Airlines & Cvionics Products
Honeywell International, Inc.
15001 N.E. 36 th Street
Redmond, WA 98052
MK XXII
Enhanced Ground Proximity
Warning System
for
Rotorwing
Aircraft
Installation Manual
060-4314-225 Rev C
Part Numbers:
965-1590-006
965-1590-008
965-1590-010
965-1590-011
Release Date: 12/14/00
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Honeywell
MK XXII EGPWS Installation Manual
Typed names constitute approval signatures. Actual signatures are on file at Honeywell in
Redmond, WA.
DRAWN
CHECK
ENGR
MFG
Dennis Martin
Sara Stark
12/8/00
12/8/00
12/8/00
Dennis Martin
QA
APVD
APVD
Dennis Martin
12/8/00
REVISIONS
DESCRIPTION
Added Software –008 Revisions.
Reason: 01 Severity: 10
Added Software –010 Revisions.
Reason: 01 Severity: 10
Added Software –011 Revisions.
Reason: 01 Severity: 10
SH
REV
DATE
APPROVED
8/9/01
8/9/01
S. Wright
D. Martin
ALL
A
ALL
ALL
B
C
3/22/02
3/22/02
D. Martin
R Gilliland
6/07/02
6/7/02
D Martin
T Curtis
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MK VI MK VIII EGPWS Installation Design Guide
TABLE OF CONTENTS
SECTION I – GENERAL INFORMATION............................................................................................ 16
1.1 INTRODUCTION.................................................................................................................................... 16
1.2 APPLICABILITY.................................................................................................................................... 16
1.3 HOW TO USE THIS DOCUMENT ........................................................................................................... 16
1.4 REFERENCE DOCUMENTS .................................................................................................................... 17
1.5 DESCRIPTION OF EQUIPMENT............................................................................................................... 18
1.5.1 MK XXII EGPWS Computer........................................................................................................ 19
1.5.2 MK XXII EGPWS Configuration Module.................................................................................... 19
1.5.3 GPS Antenna................................................................................................................................ 19
1.5.4 OAT Sensor.................................................................................................................................. 19
1.5.5 Smart Cable (PCMCIA Interface)................................................................................................ 20
1.6 TECHNICAL CHARACTERISTICS ........................................................................................................... 21
1.7 UNITS SUPPLIED .................................................................................................................................. 22
1.7.1 MK XXII EGPWS......................................................................................................................... 22
note 1: -0XX defines the Application software version......................................................................... 22
1.7.2 Configuration Module.................................................................................................................. 22
1.7.3 Smart Cable (PCMCIA Interface)................................................................................................ 22
1.8 INSTALLATION AND ACCESSORIES KITS .............................................................................................. 24
1.8.1 MK XXII EGPWS Installation Kits.............................................................................................. 24
1.8.2 RS-232 Cable............................................................................................................................... 24
1.8.3 Smart Cable ................................................................................................................................. 24
1.8.4 Terrain Database Cards .............................................................................................................. 25
1.8.5 Flight History Card ..................................................................................................................... 25
1.9 ACCESSORIES REQUIRED BUT NOT SUPPLIED....................................................................................... 25
1.9.1 ARINC 453 Terrain Display wiring............................................................................................. 25
1.9.2 GPS Antenna & cable.................................................................................................................. 26
1.9.3 Circuit Breaker ............................................................................................................................ 26
1.9.4 Annunciators & Switch/Annunciators.......................................................................................... 26
1.9.4.1 GPWS Warning (red) P/TEST; switch/annunciator assembly............................................................... 26
1.9.4.2 GPWS Caution (amber) G/S CANCLD switch/annunciator assembly.................................................. 27
1.9.4.3 LOW ALT / ON switch/annunciator assembly...................................................................................... 27
1.9.4.4 TERR INHIB / ON switch/annunciator assembly ................................................................................. 27
1.9.4.5 AUDIO INHIBIT / ON switch/annunciator assembly........................................................................... 27
1.9.4.6 GPWS INOP / TERR INOP annunciator assemblies............................................................................. 27
1.9.4.7 TERR DISPLAY / ON switch/annunciator assemblies ......................................................................... 27
1.10 COCKPIT SPEAKER (OPTIONAL)......................................................................................................... 27
1.11 TOOLS REQUIRED .............................................................................................................................. 28
1.11.1 Crimping Tool - P1, P2, P3 ...................................................................................................... 28
1.11.2 Contact Positioner - P1, P2, P3................................................................................................ 28
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MK VI MK VIII EGPWS Installation Design Guide
1.11.3 Insertion/Removal Tool - P1, P2, P3........................................................................................ 28
1.11.4 Spare Contacts - P1, P2, P3 ...................................................................................................... 28
1.12 LICENSE REQUIREMENTS................................................................................................................... 28
SECTION II - INSTALLATION .............................................................................................................................. 33
2.1 INTRODUCTION.................................................................................................................................................... 33
2.2 UNPACKING AND INSPECTING THE EQUIPMENT ................................................................................................... 33
2.3 EQUIPMENT INSTALLATION ................................................................................................................................. 33
2.3.1 General ........................................................................................................................................................ 33
2.3.2 MK XXII Computer Location....................................................................................................................... 34
2.3.3 MK XXII Computer Installation................................................................................................................... 34
2.3.4 Configuration Module Location .................................................................................................................. 35
2.3.5 Configuration Module Installation .............................................................................................................. 35
2.3.6 GPS Antenna location.................................................................................................................................. 44
2.3.7 GPS Antenna Installation ............................................................................................................................ 44
2.3.8 OAT Sensor Location................................................................................................................................... 44
2.3.9 OAT Sensor Installation............................................................................................................................... 44
2.3.10 Cockpit Annunciators / Switches................................................................................................................ 44
2.3.10.1 Description ............................................................................................................................................................ 45
2.3.10.2 Location................................................................................................................................................................. 46
2.3.10.3 Inhibit Switch Functions and Selection ................................................................................................................. 48
2.3.10.3.1 Terrain Inhibit ................................................................................................................................................ 48
2.3.10.3.2 Audio Inhibit (Timed) .................................................................................................................................... 48
2.3.10.3.3 Audio Inhibit (Not Described Above)............................................................................................................ 48
2.3.10.3.4 Low Altitude Mode ........................................................................................................................................ 48
SECTION III – SYSTEM PLANNING .................................................................................................................................57
3.1 INTRODUCTION.................................................................................................................................... 57
3.2 SYSTEM WIRING/ ELECTRICAL INTERFACES........................................................................................ 57
3.2.1 Primary Power Input ................................................................................................................................................57
3.2.2 Chassis Ground ........................................................................................................................................................57
3.2.3 GPS Antenna.............................................................................................................................................................58
3.2.4 Analog and Digital Inputs.........................................................................................................................................58
3.2.5 Discrete Inputs..........................................................................................................................................................58
3.2.6 Serial Outputs...........................................................................................................................................................58
3.2.7 Audio Output.............................................................................................................................................................59
3.2.8 Discrete Outputs .......................................................................................................................................................59
3.2.9 Configuration Module...............................................................................................................................................59
3.3 CONFIGURABLE INTERFACES............................................................................................................... 60
3.3.1 Category 1 - Aircraft / Mode Type Select .................................................................................................................60
3.3.1.1 Aircraft / Mode Type............................................................................................................................. 60
3.3.1.2 Instructions ............................................................................................................................................ 60
3.3.1.3 Generic Helicopter with and without Torque......................................................................................... 60
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3.3.2 Category 2 – Air Data Input Select...........................................................................................................................61
3.3.2.1 Instructions ........................................................................................................... ................................. 61
3.3.2.2 Examples ............................................................................................................... ................................ 62
3.3.2.3 Analog altitude and 500 ohm OAT ........................................................................................ ........... 62
3.3.2.4 Digital – ARINC 429 (Cat. 2 ID 5, 1, 6) ........................................................................................... 63
3.3.2.5 Digital –ARINC 575 (Cat. 2 ID 2) .................................................................................................... 64
3.3.2.6 Shadin 2000 (Cat. 2 ID 10) ............................................................................................................... 65
3.3.2.7 Digital – ARINC 429 Dual IOC Buses (Cat. 2. ID 255) ................................................................... 66
3.3.3 Category 3 – Position Input Select ...........................................................................................................................67
3.3.3.1 Instructions ............................................................................................................................................ 67
3.3.3.2 ARINC 743 Format ............................................................................................................................... 67
3.3.3.Examples .................................................................................................................................................. 68
3.3.3.1 ARINC 429 BUS (Cat. 3 ID 0,1,4,5)................................................................................................. 68
3.3.3.2 RS-232 Transmit-Receive, 9600 baud (Cat. 3 ID 3) ......................................................................... 68
3.3.3.3 Dual ARINC 429 BUS (Cat. 3 ID 255)............................................................................................. 69
3.3.4 Category 4 – Altitude Callouts .................................................................................................................................70
3.3.4.1 Instructions ............................................................................................................................................ 70
3.3.5 Category 5 – Audio Menu Select ..............................................................................................................................71
3.3.5.1 Instructions ............................................................................................................................................ 71
3.3.6 Category 6 – Terrain Display Select ........................................................................................................................72
3.3.6.1 Instructions ............................................................................................................................................ 72
3.3.6.2 TAD Selection....................................................................................................................................... 72
3.3.6.3 Terrain Display Configuration Group.................................................................................................... 73
3.3.6.4 Display Input Control Group................................................................................................................. 75
3.3.6.5 Output 429 Bus Group........................................................................................................................... 75
3.3.6.6 Example................................................................................................................................................. 75
3.3.7 Category 7 – Options Select Group #1.....................................................................................................................81
3.3.7.1 Instructions ............................................................................................................................................ 81
3.3.7.2 Steep Approach (Not Available in the Mk XXII).................................................................................. 81
3.3.7.3 TA&D Alternate Pop-up........................................................................................................................ 81
3.3.7.4 Peaks Mode ........................................................................................................................................... 82
3.3.7.5 Obstacle Awareness............................................................................................................................... 82
3.3.7.6 Bank Angle Callout Enabling................................................................................................................ 82
3.3.7.8 WOW Reversal...................................................................................................................................... 83
3.3.7.9 GPS Altitude Reference......................................................................................................................... 83
3.3.8 Category 8 – Radio Altitude Input Select..................................................................................................................84
3.3.8.1 Instructions ............................................................................................................................................ 84
3.3.8.2 Example................................................................................................................................................. 84
3.3.8.3 Digital Radio Altitude Interface ........................................................................................................ 84
3.3.8.4 Analog Radio Altitude Interface........................................................................................................ 85
3.3.9 Category 9 – Navigation Inputs Select .....................................................................................................................86
3.3.9.1 Instructions ............................................................................................................................................ 86
3.3.9.2 Example................................................................................................................................................. 87
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3.3.9.3 Analog Glideslope Interface (cat. 9 ID 0,1,5) ................................................................................... 87
3.3.9.4 Digital Glideslope/Localizer Interface .............................................................................................. 88
3.3.9.5 Dual Glideslope Receiver.................................................................................................................. 88
3.3.10 Category 10 – Attitude Input Select........................................................................................................................89
3.3.10.1 Attitude Signals ...................................................................................................... ............................. 89
3.3.10.2 Instructions .......................................................................................................... ................................ 89
3.3.10.3 Example............................................................................................................... ................................ 90
3.3.10.4 Analog Roll Angle (Synchro)........................................................................................... ............... 90
3.3.10.5 Digital ARINC 429 High Speed.......................................................................................... ............ 91
3.3.11 Category 11 – Heading Input Select.......................................................................................................................92
3.3.11.1 Instructions .......................................................................................................................................... 92
3.3.11.2 Magnetic Heading................................................................................................................................ 92
3.3.11.3 Example............................................................................................................................................... 93
3.3.11.3.1 Analog Heading (Synchro) (CAT. 11 ID 0) ................................................................................. 93
3.3.11.3.2 Digital ARINC 429 High Speed................................................................................................... 94
3.3.12 Category 12 – Windshear Input Select ...................................................................................................................95
3.3.12.1 Instruction............................................................................................................................................ 95
3.3.13 Category 13 – Input / Output Discrete Type Select ................................................................................................96
3.3.13.1 Instruction............................................................................................................................................ 96
3.3.13.2 Input/Output Discretes......................................................................................................................... 96
3.3.13.3 Audio Inhibit Discrete..................................................................................................................... 97
3.3.13.4 Landing Gear Discrete..................................................................................................................... 97
3.3.13.5 Weight ON Wheels (WOW) Discrete ............................................................................................. 97
3.3.13.6 Glideslope Cancel Discrete ............................................................................................................. 98
3.3.13.7 Mode 6 Low Volume Discrete ........................................................................................................ 98
3.3.13.8 Autopilot Engaged Discrete ............................................................................................................ 98
3.3.13.9 Terrain Awareness Inhibit............................................................................................................... 99
3.3.13.10 Self Test Discrete .......................................................................................................................... 99
3.3.13.11 Glideslope Inhibit Discrete............................................................................................................ 99
3.3.13.12 Timed Audio Inhibit Discrete...................................................................................................... 100
3.3.13.13 Low Altitude Mode Select Discrete ............................................................................................ 100
3.3.13.14 Output Discretes.......................................................................................................................... 100
3.3.13.15 Lamp Format............................................................................................................................... 100
3.3.13.16 GPWS INOP Discrete ................................................................................................................. 101
3.3.13.17 TAD INOP Discrete.................................................................................................................... 101
3.3.13.18 GPWS Warning Discrete............................................................................................................. 101
3.3.13.19 GPWS Alert Discrete .................................................................................................................. 101
3.3.13.20 Glideslope Cancel Discrete ......................................................................................................... 101
3.3.13.21 TCAS Inhibit Discrete................................................................................................................. 101
3.3.13.22 Terrain Display Select #1 & #2 Discrete..................................................................................... 102
3.3.13.23 Timed Audio Inhibit Discrete...................................................................................................... 102
3.3.13.24 Low Altitude Mode Discrete....................................................................................................... 102
3.3.14 Category 14 – Audio Output Level .......................................................................................................................104
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MK VI MK VIII EGPWS Installation Design Guide
3.3.14.1 Instructions .......................................................................................................... .............................. 104
3.3.15 Category 15, Autorotation Threshold...................................................................................................................105
3.3.15.1 Instruction........................................................................................................... ............................... 105
SECTION IV – CONFIGURATION MODULE PROGRAMMING AND REGIONAL TERRAIN
DATABASE LOADING........................................................................................................................................................109
4.1 INTRODUCTION.................................................................................................................................. 109
4.2 HARNESS CHECKOUT AND POWER CHECK ........................................................................................ 109
4.3 UNIT INSTALLATION.......................................................................................................................... 109
4.4 EGPWC INITIALIZATION AND CONFIGURATION ............................................................................... 109
4.4.1 RS-232 Communication with the MK XXII EGPWS.................................................................. 109
4.4.2 EGPWC Front Panel Test Connector........................................................................................ 110
4.4.3 WinVIEWS ................................................................................................................................. 110
4.4.4 WinVIEWS Operation................................................................................................................ 111
4.5 CONFIGURATION MODULE PROGRAMMING ....................................................................................... 111
4.5.1 CUW and CMR Commands ....................................................................................................... 113
4.5.2 Configuration Module Reprogramming..................................................................................... 114
4.6 REGIONAL TERRAIN DATABASE LOADING ........................................................................................ 115
4.6.1 Effectivity................................................................................................................................... 115
4.6.2 Description ................................................................................................................................ 115
4.6.3 Approval .................................................................................................................................... 115
4.6.4 Material – Cost and Availability................................................................................................ 116
4.6.5 Accomplishment Instructions..................................................................................................... 117
4.6.6 Verification of the Terrain Database Version............................................................................ 118
SECTION V – CERTIFICATION 124
5.1 INTRODUCTION ................................................................................................................................. 124
5.2 CERTIFICATION PROCEDURE ............................................................................................................. 124
5.2.2 Equipment Location ...............................................................................................................................................124
5.2.3 FAA Requirements .................................................................................................................................................124
5.2.4 Ground Test ...........................................................................................................................................................124
5.2.5 Flight Manual Revision .........................................................................................................................................124
5.2.6 Flight Test ..............................................................................................................................................................125
5.2.7 Pilots Guide ...........................................................................................................................................................125
5.2.8 Failure Modes, Effects, and Safety Analysis ..........................................................................................................125
5.2.9 Existing STC’s .......................................................................................................................................................125
APPENDIX A.........................................................................................................................................................................127
CUSTOMER WORKSHEET...............................................................................................................................................127
APPENDIX B.........................................................................................................................................................................139
SAMPLE WIRING DIAGRAMS.........................................................................................................................................139
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MK VI MK VIII EGPWS Installation Design Guide
APPENDIX C.........................................................................................................................................................................143
WINVIEWS OPERATION INSTRUCTIONS ...................................................................................................................143
APPENDIX D............................................................................................................................................ 149
VENDOR DRAWINGS............................................................................................................................ 149
D 1-0 VENDOR CONTACT INFORMATION................................................................................................. 151
D1-1
D1-2
EDMO................................................................................................................................. 153
EMTEQ............................................................................................................................... 154
GPS - RF Cable Sets......................................................................................................................... 154
TABLE 2 ............................................................................................................................................. 156
Table 2.A.1 Connectors (for TFLX cable series) - GPS ................................................................... 156
TABLE 2 (continued).......................................................................................................................... 157
Table 2.B.1 Connectors (for PFLX cable series) – GPS.................................................................... 157
TOOL FRAME AND DIE PART NUMBERS....................................................................................... 158
INSTALLATION CONSIDERATIONS:........................................................................................................... 159
D1-3
Aerospace Optics ................................................................................................................ 160
AEROSPACE OPTICS INC.................................................................................................................... 160
LED LIGHTING ...................................................................................................................................... 160
INTRODUCTION .................................................................................................................................................................166
E 1
E 2
E 3
E 4
PART NUMBER..........................................................................................................................................................166
PURPOSE...................................................................................................................................................................166
SYSTEM OVERVIEW..................................................................................................................................................166
ELECTRICAL INTERFACE ..................................................................................................................................167
E 4.1
E 4.2
Introduction .....................................................................................................................................................167
Signal Interfaces ..............................................................................................................................................167
E 4.2.1 Grounds ...........................................................................................................................................................167
E 4.2.2 Primary Power Input .......................................................................................................................................167
E 4.2.3 DC Analog Inputs ............................................................................................................................................168
E 4.2.7 AC Analog Inputs.............................................................................................................................................170
E 4.2.9 ARINC 429/575 Digital Serial Bus Inputs .......................................................................................................172
E 4.2.9.1 RS-232 / RS-422 Digital Serial Bus Inputs ..................................................................................................173
E 4.2.10
E 4.2.11
E 4.2.12
E 4.2.13
E 4.2.14
E 4.2.16
E 4.2.17
Discrete Inputs.............................................................................................................................................174
Configuration Module Interface ..................................................................................................................175
GPS Antenna Input ......................................................................................................................................175
OAT Voltage Reference Output....................................................................................................................176
Lamp Driver Outputs ...................................................................................................................................176
Audio Outputs ..............................................................................................................................................176
ARINC Digital Serial Output Busses ...........................................................................................................177
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MK VI MK VIII EGPWS Installation Design Guide
E 4.2.17.1
ARINC 429 Output Bus................................................................................................. ...........................177
ARINC 453 Output Bus................................................................................................. ...........................178
FRONT PANEL TEST INTERFACE........................................................................................................................178
RS-232 MAINTENANCE PORT (SERIAL PORT 4).............................................................................................178
PCMCIA / SmartCable Port ....................................................................................................................179
GSE Present Discrete Input.....................................................................................................................179
FRONT PANEL STATUS INDICATORS .................................................................................................................179
E 4.2.17.2
E 4.2.18
E 4.2.18.1
E 4.2.18.2
E 4.2.18.3
E 4.2.19
E 5
E 5.1
E 5.2
E 5.3
AIRCRAFT APPLICATION DATA .......................................................................................................................180
CONFIGURATION TYPES........................................................................................................................................180
CONFIGURATION SELECTION ................................................................................................................................180
Configuration Selection Tables........................................................................................................................182
E 5.3.1 Category 1, Aircraft / Mode Type Select..........................................................................................................183
E 5.3.2 Category 2, Air Data Input Select....................................................................................................................189
E 5.3.3 Category 3, Position Input Select ...................................................................................................................195
E 5.3.4 Category 4, Altitude Callouts ..........................................................................................................................199
E 5.3.5 Category 5, Audio Menu Select........................................................................................................................201
E 5.3.6 Category 6, Terrain Display Select..................................................................................................................202
E 5.3.7 Category 7, Options 1 Select ...........................................................................................................................231
E 5.3.8 Category 8, Radio Altitude Input Select...........................................................................................................233
E 5.3.9 Category 9, Navigation Input Select................................................................................................................236
E 5.3.10
E 5.3.11
E 5.3.12
E 5.3.13
E 5.3.14
E 5.3.15
Category 10, Attitude Input Select ...............................................................................................................238
Category 11, Heading Input Select..............................................................................................................240
Category 12, Windshear Input Select...........................................................................................................241
Category 13, Input / Output Discrete Type Select .......................................................................................242
Category 14, Audio Output Level ................................................................................................................245
Category 15, Autorotation Threshold ..........................................................................................................246
E 6
E 6.1
E 7
CONNECTOR INTERFACE...................................................................................................................................247
PINOUT FOR FRONT CONNECTORS SORTED BY PIN NUMBER .................................................................................247
DEFINITIONS ........................................................................................................................................................252
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MK XXII EGPWS Installation Manual
SECTION I
GENERAL INFORMATION
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MK XXII EGPWS Installation Manual
SECTION I – GENERAL INFORMATION
SECTION I – GENERAL INFORMATION............................................................................................ 16
1.1 INTRODUCTION.................................................................................................................................... 16
1.2 APPLICABILITY.................................................................................................................................... 16
1.3 HOW TO USE THIS DOCUMENT ........................................................................................................... 16
1.4 REFERENCE DOCUMENTS .................................................................................................................... 17
1.5 DESCRIPTION OF EQUIPMENT............................................................................................................... 18
1.5.1 MK XXII EGPWS Computer........................................................................................................ 19
1.5.2 MK XXII EGPWS Configuration Module.................................................................................... 19
1.5.3 GPS Antenna................................................................................................................................ 19
1.5.4 OAT Sensor.................................................................................................................................. 19
1.5.5 Smart Cable (PCMCIA Interface)................................................................................................ 20
1.6 TECHNICAL CHARACTERISTICS ........................................................................................................... 21
1.7 UNITS SUPPLIED .................................................................................................................................. 22
1.7.1 MK XXII EGPWS......................................................................................................................... 22
note 1: -0XX defines the Application software version......................................................................... 22
1.7.2 Configuration Module.................................................................................................................. 22
1.7.3 Smart Cable (PCMCIA Interface)................................................................................................ 22
1.8 INSTALLATION AND ACCESSORIES KITS .............................................................................................. 24
1.8.1 MK XXII EGPWS Installation Kits.............................................................................................. 24
1.8.2 RS-232 Cable............................................................................................................................... 24
1.8.3 Smart Cable ................................................................................................................................. 24
1.8.4 Terrain Database Cards .............................................................................................................. 25
1.8.5 Flight History Card ..................................................................................................................... 25
1.9 ACCESSORIES REQUIRED BUT NOT SUPPLIED....................................................................................... 25
1.9.1 ARINC 453 Terrain Display wiring............................................................................................. 25
1.9.2 GPS Antenna & cable.................................................................................................................. 26
1.9.3 Circuit Breaker ............................................................................................................................ 26
1.9.4 Annunciators & Switch/Annunciators.......................................................................................... 26
1.9.4.1 GPWS Warning (red) P/TEST; switch/annunciator assembly............................................................... 26
1.9.4.2 GPWS Caution (amber) G/S CANCLD switch/annunciator assembly.................................................. 27
1.9.4.3 LOW ALT / ON switch/annunciator assembly...................................................................................... 27
1.9.4.4 TERR INHIB / ON switch/annunciator assembly ................................................................................. 27
1.9.4.5 AUDIO INHIBIT / ON switch/annunciator assembly........................................................................... 27
1.9.4.6 GPWS INOP / TERR INOP annunciator assemblies............................................................................. 27
1.9.4.7 TERR DISPLAY / ON switch/annunciator assemblies ......................................................................... 27
1.10 COCKPIT SPEAKER (OPTIONAL)......................................................................................................... 27
1.11 TOOLS REQUIRED .............................................................................................................................. 28
1.11.1 Crimping Tool - P1, P2, P3 ...................................................................................................... 28
1.11.2 Contact Positioner - P1, P2, P3................................................................................................ 28
1.11.3 Insertion/Removal Tool - P1, P2, P3........................................................................................ 28
1.11.4 Spare Contacts - P1, P2, P3 ...................................................................................................... 28
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MK XXII EGPWS Installation Manual
1.12 LICENSE REQUIREMENTS................................................................................................................... 28
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MK XXII EGPWS Installation Manual
SECTION I – GENERAL INFORMATION
1.1 Introduction
The Honeywell MK XXII Enhanced Ground Proximity Warning System (MK XXII EGPWS)
provides alerts and warnings to prevent controlled flight into terrain (CFIT).
This Installation Manual must be used in conjunction with the Interface Description
Document (Appendix E) for the MK XXII Enhanced Ground Proximity Warning System (MK
XXII 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 helicopter systems associated with the installation and operation of the MK XXII
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 Applicability
This manual is applicable only to MK XXII EGPWS computers with the following part number:
MK XXII 965-1590-0XX
Part numbers 965-1590-0XX include an internal GPS card.
