA BUS AND THE KCPB.
(3.13) FOR THE COMPLETE INTERFACE TO THE BENDIX/KING
REFER TO THE WEATHER RADAR SECTION OF THIS MANUAL
THE CATEGORY 6 DISPLAY TYPE ID 10 (INTEGRATED EFIS 40/50)
37
22
P465
1A
TERRAIN POP-UP DISCRETE IN
TERRAIN SELECTED DISCRETE IN
WEATHER RADARS.
IS THE REQUIRED CONFIGURATION.
NOTES:
1.
2.
3.
THIS CONFIGURATION IS NOT SUPPORTED PRIOR TO EGPWS
THE CATEGORY 13 I/O DISCRETE TYPE ID 1 (LAMP FORMAT 2)
COMPUTER PART NUMBERS:
IS THE PREFERRED CONFIGURATION.
4.
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
Honeywell
MK VI MK VIII EGPWS Installation Design Guide
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54
TERRAIN SELECT RELAY OUT
453 DATA BUS A OUT
BENDIX/KING
WEATHER RADAR R/T
SEE NOTE 2.
429 CONTROL BUS 1A IN
429 CONTROL BUS 1B IN
KCPB A OUT58
MARK VI/VIII ENHANCED GROUND
PROXIMITY WARNING COMPUTER
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
41
453 DATA BUS B OUT
J2
36
37
40
J1
SEE NOTE 3.KCPB B OUT
TERRAIN POP-UP OUT51
59
+28VDC POWER IN
+28VDC POWER IN
40
60
SEE NOTE 1.
SEE NOTE 1.
POWER
+28VDC AVIONICS
SEE NOTE 1.
EGPWS
SEE NOTE 1.
SEE NOTE 1.
68
81
P465
22
49
2B
SEE NOTE 1.
BENDIX/KING SG 465
MFD SYMBOL GENERATOR
R/T TRANSMITTER 429 A OUT
R/T TRANSMITTER 429 B OUT
453 DATA BUS B IN
453 DATA BUS A IN
1B
P465
37
22
P465
1A
TERRAIN POP-UP DISCRETE IN
TERRAIN SELECTED DISCRETE IN
ANNUNCIATOR DIMMER
PRESS-TO-TEST
TERRAIN INOP55
TERRAIN SELECT SWITCH IN
TERRAIN INHIBIT SWITCH IN12
32
TERRAIN INHIBIT
(ALTERNATE ACTION)
PRESS-TO-TEST
ANNUNCIATOR DIMMER
ANNUNCIATOR
BUS
EGPWS FAIL
TERRAIN
ON
ANNUNCIATOR
(MOMENTARY)
BUS
USE M17/176-0002 SHIELDED WIRE OR 024-00064-0000
QUADRAX CABLE FOR THE 453 DATA BUS AND THE KCPB.
REFER TO THE WEATHER RADAR SECTION OF THIS MANUAL
(3.13) FOR THE COMPLETE INTERFACE TO THE BENDIX/KING
THIS CONFIGURATION IS NOT SUPPORTED PRIOR TO EGPWS
THE CATEGORY 6 DISPLAY TYPE ID 10 (INTEGRATED EFIS 40/50)
THE CATEGORY 13 I/O DISCRETE TYPE ID 1 (LAMP FORMAT 2)
COMPUTER PART NUMBERS:
IS THE REQUIRED CONFIGURATION.
IS THE PREFERRED CONFIGURATION.
WEATHER RADARS.
2.
NOTES:
1.
3.
4.
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
Honeywell
MK VI MK VIII EGPWS Installation Design Guide
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Rockwell Collins
WXI-701/711
J2
J1
10
11
5
12
37
36
41
40
58
59
56
57
TERR
INHIB
TERR
INOP
Lamp Test
28V Lamp Dimming Bus
Alternate Action
12
55
EGPWS
Collins WXI-701
Radar Indicator
A
B
ARINC 429 Range #1 In
A
B
ARINC 429 Range #2 In
A
B
ARINC 453 Video #1 Out
A
B
ARINC 453 Video #2 Out
Terrain Inhibit (in)
Terrain INOP (out)
MK VI 965-11X0-020 or later.