1.3 How To Use 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.
Appendix A Customer Worksheet.
Appendix B Sample Wiring Diagrams.
Appendix C provides WinViews operation instructions.
Appendix D Vendor drawings.
Appendix E Interface Description Document
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1.4 Reference Documents
Following is a list of Honeywell reference documents:
965-1590-601
993-1176-401
Product Specification for the MK XXII Enhanced Ground Proximity
Warning System (EGPWS)
Interface Control Document (ICD) for the MK VI/VIII/XXII Enhanced
Ground Proximity Warning System
965-1590-206
060-4326-000
060-4314-009
060-4314-200
060-4314-006
060-4167-167
Outline, MK XXII EGPWC
EGPWS Terrain Database Airport Coverage List
Generic RWFM Supplement For EGPWS
Mk XXII Helicopter-Enhanced GPWS Pilot’s Guide
General Flight Test Procedure
Installation Ground Test Procedure for the Mk XXII EGPWS for
Rotary Wing Aircraft
060-4314-002
060-4314-011
Failures Modes, Effects, and Safety Analysis
Line Maintenance Manual
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1.5 Description of Equipment
The MK XXII EGPWS is a rack mount ground proximity warning (GPWS) and terrain display
(TAWS) computer. Some of the system features include:
♦
♦
♦
♦
♦
♦
♦
♦
Basic Helicopter Ground Proximity Warning Modes 1-5
Mode 6 Altitude, Bank Angle, and Tail Strike Callouts
Terrain and Obstacle Awareness alert and display
Terrain map with runways
Internal GPS card
Front loading updateable database
External Configuration Module
Internal heater blanket for operation outside of the heated area of the aircraft
Fig 1.0 MK XXII EGPWC
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1.5.1 MK XXII EGPWS Computer
The MK XXII EGPWS computer is available under P/N 965-1590-0XX with internal GPS. The MK
XXII EGPWS computer is intended for Helicopters and provides 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 XXII EGPWS computer are North America, South America,
Europe, Eastern Europe, Africa, Asia, Pacific, South Pacific, and Middle East regions and are
comprises of terrain data (6 arc second where available), all known airports, many heliports and
man-made obstacles (North America only).
1.5.2 MK XXII EGPWS Configuration Module
The MK XXII EGPWS Configuration Module is available under P/N 700-1710-001 (Included in
Installation Kits, see section 1.8). The MK XXII EGPWS uses a Configuration Module installed in
the aircraft wiring to store aircraft/EGPWS interface configuration.Specifically, the module comes
prewired and replaces part of the backshell of the (P2) connector that plugs into the front of the
MK XXII computer. 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.
1.5.3 GPS Antenna
EGPWS installations using the internal GPS require an active GPS antenna and cabling. The
GPS antenna should meet the following qualifications:
Frequency:
Impedance:
Gain:
1575.42 MHz
50 ohms
33dB max, 26.5 dB preferred
5 VDC
Power:
Qualification: TSO C129 or C129a or C144
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.
King KA 91
P/N 071-01545-0200
P/N 071-01553-0200
P/N S67-1575-52
TSO-C129
King KA 92
TSO-C129
Sensor Systems
Sensor Systems
TSO-C129, ARINC 743A
TSO-C129a, ARINC 743A
P/N S67-1575-133
1.5.4 OAT Sensor
The OAT sensor is available from Computer Instruments Corp. (CIC) P/N 05257. The EGPWS
uses a separate OAT sensor (Outside Air Temperature) to measure outside air temperature on
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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 computing Geometric
Altitude. If Outside Air Temperature is not available, Geometric Altitude is computed using
pressure altitude with a corresponding reduction in accuracy.
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.
1.5.5 Smart Cable (PCMCIA Interface)
The EGPWS Smart Cable (part number 951-0386-001) is a removable PCMCIA card interface.
The Smart Card is compatible with any Honeywell supplied EGPWS PCMCIA style cards. 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 Card loading operation will closely
emulate that of an ARINC 615 Data Loader.
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FIGURE 1-1 MK XXII EGPWS SMART CABLE
1.6 Technical Characteristics
MK XXII EGPWS
TSO Compliance:
Physical size (HxWxD):
Weight:
TSO-C92c, TSO-C151a, class A
6.20” x 3.04” x 10.30”
3.9 pounds maximum
Mounting:
Standard 3 inch King Radio rack
-55°C to +70°C (F2)
Temperature (operational):
Altitude range:
55,000 feet (F2)
Cooling:
No cooling necessary
Shock:
No shock mounting required
3 Amps
Power Consumption (28 VDC):
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:
same as MK XXII EGPWS
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Physical size:
Weight:
2.68” x 1.51” x 0.32” (fits Positronic connector backshell)
<1 pound with connector and backshell
Mounts to Positronic connector backshell
same as MK XXII EGPWS
Mounting:
Temperature (operational):
Altitude range:
Cooling:
same as MK XXII EGPWS
No cooling necessary
Shock:
No shock mounting required
from MK XXII EGPWS
Power Consumption (5 VDC):
GPS Antenna Sensor
See Manufacturer’s specifications Appendix D.
OAT Sensor
See Manufacturer’s specifications Appendix D.
1.7 Units Supplied
1.7.1 MK XXII EGPWS
The MK XXII EGPWS The part number for the units is as follows:
965-1590-0XX with Internal GPS card
note 1: -0XX defines the Application software version
1.7.2 Configuration Module
The MK XXII EGPWS Configuration Module is available in one version. When ordering the
Configuration Module, order part number 700-1710-001.
1.7.3 Smart Cable (PCMCIA Interface)
The MK XXII EGPWS Smart Cable is available in one version. The Smart Cable is used for Line
Maintenance, only one Smart Cable is required for an installation house or operator. When
ordering the Smart Cable, order part number 951-0386-001.
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1.8 Installation and Accessories Kits
NOTE: Not all installation kits are immediately available, contact Honeywell Order
Administration (425-885-8719) for availability.
1.8.1 MK XXII EGPWS Installation Kits
(A) New EGPWS installation with OAT and Internal GPS
The MK XXII EGPWS Installation Kit #1, P/N 755-7013-001, contains the following parts:
Vendor Name
Vendor P/N
Description
QTY UM
Honeywell P/N
440-1158-009
440-1233-001
440-1239-001
700-1710-001
405-0383-001
107-1049-001
107-1049-002
107-1049-003
Positronic Ind. DD78F1OJVLC-15
Positronic Ind. RD50F1OJVLC-15
P1 connector
1
1
1
1
1
1
1
1
EA
EA
EA
EA
EA
EA
EA
EA
P2 connector
Amphenol
Honeywell
Bendix/King
CIC
79075
GPS Antenna connector
Configuration Module
Computer Mounting Tray
OAT Sensor
700-1710-001
071-04003-0002
05257
CIC
05257-TOMK
05257-TPIK
OAT mounting Kit
OAT Connector Kit
CIC
(B) New EGPWS installation with Internal GPS
The MK XXII EGPWS Installation Kit #5, P/N 755-7013-005, contains the following parts:
Vendor Name
Vendor P/N
Description
QTY UM
Honeywell P/N
440-1158-009
440-1233-001
440-1239-001
700-1710-001
405-0383-001
Positronic Ind. DD78F1OJVLC-15
Positronic Ind. RD50F1OJVLC-15
P1 connector
1
1
1
1
1
EA
EA
EA
EA
EA
P2 connector
Amphenol
Honeywell
Bendix/King
79075
GPS Antenna connector
Configuration Module
Computer Mounting Tray
700-1710-001
071-04003-0002
1.8.2 RS-232 Cable
The MK XXII 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
Honeywell
Vendor P/N
Description
QTY UM
EA
Honeywell P/N
704-2617-001
704-2617-001
RS-232 Cable
1
1.8.3 Smart Cable
The MK XXII EGPWS Smart Cable can be ordered using the following part numbers:
Vendor Name
Honeywell
Vendor P/N
Description
QTY UM
EA
Honeywell P/N
951-0386-001
951-0386-001
Smart Cable
1
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1.8.4 Terrain Database Cards
The MK XII EGPWS Terrain Database Cards can be ordered using the following part numbers:
Vendor Name
Honeywell
Honeywell
Honeywell
Honeywell
Honeywell
Honeywell
Honeywell
Honeywell
Honeywell
Honeywell
Vendor P/N
424NAM
424SAM
424EUR
424EEU
424AFR
Description
North America
South America
Europe
QTY UM
Honeywell P/N
718-1447-xxx
718-1448-xxx
718-1449-xxx
718-1450-xxx
718-1451-xxx
718-1452-xxx
718-1453-xxx
718-1457-xxx
718-1458-xxx
402-6075-xxx
1
1
1
1
1
1
1
1
1
1
EA
EA
EA
EA
EA
EA
EA
EA
EA
EA
Eastern Europe
Africa
424PAC
424ASI
Pacific
Asia
424SPA
South Pacific
Middle East
Label, TDB Front Panel
424MES
402-6075-xxx
1.8.5 Flight History Card
The Flight History Card is a PCMCIA card that has been loaded with a down load instruction file
to allow the down loading of flight history data from an EGPWS. Flight History files contain status
information, fault history and flight data from 20 seconds prior to 10 seconds after a EGPWS
caution or warning event. The card is used to aid in troubleshooting systems faults and or
nuisance warnings.
The MK XXII EGPWS Flight History Card can be ordered using the following part numbers:
Vendor Name
Honeywell
Vendor P/N
*
Description
QTY UM
EA
Honeywell P/N
*
Flight History Download
1
* For flight history download cards call Honeywell GPWS Hotline 1 800 813-2099
1.9 Accessories Required but 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 buss 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.
Vendor Name
Vendor P/N
Description
QTY UM
Honeywell P/N
Pic Wire&Cable D620224
Pic Wire&Cable D5102QX
Pic Wire&Cable D771553
ARINC 453 cable
Hi Temp Quadraxial
A/R
A/R
EA
EA
EA
EA
MIL-STD 1553 Data Bus A/R
ARINC 453 cable A/R
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Vendor Name
Emteq
Vendor P/N
Description
QTY UM
Honeywell P/N
D 07002-100
ARINC 453 Cable
A/R
A/R
EA
EA
M17/176-00002
Military Specification
1.9.2 GPS Antenna & cable
The GPS Antenna & cable can be ordered from their manufacturers using the following part
numbers:
Vendor Name
Bendix/King
Bendix/King
Comant
Vendor P/N
Description
QTY UM
Honeywell P/N
071-01545-0200
071-01553-0200
CI 405-2
KA 91 GPS Antenna
KA 92 GPS Antenna
KA 92 GPS Antenna
Antenna Installation Kit
S67 GPS Antenna
S67 GPS Antenna
S67 GPS Antenna
Coax Cable, RG400
Coax Cable, RG-142
TNC Angle Plug, Male
TNC Angle Plug, Male
1
1
1
EA
EA
EA
300-1147-001
300-1147-001
405-0432-001
Bendix/King
Sensor Systems
Sensor Systems
Sensor Systems
Thermax
050-03318-0000
S67-1575-38
S67-1575-52
S67-1575-133
M17/128-RG400
OPT EA
1
1
1
EA
EA
EA
A/R EA
A/R EA
Amp
225554-6
79075
1
1
EA
EA
440-1239-001
440-1239-001
Amphenol
1.9.3 Circuit Breaker
The Circuit Breaker needs to be a 3 Amp delayed action circuit breaker.
Vendor Name
Klixon (T.I.)
Vendor P/N
7277-2-3
Description
QTY UM
Honeywell P/N
3 Amp Circuit Breaker,
EGPWS power +28
1 Amp Circuit Breaker,
lamp power +28
1
EA
Klixon (T.I.)
7277-2-1
1
EA
1.9.4 Annunciators & Switch/Annunciators
The devices shown below are switch/annunciators and are representative of those used in some
installations. The installer/customer is cautioned to verify regulatory approval of the annunciation
devices installed. See Appendix D for Vendors.
1.9.4.1 GPWS Warning (red) P/TEST; switch/annunciator assembly
The ‘GPWS’ annunciator provides visual indication of an EGPWS alert. The GPWS warning (red)
annunciator also has a switch that is used to manually initiate EGPWS Self Test.
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1.9.4.2 GPWS Caution (amber) G/S CANCLD switch/annunciator assembly.
The ‘GPWS caution annunciator provides visual indication of an EGPWS alert. The EGPWS
caution (amber) annunciator also has a switch that is used to manually inhibit EGPWS Mode 5
glideslope alerts. The bottom half of the annunciator provides visual indication that the mode 5
glideslope alerts have been canceled.
1.9.4.3 LOW ALT / ON switch/annunciator assembly
The LOW ALT / ON switch/annunciator provides for manual selection of low altitude mode and
visual indication that the Mk XXII EGPWS is in low altitude mode.
1.9.4.4 TERR INHIB / ON switch/annunciator assembly
The ‘TERR INHIBIT’ switch/annunciator provides for manual selection of terrain inhibit mode and
visual indication that the EGPWS Terrain functions have been inhibited.
1.9.4.5 AUDIO INHIBIT / ON switch/annunciator assembly
The ‘AUDIO INHIBIT’ switch/annunciator provides for manual selection of audio inhibit mode and
visual indication that the EGPWS mode 6 functions have been inhibited.
1.9.4.6 GPWS INOP / TERR INOP annunciator assemblies
The ‘GPWS INOP’ annunciator provides visual indication that the EGPWS GPWS modes have a
disabled function.
The ‘TERR INOP’ annunciator provides visual indication that the EGPWS Terrain modes have a
disabled function.
1.9.4.7 TERR DISPLAY / ON switch/annunciator assemblies
The ‘TERR DISPLAY’ switch/annunciator provides for manual selection of the terrain display and
visual indication that the EGPWS Terrain Display has been selected for the associated display.
1.10 Cockpit Speaker (Optional)
The MK XXII EGPWS can interface to an 8 ohm audio speaker for cockpit annunciation of aural
alerts.
Vendor Name
Quam
Vendor P/N
30A05Z8
SP-3A
Description
QTY UM
Honeywell P/N
Audio Speaker
Audio Speaker
Audio Speaker
1
1
1
EA
EA
EA
Utah
CTS
4AC3
300-0218-002
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1.11 Tools Required
1.11.1 Crimping Tool - P1, P2, P3
Description
UM QTY
Vendor Name & Part Number
Positronic Ind. 9507
Hand Crimping Tool
Hand Crimping Tool
Hand Crimping Tool
EA
EA
EA
1
1
1
Daniels
Military
AFM8
M22520/2-1
1.11.2 Contact Positioner - P1, P2, P3
Description
UM QTY
Vendor Name & Part Number
Positronic Ind. 9502-3
Contact Positioner, Socket P1
Contact Positioner, Socket P1
Contact Positioner, Socket P1
Contact Positioner, Socket P2
Contact Positioner, Socket P2
Contact Positioner, Socket P2
Contact Positioner, Pin P3
Contact Positioner, Pin P3
Contact Positioner, Pin P3
EA
EA
EA
EA
EA
EA
EA
EA
EA
1
1
1
1
1
1
1
1
1
Daniels
Military
K41 (for 22 to 28 AWG)
M22520/2-06
Positronic Ind. 9502-5
Daniels
Military
K13-1 (20-24 AWG)
M22520/2-08
9502-4
Positronics
Daniles
Military
K42 (22-28 AWG)
M22520/2-09
1.11.3 Insertion/Removal Tool - P1, P2, P3
Description
Removal Tool P1, P3
Removal Tool P1, P3
Removal Tool P2
UM QTY
Vendor Name & Part Number
EA
EA
EA
EA
EA
EA
EA
EA
1
1
1
1
1
1
1
1
Daniels
Military
Daniels
Daniels
Military
Daniels
Military
Military
DRK 95-22M
M81969/8-02
DRK145
Insertion Tool P1, P3
Insertion Tool P1, P3
Insertion Tool P2
DAK 95-22M
M81969/8-01
DAK145
Insertion/Removal Tool P1, P3
Insertion/Removal Tool P2
M81969/1-04
M81969/1-02
1.11.4 Spare Contacts - P1, P2, P3
Description
Mil Spec Part Number
Contacts (P1) socket
Contacts (P2) socket
Contacts (P3) Pin
M39029/57-354
M39029/63-368
M39029/58-360
22-28 GA Wire
20-24 GA Wire
22-28 GA Wire
1.12 License Requirements
There are no Radio license requirements for the MK XXII EGPWS.
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SECTION II
INSTALLATION
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SECTION II – INSTALLATION
SECTION II - INSTALLATION .............................................................................................................................. 33
2.1 INTRODUCTION.................................................................................................................................................... 33
2.2 UNPACKING AND INSPECTING THE EQUIPMENT ................................................................................................... 33
2.3 EQUIPMENT INSTALLATION ................................................................................................................................. 33
2.3.1 General ........................................................................................................................................................ 33
2.3.2 MK XXII Computer Location....................................................................................................................... 34
2.3.3 MK XXII Computer Installation................................................................................................................... 34
2.3.4 Configuration Module Location .................................................................................................................. 35
2.3.5 Configuration Module Installation .............................................................................................................. 35
2.3.6 GPS Antenna location.................................................................................................................................. 44
2.3.7 GPS Antenna Installation ............................................................................................................................ 44
2.3.8 OAT Sensor Location................................................................................................................................... 44
2.3.9 OAT Sensor Installation............................................................................................................................... 44
2.3.10 Cockpit Annunciators / Switches................................................................................................................ 44
2.3.10.1 Description ............................................................................................................................................................ 45
2.3.10.2 Location ................................................................................................................................................................ 46
2.3.10.3 Inhibit Switch Functions and Selection ................................................................................................................. 48
2.3.10.3.1 Terrain Inhibit................................................................................................................................................ 48
2.3.10.3.2 Audio Inhibit (Timed).................................................................................................................................... 48
2.3.10.3.3 Audio Inhibit (Not Described Above)............................................................................................................ 48
2.3.10.3.4 Low Altitude Mode........................................................................................................................................ 48
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SECTION II - INSTALLATION
2.1 Introduction
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 Administrator.
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 then 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 XXII 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.
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2.3.2 MK XXII 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 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 XXII EGPWS has 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 the manual.
Determine the mounting location for the system components following the guidelines below.
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.
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.
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.
2.3.3 MK XXII Computer Installation
The MK XXII 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.
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).
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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 Configuration 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 700-1710-001. 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 Configuration Module Installation
The purpose of this procedure is to give an assembly sequence for assembly of the Configuration Module
with the P2 connector and backshell.
A. The P2 connector, Honeywell part number 440-1233-001, vendor part number RD50F1OJVLC-15,
when ordered comes with 50 contacts and a plastic backshell (hood).
B. The Configuration Module will replace the Backshell Plate. The Backshell Plate can be discarded.
C. Wire the Configuration Module to the P2 connector using contacts provided with the connector. Wire
per the following wire list:
Wire Color
Violet
P2 pin #
P2-17
P2-16
P2-33
Wire Color
Black
P2 pin #
P2-50
P2-49
P2-32
Blue
White
Orange
Red
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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:
ITEM 1.0
ITEM 2.0
* This item may be available from Honeywell under Part No. (440-1233-001)
Two items as follows:
Connector (P2)
Configuration Module Honeywell
Positronic Ind. RD50F10JVLC-15 *
700-1710-001
ITEM 1 DESCRIPTION:
Connector P2 (Positronic Ind. PN RD50F10JVLC-15) is a packaged kit consisting of the following parts:
1.1
1.2
1.3
1.4
1.5
1.6
1.7
1.8
1.9
Connector, 50 socket D-Sub
Contacts, size 20 crimp
Backshell housing
Backshell plate
Qty - 1
Qty - 50
Qty - 1
Qty - 1
Qty - 2
Qty - 1
Qty - 1
Qty - 2
Qty - 1
Screws, Phillips CSK
Spring Clip
Slide Lock
Screws, Slotted
Cable Clamp
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INSTALLATION ASSEMBLY SEQUENCE
STEP 1
Install all MK XXII 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 XXII 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 XXII 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 XXII 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 XXII 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 XXII 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 XXII 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 XXII EGPWS CONFIGURATION MODULE
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2.3.6 GPS Antenna location
The antenna must be mounted on top of the fuselage. Avoid mounting the antenna near any projections
such as the rotor mast, or engine exhaust, where shadows could occur or high heat could damage the
antenna. 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 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 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 may be degraded. See manufacturer’s
drawing in Appendix D for specifications of antenna, antenna cables, and connector information.
2.3.7 GPS Antenna Installation
Refer to manufacturer’s procedures or applicable STC documentation.
2.3.8 OAT Sensor Location
The OAT sensor (CIC 05257) 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’s drawing in Appendix D for
specifications.
2.3.9 OAT Sensor Installation
Refer to manufacturer’s procedures or applicable STC documentation.
2.3.10 Cockpit Annunciators / Switches
This section provides information for selecting, locating and mounting of the MK XXII EGPWS Lighted
annunciators / switches. NOTE: The nomenclature given for each lamp is an example only. Other
manufacturers use nomenclature that is also acceptable. Refer to Honeywell Product Specification 965-
1590-601 for additional information and for electrical loads specification
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2.3.10.1 Description
EGPWS warning
GPWS
P/TEST
This assembly is illuminated with Red background and black or white letters. For dark cockpits black
background and Red letters. The EGPWS warning annunciator is not normally dimmable. For Lamp
Format 1 (I/O Discrete Type 128) the lamp is activated during any Mode 1 through Mode 4, and Terrain
/Obstacle Awareness alerts and warnings. For Lamp Format 2 (I/O Discrete Type 129) the lamp is
activated during Mode 1 and Mode 2 Pull Up, and Terrain /Obstacle Awareness warnings. This assembly
also includes a momentary switch that will activate EGPWS Self Test.
EGPWS caution
GPWS
G/S CANCLD
This assembly is illuminated with Amber background and black or white letters, for dark cockpits black
background and Amber letters. The EGPWS alert annunciator is not normally dimmable. For Lamp Format
1 (I/O Discrete Type 128) the lamp is activated during any Mode 5 alert. For Lamp Format 2 (I/O Discrete
Type 129) the lamp is activated during any Mode 1 through Mode 4, and Terrain /Obstacle Awareness
alerts. This assembly also includes a momentary switch that will activate glideslope cancel.
LOW ALTITUDE
LOW ALT
ON
This assembly is illuminated with black background and white, green, or blue letters. This assembly also
includes a momentary switch that will activate / de-activate (cancel) EGPWS low altitude mode.
TERRAIN INHIBIT
TERR INHIB
ON
This assembly is illuminated with black background and white, blue, or green letters. This assembly also
includes a alternate action switch that will activate ./ de-activate (cancel) Terrain inhibit mode. (Optional
see section 2.3.10.3)
AUDIO INHIBIT
AUDIO INHIB
ON
This assembly is illuminated with black background and white, blue, or green letters This assembly also
includes a momentary switch that will activate ./ de-activate (cancel) Audio inhibit mode. (Optional see
section 2.3.10.3)
GPWS system validity
GPWS INOP
TERR INOP
This assembly is illuminated with black background and amber letters activated during any detected partial
or total failure of the GPWS modes 1-5. And TA&D
TERRAIN select
TERR DISPLAY
ON
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.
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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 2-7. For panel cutouts and assembly options
see the manufacturer’s specifications in Appendix D. The following are recommended locations:
GPWS warning (red) & GPWS alert (amber)
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.
LOW ALTITUDE
This light should be located in the flight crew’s “field of view” and within reach of both crewmembers. This
light/switch may be located in an assembly with the GPWS red and GPWS amber lights and/or other
EGPWS annunciators.
TERR INHIBIT ON (Optional see section 2.3.10.3)
This light should be located in the flight crew’s “field of view” and within reach of both crewmembers. This
light/switch may be located in an assembly with the TERR DISPLAY light(s) and/or other EGPWS
annunciators.
AUDIO INHIBIT ON (Optional see section 2.3.10.3)
This light should be located in the flight crew’s “field of view” and within reach of both crewmembers. This
light/switch may be located in an assembly with the TERR DISPLAY light(s) and/or other EGPWS
annunciators.
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 crewmembers. This light/switch may be located in an assembly with the TERR
INHIBIT light(s) and/or other EGPWS annunciators.
GPWS INOP
This light should be located within crewmember’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.
TERR INOP
This light should be located within at least one crewmember’s “field of view” or with other system INOP
lights of similar importance. Note: Annunciators are available with split legend GPWS INOP / TERR INOP
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.
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FIGURE 2-1.8
MK XXII EGPWS Annunciators/Switches Location
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2.3.10.3 Inhibit Switch Functions and Selection
The Terrain Inhibit and Audio Inhibit functions are optional but it is recommended that one be used to
inhibit the system during certain operations. The operator should evaluate the two options together with
the Low Altitude Mode function and select the one that best fits his operational requirements. The Low
Altitude Mode is also described below for reference.
2.3.10.3.1 Terrain Inhibit
The Terrain Inhibit will inhibit Terrain and Obstacle audio alerts and warnings. It will not deselect the
Terrain Display. The switch is a toggle action, which must be pressed to turn ON and re-pressed to turn
OFF. The switch lighting must be activated thru the switch contacts. This Inhibit is recommended for
corporate transport operations.
2.3.10.3.2 Audio Inhibit (Timed)
The Timed Audio Inhibit will inhibit all audio output for a period of 5 minutes. It will not affect visual alert
and warning outputs and will not deselect the terrain display. The switch is momentary and the lamp is
illuminated by an output from the EGPWS. This inhibit is recommended for EMS and SAR operations.