MK VIII 965-12X0-020 or later.
H
C
Control Bus A
T/R Data Bus
2041222-XXXX
WXI-701.vsd
NC
Collins WRX R/T
WRT-XXX
?? 8 9
TERR
ON
momentary
32
54
Terrain Display Select (in)
Terrain Display Select (out)
28V EGPWS PWR Bus
15 RT On/Off 1
6BJ1
A
B
6L
T/R Data Bus
70-ohm termination
Honeywell
MK VI MK VIII EGPWS Installation Design Guide
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Collins ProLine II
with WXP-840/850
J2
15
16
18
19
36
37
58
59
Lamp Test
28V Lamp Dimming Bus
EGPWS
Collins Wx Pnl
WXP-840/850
A
B
ARINC 429 Range #1
A
B
ARINC 453 Video #1
MK VI 965-11X0-020 or later.
MK VIII 965-12X0-020 or later.
A
B
A
B
ARINC 429 Range
ARINC 453 Picture
Note:
For interface and operation of the Collins Proline II displays see Collins
SIL 2-99
CollinsP2.vsd
TERR
ON
momentary
31Terrain Display Select (in)
Terrain Display Select (out)
28V EGPWS
PWR Bus
11 Remote ON
J1
40
41
56
57
A
B
ARINC 429 Range #2
A
B
ARINC 453 Video #2
J1
18
19
Collins Wx Pnl
WXP-840/850
A
B
ARINC 453 Picture
28V EGPWS
PWR Bus
11 Remote ON
15
16
A
B
ARINC 429 Range
54
49
Terrain Display Select (out)
TERR
ON
momentary
31Terrain Display Select (in) To WX R/T
To
WX
R/T
Honeywell
MK VI MK VIII EGPWS Installation Design Guide
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HONEYWELL
MK VI-VIII
EGPWS
965-1XXX-0XX
J2
ARINC 453 OUTPUT (A)
ARINC 453 OUTPUT (B)
58
59
P P
RANGE INPUT (A)
RANGE INPUT (B)
37
36
P
P
P1
3*
4*
#1 - IOC (ICC-4000)
PROLINE 4 INTERFACE
MK VI-VIII EGPWS Category 6, ID 5 or 6
P1
8D
10D
#1 - MFD
H - ARINC 453
L - (70 ohm terminated)
4
29
#1 - WXR
H
L
P
P1
P P
RANGE INPUT (A)
RANGE INPUT (B)
41
40
P1
3*
4*
#2 - IOC (ICC-4000)
ARINC 453 OUTPUT (A)
ARINC 453 OUTPUT (B)
56
57
P
PP1
8D
10D
#2 - MFD
H - ARINC 453
J1
LA-GP-5 bus (Label 271)
RA-GP-5 bus (Label 271)
* ICC-851A pins 13 & 14
* ICC-851A pins 13 & 14
11D L - (unterminated)
11D L - (unterminated)
L - (70 ohm terminated)
TERR RLY SELECT #1 54
TERR
+28 VDC
MOM TERR SELECT #1 32
TERR
+28 VDC
TERR RLY SELECT #2 49
MOM TERR SELECT #2 31
ARINC 453 OUT
+28 VDC
+28 VDC
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).
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MK VI MK VIII EGPWS Installation Design Guide
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34
23
35
1
H
L
J1
LEFT DISPLAY
CONTROLLER
Controller Serial Data
WX pushbutton
GND
DC-810
TERR 34
23
35
1
H
L
J1 RIGHT DISPLAY
CONTROLLER
Controller Serial Data
WX pushbutton
GND
DC-810
TERR
L-EFIS +28 VDC R-EFIS +28 VDC
78
77
Controller Serial Data
J1A
LEFT SYMBOL
GENERATOR
SG-802
H
L78
77
H
L
J1A RIGHT SYMBOL
GENERATOR
Controller Serial Data
SG-802
1
2
J1B
H
L
WX/TERR
PICTURE BUS IN
22
23
H
L
1
2
J1B
H
L
22
23
H
L
J1
H
L
58
59
H
L
H
L
H
L
Radar Serial Data
J2A
3
5
+28V
GND
L-EFIS +28 VDC
J2A
3
5
R-EFIS +28 VDC
Radar Serial Data
+28V
GND
H
L
56
57
H
L
WX/TERR
PICTURE BUS IN
PN 7003400-802 PN 7003400-802
51
J1 J1
J2
H
L
36
37
J1
Radar R/T
MK VIII EGPWS
DISPLAY
BUS #1 DISPLAY
BUS #2
TERRAIN
POP UP
LT SCI
RANGE
g
h
k
s
Left Picture
Bus
Right Picture
Bus
q
Picture Bus Shield
m
n
Left EFIS
Control Bus
e
f
Right EFIS
Control Bus
WU-650
(HPN 7008470-XXX)
(HPN 965-12XX-020)
CAT 6: ID 243
SG-802/803
CAT. 6: ID 243
32 LT DISP
SELECT 31
RT DISP
SELECT
RT SCI
RANGE
J2
H
L
10
11
54 LT RELAY
SELECT 49
RT RELAY
SELECT
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34
23
35
1
H
L
J1
LEFT DISPLAY
CONTROLLER
Controller Serial Data
WX pushbutton
GND
DC-811
TERR 34
23
35
1
H
L
J1 RIGHT DISPLAY
CONTROLLER
Controller Serial Data
WX pushbutton
GND
DC-811
TERR
L-EFIS +28 VDC R-EFIS +28 VDC
67
68
Controller Serial Data
J1A
LEFT SYMBOL
GENERATOR
SG-806
H
L67
68
H
L
J1A RIGHT SYMBOL
GENERATOR
Controller Serial Data
SG-806
30
31
J2B
H
L
WX/TERR
PICTURE BUS IN
32
33
H
L
30
31
J1B
H
L
32
33
H
L
J1
H
L
58
59
H
L
H
L
H
L
Radar Serial Data
J2A
1
8
+28V
GND
L-EFIS +28 VDC
J2A
1
8
R-EFIS +28 VDC
Radar Serial Data
+28V
GND
H
L
56
57
H
L
WX/TERR
PICTURE BUS IN
PN 7013788-806 PN 7013788-806
51
J1 J1
J2
H
L
36
37
J1
Radar R/T
MK VIII EGPWS
DISPLAY
BUS #1 DISPLAY
BUS #2
TERRAIN
POP UP
LT SCI
RANGE
g
h
k
s
Left Picture
Bus
Right Picture
Bus
q
Picture Bus Shield
m
n
Left EFIS
Control Bus
e
f
Right EFIS
Control Bus
WU-650
(HPN 7008470-XXX)
(HPN 965-12XX-020)
CAT 6: ID 244
SG-806
32 LT DISP
SELECT 31
RT DISP
SELECT
RT SCI
RANGE
J2
H
L
10
11
54 LT RELAY
SELECT 49
RT RELAY
SELECT
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MK VI MK VIII EGPWS Installation Design Guide
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Universal MFD-640
J2
J1
P1
105
115
81
80
37
36
41
40
58
59
56
57
TERR
INHIB
TERR
INOP
Lamp Test
28V Lamp Dimming Bus
Alternate Action
12
55
EGPWS MFD-640
A
B
ARINC 429 Range #1 In
A
B
ARINC 429 Range #2 In
A
B
KCPB Video #1 Out
A
B
KCPB Video #2 Out
Terrain Inhibit (in)
Terrain INOP (out)
A
B
A
B
Range out *
Video in *
Note:
For interface and operation of the Universal MFD-640
see Universal Avionics Multi-Function Disaply Installation Manual
34-20-02
6402-1XXX1-0X
106
68
NC
43
42
A
B
ARINC 429 Control Out
94
95
A
B
Display Control In *
96
67
70 ohm termination
* configurable by MFD-640
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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
Honeywell
MK VI MK VIII EGPWS Installation Design Guide
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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) False True
Landing Flap discrete = +28V Flaps Up Flaps Down
Landing Flap Discrete = Open (or GND) Flaps Down Flaps Up
Ground seeking Landing Flap discrete (J1-18) active position:
Flap Reversal
Flap Discrete (Category 13) False True
Landing Flap discrete = GND Flaps Up Flaps Down
Landing Flap Discrete = Open (or +28V) 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.