2.3.10.3.3 Audio Inhibit (Not Described Above)
The Audio Inhibit will inhibit all audio output as long as it is active. It will not affect visual alert and warning
outputs and will not deselect the terrain display. The switch is a toggle action, which must be pressed to
turn ON and re-pressed to turn OFF. The switch lighting must be activated thru the switch contacts. This
Inhibit is NOT RECOMMENTED.
2.3.10.3.4 Low Altitude Mode
To allow for helicopter operations that require low altitude flight a Low Altitude function is enabled with a
switch. This function is designed for flight at low altitude in VFR conditions. When this function is engaged
Mode 2 and Mode 4 warning boundaries are significantly reduced and Terrain Advisory look ahead
distances are reduced. . Low Altitude operation is defined as operation below 500 feet AGL. There are
other circumstances where the use of the Low Altitude Mode is appropriate. Those include operation in a
high-density metropolitan environment with high rise buildings, operation below 1250 feet AGL when the
GPS is not operational or is providing poor accuracy.
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FIGURE 2-2 MK XXII EGPWS OUTLINE
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FIGURE 2-3 MK XXII EGPWS MOUNTING TRAY
Honeywell P/N
405-0383-001
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SECTION III
SYSTEM PLANNING
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SECTION III – SYSTEM PLANNING
SECTION III – SYSTEM PLANNING..................................................................57
3.1 INTRODUCTION.................................................................................................................................... 57
3.2 SYSTEM WIRING/ ELECTRICAL INTERFACES........................................................................................ 57
3.2.1 Primary Power Input ................................................................................................................... 57
3.2.2 Chassis Ground ........................................................................................................................... 57
3.2.3 GPS Antenna................................................................................................................................ 58
3.2.4 Analog and Digital Inputs............................................................................................................ 58
3.2.5 Discrete Inputs............................................................................................................................. 58
3.2.6 Serial Outputs.............................................................................................................................. 58
3.2.7 Audio Output................................................................................................................................ 59
3.2.8 Discrete Outputs.......................................................................................................................... 59
3.2.9 Configuration Module ................................................................................................................. 59
3.3 CONFIGURABLE INTERFACES............................................................................................................... 60
3.3.1 Category 1 - Aircraft / Mode Type Select .................................................................................... 60
3.3.1.1 Aircraft / Mode Type............................................................................................................................. 60
3.3.1.2 Instructions ............................................................................................................................................ 60
3.3.1.3 Generic Helicopter with and without Torque......................................................................................... 60
3.3.2 Category 2 – Air Data Input Select.............................................................................................. 61
3.3.2.1 Instructions ............................................................................................................................................ 61
3.3.2.2 Examples ............................................................................................................................................... 62
3.3.2.3 Analog altitude and 500 ohm OAT ................................................................................................... 62
3.3.2.4 Digital – ARINC 429 (Cat. 2 ID 5, 1, 6) ........................................................................................... 63
3.3.2.5 Digital –ARINC 575 (Cat. 2 ID 2) .................................................................................................... 64
3.3.2.6 Shadin 2000 (Cat. 2 ID 10) ............................................................................................................... 65
3.3.2.7 Digital – ARINC 429 Dual IOC Buses (Cat. 2. ID 255) ................................................................... 66
3.3.3 Category 3 – Position Input Select .............................................................................................. 67
3.3.3.1 Instructions ............................................................................................................................................ 67
3.3.3.2 ARINC 743 Format ............................................................................................................................... 67
3.3.3.Examples .................................................................................................................................................. 68
3.3.3.1 ARINC 429 BUS (Cat. 3 ID 0,1,4,5)................................................................................................. 68
3.3.3.2 RS-232 Transmit-Receive, 9600 baud (Cat. 3 ID 3) ......................................................................... 68
3.3.3.3 Dual ARINC 429 BUS (Cat. 3 ID 255)............................................................................................. 69
3.3.4 Category 4 – Altitude Callouts .................................................................................................... 70
3.3.4.1 Instructions ............................................................................................................................................ 70
3.3.5 Category 5 – Audio Menu Select ................................................................................................. 71
3.3.5.1 Instructions ............................................................................................................................................ 71
3.3.6 Category 6 – Terrain Display Select ........................................................................................... 72
3.3.6.1 Instructions ............................................................................................................................................ 72
3.3.6.2 TAD Selection....................................................................................................................................... 72
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3.3.6.3 Terrain Display Configuration Group.................................................................................................... 73
3.3.6.4 Display Input Control Group................................................................................................................. 75
3.3.6.5 Output 429 Bus Group........................................................................................................................... 75
3.3.6.6 Example................................................................................................................................................. 75
3.3.7 Category 7 – Options Select Group #1........................................................................................ 81
3.3.7.1 Instructions ............................................................................................................................................ 81
3.3.7.2 Steep Approach (Not Available in the Mk XXII).................................................................................. 81
3.3.7.3 TA&D Alternate Pop-up........................................................................................................................ 81
3.3.7.4 Peaks Mode ........................................................................................................................................... 82
3.3.7.5 Obstacle Awareness............................................................................................................................... 82
3.3.7.6 Bank Angle Callout Enabling................................................................................................................ 82
3.3.7.8 WOW Reversal...................................................................................................................................... 83
3.3.7.9 GPS Altitude Reference......................................................................................................................... 83
3.3.8 Category 8 – Radio Altitude Input Select .................................................................................... 84
3.3.8.1 Instructions ............................................................................................................................................ 84
3.3.8.2 Example................................................................................................................................................. 84
3.3.8.3 Digital Radio Altitude Interface ........................................................................................................ 84
3.3.8.4 Analog Radio Altitude Interface........................................................................................................ 85
3.3.9 Category 9 – Navigation Inputs Select ........................................................................................ 86
3.3.9.1 Instructions ............................................................................................................................................ 86
3.3.9.2 Example................................................................................................................................................. 87
3.3.9.3 Analog Glideslope Interface (cat. 9 ID 0,1,5) ................................................................................... 87
3.3.9.4 Digital Glideslope/Localizer Interface .............................................................................................. 88
3.3.9.5 Dual Glideslope Receiver.................................................................................................................. 88
3.3.10 Category 10 – Attitude Input Select........................................................................................... 89
3.3.10.1 Attitude Signals ................................................................................................................................... 89
3.3.10.2 Instructions .......................................................................................................................................... 89
3.3.10.3 Example............................................................................................................................................... 90
3.3.10.4 Analog Roll Angle (Synchro).......................................................................................................... 90
3.3.10.5 Digital ARINC 429 High Speed...................................................................................................... 91
3.3.11 Category 11 – Heading Input Select.......................................................................................... 92
3.3.11.1 Instructions .......................................................................................................................................... 92
3.3.11.2 Magnetic Heading................................................................................................................................ 92
3.3.11.3 Example............................................................................................................................................... 93
3.3.11.3.1 Analog Heading (Synchro) (CAT. 11 ID 0) ................................................................................. 93
3.3.11.3.2 Digital ARINC 429 High Speed................................................................................................... 94
3.3.12 Category 12 – Windshear Input Select ...................................................................................... 95
3.3.12.1 Instruction............................................................................................................................................ 95
3.3.13 Category 13 – Input / Output Discrete Type Select ................................................................... 96
3.3.13.1 Instruction............................................................................................................................................ 96
3.3.13.2 Input/Output Discretes......................................................................................................................... 96
3.3.13.3 Audio Inhibit Discrete..................................................................................................................... 97
3.3.13.4 Landing Gear Discrete..................................................................................................................... 97
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3.3.13.5 Weight ON Wheels (WOW) Discrete ............................................................................................. 97
3.3.13.6 Glideslope Cancel Discrete ............................................................................................................. 98
3.3.13.7 Mode 6 Low Volume Discrete ........................................................................................................ 98
3.3.13.8 Autopilot Engaged Discrete ............................................................................................................ 98
3.3.13.9 Terrain Awareness Inhibit............................................................................................................... 99
3.3.13.10 Self Test Discrete .......................................................................................................................... 99
3.3.13.11 Glideslope Inhibit Discrete............................................................................................................ 99
3.3.13.12 Timed Audio Inhibit Discrete...................................................................................................... 100
3.3.13.13 Low Altitude Mode Select Discrete ............................................................................................ 100
3.3.13.14 Output Discretes.......................................................................................................................... 100
3.3.13.15 Lamp Format............................................................................................................................... 100
3.3.13.16 GPWS INOP Discrete ................................................................................................................. 101
3.3.13.17 TAD INOP Discrete.................................................................................................................... 101
3.3.13.18 GPWS Warning Discrete............................................................................................................. 101
3.3.13.19 GPWS Alert Discrete .................................................................................................................. 101
3.3.13.20 Glideslope Cancel Discrete ......................................................................................................... 101
3.3.13.21 TCAS Inhibit Discrete................................................................................................................. 101
3.3.13.22 Terrain Display Select #1 & #2 Discrete..................................................................................... 102
3.3.13.23 Timed Audio Inhibit Discrete...................................................................................................... 102
3.3.13.24 Low Altitude Mode Discrete....................................................................................................... 102
3.3.14 Category 14 – Audio Output Level .......................................................................................... 104
3.3.14.1 Instructions ........................................................................................................................................ 104
3.3.15 Category 15, Autorotation Threshold...................................................................................... 105
3.3.15.1 Instruction.......................................................................................................................................... 105
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SECTION III – SYSTEM PLANNING
3.1 Introduction
This section provides information for selecting features and wiring the electrical interfaces of the
MK XXII EGPWS. Sample wiring diagrams for the most commonly used MK XXII EGPWS
configurations are provided in Appendix B. Appendix E Section E 3 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.
1. Make a copy of Appendix E Table E 3. Use this table along with Appendix A Fig A-1.1, A1.2,
and A1.3 to record feature selection and determine the wiring interface.
3.2 System Wiring/ 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 E 4 shows the typical usage for each pin, on the Left
(J1), Right (J2) and Upper (J3) connectors.
3.2.1 Primary Power Input
The MK XXII EGPWC requires a primary power input (28 VDC input power) and ground. The
Primary power should be connected as follows.
Pin
Signal
J1-40, J1-60
J1-41, J1-61
+28 VDC Input
+28 VDC Return
Recommended EGPWC Power Control Device: 3 Amp Delayed Action Circuit Breaker
3.2.2 Chassis Ground
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
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3.2.3 GPS Antenna
A GPS antenna connector is available on the front of the MK XXII EGPWS 965-1590-0XX.
3.2.4 Analog and Digital Inputs
The analog and digital inputs to the MK XXII EGPWS are defined as the Categories are selected.
Instructions for documenting these interfaces are provided with the Category selection
instructions. Section 3.3 contains detailed category configuration information.
3.2.5 Discrete Inputs
Additional information for some discretes is provided within the Category in which they are used.
See section 3.3.13.
3.2.6 Serial Outputs
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.
Two ARINC 429 low speed output buses provided by the EGPWC. 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.
For category configuration information see section 3.3.6.
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3.2.7 Audio Output
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 Outputs
The MK XXII EGPWS provides for up to twelve 0.5 amp (1 amp maximum) Ground/Open discrete
outputs. The discrete outputs are defined in Appendix E 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. Except for fully integrated cockpits, 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). See section 3.3.13.
3.2.9 Configuration 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 700-1710-001.
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 Configurable Interfaces
The following subsections define configurable interfaces for the EGPWS. Typical interface
connection information and diagrams are provided. Use this in conjunction with Appendix E
which has detailed interface configuration information.
3.3.1 Category 1 - Aircraft / Mode Type Select
Category 1 specifies the general aircraft type, warning mode definitions, , fixed or retractable
gear, and engine torque interface.
Note: Category 15 will set the engine torque value used for autorotation mode.
3.3.1.1 Aircraft / Mode Type
The Aircraft Type identifies the aircraft as “Manufacture and Model”. The aircraft category defines
configurable data that control performance. The configurable values are not user defined or
controlled.
Appendix E Table E 3.1.1 lists the combinations of Aircraft/Mode Types and identifies the first MK
XXII EGPWS version in which the option was available (see the Effectivity entry), and describes
the options available with each Aircraft/Model type (see Description column).
3.3.1.2 Instructions
1. Using Appendix E Tables E 3, under Step/category 1 select Aircraft type. Using Table E 3.1.1
select ID number for your aircraft type and record that number on Table E 3 under Ident No.
This number will be used for programming the configuration module.
2. Using Appendix E Table E 3.1.1 under Aircraft/Model Type Table use table E 3.1.1-x to
determine the torque wiring interconnects and record it on Appendix A Fig A1-2.
Note. Aircraft types 129, 130 and 138 with software version –010 and earlier are configured for
the raw low level DC torque input. This interface will not work. With software version –011 these
types are configured to use an external Buffer Amplifier provideing a gain of 30.23. For these
applications it is recommended that either the No Torque configuration or the Shadin Converter
configuration, described below, be used.
3.3.1.3 Generic Helicopter with and without Torque
For any airframe not listed in Appendix E table E 3.1.1 contact Honeywell GPWS hot line 1
800 813-2099.
Generic helicopter types are provided for aircraft with torque interfacing problems. Category 1 ID
type 146, 147, 148, and 149, allow interface to airframes without torque input,. These types do
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not detect autorotation and thus do not provide the autorotation altitude callouts or advanced gear
warnings. Mode 1 is inhibited in these types. The generic types are segregated into retractable
and fixed gear configurations and tail strike warning profiles. Contact the Honeywell GPWS hot
line 1 800 813-2099 for help in selecting the correct generic type.
Category 1 ID types 150, 151, 152 and 153 are provided for applications where low level DC
torque signals are externally amplified and scaled to a common 0.040 VDC per %.
Category 1 ID types 154, 155, 156 and 157 are provided for applications where low level DC
torque is scaled and converted to ARINC 429 using the Shadin DC Torque to 429 Converter, Part
Number 933755-00. This is particularly applicable to S-76-A/A+/A++ /C, and Bell 407 aircraft.
Contact the Honeywell GPWS hot line 1 800 813-2099 for help in selecting the correct generic
type.
3.3.2 Category 2 – Air Data Input Select
Category 2 defines the Air Data interface. The Air Data input currently defines 5 analog and 6
digital air data types.
3.3.2.1 Instructions
1. Using Appendix E Table E 3, under Step/category 2 select Air Data Source. Using table E
3.1.2 and 3.1.2-x select the ID number for your air data source and record that number on
Table E 3 under Ident No. for step 2. This number will be used during programming of the
configuration module.
2. Using Appendix E Tables E 3.1.2-x, where x is the Air Data Type number, define the
electrical interfaces required to support your Air Data Type. Using Table E 3.1.2-x determine
the wiring interconnects and record it on Appendix A Fig A1-2.
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3.3.2.2 Examples
3.3.2.3 Analog altitude and 500 ohm OAT
EGPWS MK XXII
J1
Analog Air Data Computer
62
43
9
Uncorrected
Barometric
Altitude
(+)
(-)
Altitude Out
Signal Common
Baro Altitude Valid +28V
BIT Out
25
63
44
53
+5V Excitation
(+)
Temp. Input
(-)
500 ohm
Temperature
Probe
Chassis Ground
Analog-ADC.vsd
Cat 2
ID
Uncorrected Baro Altitude
Vendor Model
Altitude Out
J1-F
Common
J1-G
BIT Out
J1-E
CIC 04077
0
Collins ADS-65
CIC 02702
3
J1-12
J1-13
J1-5
4
J1-A
J1-B
J1-E
Honeywell AZ-241
Honeywell AZ-242
Honeywell AZ-648
Honeywell AZ-800
Honeywell AZ-810
11/12
11/12
11/12
11/12
11/12
J1-63
J1-11
J1-12
J1A-12
J1-U
J1A-40
J1-J
J1A-11
J1-G
J1A-78
J1A-78
J1A-10
J1A-10
J1A-34
J1A-34
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: Honeywell AZ-810 should only be used as an analog source if it does not have a digital interface.
NOTE: The CIC 02702 scaling was changed in –008 software. The analog barometric altitude conversion to barometric
altitude rate noise problem was fixed in –008 software.
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3.3.2.4 Digital – ARINC 429 (Cat. 2 ID 5, 1, 6)
Air Data Type 1 (AZ-800 or equivalent) is a low speed, digital ARINC 429 signal having the air
data labels 203, 206, 212, and 213.
Air Data Type 5 (AZ-800 or equivalent) is a low speed, digital ARINC 429 signal having the air
data labels 203, 204, 206, 212, and 213.
Air Data Type 6 (AZ-800 or equivalent) is a low speed, digital ARINC 429 signal having the air
data labels 203, 206, and 213.
EGPWS MK XXII
J2
ARINC 429 Air Data
ARINC 429 Bus - Hi
39
38
A
B
A
B
ARINC 429 Low Speed
Air Data Bus
ARINC 429 Bus - Lo
Digital-ADC.vsd
Cat 2
Bus 1
Bus 2
Vendor Model
Sperry AZ-8XX
CIC 04471
ID
5*
5*
*
A
B
A
B
J1B-26
J1-12
J2-J
J1B-27
J1-13
J2-K
J1B-70
J1B-71
CIC 02702 mod 6
KDC 281
*
P2811-5
P4811-U
J1-27
6
P2811-6
P4811- i
J1-9
KDC 481
*
B&D 90004
B&D 2600
5*
*
8
B&D 2601
*
14
13
B&D 2800
*
P201-11
P2-9
P201-28
P2-10
J1-22
Collins ADC 85/86
5*
5*
P2-29
P2-30
Shadin ADC-2000
(s/w mod 71.73.01)
J1-40
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 or 6 depending on availability of labels 204 and 212.
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3.3.2.5 Digital –ARINC 575 (Cat. 2 ID 2)
Air Data Type 2 (ADC-80 or equivalent) is a low speed, digital ARINC 575 signal having the air
data labels 203, 206, 212, and 213.
EGPWS MK XXII
J2
ARINC 575 Air Data
ARINC 575 Bus - Hi
39
38
A
B
A
B
ARINC 575
Air Data Bus
ARINC 575 Bus - Lo
ARINC575-ADC.vsd
Cat 2
Bus 1
Bus 2
Vendor Model
Collins ADC-80( )
Collins ADC-82A
B&D 90004
ID
2
A
B
A
B
P3-35
P3-36
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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3.3.2.6 Shadin 2000 (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 XXII EGPWC.
EGPWS MK XXII
ARINC 429 Air Data
J2
39
38
A
B
A
B
ARINC 429 Bus - Hi
ARINC 429 Bus - Lo
ARINC 429 Low Speed
Air Data Bus
J1
+5V Excitation
25
63
44
53
(+)
Temp. Input
(-)
500 ohm
Temperature
Probe
Chassis Ground
Shadin2000.vsd
Cat 2
ID
Bus 1
Bus 2
Vendor PN
A
B
A
B
962830-1,2,3
10
J2-7
J2-8
962830A-1,2,3
J1-40
J1-22
962830A-X-S-4
10
962830A-X-S-5
962830A-1-S-7(B212/412)
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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3.3.2.7 Digital – ARINC 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.
EGPWS MK VI / MK VIII
J2
IOC Buses
39
38
A
B
A
B
ARINC 429
High Speed
IOC Bus 1
41
40
A
B
A
B
ARINC 429
High Speed
IOC Bus 2
ARINC429-IOC.vsd
Cat 2
IOC Bus 1
IOC Bus 2
Vendor Model
ID
A
B
A
B
BD 100 IAPS
L-IOC (L-GP-5)
R-IOC (R-GP-5)
255
A4P1-1
A4P1-2
A4P101-1
A4P101-2
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.
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3.3.3 Category 3 – Position Input Select
Category 3 defines the Global Position System bus type and interface. GPS Input selection is
available in the following formats: ARINC 429 low speed and ARINC 429 high speed in either
ARINC 743 or 743A format, RS-232, and Internal GPS card.
CAUTION
Not all GPS receivers calculate Horizontal Figure of Merit (HFOM) and Vertical Figure of Merit
(VFOM) correctly and thus are unacceptable sources of position. The following GPS systems are
know to have FOM computational errors:
Universal GPS-1000
3.3.3.1 Instructions
1. Using Appendix E Tables E 3, Under Step/category 3 select Position Input Source. Using
table E 3.1.3 and E 3.1.3-x select ID number for your position input source and record that
number on Table E 3 under Ident No. for step 3. This number will be used during
programming of the configuration module.
2. Appendix E Tables E 3.1.3-x, where x is the position input type number, define the electrical
interfaces required to support the position input type. Using Tables E 3.1.3-x determine the
wiring interconnects and record it on Appendix A Fig A1-3.
Note:
See Category 7 to select GPS Altitude Reference (mean sea level or WGS-84)
for ARINC 429 label 076.
3.3.3.2 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.
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3.3.3.Examples
3.3.3.1 ARINC 429 BUS (Cat. 3 ID 0,1,4,5)
EGPWS MK XXII
J2
ARINC 429 GPS
25
8
A
B
A
B
ARINC 429 Bus - Hi
ARINC 429
GPS Bus
ARINC 429 Bus - Lo
ARINC429-GPS.vsd
429
GPS Alt
Ref.
ARINC
743/743A
743A
Bus 1
Bus 2
Vendor Model
Speed
Low
A
B
A
B
GNS-XLS (17960-0203-)
or (17960-0102-) SM06
MSL
J101-N5 * J101-N6 *
GNS-XL (18355-) SM06
HG2021GBXX
Low
H/L**
H/L**
MSL
MSL
MSL
743A
743
J101-N5
J1-38
J101-N6
J1-39
J1-24
J1-24
J1-25
J1-25
HG2021GDXX
743A
J1-38
J1-39
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.
*
GNS-XLS ARINC 429 bus also contains Range label
** Pin 21 open = high speed; Pin 21 GND = Low speed
3.3.3.2 RS-232 Transmit-Receive, 9600 baud (Cat. 3 ID 3)
EGPWS MK XXII
J2
RS-232 GPS
NC
45
29
TX
RX
RX – Receive In
TX – Transmit Out
GND
RS – 232
GPS Bus
CM 28
RS232-GPS.vsd
GPS Alt
ARINC
RS-232
Vendor Model
Ref.
743/743A
N/A
RX
TX
GND
Chassis
GARMIN GNS430
Software Version 2.21
MSL
P4001-56
KLN 900
MSL
N/A
P9002-13
Chassis
066-04034-0104 or 066-04034-0204
KLN 94
MSL
N/A
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.
The KLN 90B is not compatible with EGPWS.
The GNS 430 software mod is also applicable to the GPS 400 and GNC 420 units.
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3.3.3.3 Dual ARINC 429 BUS (Cat. 3 ID 255)
NOTE: If GPS #2 is not installed in the aircraft, then GPS bus #1 must be connected in parallel to
both EGPWS GPS input ports.
EGPWS MK XXII
J2
ARINC 429 GPS
Hi
25
8
A
B
A
B
ARINC 429
GPS Bus
ARINC 429 Bus 1
Lo
23
6
A
B
Hi
A
B
ARINC 429
GPS Bus
ARINC 429 Bus 2
Lo
ARINC429-DualGPS.vsd
429
GPS Alt
Ref.
ARINC
Bus 1
Bus 2
A
Aircraft Model
Speed
743/743A
A
B
B
BD 100
GPS-1 (L-GPS-2)
GPS-2 (R-GPS-2)
High
High
MSL
MSL
743A
743A
A25BP1-6A
A25BP1-6B
A24BP1-6A
A24BP1-6B
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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3.3.4 Category 4 – Altitude Callouts
Category 4 defines the Altitude Callout menu choices and Smart ‘500’ Callout selection along with
Autorotation callout enablement.
Appendix E Table E 3.1.4 defines the Altitude Callout Menu options and identifies the first MK
XXII EGPWS version in which the option was available (see the Effectivity entry).
The Altitude callout menus have selected combinations of “Minimums-Minimums”, Smart “500”,
“200”, “100”, “50”, “40”, “30”, “20”, and “10”. Autorotation mode, and no altitude callouts may also
be selected. Recommended selections are ID 133, 135 or 136.
NOTE: For applications that use Category 1 (Aircraft Type) ID 146, 147, 148 or 149, where
autorotation will not be detected, it is strongly recommended that a callout menu be selected that
provides, as a minimum, 200 and 100 feet such as ID 132 or 136.
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 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.
“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.
3.3.4.1 Instructions
1.
Using Appendix E Table E 3.1.4 , select the preferred Altitude Callout Menu Type (ID)
that matches the feature preferences and version (part number) being installed. Using
table E 3.1.4 select ID number for your Altitude callouts and record that number on Table
E 3 under Ident No. for step 4. This number will be used during programming of the
configuration module.
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 E 3.1.8-x to
generate the installation wiring diagrams.
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3.3.5 Category 5 – Audio Menu Select
Category 5 defines one Audio Menu options for Helicopters (ID 128).
3.3.5.1 Instructions
1. Using Appendix E Tables E 3, Under Step/category 5 select Audio Menu. Using table E 3.1.5,
select ID number for your audio menu and record that number on Table E 3 under Ident No.
This number will be used for programming the configuration module.
2. Audio Menu has no bearing on Aircraft wiring interface
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3.3.6 Category 6 – Terrain Display Select
Category 6 defines the Terrain Display options available.
Appendix E Table E 3.1.6 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 XXII EGPWS version in which the option was available (see the Effectivity
entry).
Note: TA&D mode enabling/disabling is controlled by Category 6. Chose ID 2 for aircraft without
TA&D.
3.3.6.1 Instructions
1. Using Appendix E Tables E3.1.6 and E 3.1.6-x 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 E
3 under the Ident No. heading for Step (Category) 6 .
2. Using the I D number Table E 3.1.6 as “x”, go to the Table E 3.1.6-x . The electrical interfaces
(pin-outs) for the Display are shown in the Display Configuration Group, Display Input
Control Group, and Output 429 Bus Group, Table E 3.1.6-x are used to generate the
installation wiring diagrams. Determine the wiring interconnects and record it on Appendix A
Fig A1-1.