Honeywell
MK VI MK VIII EGPWS Installation Design Guide
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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.
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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)
21
4
J2
Radio Altimeter R/T
A
B
EGPWS MK VI / MK VIII
A
B
ARINC 429
Radio Altitude ARINC 429
DH Discrete (Gnd) 33
Radio Altimeter Indicator
DH out
J1
Digital-RA.vsd
DH wiper
Vendor Model Ind. DH R/T
R/T Indicator SCALE wiper/out A B
Collins RAC-870 ALI-55 ARINC 429 P1-R/V P1-2 P1-3
Honeywell ALA-52A/B ARINC 429 MP-B2 MP-B3
Honeywell KRA-405B KNI-415/416 ARINC 429 P1-M/A P4051-B P4051-C
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.
Honeywell
MK VI MK VIII EGPWS Installation Design Guide
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3.10.4 Analog Rad io Altitude Interface (Cat. 8 ID 0,1,3,4)
64
45
29
J1
Radio Altimeter R/T
+
-
EGPWS MK VI / MK VIII
(+)
(-)
Analog Radio Altitude ARINC 552, ALT 55,
RT-200/300
Radio Altitude Valid +28V Valid
DH Discrete (Gnd) 33
Radio Altimeter Indicator
DH wiper
DH out
Analog-RA.vsd
Vendor Model Cat. Ind. DH R/T
R/T Indicator ID wiper/out + - Valid
Collins ALT 55 ALI-55 1 P1-R/V P1-57 P1-59 P1-49
Honeywell HG7502(BC) 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.
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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.
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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.
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3.11.5 Analog Glid eslope Interface (Cat. 9 ID 0,1,5)
J1
ILS Receiver
EGPWS MK VI / MK VIII
GS Valid +28
11
+
-
Low Level
GS Valid
+28
GND
ILS
Tuned
+
-
GS Deviation 65
46
30
10
39
20
Super Flag +28V
+
-
Delayed ILS Mode
ILS Energize
GS Flag
(Low Level)
+Up
+Dn
GS Deviation
Analog-ILS-1.vsd
LOC Valid +28
48
LOC Val +28V
+
-
LOC Deviation 30
10
+L
+R
LOC Deviation
GS Inhibit (BC) +28
38
Backcourse
GS Inhibit (BC) GND
19
Backcourse
GS Valid LOC Valid ILS Tuned Deviation
Vendor Model Cat. 9
ID
SuperFlag
+28V
Low Level
Flag
SuperFlag
+28V GND GS +up
+dn
LOC +R
+L
Honeywell
KNR 6030 5 J1003-27 J1003-21
J1003-22 J1002-50 J1002-18 J1003-8
J1003-9
J1002-39
J1002-40
Honeywell
KNR 660 1P1-e
P1-q P1-k P1-T
P1-V
Honeywell
KNR 634 15 P6342-50 P6342-34
P6342-18 P6342-49 P6341-17 P6342-36
P6342-35
P6342-23
P6342-7
Honeywell
KGM-691 0 P692-W P692-S
P692-T P692-a P692-B
P692-C
Honeywell
KNR 600A 1P601-e
P601-q P601-A P601-k P601-r
P601-s
P601-m
P601-n
Collins
51RV-1, 51RV-4( ) 5 TP-27 2TP-21
TP-22 BP-50 BP-18 TP-8
TP-9
BP-39
BP-40
Collins
VIR-30, -31, -32 5 P1-17 P1-9
P1-13 P2-18 P2-40 P1-5
P1-1
P2-10
P2-13
Honeywell
VNS 41A 5 P1001-60 P1001-101 J1001-56 J1001-90
J1001-23
J1001-38
J1001-92
Honeywell
RNA-34A 5 TP-27 TP-21 BP-50 BP-18 TP-8
TP-9
BP-39
BP-40
Honeywell
KN 53 1P2-13
P2-R P2-12 P2-P
P2-14
Honeywell
KN 72
P1-2
P1-10
Honeywell
RNZ 850 5P1-A74 P1-B60
P1-B106 P1-B91 P1-B64 P1-B79
P1-B75
P1-B78
P1-B75
Honeywell
KX-155/165 1P901-U
P901-R P401-14 P401-8 P901-S
P901-T
P901-s (KX-165)
P901-k (only
NOTE: 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.