Figure 3.8-1 is an example of single tube Wx/Terrain display wiring connections.
3.3.6.2 TAD Selection
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 terrain data relative to aircraft altitude.
A “False” entry in Appendix E Table E 3.1.6 for “TAD Disable” indicates that TA&D is ENABLED
(the “Disable” is disabled).
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3.3.6.3 Terrain Display 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
Sweep Type
Auto Pop Up
Display manufacturer, model, etc.
The type of sweep used for terrain data (fan, standard, etc.)
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
Describes if/when terrain display(s) can be manually deselected
Manual deselect
Defines if the display data is automatically scaled and, if so, the scale used
(such as 10 nautical miles)
Auto Range
Moving Marker
Overlay Page
Indicates whether or not a moving marker is provided
Describes where “TERR” and Peaks Elevations overlays will be located on the
display screen.
Indicates the priority for displaying terrain data. For example:
Standard (PWS Warn, Terrain Warn, PWS Caution, Terrain Caution)
Display Priority
Searchlights
Defines the display bus type ‘KC Picture Bus’ (ASPB), ‘Honeywell Picture Bus’
or ‘ARINC 453’.
Display bus type
CHANNEL
TX453-1
CONNECT TO:
A = J1-58
B = J1-59
CHANNEL
TX453-2
Indicates the correct connection for these pins
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 0-1 Definition of Display Configuration Group Tables (Appendix E Section 5.3.6)
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3.3.6.4 Display Input 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 XXII EGPWC.
3.3.6.5 Output 429 Bus Group
This output bus is commonly connected to EFIS and/or EICAS displays and Flight Recorders and
transmits MK XXII EGPWC alert, fault, and mode status to other systems.
3.3.6.6 Example
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3.3.7 Category 7 – Options Select Group #1
Category 7 enables/disables the following Options: Steep Approach (not available in MkXXII),
TA&D Alternate Pop Up, Peaks Mode, Obstacle Awareness, Bank Angle, WOW Reversal, and
GPS Altitude Reference.
Appendix E Table E 3.1.7 defines the Options Select group and identifies the first MK XXII
EGPWS version in which the option was available (see the Effectivity entry).
Note: Disabling peaks mode is not an option in the Mk XXII
3.3.7.1 Instructions
1. Review the sections below for information on Steep Approach, TA&D Pop Up, Peaks Mode,
Obstacle Awareness, Bank Angle, WOW Reversal, and GPS Altitude Reference
2. Using Appendix E Tables E 3.1.7, 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 E 3 under the Ident No. heading for Step (Category) 7. This number will be used for
programming the configuration module
3.3.7.2 Steep Approach (Not Available in the Mk XXII)
This feature is not applicable to MK XXII.
3.3.7.3 TA&D Alternate 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.)
Category 7 enables/disables Alternate Pop Up.
Pop-Up and
Defines whether EGPWC visual alerts will “pop-up” on displays not
currently displaying terrain data. The entries are:
Alternate Pop-Up
False
Selected terrain-compatible displays will switch to display
surrounding terrain data. (Some displays will only Pop Up
when display is in the proper mode.)
True
EGPWS alerts will not pop-up in terrain-compatible
displays.
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For Helicopters TA&D Alternate Pop Up should always be set to False.
3.3.7.4 Peaks Mode
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 terrain display is typically blank during
the cruise portion of a flight. Peaks mode provides increased situational awareness by providing
the same information as the standard 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.
Disabling peaks mode is not an option in the Mk XXII. Peaks Mode is always selected.
3.3.7.5 Obstacle Awareness
The Obstacle Awareness feature adds a database of (man-made) obstacles that are greater than
100 feet taller than the surrounding terrain to the Terrain Awareness Alerting calculations. (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.) Obstacle data is currently available for North America and parts of
the Caribbean. 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 must be enabled if Obstacle Awareness is enabled.
Honeywell strongly recommends the selection of Obstacle Awarness.
3.3.7.6 Bank Angle Callout Enabling
The Bank Angle feature provides protection for over banking during maneuvering on approach or
climb-out and while at altitude.. The Bank Angle callout can be enabled or disabled as
appropriate for this installation.
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3.3.7.8 WOW Reversal
The WOW 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 WOW discrete active position:
WOW Reversal
WOW Discrete (Category 13)
WOW Discrete = +28V
Not Selected
WOW
Selected
Not WOW
WOW
WOW Discrete = Open
Not WOW
Ground seeking WOW discrete active position:
WOW Reversal
WOW Discrete (Category 13)
WOW Discrete = GND
Not Selected
WOW
Selected
Not WOW
WOW
WOW Discrete = Open
Not WOW
3.3.7.9 GPS Altitude Reference
The GPS Altitude (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. If using the internal GPS card select MSL.
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3.3.8 Category 8 – Radio Altitude Input Select
Category 8 defines the Radio Altitude and Decision Height interface.
3.3.8.1 Instructions
1. Using Appendix E Tables E 3, under Step/category 8 select Radio Altitude Type. Using table
E 3.1.8 and E 3.1.8-x select ID number for your Radio Altimeter and record that number on
Table E 3 under Ident No. for step 8. This number will be used during programming of the
configuration module.
2. Appendix E Tables E 3.1.8-x, where x is the Radio Altimeter Type number, define the
electrical interfaces required to support each Radio Altimeter. Using Table E 3.1.8-x
determine the wiring interconnects and record it on Appendix A Fig A1-1.
3. The Decision Height discrete (J1-33, Category 8) indicates to the MK XXII 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. Using
Table E 3.1.8-x determine the wiring interconnects for Decision Height and record it on
Appendix A Fig A1-1.
3.3.8.2 Example
3.3.8.3 Digital Radio Altitude Interface
EGPWS MK XXII
J2
Radio Altimeter R/T
A
A 21
ARINC 429
Radio Altitude
ARINC 429
B
B
4
J1
Radio Altimeter Indicator
DH
DH Discrete (Gnd)
33
Vendor Model
R/T
Indicator
R/T
Indicator
ALI-55
SCALE
DH
A
P1-2
MP-B2
B
B
Collins RAC-870
ARINC 429
ARINC 429
ARINC 429
P1-V
P1-3
MP-B3
C
Honeywell ALA-52A
Honeywell KRA 405B
KNI-415/416
M
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3.3.8.4 Analog Radio Altitude Interface
J1
EGPWS MK XXII
Radio Altimeter R/T
ARINC 552, ALT 55,
RT-200/300
+
-
(+) 64
(-) 45
Analog Radio Altitude
Valid
Radio Altitude Valid +28V 29
Radio Altimeter Indicator
DH
DH Discrete (Gnd)
Vendor Model
33
Indicator
DH
R/T
R/T
Indicator
ALI-55
SCALE
ALT55
+
-
Valid
P1-49
P1-49
P4-27
P1-Y
P1-Y
S
Collins ALT 55 (3)
P1-V
P1-57
P1-57
P4-47
P1-X
P1-N
P1-B
E
P1-59
P1-59
P4-46
P1-N
P1-W
P1-g
X
Collins ALT 50
-20 to 2100 ft
ARINC 552
ARINC 552
-.4mV/ft
Honeywell HG7502
Honeywell RT-300 (1)
Honeywell RT-200 (2)
Honeywell KRA-405
JG1072( )
RA-315
P1-e
P1-F
P1-F
M
RA-215
KNI-415/416
ALT55
Honeywell KRA 405B KNI-415/416
KRA 405B (2)
ALT55
M
j
-4mV/ft
G
Z
j
066-01153-0101
KRA 405B
ARINC 552A
ARINC 552
ARINC 552
Z
G
j
066-01153-0202
Honeywell ALA-51A
INA-51( )
339H-1/-2
P2-e
P1-e
P1B-
47
P1B-46
P1B-46
P1B-27
P1B-27
Collins 860F-1
P1B-
47
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. Some RT-
200’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.
NOTE 3: The ALT-55 provides compromised EGPWS performance due to the average altitude
tracking algorithm employed.
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3.3.9 Category 9 – Navigation Inputs Select
Category 9 selects the Glideslope and Localizer Deviation interfaces and Glideslope Validity and
ILS Tuned discretes.
Appendix E Table E 3.1.9 defines the Category 9 Navigation Inputs Select options (called
Navigation Inputs Select Types) and identifies the first MK XXII EGPWS version in which the
option was available (see the Effectivity entry).
3.3.9.1 Instructions
1. Using Appendix E Tables E 3, E 3.1.9 and E 3.1.9-x as described above, select the
Navigation Input Select Type that matches the aircraft configuration, feature preferences, and
version (part number) being installed.
2. Record the ID number for the Navigation Inputs Select Type from Appendix E Table E 3
under the Ident No. heading for Step (Category) 9. This number will be used during
programming of the configuration module.
3. Using the Navigation Inputs Select number from Appendix E Table E 3.1.9 as “x”, go to
Appendix E Table E 3.1.9-x. .The electrical interfaces (pin-outs) for the Navigation Inputs
Select Type are shown in Appendix E Table E 3.1.9-x and are used to determine the wiring
interconnects and record it on Appendix A Fig A1-1.
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) and is available in digital format only.
Glideslope Validity
Glideslope Validity (+28V Super Flag) is required for Navigation Inputs Select 0 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 (Navigation Inputs 2 & 3) do not require Glideslope Validity input.
ILS Tuned Discrete Input #1 (+28V) and #2 (GND)
The ILS Tuned Discrete indicates that an Instrument Landing System frequency has been
selected on the Captain’s (or selected) ILS. The ILS Tuned Discretes #1 (+28V) and #2 (GND)
are optional to each other. These discretes are used with the analog Glideslope inputs. When an
ILS is tuned, the MK XXII EGPWS checks the Glideslope Validity discretes and monitors the
Glideslope inputs.
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3.3.9.2 Example
3.3.9.3 Analog Glideslope Interface (cat. 9 ID 0,1,5)
EGPWS MK XXII
GS Deviation
J2
ILS Receiver
+Up
+
-
65
46
GS Deviation
+Dn
11
GS Valid +28
Super Flag +28V
+
Low Level
GS Valid
GS Flag
(Low Level)
+
-
30
10
-
39
+28
Delayed ILS Mode
ILS Energize
ILS Tuned
GND 20
Valid
SuperFlag Low Level
ILS Tuned
+28V GND
Deviation
GS
Vendor Model
+28V
Flag
+up/+dn
Honeywell
KNR 630
Honeywell
KNR 634
Honeywell
KGM-691
Honeywell
KNR 600A
Collins
J1003-27
J1003-21
J1003-22
P6342-34
P6342-18
P692-S
P692-T
P601-e
P601-q
TP-22
J1002-18
P6341-17
P692-a
P601-k
BP-18
J1003-8
J1003-9
P6342-36
P6342-35
P692-B
P692-C
P601-r
P601-s
TP-8
P6342-50
51RV-1
TP-21
TP-9
Collins
P1-17
P1001-60
TP-27
J1-9
P2-40
P1-5
VIR-30, -31, -32
Honeywell
VNS 41A
Honeywell
RNA-34A
Honeywell
KN 53
J1-13
P1-1
J1001-56
BP-18
J1001-90
J1001-23
TP-8
TP-21
TP-9
P2-13
P2-R
P2-12
P2-P
P2-14
Honeywell
RNZ 850
P1-A74
P1-B64
P1-B79
P1-B75
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3.3.9.4 Digital Glideslope/Localizer Interface
EGPWS MK VI / MK VIII
J2
ILS Bus
A
A 22
ARINC 429
Low Speed
ARINC 429 ILS
B
B
5
Vendor Model
ARINC 429 Bus 1
ARINC 429 Bus 2
A
B
A
B
Honeywell KNR 634A
Honeywell VNS 41A
Honeywell RNA-34A
Honeywell KN 40A(B)
Collins VIR-432
P6342-41
P1001-62
P1024-24
P401 (403) –41
P1-35
P6342-42
P1001-103
P1024-28
P401 (403) –42
P1-36
P6342-44
P6342-45
P1024-21
P1024-25
P401 (403)-44 P401 (403)-45
P1-22
P1-23
3.3.9.5 Dual Glideslope Receiver
An example of dual Glideslope receivers are shown on Fig A1-1 Appendix A
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3.3.10 Category 10 – Attitude Input Select
Category 10 defines the Roll and Pitch Attitude interface.
3.3.10.1 Attitude Signals
Roll Angle is used for Bank Angle callout, Pseudo Altitude Algorithm and Terrain Awareness
display.
Pitch Angle is used for the Tail Strike alert.
NOTE: For MD900 series aircraft where no Tail Strike alert is applicable, Pitch is not required, so
a roll only configuration may be selected.
Appendix E Table E 3.1.10 defines the Attitude Input Select type and identifies the first MK XXII
EGPWS version in which the option was available (see the Effectivity entry).
3.3.10.2 Instructions
1. Using Appendix E Tables E 3 and Table E 3.1.10 ,select the Attitude Input Select type that
matches the aircraft configuration, feature preferences, and version (part number) being
installed.
2. Record the ID number for the Attitude Input Select from Appendix E Table E 3.1.10 under the
Ident No. heading for Step (Category) 10 on Table E 3. This number will be used for
programming the configuration module
3. Using the Attitude Input Select ID number from Appendix E Table E 3.1.10 as “x”, go to
Appendix E Table E 3.1.10-x. The electrical interfaces (pin-outs) for the Attitude Input Select
Type are used to determine the wiring interconnects and record it on Appendix A Fig A1-3.
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3.3.10.3 Example
3.3.10.4 Analog Roll Angle (Synchro)
J1
EGPWS MK XXII
Vertical Gyro
X
X
1
Roll Angle
Roll Synchro
Y
Z
Y 21
Z
2
X
X
5
7
6
Pitch Angle
Pitch Synchro
Y
Z
Y
Z
Vendor Model
Attitude
Valid +28
P1-U
Pitch Synchro
Roll Synchro
V/G
X
Y
P1-B
P2-51
B
Z
P1-C
P2-52
C
X
P1-D
P2-42
D
Y
P1-E
P2-43
E
Z
P1-F
P2-44
F
Aeronetics RVG 801
Collins AHC-85( )
Collins 332D-11
Honeywell HG1075
Jet VG-208
P1-A
P2-50
A
P1-13
N
J1B-C9 J1B-C10 J1B-C11
J1B-D9 J1B-D10 J1B-D11
P1-U
HH
P1-A
X
P1-B
Y
P1-C
Z
P1-D
P
P1-E
Q
P1-F
R
King KVG-350
Litef LTR-81
MP-A11
Note 2
Note 3
P1-45
MP-B1
J3-11
X
MP-B2
J3-40
Y
MP-B3
J3-26
Z
MP-B4
J3-16
P
MP-B5
J3-39
Q
MP-B6
J3-25
R
Litef LCR-92& 93
Sperry VG-14A
Sperry VG-311
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.
Note 3: See airframe drawing.
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3.3.10.5 Digital ARINC 429 High Speed
Attitude Input ID 128 (Litef LCR 92S or equivalent) is a high speed, digital ARINC 429 signal
having roll pitch angle, and roll pitch rate labels 325, 324, 327, and 326.
J2
EGPWS MK XXII
AHRS
A
AHRS 429 A 23
HS
Roll Pitch
Angle
B
B
6
Vendor Model
AHRS
Litef LCR 92S
429 High Speed
B
A
P2-23
P2-6
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3.3.11 Category 11 – Heading Input Select
Category 11 defines the Magnetic Heading interface.
Appendix E Table E 3.1.11 defines the Heading Input Select types and identifies the first MK XXII
EGPWS version in which the option was available (see the Effectivity entry).
3.3.11.1 Instructions
1.
2.
3.
Using Appendix E Tables E 3, E 3.1.11 and E 3.1.11-x, select Heading Input 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 E 3.1.11
under the Ident No. heading for Step (Category) 11 on Table E 3. This number will be
used for programming the configuration module.
Using the Heading Input Select number from Appendix E Table E 3.1.11 as “x”, go to
Appendix E Table E 3.1.11-x. The electrical interfaces (pin-outs) for the Heading Input
Select Type are shown in Appendix E Table E 3.1.11-x are used to determine the wiring
interconnects and record it on Appendix A Fig A1-3.
3.3.11.2 Magnetic Heading
Magnetic Heading is used for Terrain Awareness alert and display and for Envelope Modulation.
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3.3.11.3 Example
3.3.11.3.1 Analog Heading (Synchro) (CAT. 11 ID 0)
J1
EGPWS MK XXII
Directional Gyro
X
X 22
Y 23
Heading
Y
Heading Synchro
3
Z
Z
H
H
C
4
24
26 VAC Reference
Heading Ref
C
Vendor Model
V/G
Heading Reference
Heading Synchro
Y
H
C
X
Z
Aeronetics Model 9100
P1-28
P1-6
P1-7
P2-57
P1-3
P1-8
P2-34
P1-25
P1-9
P2-35
P1-40
P1-10
P2-36
P1-24
Collins AHC-85( )
Collins DGS-65
Honeywell HG 1075
Honeywell KSG 105
Jet DN-104
P2-57
P1-6
P1-50
J1B-G2
P1-V
J1B-F13
P1-P
J1B-G13 J1B-E10 J1B-E11 J1B-E12
P1-d
P2-10
MP-B13
J3-20
P1-J
P1-Z
P2-1
P1-W
P2-2
P1-T
P2-3
P2-31
MP-E15
Note 2
P1-e
P2-9
Litef LTR-81
MP-B12
J3-05
P1-H
MP-B9
J3-13
P1-L
MP-B10
J3-42
P1-M
MP-B11
J3-28
P1-K
Litef LCR 92/LCR-93
Sperry C-14A
Sperry C-14D
P1-DD
P1-X
P1-Y
P1-AA
P1-BB
P1-Z
Sperry DG-234
P2-F
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.
Note 3: See airframe drawing.
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3.3.11.3.2 Digital ARINC 429 High Speed
Heading Input ID (Litef LCR 92S or equivalent) is a high speed, digital ARINC 429 signal having
roll angle, pitch angle, roll rate, pitch rate, and heading labels 320, 325, 324, 327, and 326.
J2
EGPWS MK XXII
AHRS
A
AHRS 429 A 23
HS
Heading
B
B
6
Vendor Model
AHRS
Litef LCR 92S
429 High Speed
B
A
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3.3.12 Category 12 – Windshear Input Select
Category 12 defines the Windshear interface.
Windshear is not applicable to MK XXII.
3.3.12.1 Instruction
Select ID 0 for all helicopter configurations.
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3.3.13 Category 13 – 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 E 3.1.13 defines the Input/Output discretes options and identifies the first MK
XXII EGPWS version in which the option was available (see the Effectivity entry).
3.3.13.1 Instruction
1. Using Appendix E Tables E 3, E 3.1.13, and E 3.1.13-x, select the Input/Output Discrete
Type number that matches the aircraft configuration, feature preferences and version (part
number) being installed.
Note: Helicopter I/O Discrete options are Types 128 or 129. The difference is the Output Lamp
format described below in section 3.3.13.3.1.
2. 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 E 3. This
number will be used for programming the configuration module.
3. Using the Input/Output Discrete Type number from Appendix E Table E 3.1.13 as “x”, the ICD
Table E 3.1.13-x. is used to determine the wiring interconnects, record it on Appendix A Fig
A1-1, A1-2, and A1-3.
Note: When there are two discrete pin choices for the same pin function in Appendix E Table E
3.1.13-x, use only the one that matches the aircraft wiring (use only the +28V and 0V or the
Ground and Open definitions).
3.3.13.2 Input/Output Discretes
Additional information for the discretes is provided below.
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3.3.13.3 Audio Inhibit Discrete
The Audio Inhibit discrete is an optional input 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):
-
a separately labeled guarded cockpit switch
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 this installation.
Discrete
Position / Status
Inhibit = +28V
Connector Pin
J1-36
Audio Inhibit +28
Not Inhibit = Gnd/Open
Honeywell does not recommend the use of this input for Helicopters.
3.3.13.4 Landing Gear 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.
Discrete
Position / Status
Down = +28V
Connector Pin
J1-35
Landing Gear +28
Not Down = Gnd/Open
Down = Gnd
Landing Gear Gnd
J1-16
Not Down = +28V /Open
For fixed gear or skid equipped aircraft this input is not required.
3.3.13.5 Weight ON Wheels (WOW) Discrete
The Weight on Wheels (WOW) discrete is supplied by the WOW system in the aircraft.
Connection can be made to the actual OLEO switch or relay logic later in the aircraft wiring.
For aircraft without WOW indication such as those with fixed gear or skids, this input discrete is
not required.
Discrete
Position / Status
On Ground = +28V
In Air = Gnd/Open
On Ground = Gnd
In Air = +28V /Open
Connector Pin
J1-37
WOW +28
WOW Gnd
J1-18
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NOTE: The logic sense of the WOW discrete can be reversed by selecting the WOW eversal
option in Category 7, see section 3.3.7.
3.3.13.6 Glideslope Cancel Discrete
The Glideslope Cancel discrete provides the crew with the capability to manually cancel Mode 5
for an approach. This 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
Cancel = Gnd
Normal = Open
Connector Pin
J1-15
Glideslope Cancel
3.3.13.7 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.
Discrete
Position / Status
Low Volume = Gnd
Connector Pin
J1-13
Mode 6 Low Volume
Not Low Volume = Open
3.3.13.8 Autopilot Engaged Discrete
For helicopters this discrete is currently not used.
Discrete
Position / Status
Connector Pin
J1-8
Autopilot Engaged
Engaged = +28V
Not Engaged = Open
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3.3.13.9 Terrain Awareness Inhibit
The Terrain Awareness inhibit discrete, inhibits the Terrain Awareness modes in the MK XXII
EGPWS.
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
Inhibit = Gnd
Connector Pin
J1-12
TA Inhibit
Not Inhibit = Open
3.3.13.10 Self Test Discrete
The cockpit Self Test discrete is provided to manually initiate test of the EGPWC, EGPWS aircraft
interface, and to annunciate 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
Self Test
Position / Status
Self Test = Gnd
Normal = Open
Connector Pin
J1-34
3.3.13.11 Glideslope Inhibit Discrete
The Glideslope Inhibit Discrete, also known as the Backcourse Inhibit, provides an inhibit to the
Glideslope alert when on a backcourse approach.
The Glideslope Inhibit is usually connected to the Flight Director or FMS backcourse discrete
output.
Discrete
Position / Status
Inhibit = +28V
Connector Pin
J1-38
Glideslope Inhibit +28
Not Inhibit = Gnd/Open
Inhibit = Gnd
Glideslope Inhibit Gnd
J1-19
Not Inhibit = +28V /Open
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3.3.13.12 Timed Audio Inhibit Discrete
The Timed Audio Inhibit will cause the inhibiting of all audio messages for a period of 5 minutes
or until reset. The discrete input is connected to a momentary lighted switch. When pressed the
condition is latched in memory and will be reset after 5 minutes have elapsed or pressing the
switch again or when landing. The switch lighting, indicating the Audio is Inhibited is driven by a
discrete output described below.
Discrete
Position / Status
Momentary Toggle = Gnd
Normal = Open
Connector Pin
J1-17
Timed Audio Inhibit
NOTE: Either the Timed Audio Inhibit or the Terrain Inhibit should be used depending on the
aircraft operations. See discussion is section 1.
3.3.13.13 Low Altitude Mode Select Discrete
The Low Altitude Mode select is a required input and is used for cruise operation below 500 feet
AGL and for operation in high density metropolitan environments such as tall buildings. When
selected, the Low Altitude Mode inhibits Excessive Terrain Closure (Mode 2) warnings, retards
the Terrain Clearance warnings (Mode 4), and reduces the Terrain look ahead distances and
width. When selected, Low Altitude Mode may be de-selected by pressing the switch again.
The Low Altitude select switch is a lighted momentary switch where the selected condition lighting
is driven by an output discrete described below.
3.3.13.14 Output Discretes
The discrete outputs are defined in Appendix E Section 7.4. The MK XXII 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 (Terrain Display Select,
etc.) of the EGPWS.
Short-term current limit protection is provided on all drivers for output shorting conditions. Ground
going output discretes may be connected together to produce a ‘wired OR’ function for the active
low state of the outputs. If output discretes are ‘wire OR’d’ then diodes must be installed for
isolation.
3.3.13.15 Lamp Format
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.
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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 “EGPWS” lamp is driven by the GPWS Warning (Pull Up,
Warning Terrain, and Warning Obstacle only) discrete and the amber “EGPWS” lamp is driven by
the remaining alerts and warnings.
3.3.13.16 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.
3.3.13.17 TAD INOP Discrete
The TAD INOP discrete (J1-55) indicates, Terrain Awareness (TA), and Terrain Display are ‘Not
Available’. This feature activates a ‘TERRAIN INOP” lamp located in the cockpit within sight of the
pilots.
3.3.13.18 GPWS Warning 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, and 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.
3.3.13.19 GPWS Alert 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” red lamp located in the cockpit within sight of each pilot.
3.3.13.20 Glideslope Cancel Discrete
-Optional- Glideslope Cancel 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 CAN” amber lamp located in the cockpit within sight of the pilots.
3.3.13.21 TCAS Inhibit Discrete
-Optional- TCAS Inhibit discrete (J1-69) will activate during any EGPWS voice annunciation. This
output is used to inhibit TCAS from talking during EGPWS annunciation. This feature does not
have a lamp associated with it.
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3.3.13.22 Terrain Display 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.
3.3.13.23 Timed Audio Inhibit Discrete
The Timed Audio Inhibit discrete (J1-52) will activate after a Timed Audio Inhibit switch
(momentary) is pressed in the cockpit. The discrete will stay active until the Timed Audio Inhibit
latch resets after 5 minutes or the switch is pressed again or the aircraft lands. The discrete is
used to light the ON status portion of the Timed Audio Inhibit lighted switch assembly.
3.3.13.24 Low Altitude Mode Discrete
The Low Altitude Mode discrete (J1-73) will activate after a Low Alt switch (momentary) is
pressed in the cockpit. The discrete is used to light the ON status portion of the Low Altitude
lighted switch assembly. The discrete will stay active as long as the Low Altitude Mode is
selected. The Low Altitude Mode may be de-selected by pressing the Low Alt switch again.
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Table 0-1 MKXXII EGPWS – Example Cockpit Lights
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3.3.14 Category 14 – 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 E 3.1.14 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).
3.3.14.1 Instructions
1. Using Appendix E Tables E 3 and E 3.1.14 as described above, select the Audio Output
Level ID number that matches the feature preferences and version (part number) being
installed.
2. Record the ID number for the Audio Output Level from Appendix E Table E 3.1.14 under the
Ident No. heading for Step (Category) 14 in Appendix E Table E 3.
The Nominal Volume Select is equivalent to MK XXII 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.
H
L
J1-70
J1-71
High level audio
Low level audio
8 ohm
600 ohm
Audio
Panel
H
L
J1-75
J1-74
FIGURE 3.16-1 Audio Interface
Note: Because most helicopters use a full muff headset, cockpit speakers are not applicable.
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3.3.15 Category 15, Autorotation Threshold
Category 15 controls the Autorotation Threshold level used for Autorotation detection. Actual
thresholds are determined during first of type flight. The thresholds are found in Table 3.1.15-1-1
below.
Appendix E Table E 3.1.15 defines the Autorotation threshold options.
3.3.15.1 Instruction
1.
2.
Using Table 3.1.15-1-1 below and Appendix E Tables E 3 and E 3.1.15 as described
above, select the Autorotation threshold torque ID number that was determined during
flight test.
Record the ID number for the Autorotation threshold torque Level from Table 3.1.15-1 or
Table 3.1.15-1 below under the Ident No. heading for Step (Category) 15 in Appendix E
Table E 3.
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AUTOROTATION THRESHOLD
Aircraft Type ID
Aircraft Model
S-76 B/C+
Threshold %
Threshold ID
128
129
130
131
131
132
133
133
134
135
136
137
138
139
140
141
142
143
144
145
7.5
7.5
7.5
6
15
15
15
12
12
15
15
15
S-76C/A++
S-76A/A+
Bell 212
Bell 412
EC-155B
MD900
6
7.5
7.5
7.5
MD902
AS 365N3
7.5
15
12
Bell 412, DC Torque
6
Table 3.1.15-1: Autorotation Thereshold
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SECTION IV
CONFIGURATION MODULE PROGRAMMING
AND
REGIONAL TERRAIN DATABASE LOADING
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SECTION IV – CONFIGURATION MODULE PROGRAMMING AND
REGIONAL TERRAIN DATABASE LOADING
SECTION IV – CONFIGURATION MODULE PROGRAMMING AND REGIONAL TERRAIN
DATABASE LOADING.................................................................................................................109
4.1 INTRODUCTION.................................................................................................................................. 109
4.2 HARNESS CHECKOUT AND POWER CHECK ........................................................................................ 109
4.3 UNIT INSTALLATION.......................................................................................................................... 109
4.4 EGPWC INITIALIZATION AND CONFIGURATION ............................................................................... 109
4.4.1 RS-232 Communication with the MK XXII EGPWS.................................................................. 109
4.4.2 EGPWC Front Panel Test Connector........................................................................................ 110
4.4.3 WinVIEWS ................................................................................................................................. 110
4.4.4 WinVIEWS Operation................................................................................................................ 111
4.5 CONFIGURATION MODULE PROGRAMMING ....................................................................................... 111
4.5.1 CUW and CMR Commands ....................................................................................................... 113
4.5.2 Configuration Module Reprogramming..................................................................................... 114
4.6 REGIONAL TERRAIN DATABASE LOADING ........................................................................................ 115
4.6.1 Effectivity................................................................................................................................... 115
4.6.2 Description ................................................................................................................................ 115
4.6.3 Approval .................................................................................................................................... 115
4.6.4 Material – Cost and Availability................................................................................................ 116
4.6.5 Accomplishment Instructions..................................................................................................... 117
4.6.6 Verification of the Terrain Database Version............................................................................ 118
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SECTION IV – CONFIGURATION MODULE PROGRAMMING AND
REGIONAL TERRAIN DATABASE LOADING
4.1 Introduction
The following procedures outline the steps necessary to accomplish a complete configuration of
the MK XXII 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 XXII EGPWS
that will be operating outside of the North American region.
4.2 Harness Checkout 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 Installation
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 Initialization and Configuration
The first time a MK XXII 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 Communication with the MK XXII EGPWS
The MK XXII EGPWS computer contains software that allows monitoring of its internal
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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
4.4.2 EGPWC Front 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)
Standard (PC)* DB9 Connector
Pin 3
Pin 3
Pin 4
Pin 2
Pin 1
Pin 5
*NOTE: Some PC Comm Ports have Pins 2 & 3 reversed from what is described above.
Connector, AMP 748364-1
Pin Contact, 204370-2, QTY 4
Backshell, AMP 745854-5
Jackscrew, AMP 747784-3
Grommet Set, AMP 747746-1
P3
Connector, AMP 205161-1
Socket Contact, AMP 205090-1, QTY 3
PCOM
3
2
5
3
4
1
Length as required (5’ to 50’)
12
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.
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To obtain a copy of the WinVIEWS software, contact:
Honeywell
Honeywell
or
Aerospace Electronic Systems
PO Box 97001
Aerospace Electronic Systems
PO Box 97001
Redmond, WA 98073-9701 USA
Attn: Order Administration M/S 33
Phone: (425) 885-8719
Redmond, WA 98073-9701 USA
Attn: EGPWS Applications Engineering
Phone: (425) 885-3711
FAX:
(425) 885-8988
FAX:
(425) 885-2994
GPWS Hotline: (800) 813-2099
WinVIEWS can be sent via e-mail when an e-mail address is provided or downloaded from the
web (www.egpws.com)
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 Configuration 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.
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:
CUW 0/15 # # # # # # # # # # # # # # #/
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-
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 14 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, pressing ENTER the cursor will flash 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.
Note: Using Kermit or a similar terminal emulator pressing ENTER results in a question:
“Confirm this data reflects configuration to be programmed (Y/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
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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.
4.5.1 CUW and CMR Commands
An example CUW command/data string, its definition, and the corresponding CWR list is provided
below.
CUW command/data string:
CFG > CUW 0/15 128 3 2 134 128 3 29 1 0 2 0 0 129 0 15/
Above configuration defined:
Category 1 Aircraft/Mode Type:
Category 2 Air Data Type:
128
3
Category 3 Position Type:
2
Category 4 Altitude Callouts Menu:
Category 5 Audio Menu:
Category 6 Display Type:
134
128
3
(All Callouts)
(Basic menu)
Category 7 Options Select Group #1:
29
(TA&D Alternate pop-up False)
(Peaks Mode True)
(Obstacle Awareness True)
(Bank Angle True)
(Weight on Wheels Reversal)
(GPS Altitude Ref. MSL)
Category 8 Radio Altitude Type:
Category 9 Navigation Type:
1
0
Category 10 Attitude Type:
2
Category 11 Heading Type:
0
Category 12 Windshear select Type:
Category 13 Discrete I/O Type:
Category 14 Audio Output Level Type:
Category 15 Autorotation Threshold
0
129
0
15
CWR list: (based on the above configuration)
CFG > CMR<Enter>
CONFIGURATION MODULE:
Format Version:
Category 1 ID:
Category 2 ID:
Category 3 ID:
Category 4 ID:
Category 5 ID:
Category 6 ID:
0
128
3
2
134
128
3
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Category 7 ID:
Category 8 ID:
Category 9 ID:
Category 10 ID:
Category 11 ID:
Category 12 ID:
Category 13 ID:
Category 14 ID:
Category 15 ID:
CRC:
29
1
0
2
0
0
129
0
15
527518533
4.5.2 Configuration 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 XXII Installation Manual (Appendix E), document number 060-4314-225.
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” to restart the
Configuration sub-mode. At the CFG > prompt, type “CMR<Enter>”. Each category and its
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associated ID is read from the Configuration Module and listed on the PC display. Alternately,
when not in the Configuration sub-mode, the command “PS<Enter>” (Present Status) will
display the EGPWC and Configuration Module data.
7. Configuration Module reprogramming is complete.
4.6 Regional Terrain Database Loading
4.6.1 Effectivity
The MK XXII EGPWS (965-1590-0XX) are shipped from the factory with the North American
Regional Terrain Database installed. Aircraft operating outside of the North American region will
have to load one of the other eight Regional Terrain Databases before beginning the ground test.
Use (operation) of a MK XXII EGPWS outside of the loaded Regional Terrain Database will result
in the Terrain Awareness function being unavailable.
4.6.2 Description
This modification consists of loading the PCMCIA card into the EGPWS either In The Aircraft or
On The Bench. An optional verification procedure is provided.
4.6.3 Approval
This procedure contains no modification information that revises the approved configuration and
therefore does not require FAA or other regulatory agency approval.
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4.6.4 Material – Cost and Availability
The Regional Terrain Database PCMCIA card is available at no charge to Operators that will be
operating outside of the North America region. Order part from:
Honeywell
Honeywell Aerospace
Toulouse Office
Centreda, Avenue Didier Daurat
31700 Blagnac, France
Airlines & Avionics Products
Order Administration M/S 33
PO Box 97001
Redmond, WA 98073-9701
Phone:
Fax:
(33) 5-6171-0079
(33) 5-6130-0497
Phone:
Fax:
425-885-8719
425-885-8988
Vendor Name
Honeywell
Honeywell
Honeywell
Honeywell
Honeywell
Honeywell
Honeywell
Honeywell
Vendor P/N
424NAM
424 SAM
424EUR
424EEU
424AFR
424PAC
424SPA
424MES
Description
QTY UM
Honeywell P/N
718-1447-XXX
718-1448-XXX
718-1449-XXX
718-1450-XXX
718-1451-XXX
718-1452-XXX
718-1457-XXX
718-1458-XXX
North America
South America
Europe
1
1
1
1
1
1
1
1
EA
EA
EA
EA
EA
EA
EA
EA
Eastern Europe
Africa
Pacific
South Pacific
Middle East
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4.6.5 Accomplishment Instructions
Load the PCMCIA card data as described in paragraphs 4.6.5 A. or 4.6.5 B. below. Loading time
will be approximately 70 minutes.
A. Loading the PCMCIA Card Data with the Computer mounted in the Aircraft.
(1) Connect the Smart Cable (Honeywell PN 951-0386-001) to the EGPWC J3
connector.
(2) Ensure that the 28 VDC circuit breaker to the EGPWC is ON and that the
COMPUTER OK LED on the EGPWC front panel is on.
(3) Insert the PCMCIA card into the Smart Cable PCMCIA card slot.
NOTE: Precautionary notes on the PCMCIA card, regarding insertion and/or removal
while power is applied, should be ignored since the EGPWC automatically
handles the application and removal of PCMCIA card power.
(4) While the loading is in progress, the IN PROG LED on the Smart Card remains ON
and the COMPUTER OK LED on the EGPWC is OFF.
(5) When loading is complete the XFER COMP LED on the Smart Card turns ON.
(6) Remove the PCMCIA card from the Smart Card slot.
(7) After approximately 15 seconds the COMPUTER OK LED comes ON to indicate that
the contents of the PCMCIA card were successfully transferred.
(8) Remove the Smart Card connector from the EGPWC front panel J3 connector.
(9) To perform the verification of the Terrain Database version, go to paragraph 4.6.6
below.
B. Loading the PCMCIA Card Data with the Computer removed from aircraft
(1) Locate a 28 VDC Power Supply with a minimum supply current of 2 amps.
(2) With the Power Supply turned OFF, connect the Power Supply to the J1 connector of
the EGPWC as follows:
J1 connector Pin
J1-40, J1-60
J1-41, J1-61
J1-42, J1-53
Pin Nomenclature
28 VDC (+)
28 VDC (-)
Chassis GND
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(3) Connect the Smart Cable (Honeywell PN 951-0386-001) to the EGPWC J3
connector.
(4) Turn the Power Supply ON and verify the COMPUTER OK LED on front of the
EGPWC panel is on.
(5) Insert the PCMCIA card into the Smart Cable PCMCIA card slot.
NOTE: Precautionary notes on the PCMCIA card, regarding insertion and/or removal
while power is applied, should be ignored since the EGPWC automatically
handles the application and removal of PCMCIA card power.
(6) While the loading is in progress, the IN PROG LED on the Smart Card remains ON
and the COMPUTER OK LED on the EGPWC remains OFF.
(7) When loading is complete the XFER COMP LED on the Smart Card turns ON.
(8) Remove the PCMCIA card from the Smart Card slot.
(9) After approximately 15 seconds the COMPUTER OK LED comes ON to indicate that
the contents of the PCMCIA card were successfully transferred.
(10)Remove the Smart Card connector from the EGPWC front panel J3 connector.
(11)To perform the verification of the Terrain Database version, go to paragraph 4.6.6
below.
4.6.6 Verification of the Terrain Database Version
Since the EGPWC software verifies the PCMCIA card loading process, this verification is to
assure the operator/installer that the correct Regional Terrain Database version is installed.
Terrain Database version verification is accomplished with the EGPWS Self Test (ST) function.
The ST function may be initiated from the aircraft cockpit with the GPWS Test Switch. NOTE:
Initiation of the cockpit ST function may vary from one aircraft to another. For example, the ST
function may be initiated by pressing the GPWS (PULL-UP) light assembly, or by activating a
separate ST switch.
The EGPWS ST function has 6 levels that describe the current condition and configuration of the
EGPWS, the fault and warning history, and the condition of the various inputs. To help navigate
through the various levels, there are 2 cancel functions: SHORT CANCEL (press and hold the ST
button for more than 0.5 seconds, but less than 2 seconds) and LONG CANCEL (press and hold
the ST button for more than 2 seconds, but less than 8 seconds). The Short Cancel and Long
Cancel functions operate differently, depending upon the ST level. To initiate a ST sequence, or
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to continue from level-to-level, the ST button must also be ‘pressed and held’ for more than 0.5
seconds, but less than 2 seconds, which is identical to the Short Cancel function.
Therefore, for simplicity, the phrase “Press ST Button” in the verification procedure means to
press and hold the ST button for more than 0.5 seconds, but less than 2 seconds. The procedure
guides the operator directly to ST Level 3, “System Configuration”, skipping most of ST Level 1
and Level 2.
To verify the Regional Terrain Database that was just loaded into the EGPWC, perform these
steps:
NOTE: ‘On the Bench’, this test requires an audio speaker and a self test button.
(1) Ensure the EGPWC power is ON
(2) Press ST button to initiate ST Level 1.
(3) After ST Level 1 message starts, Press ST button to cancel Level 1 and start Level 2.
(4) After ST Level 2 message, “Current Faults”, is heard, Press ST button to cancel Level 2.
(5) When the message, “Press to Continue”, is heard, Press ST button to start ST Level 3.
(6) Verify the Terrain Database version annunciated in the following sequence:
a) “SYSTEM CONFIGURATION”
b) “PART NUMBER 965-1590-XXX”
c) “MOD STATUS XX”
d) “SERIAL NUMBER XXXX”
e) “APPLICATION SOFTWARE VERSION XXXXX”
f) “TERRAIN DATABASE VERSION XXXX”
The following example of Terrain Database Version annunciation: “424NAM” (for
NORTH AMERICA), “424EUR” (for EUROPE), or “424PAC” (for PACIFIC). Other
versions will follow the same pattern.
(7) Other messages that follow the Terrain Database Version can be ignored. When ST
Level 3 finishes, the message “Press to Continue” is heard. If the ST button is not
pressed again the ST sequence terminates.
NOTE: If power was connected to the EGPWC per steps B1 through B4, perform shut-down per
steps (7) and (8) following.
(8) Turn Power Supply OFF.
(9) Disconnect Power leads from the EGPWC.
END OF TEST
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SECTION V
CERTIFICATION
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SECTION V – CERTIFICATION 124
5.1 INTRODUCTION ................................................................................................................................. 124
5.2 CERTIFICATION PROCEDURE ............................................................................................................. 124
5.2.2 Equipment Location .................................................................................................................. 124
5.2.3 FAA Requirements .................................................................................................................... 124
5.2.4 Ground Test .............................................................................................................................. 124
5.2.5 Flight Manual Revision ............................................................................................................ 124
5.2.6 Flight Test ................................................................................................................................. 125
5.2.7 Pilots Guide .............................................................................................................................. 125
5.2.8 Failure Modes, Effects, and Safety Analysis ............................................................................. 125
5.2.9 Existing STC’s .......................................................................................................................... 125
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SECTION V – CERTIFICATION
5.1 Introduction
This section outlines the procedures required to obtain FAA approval for the MK XXII EGPWS
installation.
5.2 Certification Procedure
5.2.1.1 Equipment Compatibility
Careful consideration must be paid to the electrical characteristics of existing equipment or
possible additions that will be interfaced to the MK XXII EGPWS, in order to ensure system
compatibility. Section III of this manual provides system-planning guidelines, and defines the
electrical characteristics of the EGPWS. The installing agency should contact Honeywell
Product Support (800-813-2099), for information regarding the compatibility of equipment
not listed in Section III or interface into any airframe not listed in Appendix E Table E 3.1.1.
Normal business hours are 8:00 AM to 5:00 PM Pacific Time, Monday through Friday.
5.2.2 Equipment Location
The EGPWS and associated indicators, annunciators, and switches should be clearly visible and
within easy reach of the pilot(s). Refer to Section II of this manual for complete installation
information.
5.2.3 FAA Requirements
The installing agency should contact a local FAA Inspector who will determine whether the
installation may be approved by Supplemental Type Certificate (STC) or by submitting FAA Form
337 with an applicable STC package.
5.2.4 Ground Test
Honeywell has developed a generic Installation Ground Test Procedure for the MK XXII EGPWS,
drawing number 060-4167-167.
5.2.5 Flight Manual Revision
Honeywell has developed a generic Rotorwing Flight Manual Supplement for the MK XXII
EGPWS, drawing number 060-4314-009.
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5.2.6 Flight Test
Honeywell has developed a generic Flight Test procedure for the MK XXII EGPWS, drawing
number 060-4314-006. The Flight Test procedure was developed for first of type installations, for
these installations all sections of the Flight Test procedure shall be performed.
For follow on installations of the same aircraft type and interface, the flight test is not required.
When updating an STC to the current part number it is only necessary to flight test significant new
features. The notice of change is available in Honeywell Service Bulletins.
5.2.7 Pilots Guide
Honeywell has developed a Pilot’s Guide for the MK XXII EGPWS, drawing number 060-4314-
200 that provides a description of the modes and the controls of the EGPWS.
5.2.8 Failure Modes, Effects, and Safety Analysis
Honeywell has developed a Failure Modes, Effects, and Safety Analysis document for the MK
XXII EGPWS, drawing number 060-4314-002 that provides an analysis of the failure modes of
the EGPWS.
5.2.9 Existing STC’s
For more information and a list of existing STC’s see the EGPWS web site www.egpws.com
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APPENDIX A
CUSTOMER WORKSHEET
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APPENDIX B
SAMPLE WIRING DIAGRAMS
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APPENDIX C
WinViews OPERATION INSTRUCTIONS
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APPENDIX C – WinViews Operation Instructions
RS-232 COMMUNICATION WITH THE EGPWS
The EGPWS contains software that allows monitoring of its internal parameters, for testing
purposes, without altering its operation. The monitoring of these parameter values enables the
operator to quickly determine if the correct signal and scaling is being used by the EGPWS
computer. The communication link utilizes the RS-232 Communication Protocol configured as
follows:
19200 Baud, No Parity, 8 bits, and 1 stop bit.
The RS-232 interface with the EGPWS is accomplished via the J3 test connector on the front of
the EGPWS. The connection between a PC (with a standard DB9 serial port connector) and the
EGPWS RS-232 interface is defined as follows: (Please note that the EGPWS will activate its RS-
232 port only when it receives the command CONTROL Z after power is applied to the EGPWS.
The CONTROL Z command is automatically sent by WinVIEWS)
RS-232 Receive RS-232 Transmit RS-232 Ground
EGPWS Front Connector
Pin 3
Pin 4
Pin 2
Pin 1
Pin 5
Standard DB9 Connector (for a PC)* Pin 3
*NOTE:Some PC Comm Ports have Pins 2 & 3 reversed from what is described above.
The mating connector for the EGPWS J3 test connector is a male (pins) 15 pin double density D-
subminiature type, Positronics Industries (kit) part number ODD15M1OYOZ or the following
individual parts:
Nomenclature (AMP)
Amp Part Number Military Part Number
Connector Shell (HDP-22 Crimp Snap In Contact)
Size 22 DM Crimp Snap In Contacts Pin 0.030
Backshell (Shielded Cable Clamp Assembly)
Jackscrews, 2 required (4-40 Male Jackscrew Kit)
Grommet Sets
748364-1
204370-2
745854-5
747784-8
747746-1
reference MIL-C-24308
M39029/58-360
The following tools will work with Positronics, Amp, and Mil Spec Connectors:
Insertion / Extraction Tool
Hand Crimp Tool
Positioner
91067-1
M81969/1-04
M22520/2-01
M22520/2-09
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MK XXII Installation Manual
WinVIEWS OPERATION:
Windows Virtual Interface to the Enhanced Warning System
WinVIEWS software is a tool developed by Honeywell to monitor or view values within the EGPWS.
The WinVIEWS software provides a monitor function that does not alter the operation of the EGPWS.
The monitoring of values assists in the installation testing of the EGPWS by allowing the operator to
quickly determine if the correct signal and scaling is being used by the EGPWS. Additionally,
WinVIEWS provides a detailed status of the software configuration and input signals which enables
quick identification of system anomalies.
WinVIEWS software can be ordered as Honeywell part number 998-2846-500. A User’s Guide to
WinVIEWS is available as Honeywell document number 998-2846-600. The software consists of the
WinVIEWS executable file, a help file, and sample command files.
The command file is a simple text file that should include each CVT Item used in this test procedure.
A sample command file for this test procedure is found on the following page. The file must be a
‘Text Only’ type of file, such as those created in the Microsoft Windows Note Pad program. It should
have a filename extension of .CMD. Once this file is loaded, WinVIEWS can automatically display
the current value of each parameter listed in the file.
Normal Operation for Ground Testing the EGPWS:
STEP 1 - Connect the PC to the EGPWS via the RS-232 cable as defined above.
STEP 2 - On the PC, start Windows 3.1, or higher.
STEP 3 - Start the WinVIEWS program.
STEP 4 - Under the File Menu select the “Load Command File” option and load the appropriate
Command File.
STEP 5 - Use F6 to select Data Display Mode. Each CVT Item listed in the Command File will
be continuously updated at a rate of greater than once per second. The values
shown for the CVT Items listed will be the test values.
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Command File: MK XXII_GTP.CMD
The format for the WinVIEWS command file is:
1. ASCII Text Only; no spaces
2. A CVT Item as specified in the test procedure
3. Each CVT Item Name is followed by a <return> or <enter>
RawRA1
ARA1Val
VF
V
DHDsc
V
RawBAlt1
RawBaroRt1
RawCAS1
RawSAT1
ILSTuned1
GnILSTuned1
VF
VF
VF
VF
V
V
RawAACGS1 VF
AGS1Val
V
GPSLatude1 VF
GPSLngude1 VF
RawGLat1
RawGLng1
RawGAlt1
RawVFOM1
RawHFOM1
VF
VF
VF
VF
VF
RawGGSpd1 VF
RawHil1
VF
VF
VF
VF
V
RawGTTk1
RawRoll1
RawPitch1
AnAtt1Val
RawAACMHD VF
AACMHDVal
WOWDsc
LandGrDsc
GSCan
V
V
V
V
AudInhDsc
M6LwVolDsc
GSInh
V
V
V
GSlnhDsc
TAWxRng1
TAWxRng2
TerrDis
V
VF
VF
V
AnaTerrDis
V
RawTorque1 VF
RawTorque2 VF
TacticalSel
TAInop
V
C
TAInop1
C
TAInop2
C
EngTorque1
EngTorque2
DispRngOut1
DispRngOut2
VF
VF
V
V
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MK XXII EGPWS Installation Manual
APPENDIX D
VENDOR DRAWINGS
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D 1-0 Vendor Contact Information
The vendor contact information provided below is current at the time of publication of this
document.
AMP
2800 Fulling Mill Road
MS 038-035
Middletown, PA 17507
800 806-0480
Barry Controls
Burbank, CA
818 843-1000
United Kingdom:
Surrey, England
44 (0932) 22-4122
Brighton, MA
616 787-1555
Germany:
Raunheim, Germany
49 (6142) 43077/8/9
EDMO
5505 E. Rutter Ave.
Spokane, WA 99212
www.edmo.com
1 800 235-3300
Electronic Cable Specialists 5300 W Franklin Drive
and Electrical Conservation
Systems, Inc.
Franklin, WI 53132-8642
414 421-5300
EMTEQ, Inc.