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3.11.6 Digital Glid eslope / Localizer / ILS Select Interface (Cat. 9 ID 2,3,4)
22
5
J2
ILS 429 Bus
A
B
EGPWS MK VI / MK VIII
A
B
ARINC 429 ILS
ARINC 429
Low Speed
Digital-ILS.vsd
Vendor Model Cat 9 ARINC 429 Bus 1 ARINC 429 Bus 2
IDABA B
Honeywell KNR 634A 2,3 P6342-41 P6342-42 P6342-44 P6342-45
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 P1024-28 P1024-21 P1024-25
Honeywell KN 40A(B) 4 P401(403)-41 P401(403)-42 P401(403)-44 P401(403)-45
Collins VIR-432 2,3 P1-35 P1-36 P1-22 P1-23
Garmin GNS-430 2,3 P4006-24 P4006-23
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.
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
251 100, 173, and 174
252 173 and 174 *
253 173 and 174
254 163, 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.
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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.
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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)
1
21
2
J1
Vertical Gyro
X
Y
X
Y
Roll Synchro Roll Angle
ZZ
Attitude Validity
5
7
6
X
Y
X
Y
Pitch Synchro Pitch Angle
ZZ
68 +28 = Valid
Analog-VG.vsd
EGPWS MK
VI / MK VIII
Vendor Model Attitude Pitch Synchro (Note 1) Roll Synchro (Note 1)
Vertical Gyro Valid +28 XYZXYZ
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
JET VG-208 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
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.
Note 2: See LCR installation manual.
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3.12.3 Digital Pitc h & Roll Angle (ARINC 429 High Speed) (Cat. 10 ID 5 & 6)
23
6
J2
AHRS 429 Bus
A
B
EGPWS MK VI / MK VIII
A
B
ARINC 429 AHRS
ARINC 429
High Speed
Digital-AHRS.vsd
Vendor Model Cat 10 ARINC 429 Bus 1 ARINC 429 Bus 2
IDABA B
Collins AHC-85(D/E only) 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.
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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)
22
23
3
J1
Directional Gyro
X
Y
EGPWS MK VI / MK VIII
X
Y
Heading Synchro
Heading
ZZ
H
C
4
24
26 VAC Reference H
C
Heading Ref
28Mag Hdg Validity
+28V = Valid
Analog-HDG.vsd
Vendor Model Heading Heading Reference Heading Synchro (Note 1)
Directional Gyro Valid H C 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 J1B-F13 J1B-G13 J1B-E10 J1B-E11 J1B-E12
Honeywell KSG 105 P1-V P1-P 1
P1-C 2
P1-D 1
P1-F 2
P1-Z 1
P1-T 2
P1-W 1
P1-P 2
P1-T 1
P1-K 2
Honeywell KI-525 3(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
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-14A3P1-e P1-H 1P1-J 1P1-L 1P1-M 1P1-K 1
Sperry C-14D3P1-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 J1-C(115VAC) J1-M P1-L P1-K P1-J
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.
Note 2: See LCR installation manual.
1 #1 Heading Output
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2 #2 Heading Output
3 Do not use #2 output, reserved for autopilot only.
Note 3: 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.
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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.
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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)
Flap Discrete (J1-37) False True
Landing Flap discrete = +28V Flaps Up Flaps Down
Landing Flap Discrete = Open (or GND) Flaps Down Flaps
Cat. 13 ID 254/255 only *
Flap Override = OVRD +28V +28V
Flap Override = NORM Open Open
* Category 13 ID 254/255 must use this method for Flap Override.
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Ground seeking Landing Flap discrete active position:
Flap Reversal (Category 7)
Flap Discrete (J1-18) False True
Landing Flap discrete = GND Flaps Up Flaps Down
Landing Flap Discrete = Open (or +28V) Flaps Down Flaps
Cat. 13 ID 254/255 only *
Flap Override = OVRD GND GND
Flap Override = NORM Open Open
* 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 Receiver-
Transmitter 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.
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MK VI EGPWS
COMPUTER
FIXED LANDING GEAR/FLOAT AIRCRAFT
ALTERNATE AIR SWITCH ARRANGEMENT
(Example Shown: Twin Otter)
W* * KRA 405B Adjustable
Trip pins W,V, & F.
KRA 405B
Adjustable Trip
Landing Flap Discrete (Gnd)
Landing Gear Discrete
(+28)
Power Input: +28VDC
Landing Gear Discrete
On Ground = DC Gnd
16
40
60
35
18
P1 J1
FLAPS UP
APPROACH
FLAPS
APPROACH FLAP
POSITION (5°-7°)
EGPWS
3 AMP
AIRCRAFT +28VDC
Not LANDING
LANDING
FULL LANDING FLAP
POSITION (16°-18°)
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.
Landing Flap Discrete
(Gnd)
MK VI EGPWS
COMPUTER
FIXED LANDING GEAR/FLOAT AIRCRAFT
ALTERNATE AIR SWITCH ARRANGEMENT
(Example Shown: Twin Otter)
Landing Gear Discrete
(+28)
Power Input: +28VDC
Landing Gear Discrete
On Ground = DC Gnd
16
40
60
35
18
J1P1
Not LANDING
LANDING
FULL LANDING FLAP
POSITION (16°-18°)
APPROACH FLAP
POSITION (5°-7°)
FLAPS UP
APPROACH
FLAPS
EGPWS
3 AMP
AIRCRAFT +28VDC
NC
NO
AIR SWITCH
RELAY
DIODE
AIR SWITCH
(SHOWN AS A/C ON GROUND)
NO
OPTIONAL EQUIPMENT
EXISTING ON AIRCRAFT
HOUR METER
+28VDC
AIR STREAM
~40 KNOTS
~
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.
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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.
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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 Connector Pin
Self Test Self Test = Gnd
Normal = Open
J1-34
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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 Connector Pin
Steep Approach 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.
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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 “GPWSlamp 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.
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(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.
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TCAS/TAS Connector
Vendor Model Function PIN #
Honeywell CAS-81, TCAS II,
TPA-81A
TA Only
Inhibit Audio
RBP-5C
RBP-5D
Collins TTR-920, TCAS II TA Only
Inhibit Audio
RBP-5C
RBP-5D
CAS 66, 67 Standby
Inhibit Audio
P1A-17
P1A-18
Goodrich*
Skywatch HP (SKY899)
Skywatch (SKY497)
TCAS I (TCAS791/A)
Inhibit Audio P1-34
P1-32
P1-9
* Interface with the Goodrich Skywatch TAS
requires a +28V pullup resistor in the aircraft
wiring as shown in Figure 3.15-1 below.
A
A
A
BRT / DIM / TEST
(7 places)
Self-Test Discrete Input
J1-14
GPWS
INOP
TERR
FAIL
Momentary
J1-34
J1-78
J1-15
J1-77
J1-72
J1-55
J1-12
J1-76
J1-73
J2-31
G/S Cancel Discrete Input
Terrain Inhibit Discrete Input
GPWS Warning Alert Discrete Output
GPWS Caution Alert Discrete Output
GPWS Inoperative Discrete Output
Terrain Not Available Discrete Output
G/S Canceled Discrete Output
G/S
CANCLD
GPWS
FLP OVRD
Momentary
Guarded
ON
Steep Approach Select Discrete Input
Flap Override Discrete Input
Flap Override Discrete Output
A
A
A
TERR
INHIB
ON
Alternate
A
GPWS
P / CANCEL
Momentary
GPWS
STP APR
ON
Guarded
Momentary *
J1-69 Audio On Discrete Output
TCAS
INHIBIT
Note: All EGPWS Outputs are Ground active and are intended to operate
with a +28V lamp source or +28V pullup external to the EGPWS
EGPWS
Lamps2.vsd
J1-52
Steep Approach Select Discrete Output
PULLUP
P / TEST
* Requires -008
software or later
Optional
+28V pullup
100K
ohm
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 & J1-
49) are commonly combined in switch-lamp assemblies mounted near the displays being selected.