S84 W18693 Enterprise Drive
Muskego, WI 53150
(888) 679-6170
(262) 679-6170
(262) 679-6175 Fax
e-mail: [email protected]
Hollingsead International
IDD Aerospace
Sante Fe Springs, CA
213 921-3436
Redmond, WA
425 885-4353
ITT Cannon
Santa Ana, CA
714 557-4700
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MK XXII EGPWS Installation Manual
Korry Electronics
901 Dexter Avenue North Seattle,
WA
Attention: Airline Sales
206 281-1300
800 257- 8921
For orders and AOG requirements, contact:
Sonya Cordova
206 281-3567
email: [email protected]
fax: 206 281-3576
SITA: SEAKEXD
For engineering inquiries, contact:
Bob Jacques
Tom Howard
Airline Business Manager
206 281-3584
Airline Business Manager
206 281-1458
email: [email protected]
fax: 206 273-4128
email: [email protected]
fax: 206 273-4128
Master Specialties Co.
Optima Wire
Costa Mesa, CA
714 642-2427
1120 Harpeth Industrial Ct.
Franklin, TN 37064
615 599-3770
Cathy Harper
PIC Wire & Cable Supply
N63 W22619 Main Street
P.O. Box 330
Sussex, WI 53089-0330
414 246-0500
Fax: 414 246-0450
Sensor Systems, Inc.
StacoSwitch
8929 Fullbright Avenue
Chatsworth, CA 91311
818 341-5366
Fax: 818 341-9059
1139 Baker Street
Dan Sugg
Costa Mesa, CA 92626-4191
www.stacoswitch.com
714-549-3041
Also contact EDMO – Avionics
Distributor for StacoSwitch
Fax: 714-549-0930
West Coast Specialties
P.O. Box 5010
Preston, WA 98050
425 222-3118
Fax: 425-222-3119
Contact:
Bruce Maxwell, (Rep)
206-232-2871
Fax: 206-232-3174
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D1-1
EDMO
EDMO Distributors (800)235-3300 – “One Stop Shopping” for the following EGPWS
and TAWS support products:
* MD41-12XX/13XX TAWS ACU’s from Mid-Continent Instruments
* 90-44802-1 PMA’d TAWS ACU from West Coast Specialties
* Eaton and StacoSwitch EGPWS split switch & annunciator kits
* Shadin XYZ compass to RS-232/422 Converters
* Shadin low cost Airdata computers
* Solid State Altitude Encoders (most models)
* GAE-1575 GPS Repeater for hangar testing
* Installation Supplies
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D1-2
EMTEQ
EMTEQ, Inc. supports all EGPWS/TAWS systems manufactured by Honeywell, Inc. by offering
products to help complete your installation. The installation provisions are fully compliant with
ARINC specifications and standards.
We have a full understanding of the system requirements for coaxial components, wire
harnesses, Switchpanels and mounting accessories.
♦
♦
Fully certified and tested RF cable sets for GPS
Bulk coax cable (cut to length) and the necessary coax connectors to complete the
installation on your own
♦
♦
♦
♦
Avionics Trays
Switchpanel and mounting hardware
ARINC Rack Connectors, Circular Connectors, etc
Wire harnesses
GPS - RF Cable Sets
EMTEQ performs the critical electrical testing for GPS cables using a Hewlett Packard 8753D
Vector Network Analyzer. The state of the art equipment stores all profiles at the exact time the
cables were tested. Comprehensive reports are supplied on all cable assemblies manufactured.
Individual assemblies can be matched electrically to an original set of cables when necessary due
to the assignment of unique serial numbers on all cable units.
EMTEQ offers a unique option in the marketplace with a choice in two families of RF cable types
to meet your specifications and budget. We offer Teflon ® (TFLX series) and PE (PFLX series)
cables as shown in Table 1 (Table 1.A. Teflon ®; Table 1.B. Polyethylene (PE)) . Both types are
Skydrol resistant, meet or exceed MIL-C-17, and meet or exceed FAA Flammability requirements.
The characteristics of each option give you the choice that fits your requirements. Pricing will
differ between the two options, so please call us to discuss your particular project requirements.
This phone call may give you the competitive edge required to win your bid. We have this
outcome in mind when we offered options to our customers.
For each option, EMTEQ offers connectors to meet the system requirements. Connectors for
PFLX and TFLX cable types are listed in Table 2.
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TABLE 1
Table 1.A. (Teflon ® Jacketed RF Coax) (High Temp)
Cable Type
Loss @ 1600 Mhz
Per 100 ft
21.60 dB
O.D.
(inches)
0.130 “
0.161”
Bend Radius
Minimum
½”
P/N
TFLX130-100
TFLX165-100
TFLX205-100
TFLX295-100
TFLX480-100
17.00 dB
1 ¾”
13.90 dB
0.195 “
0.205 “
0.480 “
1 ¾”
7.60 dB
3.0 “
4.75 dB
2.40 “
Table 1.B. (PE – Polyethylene Jacketed RF Coax) (85 C temp)
Cable Type
P/N
Loss @ 1600 Mhz
Per 100 ft
14.00 dB
O.D.
(inches)
0.195 “
0.242 “
0.340 “
0.500 “
Bend Radius
Minimum
PFLX195-500
PFLX240-500
PFLX340-500
PFLX500-500
½”
¾”
11.00dB
7.59 dB
1”
4.27 dB
1 ¼”
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TABLE 2
Table 2.A.1 Connectors (for TFLX cable series) - GPS
GPS
Connector
Type
Application
Description
TFLX130-100
TFLX165-100
TFLX205-100
TNC male
TNC male
TNC female
C male
Antenna
Antenna
Disconnects
Antenna
Antenna
Straight
TMS130-1
TMR130-1
TFS130- 2
CMS130-1
CMR130-1
TMS165-1
TMR165-1
TFS165-2
CMS165-1
CMR165-1
TMS205-1
TMR205-1
TFS205-2
CMS205-1
CMR205-1
Right Angle
Bulkhead Straight
Straight
C male
Right Angle
GPS
Connector
Type
Application
Description
TFLX295-100
TFLX480-100
TNC male
TNC male
TNC female
C male
Antenna
Antenna
Straight
TMS295-1
TMR295-1
TFS295-2
CMS295-1
CMR295-1
TMS488-1
TMR488-1
TFS488-2
CMS488-1
CMR488-1
Right Angle
Bulkhead Straight
Straight
Disconnects
Antenna
C male
Antenna
Right Angle
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TABLE 2 (continued)
Table 2.B.1 Connectors (for PFLX cable series) – GPS
GPS
Connector
Type
Application
Description
PFLX195-500
PFLX240-500
PFLX340-500
TNC male
TNC male
TNC female
C male
Antenna
Antenna
Disconnects
Antenna
Antenna
Straight
TMS195-1
TMR195-1
TFS195-2
CMS195-1
CMR195-1
TMS240-1
TMR240-1
TFS240-2
CMS240-1
CMR240-1
TMS340-1
TMR340-1
TFS340-2
CMS340-1
CMR340-1
Right Angle
Bulkhead Straight
Straight
C male
Right Angle
GPS
Connector
Type
Application
Description
PFLX500-500
TNC male
TNC male
TNC female
C male
Antenna
Straight
TMS500-1
TMR500-1
TFS500-2
N/A
Antenna
Right Angle
Bulkhead Straight
Straight
Disconnects
Antenna
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MK XXII EGPWS Installation Manual
Tool Frame and Die Part Numbers
Mil-Spec P/N Daniels
for Hex Die P/N for Hex Die Tool Frame
Cable Type
Die Hex
PFLX195
PFLX200
PFLX240
PFLX340
PFLX500
M22520/5-19 Y142
M22520/5-19 Y142
M22520/5-43 Y141
M22520/5-35 Y137
M22520/5-21 Y149
M22520/5-01 (HX4)
M22520/5-01 (HX4)
M22520/5-01 (HX4)
M22520/5-01 (HX4)
M22520/5-01 (HX4)
B Hex
B Hex
A Hex
A Hex
A Hex
TFLX130
TFLX165
TFLX205
TFLX295
TFLX488
M22520/5-43 Y141
M22520/5-19 Y142
M22520/5-43 Y141
M22520/5-35 Y137
M22520/5-27 Y151
M22520/5-01 (HX4)
M22520/5-01 (HX4)
M22520/5-01 (HX4)
M22520/5-01 (HX4)
M22520/5-01 (HX4)
A (ARINC) / B Hex
B Hex
A Hex
A Hex
A Hex
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Installation Considerations:
Meeting the specifications when faced with a long cable run could be challenging at some times.
Solutions typically are found when combining a Low Loss Cable (large OD) for the majority of the
run with a “pig tail” at the box or antenna sides. The “pig tail” cable will have a small OD, and will
be very flexible to make the installation in difficult areas easier. Please use the Tables above for
additional information. You can also call EMTEQ’s knowledgeable staff at the below numbers to
help in the configuration and meet your requirements.
EMTEQ, Inc.
S84 W18693 Enterprise Drive
Muskego, WI 53150
(888) 679-6170 Toll Free
(262) 679-6170
Fax: (262) 679-6175
e-mail: [email protected]
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D1-3
Aerospace Optics
Aerospace Optics Inc.
Aerospace Optics Inc. is pleased to support the Honeywell EGPWS/TAWS team
with our line of Vivisun LED lighted switches and indicators. We would welcome
the opportunity to assist with your installation and address your Honeywell
EGPWS/TAWS lighting requirements.
LED Lighting
The Honeywell EGPWS/TAWS systems offer state-of-the-art performance.
Accordingly, several recent innovations in LED cockpit lighting have emerged
which truly complement the performance of the Honeywell Systems.
Traditionally, lighted cockpit switches have used incandescent lamps which are
known for the excessive face cap temperatures they generate. The lamps are
also subject to high failure rates which degrades sunlight readability and creates
reliability concerns. LED lighting resolves each of these limitations as they
consume less than half the power of typical incandescent lamps and offer life-of-
the-aircraft reliability. However, the use of LED lighting also has a number of
additional challenges, which can quickly dilute their utility.
When using LED lighting in the past, sunlight readability and viewing angles were
limited and uniform dimming required special pulse width modulation.
Additionally, unprotected LEDs were susceptible to damage from transients and
voltage spikes from severe electrical environments as defined in RTCA/DO-
160D. However, today, with the evolution of LED technology and innovative
design techniques, it is possible to take advantage of the efficiencies afforded by
LEDs while continuing to meet the lighting and environmental requirements of
aircraft design.
The Vivisun LED resolves each of these challenges including DO-160D
compliance and standard voltage controlled dimming. LEDs are the lighting
source for the future and the ideal compliment to the Honeywell EGPWS/TAWS
Systems.
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Please feel free to contact the Aerospace Optics Technical Sales Team for
assistance in addressing the use of LED lighted switches and indicators.
Aerospace Optics Inc.
3201 Sandy Lane
Fort Worth TX, 76016
1-(888)VIVISUN- (848-4786) Toll Free
Fax (817) 654-3405
www.vivisun.com
e-mail : [email protected]
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D1-4 StacoSwitch
StacoSwitch
As a supplier of high reliability switches and indicators for avionics since 1958,
StacoSwitch is proud to be integrated with many Honeywell products and
divisions. Through our relationship with EDMO Distributors in Spokane, WA, we
supply AV17 kits that include all the switches, annunciators, and crimp pins
needed to complete the installation of your Honeywell EGPWS (TAWS) system.
These kits meet all lighting and color requirements in the shortest and lightest
switch and indicator units available on the market. EDMO stocks these kits and
can even generate customized legend and color combinations with extremely
fast delivery, usually within a couple days.
StacoSwitch can also provide solutions to most switch needs that may arise,
such as LED lighting, Night Vision (NVIS) compatibility, EMI/RFI shielding,
watertight seals, Digital Dimming Modules that can dim both incandescent and
LED lights with consistency, pushbutton guards, and customized-legend switch
and indicator assemblies that can be packaged into impressive matrix mounts.
Please check out our full line of products at www.stacoswitch.com. It includes all
the detailed information to help answer any questions you may have during an
installation and also a link to EDMO.
Contact Information:
Dan Sugg – Vice President of Sales
StacoSwitch
1139 Baker Street
Costa Mesa, CA 92626
Phone:
Fax:
(714) 549-3041
(714) 549-0930
www.stacoswitch.com
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APPENDIX E
INTERFACE DESCRIPTION DOCUMENT
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INTRODUCTION ...................................................................................................................................................................166
E 1
E 2
E 3
E 4
Part Number.............................................................................................................................................................166
Purpose.....................................................................................................................................................................166
System Overview .....................................................................................................................................................166
ELECTRICAL INTERFACE ..................................................................................................................................167
E 4.1
E 4.2
Introduction......................................................................................................................................................167
Signal Interfaces...............................................................................................................................................167
E 4.2.1 Grounds............................................................................................................................................................167
E 4.2.2 Primary Power Input ........................................................................................................................................167
E 4.2.3 DC Analog Inputs ............................................................................................................................................168
E 4.2.7 AC Analog Inputs ............................................................................................................................................170
E 4.2.9 ARINC 429/575 Digital Serial Bus Inputs.......................................................................................................172
E 4.2.9.1 RS-232 / RS-422 Digital Serial Bus Inputs..................................................................................................173
E 4.2.10
E 4.2.11
E 4.2.12
E 4.2.13
E 4.2.14
E 4.2.16
E 4.2.17
E 4.2.17.1
E 4.2.17.2
Discrete Inputs .............................................................................................................................................174
Configuration Module Interface...................................................................................................................175
GPS Antenna Input.......................................................................................................................................175
OAT Voltage Reference Output...................................................................................................................176
Lamp Driver Outputs ...................................................................................................................................176
Audio Outputs ..............................................................................................................................................176
ARINC Digital Serial Output Busses...........................................................................................................177
ARINC 429 Output Bus ...........................................................................................................................177
ARINC 453 Output Bus ...........................................................................................................................178
Front Panel Test Interface ................................................................................................................................178
RS-232 Maintenance Port (serial port 4)......................................................................................................178
PCMCIA / SmartCable Port.....................................................................................................................179
GSE Present Discrete Input......................................................................................................................179
Front Panel Status Indicators............................................................................................................................179
E 4.2.18
E 4.2.18.1
E 4.2.18.2
E 4.2.18.3
E 4.2.19
E 5
E 5.1
E 5.2
E 5.3
AIRCRAFT APPLICATION DATA...........................................................................................................................180
Configuration Types.............................................................................................................................................180
Configuration Selection .......................................................................................................................................180
Configuration Selection Tables........................................................................................................................182
E 5.3.1 Category 1, Aircraft / Mode Type Select .........................................................................................................183
E 5.3.2 Category 2, Air Data Input Select ....................................................................................................................189
E 5.3.3 Category 3, Position Input Select....................................................................................................................195
E 5.3.4 Category 4, Altitude Callouts...........................................................................................................................199
E 5.3.5 Category 5, Audio Menu Select .......................................................................................................................201
E 5.3.6 Category 6, Terrain Display Select ..................................................................................................................202
E 5.3.7 Category 7, Options 1 Select............................................................................................................................231
E 5.3.8 Category 8, Radio Altitude Input Select...........................................................................................................233
E 5.3.9 Category 9, Navigation Input Select ................................................................................................................236
E 5.3.10
E 5.3.11
E 5.3.12
E 5.3.13
E 5.3.14
E 5.3.15
Category 10, Attitude Input Select...............................................................................................................238
Category 11, Heading Input Select...............................................................................................................240
Category 12, Windshear Input Select...........................................................................................................241
Category 13, Input / Output Discrete Type Select........................................................................................242
Category 14, Audio Output Level ................................................................................................................245
Category 15, Autorotation Threshold...........................................................................................................246
E 6
E 6.1
E 7
CONNECTOR INTERFACE ......................................................................................................................................247
Pinout for Front Connectors sorted by pin number..............................................................................................247
DEFINITIONS.........................................................................................................................................................252
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INTRODUCTION
E 1 PART NUMBER
This document is the Interface Description for the MKXXII Helicopter Enhanced Ground Proximity Warning System
(EGPWS) part number 965-1590-0XX.
The MK XXII EGPWC 10 digit part number will identify the configuration of the EGPWC as follows:
•
•
965-1590-XXX (example 965-1590-010)
XXX = Application Software (including Configuration Software)
The Terrain Database (including the Envelope Modulation Database) Version is not identified in the 10-digit part number but
with a separate identifier on the nameplate.
All modification changes not affecting form, fit or function will be identified via “mod dots”.
The digits identifying the Application software will match the respective version number of the Application software.
E 2 PURPOSE
This Appendix describes all of the system external interfaces for the MK XXII Enhanced Ground Proximity Warning System
(EGPWS).
E 3 SYSTEM OVERVIEW
For more information please refer to the EGPWS Product Specification document 965-1590-601.
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E 4 ELECTRICAL INTERFACE
E 4.1 INTRODUCTION
The MK XXII EGPWS provides electrical interfaces for aircraft systems and to support maintenance functions. The
interfaces are made via the front panel aircraft interface connectors, front panel maintenance/test port and front panel LED’s.
A TNC coaxial connector is located on the front panel for internal GPS receivers in the 965-1590-0XX MK XXII EGPWC.
The following sections describe the types of electrical interfaces provided in the EGPWC. See Section E 5 for the specific
interface configuration capabilities of the MK XXII EGPWS.
E 4.2 SIGNAL INTERFACES
This section identifies and describes the number and characteristics of each interface type provided in the front aircraft
interface connectors. The aircraft interface connectors are defined as P1 (78 pins) and P2 (50 pins). Section E 6 identifies the
connector pin assignments. The signal mnemonic for each signal in Section E 6 is included in the following sections. All
synchro inputs are brought in as three or five wire devices. No two wire absolute AC signals are available. All analog inputs
provide broken wire detection on all input signal legs. Unless otherwise stated, the “Maximum reverse fault current” is
defined as the current resulting from an internal component failure, with the input signal at zero volts.
E 4.2.1
GROUNDS
CHASSIS GROUND
Used for redundant metal connection. This pin is internally connected to DC Ground (see section 0).
Pin Assignment (Signal Mnemonic):
J1-42, J1-53
(GND)
DC GROUND
For discrete inputs and lamp driver outputs. These pins are also internally connected to Chassis Ground (see section 0).
Pin Assignment (Signal Mnemonic):
(same as +28 VDC Return)
J1-41, J1-61
(PWR_L)
NOTE: All analog signals are differential input.
E 4.2.2
PRIMARY POWER INPUT
Nominal Input
28 VDC
Normal Voltage Range
22.0 to 30.3 VDC
15 – 40VDC (30 msec)
20.5 to 32.2 VDC
37.8 VDC (1sec); 46.3 VDC (100 msec)
not applicable
Normal Surge Voltage Range
Abnormal Voltage Range
Abnormal Surge Voltage Range
Normal Frequency Range
Frequency Transients
not applicable
Power Requirements
9 Watts - No Warnings
+7 Watts with warning voice over 8 Ω speaker
+3 Watts with Internal GPS (includes antenna power)1
+49 Watts (typical) with heater blanket on2
3 Amp delayed action circuit breaker.
Recommended Power Control Device
Pin Assignment (Signal Mnemonic):
+28 VDC Input
J1-40, J1-60
J1-41, J1-61
(PWR_H3)
(PWR_L3)
+28 VDC Return
1Based on the Honeywell GPS Pxpress card specification and applies to 965-1590-0XX only.
2The heater blanket turns on at temperatures ≤ -23° C and turns off at temperatures ≥ -20° C.
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3Note that this is not a floating input. +28 VDC must be applied to both PWR_H and +28 VDC Return to both
PWR_L inputs.
E 4.2.3
DC ANALOG INPUTS
Unless otherwise specified, Input Signal accuracy is1% linearity +0.1% full scale offset.
E 4.2.3.1
RADIO ALTITUDE
Quantity
1
Input Impedance, each leg
Maximum Reverse Fault Current
Signal Range
> 83 KΩ
< 200 µamps
0 to 2500 feet
Input Voltage Range (VRA
Conversion Range (Vc)
Input Filter
)
37.7V ≥ VRA ≥ -2.5V
29.7V ≥ Vc ≥ -0.4V
0.1 Second Low Pass, 10%
Input will be biased to less than -50 feet
Broken Wire Detect
Pin Assignment (Signal Mnemonic):
Signal (+)
Return (-)
J1-64
J1-45
(RALT_H)
(RALT_L)
E 4.2.3.2
LOW LEVEL GLIDESLOPE
Quantity
1
Input Impedance, each leg
Reverse Fault Current
Signal Range
Input Voltage Range
Input Filter
> 2.5 MΩ
< 6.2 µamps
12 Dots
0.9VDC
0.1 Second Low Pass, 10%
Differential
Input Type
Common Mode Voltage Range (VCM
Broken Wire Detect
Pin Assignment (Signal Mnemonic):
)
11V ≥ VCM ≥ -2V
Input will be biased less than -15 dots
+Up, Below Beam, Fly Up
+Down, Above Beam, Fly Down
J1-65
J1-46
(GSDEV_H)
(GSDEV_L)
E 4.2.3.3
LOCALIZER DEVIATION OR LOW LEVEL GLIDESLOPE VALIDITY
This input can be configured as either a low level glideslope valid, or as a localizer deviation input. Installations that only
have the low level validity signal for glideslope can not activate the analog localizer input. See section 5.3.9 for more
information.
Quantity
1
Input Impedance, each leg
Reverse Fault Current
Input Filter
Input Type
> 2.5 MΩ
< 6.2 µA
0.1 Second Low Pass, 10%
Differential
Common Mode Voltage Range (VCM
Pin Assignment (Signal Mnemonic):
)
11V ≥ VCM ≥ -2V
+
-
J1-30
J1-10
(GS_VAL_H)
(GS_VAL_L)
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When used as a validity input:
Active Voltage Range (Logic True)
Inactive Voltage Range (Logic False)
Broken Wire Detect
+160 to +840 mVDC
0 to 50 mVDC
Input will be biased less than –1 VDC
When used as a localizer input:
Signal Range
12 Dots
Input Voltage Range
Broken Wire Detect
0.9VDC
Input will be biased less than -15 dots
E 4.2.4
BAROMETRIC ALTITUDE
Quantity
1
Input Impedance, each leg
Reverse Fault Current
Input Voltage Range
Input Filter
> 83 KΩ
< 200 µamps
-0.18VDC to +15VDC
0.1 Second Low Pass, 10%
Differential
Input Type
Broken Wire Detect
Pin Assignment (Signal Mnemonic):
Signal (+)
Input will be biased less than -3000 feet
J1-62
J1-43
(ALT_H)
(ALT_L)
Return (-)
E 4.2.5
OUTSIDE AIR TEMPERATURE
Quantity
1
Input Impedance, each leg
Reverse Fault Current
Input Voltage Range
Input Filter
> 100 KΩ
< 200 µamps
+0.3 VDC to +0.6VDC
0.1 Second Low Pass, 10%
Differential
Input Type
Broken Wire Detect
Pin Assignment (Signal Mnemonic):
Signal (+)
Input will be biased less than -80° C
J1-63
J1-44
(OAT_H)
(OAT_L)
Return (-)
NOTE: For temperature probe voltage reference see section 0.
E 4.2.6
CONFIGURATION DEFINED DC INPUTS
Quantity
2
Input Impedance, each leg
Reverse Fault Current
Input Voltage Range
Input Filter
> 83 KΩ
< 200 µamps
5 VDC
0.1 Second Low Pass, 10%
Differential
Input Type
Broken Wire Detect
Pin Assignment (Signal Mnemonic):
#1 Signal (+)
Input will be biased less than –6 VDC
J1-26
J1-27
J1-66
J1-47
(TORQUE_1H)
(TORQUE _1L)
(TORQUE _2H)
(TORQUE _2L)
#1 Return (-)
#2 Signal (+)
#2 Return (-)
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E 4.2.7
AC ANALOG INPUTS
Unless otherwise specified, Input Signal accuracy is1% linearity +0.1% full scale offset
E 4.2.7.1
SYNCHRO ROLL ATTITUDE
Quantity
1
Input Impedance: X leg
Input Impedance: Y leg
Input Impedance: Z leg
Maximum Reverse Fault Current
Input Voltage Range
Synchro Angle Range
Reference Voltages
Accuracy
> 140 KΩ
> 140 KΩ
> 140 KΩ
< 200 µamps
±11.8 VACRMS ± 20% (leg to leg)
±80 deg
Not Required
2.5% linearity + 0.1% full scale offset
Pin Assignment (Signal Mnemonic):
X leg
J1-1
J1-21
J1-2
(SYN_1X)
(SYN_1Y)
(SYN_1Z)
Y leg
Z leg
E 4.2.7.2
SYNCHRO MAGNETIC HEADING
Quantity
1
Input Impedance: X leg
Input Impedance: Y leg
Input Impedance: Z leg
Maximum Reverse Fault Current
Input Voltage Range
Reference Voltages
Accuracy
> 140 KΩ
> 140 KΩ
> 140 KΩ
< 200 µamps
±11.8 VACRMS ± 20% (leg to leg)
26 VACRMS ± 20% (see 4.2.4.4)
2.5% linearity + 0.1% full scale offset
Pin Assignment (Signal Mnemonic):
X leg
J1-22
J1-23
J1-3
(SYN_2X)
(SYN_2Y)
(SYN_2Z)
Y leg
Z leg
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E 4.2.7.3
CONFIGURATION DEFINED SYNCHRO INPUTS
Quantity
3
Input Impedance: X leg
Input Impedance: Y leg
Input Impedance: Z leg
Maximum Reverse Fault Current
Input Voltage Range
Reference Voltages
Accuracy
> 140 KΩ
> 140 KΩ
> 140 KΩ
< 200 µamps
±11.8 VACRMS ± 20% (leg to leg)
26 VACRMS ± 20%
2.5% linearity + 0.1% full scale offset
Pin Assignment (Signal Mnemonic):
#1 X leg
J1-5
J1-7
J1-6
J2-1
J2-2
J2-18
J2-19
J2-20
J2-3
(SYN_3X)
(SYN_3Y)
(SYN_3Z)
(SYN_4X)
(SYN_4Y)
(SYN_4Z)
(SYN_5X)
(SYN_5Y)
(SYN_5Z)
#1 Y leg
#1 Z leg
#2 X leg
#2 Y leg
#2 Z leg
#3 X leg
#3 Y leg
#3 Z leg
E 4.2.8
SIGNAL TIMING REFERENCE INPUTS
These inputs accept 400 Hz AC signals, and detect the “zero crossings” of these signals. These zero crossings are used to
time the conversion and input of AC signals. Absolute voltage level of these signals is not measured, but it must be within
the range specified below. Voltage below the specified minimum value may result in intermittent or “jittery” zero cross
detection.
Timing reference signals are required for input of most AC devices (not required for roll). These references can be brought
into the appropriate timing reference input, or the system can be configured to derive a reference from the signal. Timing
reference signals are specified for synchro inputs requiring a range greater than 80 degrees. Inputs requiring less (i.e., Roll
Attitude) are configured to derive a reference from the synchro input signal and do not require a separate reference voltage
input.
Quantity
2
Input Impedance
> 140KΩ each line to signal ground
< 120 µamps
Maximum Reverse Fault Current
A/C Input Signal Frequency Range
Maximum Input Voltage Swing (differential)
Maximum Input Voltage Swing (ref. to Gnd)
Input Hardware Filtering
400 Hz, 10%
50V between input legs
50V from any leg to signal ground
None
Minimum Input Voltage
0.5 VAC
Pin Assignment (Signal Mnemonic):
26VAC Reference #1 H
J1-4
(26REF_1H)
(26REF_1L)
(26REF_2H)
(26REF_2L)
26VAC Reference #1 C
26VAC Reference #2 H
26VAC Reference #2 C
J1-24
J2-34
J2-35
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E 4.2.9
ARINC 429/575 DIGITAL SERIAL BUS INPUTS
Quantity
Format
Low Speed Data Rate
8
1
DITS, ARINC 429/575 Low or high speed
12.0 KBPS to 14.5 KBPS
High Speed Data Rate
Direction of Information Flow
Word/Frame Structure
100 KBPS 1%
Type ‘A’ broadcast for ARINC 429/575
Type ‘B’ 32 bit words consisting of 8 bits label and 24
bits data/status
Data definition
Refer to Section 6 of this document
Pin Assignment (Signal Mnemonic):
Receive #1 A leg
Receive #1 B leg
Receive #2 A leg
Receive #2 B leg
Receive #3 A leg
Receive #3 B leg
Receive #4 A leg
Receive #4 B leg
Receive #5 A leg
Receive #5 B leg
Receive #6 A leg
Receive #6 B leg
Receive #7 A leg
Receive #7 B leg
Receive #8 A leg
Receive #8 B leg
J2-37
J2-36
J2-39
J2-38
J2-41
J2-40
J2-25
J2-8
J2-21
J2-4
J2-22
J2-5
(429/422RX_1A)
(429/422RX_1B)
(429RX_2A)
(429RX_2B)
(429RX_3A)
(429RX_3B)
(429RX_4A)
(429RX_4B)
(429RX_5A)
(429RX_5B)
(429RX_6A)
(429RX_6B)
(429RX_7A)
(429RX_7B)
(429RX_8A)
(429RX_8B)
J2-23
J2-6
J2-24
J2-7
SSM/SDI Definition:
Refer to Section 6 of this document
1
The bus speed is defined in the configuration selection, see Section 5 for details.
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E 4.2.9.1
RS-232 / RS-422 DIGITAL SERIAL BUS INPUTS
Two full duplex RS-232 / RS-422 buses and a third RS-422 receiver are provided at the aircraft interface connectors. The
RS-422 transceivers are electrically multiplexed with the RS-232 transceivers, and are selected through the configuration
process. The third RS-422 receiver is electrically multiplexed with the ARINC 429 channel 1 receiver. The maintenance
RS-232 bus is described in section 0. The specific characteristics (data rate, parity, data bits, stop bits) is defined in the
configuration selection, see Section 5 and 6 for details. RS-422 cable termination will not be required for typical
applications, see TIA/EIA-422-B Annex A.
The RS-232 bus meets the characteristics specified in RS232C and supports the following characteristics:
Data Rate
1200, 2400, 4800, 9600, 19200 or 38400 bits/Sec
Parity
None, Odd or Even
Data bits
7 or 8
Stop bits
1 or 2
Maximum Recommended Cable Length
Data definition
15 meters
Refer to Section 6 of this document
The RS-422 bus meets the characteristics of TIA/EIA-422-B and supports the following characteristics:
Data Rate
1200, 2400, 4800, 9600, 12000, 19200 or 38400 bits/Sec
Maximum Transceivers on Bus
Receiver Input Impedance
Word/Frame Structure
Data definition
20
12 KΩ
Refer to Section 6 of this document
Refer to Section 6 of this document
E 4.2.9.2
GPS RS-232 DIGITAL SERIAL BUS (SERIAL PORT 3)
One port is provided for use with external or internal RS-232 GPS interfaces. This port is common with the GPS RS-422 port
described in Section 0 and can only function as a RS-232 interface or a RS-422 interface but not both.
Pin Assignment (Signal Mnemonic):
Transmit
Receive
Common
J2-45
J2-29
J2-28
(GPS_TXA)
(GPS_RXA)
(GND)
NOTE: If an internal GPS configuration is used (965-1186-0XX, 965-1216-0XX or 965-1590-0XX) then the receive
input will be non-functional.
E 4.2.9.3
GPS RS-422 DIGITAL SERIAL BUS (SERIAL PORT 3)
One port is provided for use with external GPS interfaces. This port is common with the GPS RS-232 port described in
Section 0 and can only function as a RS-232 interface or a RS-422 interface but not both.
Pin Assignment (Signal Mnemonic):
Transmit A leg
Transmit B leg
Receive A leg
Receive B leg
J2-45
J2-46
J2-29
J2-12
(GPS_TXA)
(GPS_TXB)
(GPS_RXA)
(GPS_RXB)
NOTE: If an internal GPS configuration is used (965-1186-0XX, 965-1216-0XX or 965-1590-0XX) then the receive
input will be non-functional.
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E 4.2.9.4
AIR DATA RS-232 DIGITAL SERIAL BUS (SERIAL PORT 2)
One port is provided for use with Air Data computer or Static Pressure Sensor interfaces. This port is common with the Air
Data RS-422 port described in Section 0 and can only function as a RS-232 interface or a RS-422 interface but not both.
Pin Assignment (Signal Mnemonic):
Transmit
Receive
Common
J2-27
J2-11
J2-28
(ADC_TXA)
(ADC_RXA)
(GND)
E 4.2.9.5
AIR DATA RS-422 DIGITAL SERIAL BUS (SERIAL PORT 2)
One port is provided for use with Air Data computer or Static Pressure Sensor interfaces. This port is common with the Air
Data RS-232 port described in Section 0 and can only function as a RS-232 interface or a RS-422 interface but not both.
Pin Assignment (Signal Mnemonic):
Transmit A leg
Transmit B leg
Receive A leg
Receive B leg
J2-27
J2-44
J2-11
J2-10
(ADC_TXA)
(ADC_TXB)
(ADC_RXA)
(ADC_RXB)
E 4.2.9.6
SCI RANGE RS-422 DIGITAL SERIAL BUS (SERIAL PORT 1)
One port is provided for use with the SCI range bus interfaces. This port is common with the ARINC 429 channel 1 port
described in Section 0 and can only function as a RS-422 interface or an ARINC 429 interface but not both.
Pin Assignment (Signal Mnemonic):
Recieve A leg
Recieve B leg
J2-37
J2-36
(429/422RX_1A)
(429/422RX_1B)
E 4.2.10
DISCRETE INPUTS
Discrete signals are intended for remote switching through the aircraft, and are therefore subject to being connected to other
signals, and are also subject to transient voltage conditions. For these reasons, the following rules apply to each input, unless
otherwise stated.
Each input is capable of withstanding voltage transients of 600VDC for 10 µs, without damage. The +28 VDC discretes
are internally biased via a pull down resistor, and are externally pulled up to +28VDC when active. The characteristics of
each +28 VDC discrete input are as follows:
+28 VDC Discrete Characteristics
Quantity
13
Active Voltage Range (Logic True)
Inactive Voltage Range (Logic False)
Diode Isolation
> +17 VDC
< +4.4 VDC
None
Input Impedance
Maximum Fault Current
Pin Assignment (Signal Mnemonic):
> 95 KΩ
< 60 µA
See specific discrete in Category 13 (28V_DISC_xx)
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The Ground discretes are internally biased via a pull up resistor, and are externally pulled down to ground when active. The
characteristics of each Ground discrete input are as follows:
Ground Discrete Characteristics
Quantity
15
Active Voltage Range (Logic True)
Inactive Voltage Range (Logic False)
Diode Isolation
Input Impedance
Maximum Fault Current
Pin Assignment (Signal Mnemonic):
< +3 VDC
> 100 KΩ (to ground) or > +3.5 VDC
Each input is diode isolated to prevent current sinking
> 10 KΩ
< 100 µA (at +28 VDC input)
See specific discrete in Category 13 (GND_DISC_xx)
E 4.2.11
CONFIGURATION MODULE INTERFACE
System configuration is defined via a Configuration Module, which resides in the MKIV/VI/VIII/XXII EGPWS aircraft
wiring harness backshell. The EGPWS Configuration Module contains the aircraft interface and functionality definitions
specific to the installed aircraft. Refer to Section 5 for interface and functional definitions by category.
Electrical Characteristics
Data definition
Refer to the EGPWS Configuration Module specification
Refer to the EGPWS Configuration Module specification
Pin Assignment (Signal Mnemonic):
Clock
J2-32 (RED)
J2-50 (BLK)
J2-33 (ORN)
J2-49 (WHT)
J2-17 (VIO)
J2-16 (BLU)
(SPICLK)
Master Data Out
Master Data In
Configuration Module Select
Configuration Module +5VDC
(SPIMOSI)
(SPIMISO)
(SPISEL_CM#)
(SC_PWR)
(GND)
Configuration Module +5VDC Return
Output to Config Module
Logic Low (nominal)
Logic High (nominal)
EMK4/6/8/22
EMK4/6/8/22
Clock Out
Master Data Out
Config Module Select
0 V
0 V
0 V
5 V
5 V
5 V
INTERFACE OF EGPWS OUTPUTS TO CONFIGURATION MODULE
E 4.2.12
GPS ANTENNA INPUT
A GPS input connector is available on the front of the MK VI EGPWS (965-1186-0XX only), MK VIII EGPWS (965-1216-
0XX only), MK XXII EGPWS (965-1590-0XX only), and MK IV EGPWS (965-1686-0XX only).
Quantity
1
Cable Length/Allowed Signal Loss
Not more than 8 dB, at 1575.42 MHz, for cable and
connector loss from antenna to unit.
TNC
Connector Type
Low Level DC on RF Output
Pin Assignment (Signal Mnemonic):
+5 VDC ±5%, 50 mAmps maximum, Shield Ground.
GPS ANT
(COAX)
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E 4.2.13
OAT VOLTAGE REFERENCE OUTPUT
This output is an accurate voltage source for 500 Ω resistive temperature sensors.
Quantity
1
Output Voltage
5.000 VDC 10 mVDC (no load)
Nominal Load
Pin Assignment (Signal Mnemonic):
500 Ω
J1-25
(OAT_REF)
NOTE: This output has a source impedance of 4.42 KΩ, 0.1%.
E 4.2.14
LAMP DRIVER OUTPUTS
The MK IV, VI, VIII and XXII EGPWS supports two kinds of Ground/Open discrete outputs used to signal various discrete
conditions. Monitor outputs are used to signal failure conditions for the MK IV, VI, VIII and XXII EGPWS. Monitor
outputs default to an active state when there is a failure or if power is removed from the MK IV, VI, VIII and XXII EGPWS.
The other Lamp Driver outputs are used to signal the alert or mode control status of the MK IV, VI, VIII and XXII EGPWS.
Short-term current limit protection is provided on all drivers for output shorting conditions. Ground going output discretes
may be connected together to produce a “wired OR” function for the active low state of the signals. If output discretes are
“wired or’ed” then diodes must be installed for isolation.
E 4.2.14.1 MONITOR OUTPUT CHARACTERISTICS
Quantity
3
Type of Output:
Max. Open Circuit Voltage:
Current Limit
Switch Closure to Ground
30 VDC
1 Amp
Potential Across “Closed” Switch:
Pin Assignment (Signal Mnemonic):
2.5 VDC Max
See specific output in Category 13
(MON_OUT_xx)
NOTE: Intended to operate with +28VDC lamp sources and will not operate with +5VDC lamp sources.
E 4.2.15
DISCRETE OUTPUT CHARACTERISTICS
Quantity
9
Type of Output:
Max. Open Circuit Voltage:
Current Limit
Potential Across “Closed” Switch:
Pin Assignment (Signal Mnemonic):
Switch Closure to Ground
30 VDC
500 mAmp (typical)
1 VDC Max
See specific output in Category 13
(DISC_OUT_xx)
E 4.2.16
AUDIO OUTPUTS
There are two audio outputs provided – one 8-ohm output and one 600-ohm output. There are several possible volume levels
available with the MKIV/VI/VIII/XXII EGPWS as shown below, with maximum output being 4W (8Ω) or 100mW (600Ω).
The actual audio level output by the EGPWS is dependent on several items:
•
Selection of nominal alert audio volume level (max, -6, -12, -18 or -24 dB) via Category 14. (Section 5.3.14)
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MK XXII EGPWS Installation Manual
•
•
•
If a ‘soft’ Glideslope alert is being issued (given 6 dB below nominal alert volume level).
If a Self Test is in progress, alerts are given 6 dB below nominal alert volume level.
Selection of Mode 6 Low Volume Discrete (lowers callout volume by 6 dB - See Section 5.3.13).
E 4.2.16.1 HIGH LEVEL (SPEAKER) AUDIO OUTPUT
The 8-ohm output is capable of driving a speaker directly but can also be used to drive other devices with equal or higher
impedance.
Quantity
1
Maximum Power Output
Nominal Output Impedance
Load Impedance
Number of Available Power Output Levels
Pin Assignment (Signal Mnemonic):
Signal (+)
4 Watts Nominal
8Ω
8Ω or greater
1
5
J1-70
J1-71
(AUD_HL_H)
(AUD_HL_L)
Return (-)
E 4.2.16.2 LOW LEVEL (INTERPHONE) AUDIO OUTPUT
The 600-ohm output is capable of driving one 600-ohm load at the specified level (or at a reduced level). This output is
primarily designed for headphones and interphone systems.
Quantity
1
Nominal Output Impedance
Maximum Single Channel Power Output
Available Power Output Levels
Pin Assignment (Signal Mnemonic):
Signal (+)
600Ω 10%
100 mW Nominal ()
1
5
J1-75
J1-74
(AUD_LL_H)
(AUD_LL_L)
Return (-)
E 4.2.17
ARINC DIGITAL SERIAL OUTPUT BUSSES
E 4.2.17.1 ARINC 429 OUTPUT BUS
The ARINC 429 output buses are defined in the terrain display select Section 5.3.6.3, output 429 bus group.
Quantity
2
Format
DITS, ARINC 429
Low Speed Data Rate
High Speed Data Rate
Direction of Information Flow
Word/Frame Structure
12.0 KBPS to 14.5 KBPS
100 KBPS 1%
Type ‘A’ broadcast for ARINC 429
Type ‘B’ 32 bit words consisting of 8 bits label and 24
bits data/status
Data definition
Refer to Section 7
Pin Assignment (Signal Mnemonic):
Bus #1 (A leg)
J2-43
J2-42
J2-26
J2-9
(429TX_1A)
(429TX_1B)
(429TX_2A)
(429TX_2B)
2
Bus #1 (B leg)
Bus #2 (A leg)
Bus #2 (B leg)
2
Five Selectable levels excluding the Mode 6 Audio Reduction function.
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E 4.2.17.2 ARINC 453 OUTPUT BUS
Quantity
2
Format
Data Rate
1600 bit Manchester BI-phase per ARINC 708A
1 Mb per second
Word/Frame Structure
Data definition
Refer to Section 7.2
Refer to Section 7.2
Pin Assignment (Signal Mnemonic):
Bus #1 (A leg)
J1-58
J1-59
J1-56
J1-57
(KCPB_1A)
(KCPB_1B)
(KCPB_2A)
(KCPB_2B)
Bus #1 (B leg)
Bus #2 (A leg)
Bus #2 (B leg)
E 4.2.18
FRONT PANEL TEST INTERFACE
The MK IV, VI, VIII and XXII EGPWS provides a 15 pin (double density, D-Sub) test connector on the front panel, which
provides interfaces for various test and maintenance functions. This connector provides the following interfaces.
E 4.2.18.1 RS-232 MAINTENANCE PORT (SERIAL PORT 4)
One port is provided which meets the characteristics specified in RS232C. This bus can be used to read internal data from
the MK IV, VI, VIII and XXII EGPWS for both bench, and aircraft testing or transmitting configuration data for selected
EGPWS interfaces and options.
Baud Rate
19,200
Parity
None
Data bits
8
Stop bits
1
Maximum Recommended Cable Length
15 meters
Pin Assignment (Signal Mnemonic):
Transmit
Receive
Common
J3-4
J3-3
J3-1
(RS232TXD_MON)
(RS232RXD_MON)
(GND)
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E 4.2.18.2 PCMCIA / SMARTCABLE PORT
One port is provided which meets the Motorola SPI characteristics. The PCMCIA / SmartCable interface allows for both the
uploading, and downloading of internal MK IV, VI, VIII and XXII EGPWS information. Using this interface system,
software and databases can be updated. Control of the upload/download process is accomplished by insertion of the
PCMCIA card / SmartCable to the MK IV, VI, VIII and XXII EGPWS front panel test connector. LEDs are provided on the
SmartCable for PCMCIA interface operation. The PCMCIA / SmartCable is not intended as an on-line/in-flight storage
medium and must be removed after completion of the upload/download operation.
Electrical Characteristics
Data definition
Maximum Recommended Cable Length
Pin Assignment (Signal Mnemonic):
Clock
Refer to the Motorola SPI specification
Refer to the Motorola SPI specification
2 meters
J3-7
(SPICLK)
Master Data Out
Master Data In
SmartCable Select
SmartCable +5VDC
SmartCable +5VDC Return
PCMCIA Card Present
SmartCable Ground
J3-9
J3-8
J3-10
J3-6
J3-1
(SPIMOSI)
(SPIMISO)
(SPISEL_SC#)
(SC_PWR)
(GND)
J3-2
J3-12, -13, -14
(CARD_PRES#)
(GND)
NOTE: SmartCable +5VDC Return is common with RS-232 Maintenance Port common.
E 4.2.18.3 GSE PRESENT DISCRETE INPUT
A discrete input for test and Ground Support Equipment is provided. Grounding this pin indicates to the EGPWS that test or
Ground Support Equipment is connected to the system.
Active Threshold Voltage (Logic True)
Inactive Threshold Voltage (Logic False)
Input Impedance
Maximum Fault Current
Pin Assignment (Signal Mnemonic):
< 0.8 VDC
> 2.0 VDC
> 20 KΩ
< 500 µAmps
J3-11
(GSE_PRES#)
E 4.2.19
FRONT PANEL STATUS INDICATORS
The MK XXII EGPWC front panel provides three LEDs for indicating system and LRU status. A yellow LED labeled
“EXTERNAL FAULT” is activated when a signal fault external to the MK XXII EGPWS is detected. A green LED labeled
“COMPUTER OK” is activated when the MK XXII EGPWS itself is okay. A red LED labeled “COMPUTER FAIL” is
activated when the MK XXII EGPWS has detected an internal computer fault.
Refer to Product Specifications 965-1590-601 for a detailed discussion of status indications, recommended maintenance
actions, Self-Test activation and response.
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E 5 AIRCRAFT APPLICATION DATA
This section describes the MK XXII EGPWS interfaces for aircraft applications. Section E 5.1 is a listing of the selection
categories defining the various aircraft sensor interfaces and EGPWS functional options. Section E 5.2 describes how the
Category ID’s are selected and programmed for the interface to aircraft sensors and EGPWS functional options. Section E
5.3 and its sub-sections define the specific aircraft interfaces available for the MK XXII EGPWS.
E 5.1 CONFIGURATION TYPES
The selection of the basic interfaces to the MK XXII EGPWS can be found in the following categories:
Category 1
Category 2
Category 3
Category 4
Category 5
Category 6
Category 7
Category 8
Category 9
Category 10
Category 11
Category 12
Category 13
Category 14
Category 15
Aircraft / Mode Type Select
Air Data Input Select
Position Input Select
Altitude Callous
Audio Menu Select
Terrain Display Select
Options 1 Select
Radio Altitude Input Select
Navigation Input Select
Attitude Input Select
Heading Input Select
Windshear Input Select
I / O Discretes Select
Audio Output Level
Autorotation Threshold
E 5.2 CONFIGURATION SELECTION
Each category provides information relative to aircraft interfaces or EGPWS functional options required or used for EGPWS
operation. Each category must be defined for the specific aircraft application according to the available aircraft sensors or
equipment and the intended EGPWS function. The choices provided are available in each category identified by an “ID”
number. The ID number is selected for each category and is used to load the selected configuration in a configuration
module installed in the aircraft wiring (physically part of one of the EGPWC mating connectors). For example, selecting
Category 2, ID 1 defines the Air Data Input as ARINC 429 per Table E 3.1.2-1 in Category 2. With this ID programmed into
the configuration module the EGPWC will look for and use the interface defined for this ID. Table E 3 can be used to record
the selected ID for each category for later reference when programming the configuration module. This programming is
accomplished using a programming software tool available from Honeywell or generating a data text string and transferring
this data (in either case) via the EGPWC RS-232C to the configuration module. Once programmed, the configuration is
available and read by any installed EGPWC on power up.
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TABLE E 3 CATEGORY ID SELECTION PROCEDURE
Signal
Selection
Step
(Category)
Instruction
Ident No.
Selects:
Using Table 5.3.1, and any sub-tables
contained within, locate the Aircraft / Mode
Type.
Record the Ident (ID No.) on the space
available on Ident column of this table.
a) Aircraft
Type
_______
ID #
1
b) Mode Type
Selects:
Using Table 5.3.2, and any sub-tables
contained within, locate the desired Air
Data signal type.
Record the Ident (ID No.) on the space
available on Ident column of this table.
_______
ID #
2
3
a) Air Data
Source
Selects:
Using Table 5.3.3, and any sub-tables
contained within, locate the desired Position available on Ident column of this table.
signal type.
Record the Ident (ID No.) on the space
_______
ID #
a) Position
Source
Selects:
Using Table 5.3.4 and any sub-tables
Record the Ident (ID No.) on the space
contained within, locate the desired Altitude available on Ident column of this table.
Call-Out Menu.
_______
ID #
a) Altitude
Callouts
4
Menu
Selects:
Using Table 5.3.5 and any sub-tables
contained within, locate the desired Audio
Menu type.
Record the Ident (ID No.) on the space
available on Ident column of this table.
_______
ID #
5
6
a) Audio Menu
Selects:
Using Table 5.3.6 and any sub-tables
contained within, locate the desired Display
indicator type / range bus type.
Record the Ident (ID No.) on the space
available on Ident column of this table.
_______
ID #
a) Display
Config.
Selects:
Using Table 5.3.7 and any sub-tables
Record the Ident (ID No.) on the space
available on Ident column of this table.
contained within, select the desired True or
False condition for TA&D Alternate Pop
Up, Obstacle Awareness Enable, Peaks
Mode Enable, Bank Angle Enable, WOW
Reversal Select, Steep Approach Enabled
functions and GPS Altitude Reference type.
a) Steep
Approach
Enabled
b) TA&D
Alternate
Pop Up
c) Peaks Mode
Enable
_______
ID #
d) Obstacle
Awareness
Enable
7
e) Bank Angle
Enable
f)
Weight on
Wheels
Reversal
g) GPS
Altitude
Reference
Selects:
a) Radio
Using Table 5.3.8, and any sub-tables
contained within, locate the desired Radio
Altitude signal type.
Record the Ident (ID No.) on the space
available on Ident column of this table.
_______
ID #
8
Altitude
Source
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Signal
Selection
Step
(Category)
Instruction
Ident No.
Selects:
Using Table 5.3.9, and any sub-tables
contained within, locate the desired
Navigation signal type.
Record the Ident (ID No.) on the space
available on Ident column of this table.
a) Glideslope
and/or
_______
ID #
9
Localizer
Source
Selects:
Using Table 5.3.10, and any sub-tables
Record the Ident (ID No.) on the space
contained within, locate the desired Attitude available on Ident column of this table.
signal type.
_______
ID #
10
a) Attitude
Source
Selects:
Using Table 5.3.11, and any sub-tables
contained within, locate the desired
Magnetic Heading signal type.
Record the Ident (ID No.) on the space
available on Ident column of this table.
_______
ID #
a) Magnetic
Heading
11
12
Source
Selects:
Using Table 5.3.12, no Windshear is
available for helicopter applications. Please available on Ident column of this table.
select ID 0.
Record the Ident (ID No.) on the space
0
_______
ID #
Selects:
Using Table 5.3.13, and any sub-tables
contained within, locate the desired I / O
Discrete type.