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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.
WXR System R/T
J2-37
J2-36
J1-58
J1-59
J1-51
J1-32
A
B
A
BARINC 453 TERRAIN BUS #1
ARINC 429 RANGE BUS
J1-54
Terrain Display Select #1 Discrete Output
Terrain Pop-Up Discrete Output
Display Select
Discrete #1 Input
DSD #1 Gnd
Discrete
Range #1
Discrete
TERR
ON
Momentary
A
* 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
28 VDC
DISPLAY RELAY *
429 IN 453 OUT
453 #1
J1-56
J1-57
A
B
453 #2
J2-41
J2-40
A
B
Range #2
J1-31DSD #2 Gnd
453 WX /
TERR BUS
A
B
A
B
TERRAIN
POP-UP
TERRAIN
SELECTED
429 Range
Output Bus
J2-43
J2-42
A
B
429 Tx Spare #2
Spare #2
Spare #2
WXR/TERR
Display
EM6-disp.vsd
FIGURE 3.15-2 Example of Terrain Display Interface
TERR DISPLAY
OFF ON
Amber Green
+28V
+28V
EGPWS
J1-32
EGPWS
J1-54
TerrDisSw.vsd
Figure 3.15-3 Example of Terrain Display switch with relay
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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 milli-
watts 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.
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High level audio
600 ohm
Audio
Panel
Low level audio
J1-70
H
J1-71
L
J1-75H
J1-74L
8 ohm
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.
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SECTION IV
CONFIGURATION MODULE PROGRAMMING
AND
TERRAIN DATABASE LOADING
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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
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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
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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 205161-1
Socket Contact, AMP 205090-1, QTY 3
M39029/63-368
PCOM
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
2
3
5
3
4
1
Length as required (5' to 50')
* Alternate part number 748364-1 connector and 748333-4 or -7 pin contact.
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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. Connect the PC to the EGPWC using the RS-232 cable as described in section 4.4.2
2. On the PC, start Windows 3.1, or higher.
3. Start the WinVIEWS.EXE program.
4. 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.
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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<space>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.
- <space><Cat 1 ID#><space><Cat 2 ID #>…<Cat 15 ID#>/ 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<Enter>”. 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<Enter>” (Present
Status) will display EGPWC and configuration data.
7. Configuration Module programming is complete. If the “CFG >” prompt is still present type “Exit<Enter>” to
exit the Configuration sub-mode.
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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: 2
Category 2 Air Data Type: 3
Category 3 Position Type: 2
Category 4 Altitude Callouts Menu: 0
Category 5 Audio Menu: 0 (Basic menu)
Category 6 Display Type: 3
Category 7 Options Select Group #1: 93 (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)
Category 8 Radio Altitude Type: 1
Category 9 Navigation Type: 0
Category 10 Attitude Type: 0
Category 11 Heading Type: 0
Category 12 Windshear select Type: 0
Category 13 Discrete I/O Type: 0
Category 14 Audio Output Level Type: 0
Category 15 Undefined Type: 0
CMR list: (based on the previous configuration)
CFG > CMR<Enter>
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
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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<space><category #><space><ID#><space><T or F><Enter>
- <category #> is the Appendix E Category to change (example 7)
- <ID #> is the new ID to change to (example 92)
- <T or F> is True or False for rebooting the EGPWC. Use “T” if only one category is to be changed and the
EGPWC will reboot following <Enter>. Use “F” if another individual ID is to be changed by another CAT
operation.
Example: CFG > CAT 7 92 T<Enter>
5. After inputting the desired change information, pressing <Enter> 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