Record the Ident (ID No.) on the space
available on Ident column of this table.
a) Input
Discrete
_______
ID #
Functions
13
b) Output
Discrete
Functions
Selects:
Using Table 5.3.14, and any sub-tables
Record the Ident (ID No.) on the space
contained within, locate the desired Volume available on Ident column of this table.
type.
_______
ID #
14
15
a) Audio
Output Level
Selects:
Using Table 5.3.15, locate the desired
Autorotation Threshold. This Category is
used on helicopters only.
Record the Ident (ID No.) on the space
available on Ident column of this table.
_______
ID #
a) Autorotation
Threshold
LIMITATIONS: The described use of the configuration module provides for maximum flexibility in selection of input
sensors and output behavior. Every attempt has been made to avoid conflicts arising between categories and to reflect the
known configurations of aircraft. However in the case of input sensors it should not be construed that all combinations are
valid configurations. There may be configurations not supported by the EGPWS software configuration building process
(which will cause the EGPWS to fail in an obvious manner). In general you can not have redundancy through the mixing of
analog and digital sources, however redundant digital signals on different buses are permissable. As it is not practical to
verify all possible sensor combinations, verification of particular sensor combinations is part of the installation certification
process. If you intend to implement a sensor configuration not currently identified in Section E 3, please contact Honeywell
or an authorized dealer/installer.
E 5.3 CONFIGURATION SELECTION TABLES
Configuration selection is defined by category (or group of functions or inputs). The Category number identifies the
subsection where the details are defined. For example Air Data, Category 2, is defined in Section E 5.3.2, and Position Input
Source, Category 3, is defined in Section E 5.3.3.
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E 5.3.1
CATEGORY 1, AIRCRAFT / MODE TYPE SELECT
Category 1 defines the Aircraft Type. This determines the warning modes algorthm configuration, gear type and Torque
Interface characteristics.
The following table provides ID values for each of the basic helicopter type descriptions. For purposes of selecting an ID,
use the “Description” provided in Table E 3.1.1 appropriate to the desired variables as given above. Refer to the identified
Table E .3.1.1-X for the Engine Torque input requirements.
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TABLE E 3.1.1: HELICOPTER TYPE ID AND TORQUE INPUTS FOR EGPWS MK XXII
Torque
DESCRIPTION
Type
ID
Effectivity
App. Cfg.
Table (E
3.1.1-x)
128
129
130
131
132
133
134
135
136
0
1
2
3
4
5
6
7
8
Helo, S-76B/C+, Retractable Gear
Helo, S-76C/A++, Retractable Gear
Helo, S-76A/A+, Retractable Gear
Helo, Bell 212/412 Fixed Gear
Helo, EC-155B, Retractable Gear
Helo, MD 900, Fixed Gear
Helo, Super Puma, Retractable Gear
Helo, AS365 Dauphin N1, N2, Retractable Gear
Helo, AS365 Dauphin N3, Retractable Gear
Helo, Bell 430, Retractable Gear
Helo, Bell 407, Fixed Gear
-003
-003
-003
-006
-006
-006
-008
-008
-008
-008
-008
-008
-003
-003
-003
-006
-006
-006
-008
-008
-008
-008
-008
-008
137
138
139
9
10
5
Helo, Agusta 109E Power, Retractable Gear
Reserved
141
11
9
Bell 212/412, Fixed gear DC torque
Bell 430, Fixed gear
-010
-010
-010
-010
142
Reserved
Reserved
145
12
13
Coast Guard HH-65, Dauphin N2
Generic Helo, No Torque, Retractable Gear, Tail
Strike Type 1
Generic Helo, No Torque, Retractable Gear, Tail
Strike Type 2
Generic Helo, No Torque, Fixed Gear, Tail Strike
Type 1
Generic Helo, No Torque, Fixed Gear, Tail Strike
Type 2
Generic Helo, Common DC Torque, Retractable
Gear, Tail Strike Type 1.
Generic Helo, Common DC Torque, Retractable
Gear, Tail Strike Type 2.
Generic Helo, Common DC Torque, Fixed Gear, Tail
Strike Type 1.
Generic Helo, Common DC Torque, Fixed Gear, Tail
Strike Type 2.
Generic Helo, Shadin 429 Torque, Retractable Gear,
Tail Strike Type 1.
Generic Helo, Shadin 429 Torque, Retractable Gear,
Tail Strike Type 2.
Generic Helo, Shadin 429 Torque, Fixed Gear, Tail
Strike Type 1.
Generic Helo, Shadin 429 Torque, Fixed Gear, Tail
Strike Type 2.
-010
-011
-010
-011
146
147
148
149
150
151
152
153
154
155
156
157
13
13
13
14
14
14
14
15
15
15
15
-011
-011
-011
-011
-011
-011
-011
-011
-011
-011
-011
-011
-011
-011
-011
-011
-011
-011
-011
-011
-011
-011
Note:
For any airframe not listed in table E 3.1.1 and help selecting application ID contact Honeywell GPWS hot line 1 800 813-
2099.
Category 1 ID type 146, 147, 148 and 149 allow interface to airframes without torque input, these installation will not
provide autorotation detection and have Mode 1 inhibited. See section 3.3.1 for additional commentary and instructions.
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E 5.3.1.2
ENGINE TORQUE DATA SELECTION
WHEN A SINGLE ENGINE HELICOPTER IS ADDED TO THIS SECTION, IT NEEDS TO BE TREATED AS IF THERE WERE TWO
ENGINES VIA AIRCRAFT WIRING. THE SRD REQURIEMENTS ARE ALL WRITTEN FOR TWO ENGINES, BUT SINGLE ENGINES
WERE ACCOUNTED FOR AS LONG AS THIS METHOD IS USED.
TABLE E 3.1.1-0
TORQUE DATA SELECT 0 (S-76B/C+)
CHANNEL
RX429-8
CONNECT TO:
Eng #1 (low speed)
Fault Designation: ENGINE 1 BUS
Bus Type: Basic
A = J2-24
B = J2-07
CHANNEL
RX429-5
(Note 1)
Data
Torque
CONNECT TO:
Eng #2 (low speed)
Label
243
Sig. Bits
15
Range
799%
Signal Type
Basic
Resolution
0.1
Rate (ms)
200
Fault Designation: ENGINE 2 BUS
Bus Type: Basic
A = J2-21
B = J2-04
Data
Torque
Label
243
Sig. Bits
15
Range
799%
Signal Type
Basic
Resolution
0.1
Rate (ms)
200
Note 1: Digital Radar Altitude (type 2) can not be used with this configuration.
TABLE E 3.1.1-1
TORQUE DATA SELECT 1 (S-76C/A++)
SIGNAL
Engine Torque #1
CONNECTION
(+) = J1-26
SUMMARY DATA
Format: DC
(-) = J1-27
Input Type: Basic
Fault Designation: ENGINE TORQUE 1
Engine Torque #2
(+) = J1-66
(-) = J1-47
Format: DC
Input Type: Basic
Fault Designation: ENGINE TORQUE 2
TABLE E 3.1.1-2
TORQUE DATA SELECT 2 (S-76A/A+)
SIGNAL
Engine Torque #1
CONNECTION
(+) = J1-26
SUMMARY DATA
Format: DC
(-) = J1-27
Input Type: Basic
Fault Designation: ENGINE TORQUE 1
Validity: none
Engine Torque #2
(+) = J1-66
(-) = J1-47
Format: DC
Input Type: Basic
Fault Designation: ENGINE TORQUE 2
Validity: none
TABLE E 3.1.1-3
TORQUE DATA SELECT 3 (BELL 212/412)
SIGNAL
Engine Torque #1
CONNECTION
(X) = J2-1
SUMMARY DATA
Format: 5 Wire Synchro
(Y) = J2-2
Input Type: Basic
(Z) = J2-18
Fault Designation: ENGINE TORQUE 1
Reference
Validity: none
(H) = J2-34
(C) = J2-35
(X) = J2-19
(Y) = J2-20
(Z) = J2-3
Engine Torque #2
Format: 5 Wire Synchro
Input Type: Basic
Fault Designation: ENGINE TORQUE 2
Reference
(H) = J2-34
(C) = J2-35
Validity: none
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TABLE E 3.1.1-4
TORQUE DATA SELECT 4 (EC-155B, AS-365N3)
CHANNEL
RX429-8
CONNECT TO:
Eng #1 (high speed)
Fault Designation: ENGINE 1 BUS
Bus Type: Basic
A = J2-24
B = J2-07
CHANNEL
RX429-5
(Note 1)
Data
Torque
CONNECT TO:
Eng #2 (high speed)
Label
053
Sig. Bits
15
Range
0 to 180%
Signal Type
Basic
Resolution
0. 0078125
Rate (ms)
20
Fault Designation: ENGINE 2 BUS
Bus Type: Basic
A = J2-21
B = J2-04
Data
Torque
Label
053
Sig. Bits
15
Range
0 to 180%
Signal Type
Basic
Resolution
0. 0078125
Rate (ms)
20
Note 1: Digital Radar Altitude (type 2) can not be used with this configuration.
TABLE E 3.1.1-5
TORQUE DATA SELECT 5 (MD900/902, AGUSTA 109E)
Fault Designation: ENGINE 1 BUS
Bus Type: (RS-422 – 9600 baud)
CHANNEL
429_422RX_1
Note 1
CONNECT TO:
Eng #1
A = J2-36
B = J2-37
Data
Torque
Torque Valid
CONNECT TO:
Eng #2
Word
5
13
Sig. Bits
15
16
Range
256%
N/A
Signal Type
Basic
Basic
Resolution
0.0078125
N/A
Rate (ms)
250
250
CHANNEL
RX422-2
Note 1
Fault Designation: ENGINE 2 BUS
Bus Type: (RS-422 – 9600 baud)
A = J2-10
B = J2-11
Data
Torque
Torque Valid
Word
5
13
Sig. Bits
15
16
Range
256%
N/A
Signal Type
Basic
Basic
Resolution
0.0078125
N/A
Rate (ms)
250
250
Note 1: This type is only compatible with display type 242 that uses RX429-8 for range control.
TABLE E 3.1.1-6
TORQUE DATA SELECT 6 (SUPER PUMA)
SIGNAL
Engine Torque #1
CONNECTION
(+) = J1-26
SUMMARY DATA
Format: DC
(-) = J1-27
Input Type: Basic
Fault Designation: ENGINE TORQUE 1
Validity: none
Engine Torque #2
(+) = J1-66
(-) = J1-47
Format: DC
Input Type: Basic
Fault Designation: ENGINE TORQUE 2
Validity: none
TABLE E 3.1.1-7
TORQUE DATA SELECT 7 (AS365 DAUPHIN N1 & N2)
SIGNAL
Engine Torque #1
CONNECTION
(+) = J1-26
SUMMARY DATA
Format: DC
(-) = J1-27
Input Type: Basic
Fault Designation: ENGINE TORQUE 1
Validity: none
Engine Torque #2
(+) = J1-66
(-) = J1-47
Format: DC
Input Type: Basic
Fault Designation: ENGINE TORQUE 2
Validity: none
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TABLE E 3.1.1-8
TORQUE DATA SELECT 8 (AS365 DAUPHIN N3)
CHANNEL
RX429-8
CONNECT TO:
Eng #1 (low speed)
Fault Designation: ENGINE 1 BUS
Bus Type: Basic
A = J2-24
B = J2-07
CHANNEL
RX429-5
(Note 1)
Data
Torque
CONNECT TO:
Eng #2 (low speed)
Label
211
Sig. Bits
15
Range
799%
Signal Type
Basic
Resolution
0.1
Rate (ms)
100
Fault Designation: ENGINE 2 BUS
Bus Type: Basic
A = J2-21
B = J2-04
Data
Torque
Label
211
Sig. Bits
15
Range
799%
Signal Type
Basic
Resolution
0.1
Rate (ms)
100
Note 1: Digital Radar Altitude (type 2) can not be used with this configuration.
TABLE E 3.1.1-9
TORQUE DATA SELECT 9 (BELL 430)
CHANNEL
RX429-8
CONNECT TO:
Eng #1 (low speed)
Fault Designation: ENGINE 1 BUS
Bus Type: Basic
A = J2-24
B = J2-07
CHANNEL
RX429-5
(Note 1)
Data
Torque
CONNECT TO:
Eng #2 (low speed)
Label
050
Sig. Bits
15
Range
0 to +126
Signal Type
Basic
Resolution
0.1
Rate (ms)
100
Fault Designation: ENGINE 2 BUS
Bus Type: Basic
A = J2-21
B = J2-04
Data
Torque
Label
050
Sig. Bits
15
Range
0 to +126
Signal Type
Basic
Resolution
0.1
Rate (ms)
100
Note 1: Digital Radar Altitude (type 2) can not be used with this configuration.
TABLE E 3.1.1-10
TORQUE DATA SELECT 10 (BELL 407)
SIGNAL
Engine Torque #1
CONNECTION
(+) = J1-26
SUMMARY DATA
Format: DC
(-) = J1-27
Input Type: Basic
Fault Designation: ENGINE TORQUE 1
Validity: none
Engine Torque #2
(+) = J1-66
(-) = J1-47
Format: DC
Input Type: Basic
Fault Designation: ENGINE TORQUE 2
Validity: none
TABLE E 3.1.1-11
TORQUE DATA SELECT 11 (BELL 212/412)
SIGNAL
Engine Torque #1
CONNECTION
(+) = J1-26
SUMMARY DATA
Format: DC
(-) = J1-27
Input Type: Basic
Fault Designation: ENGINE TORQUE 1
Validity: none
Engine Torque #2
(+) = J1-66
(-) = J1-47
Format: DC
Input Type: Basic
Fault Designation: ENGINE TORQUE 2
Validity: none
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TABLE E 3.1.1-12
TORQUE DATA SELECT 14 (COAST GUARD HH-65)
SIGNAL
Engine Torque #1
CONNECTION
(+) = J1-26
SUMMARY DATA
Format: DC
(-) = J1-27
Input Type: Basic
Fault Designation: ENGINE TORQUE 1
Validity: none
Engine Torque #2
(+) = J1-66
(-) = J1-47
Format: DC
Input Type: Basic
Fault Designation: ENGINE TORQUE 2
Validity: none
TABLE E3.1.1-13
: TORQUE DATA SELECT 15 (GENERIC FIXED TORQUE 20%)
SIGNAL
CONNECTION SUMMARY DATA
Engine Torque #1
No Connection
No Connection
Format: Fixed Internal
Input Type: Basic
Fault Designation:
Format: Fixed Internal
Input Type: Basic
Fault Designation:
Engine Torque #2
TABLE E3.1.1-14
TORQUE DATA SELECT 16 (COMMON DC TORQUE)
SIGNAL
Engine Torque #1
CONNECTION
(+) = J1-26
SUMMARY DATA
Format: DC
(-) = J1-27
Input Type: Basic
Fault Designation: ENGINE TORQUE 1
Engine Torque #2
(+) = J1-66
(-) = J1-47
Format: DC
Input Type: Basic
Fault Designation: ENGINE TORQUE 2
TABLE E3.1.1-15
TORQUE DATA SELECT 17 (GENERIC SHADIN DC TO 429 CONVERTER)
CHANNEL
RX429-8
CONNECT TO:
Eng #1 (high speed)
Fault Designation: ENGINE 1 BUS
Bus Type: Basic
A = J2-24
B = J2-07
Data
Torque 1
Torque 2
Label
053
054
Sig. Bits
15
15
Range
0 to 180%
0 to 180%
Signal Type
Basic
Basic
Resolution
0. 0078125
0. 0078125
Rate (ms)
50
50
Note 1: The actual number of significant bits is 16 but 15 bits will support the data range. This is adjusted to make the input
processing work with the actual MSB = to bit 29.
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E 5.3.2
CATEGORY 2, AIR DATA INPUT SELECT
The following table provides identification of the Air Data source type. The entry in the Air Data Type corresponds to a
table that provides detailed information on the configuration. For example, the details for Air Data Type #2 are found in
Table E 3.1.2. In this category, only the following signals are defined:
•
•
•
•
•
Uncorrected Barometric Altitude in analog and/or RS-422 or ARINC 429 format, and associated validity.
Temperature (Outside Air or Static Air) in analog or ARINC 429 format.
Corrected Barometric Altitude in ARINC 429 format.
Barometric Rate in ARINC 429 format.
Computed Airspeed in ARINC 429 format.
TABLE E 3.1.2: AIR DATA INPUT SELECT FOR EGPWS MKXXII
ID
Description
Effectivity
Air Data Type
(Table E 3.1.2-x)
App.
-001
Cfg.
-001
0
0
Analog - altitude and 500Ω OAT (i.e., CIC
04077)
1
2
1
2
Digital – ARINC 429 (i.e., Bendix KDC 281) -001
-001
-001
Digital – ARINC 575 (i.e., Collins ADC-80,
-001
-001
-001
81, 82)
Analog - altitude and 500Ω OAT (i.e., Collins
ADS-65)
Analog - altitude and 500Ω OAT (i.e., CIC
02702)
3
4
5
3
4
5
-001
-001
-001
Digital – ARINC 429 with Corrected Altitude -001
label 204
(i.e., Bendix KDC 481T)
6
6
Digital – ARINC 429 without Baro Rate label
212
-001
-001
(i.e., Honeywell AZ-810)
10
11
10
11
-003
-004
-003
-004
Digital – ARINC 429 and 500Ω OAT (i.e.
Shadin 2000)
Analog – altitude and 500Ω OAT (i.e.,
Honeywell AZ-241 or AZ-800 with additional
OAT). (Note 1)
12
12
Analog – altitude and internal constant for
OAT (i.e., Honeywell AZ-800 or AZ-241).
(Note 1)
-006
-006
Note 1: The AZ-800 provides an OAT signal with reference provided by the ADC. This is not compatible with the EGPWS
interface. The AZ-241 provides no OAT interface. The customer may either add an additional OAT probe (ID 11) or use the
internal constant (ID 12). ID 11 is to be recommended in operations in temperature extremes.
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TABLE E 3.1.2-0: AIR DATA INPUT SELECT #0
SIGNAL
CONNECTION
SUMMARY DATA
Uncorrected Barometric
Altitude
(+) = J1-62
(-) = J1-43
Format: DC with Validity Flag
Input Type: Basic
Fault Designation: BAROMETRIC ALTITUDE FAULT
Validity: Barometric Alt Valid (+28V)
Format: DC
Outside Air Temp
Total Air Temperature
Input Type: Basic
Fault Designation: STATIC AIR TEMPERATURE FAULT
Probe element
Excitation:
5 V = J1-25
J1
25
(5 V Ref)
Temp Input
(probe element):
(+) = J1-63
(-) = J1-44
4.42 K Ohms
+
-
63
44
Temp In
Ground
GND = J1-53
Chassis Gnd
53
Note: Nominal 500 Ω Temperature Probe only.
Resistance @ 0°C: 500Ω 0.6Ω
Connection example:
CIC Temperature Sensor, P/N 05257 (2 wire). Connect positive lead
to both J1-25 and J1-63. Connect negative lead to both J1-44 and J1-
53 (Chassis Ground).
Other probes may have three contacts.
Substitute Ground Speed for Airspeed (airspeed is not available with this air data input)
CHANNEL
Computed Airspeed
No Connection
CONNECTION
J1-9
N/A
PIN TYPE
Input
PIN FUNCTION
DESIGNATION
REFERENCE
Polarity/Configuration
References
Barometric Altitude
Validity Discrete
(+28V)
28V_DISC_08
>+17V = Valid
< +4.4V = Invalid
6.6.19
4.2.7
Configuration Data
Derive Baro Altitude Rate
Type
Summary Data
Analog
Baro Altitude Rate is derived using
Uncorrected Barometric Altitude. Baro Rate
is not available with this air data source.
TABLE E 3.1.2-1: AIR DATA INPUT SELECT #1
CONNECT TO:
ADC #1 (Low Speed)
Format: ARINC 429
Data
Uncorrected. Baro. Alt
Computed Airspeed
Barometric Rate
Fault Designation: AIR DATA BUS
Bus Type: Basic
CHANNEL
429RX_2
A = J2-39
B = J2-38
Label
203
Sig. Bits
Range
Signal Type
Basic
Resolution
1.0
0.0625
16.0
Rate (ms)
31.3-62.5
62.5-125
31.3-62.5
250-500
17
14
11
11
±131,072 FT
±1024 KTS
±32768 FPM
512 Degrees
206
Basic
212
Basic
Static Air Temperature
213
Basic
0.25
TABLE E 3.1.2-2: AIR DATA INPUT SELECT #2
CONNECT TO:
ADC #1 (Low Speed)
Format: ARINC 575
Data
Uncorrected. Baro. Alt
Computed Airspeed
Barometric Rate
Fault Designation: AIR DATA BUS
Bus Type: Basic
CHANNEL
429RX_2
A = J2-39
B = J2-38
Label
203
Sig. Bits
Range
Signal Type
Basic
Resolution
1.0
0.125
10.0
Rate (ms)
31.3-62.5
62.5-125
31.3-62.5
250-500
17
13
11
10
±131,072 FT
±1024 KTS
±20480 FPM
±512 Degrees
206
Basic
212
Basic
Static Air Temperature
213
Basic
0.5
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TABLE E 3.1.2-3: AIR DATA INPUT SELECT #3
SIGNAL
CONNECTION
SUMMARY DATA
Uncorrected Barometric
Altitude
(+) = J1-62
(-) = J1-43
Format: DC with Validity Flag
Input Type: Basic
Fault Designation: BAROMETRIC ALTITUDE FAULT
Validity: Barometric Alt Valid (+28V)
Format: DC
Outside Air Temp
Total Air Temperature
Input Type: Basic
Fault Designation: STATIC AIR TEMPERATURE FAULT
Probe element
Excitation:
5 V = J1-25
J1
25
(5 V Ref)
Temp Input
(probe element):
(+) = J1-63
(-) = J1-44
4.42 K Ohms
+
-
63
44
Temp In
Ground
GND = J1-53
Chassis Gnd
53
Note: Nominal 500 Ω Temperature Probe only.
Resistance @ 0°C: 500Ω 0.6Ω
Connection example:
CIC Temperature Sensor, P/N 05257 (2 wire). Connect positive lead
to both J1-25 and J1-63. Connect negative lead to both J1-44 and J1-
53 (Chassis Ground).
Other probes may have three contacts.
Substitute Ground Speed for Airspeed (airspeed is not available with this air data input)
CHANNEL
Computed Airspeed
No Connection
CONNECTION
J1-9
N/A
PIN TYPE
Input
PIN FUNCTION
DESIGNATION
REFERENCE
Polarity/Configuration
References
Barometric Altitude
Validity Discrete
(+28V)
28V_DISC_08
>+17V = Valid
< +4.4V = Invalid
6.6.19
4.2.7
Configuration Data
Derive Baro Altitude Rate
Type
Summary Data
Analog
Baro Altitude Rate is derived using
Uncorrected Barometric Altitude. Baro Rate
is not available with this air data source.
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TABLE E 3.1.2-4: AIR DATA INPUT SELECT #4
SIGNAL
CONNECTION
SUMMARY DATA
Uncorrected Barometric
Altitude
(+) = J1-62
(-) = J1-43
Format: DC with Validity Flag
Input Type: Basic
Fault Designation: BAROMETRIC ALTITUDE FAULT
Validity: Barometric Alt Valid (+28V)
Format: DC
Outside Air Temp
Total Air Temperature
Input Type: Basic
Fault Designation: STATIC AIR TEMPERATURE FAULT
Probe element
Excitation:
5 V = J1-25
J1
25
(5 V Ref)
Temp Input
(probe element):
(+) = J1-63
(-) = J1-44
4.42 K Ohms
+
-
63
44
Temp In
Ground
GND = J1-53
Chassis Gnd
53
Note: Nominal 500 Ω Temperature Probe only.
Resistance @ 0°C: 500Ω 0.6Ω
Connection example:
CIC Temperature Sensor, P/N 05257 (2 wire). Connect positive lead
to both J1-25 and J1-63. Connect negative lead to both J1-44 and J1-
53 (Chassis Ground).
Other probes may have three contacts.
Substitute Ground Speed for Airspeed (airspeed is not available with this air data input)
CHANNEL
Computed Airspeed
No Connection
CONNECTION
J1-9
N/A
PIN TYPE
Input
PIN FUNCTION
DESIGNATION
REFERENCE
Polarity/Configuration
References
Barometric Altitude
Validity Discrete
(+28V)
28V_DISC_08
>+17V = Valid
< +4.4V = Invalid
6.6.19
4.2.7
Configuration Data
Derive Baro Altitude Rate
Type
Summary Data
Analog
Baro Altitude Rate is derived using
Uncorrected Barometric Altitude. Baro Rate
is not available with this air data source.
TABLE E 3.1.2-5: AIR DATA INPUT SELECT #5
CONNECT TO:
ADC #1 (Low Speed)
Format: ARINC 429
Data
Uncorrected. Baro. Alt
Corrected Baro. Alt
Computed Airspeed
Barometric Rate
Fault Designation: AIR DATA BUS
Bus Type: Basic
CHANNEL
429RX_2
A = J2-39
B = J2-38
Label
203
204
206
212
213
Sig. Bits
17
17
14
11
Range
Signal Type
Basic
Basic
Basic
Basic
Resolution
1.0
1.0
0.0625
16.0
0.25
Rate (ms)
31.3-62.5
31.3-62.5
62.5-125
31.3-62.5
250-500
±131,072 FT
±131,072 FT
±1024 KTS
±32678 FPM
±512 Degrees
Static Air Temperature
11
Basic
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TABLE E 3.1.2-6: AIR DATA INPUT SELECT #6
CONNECT TO:
ADC #1 (Low Speed)
Format: ARINC 429
Data
Uncorrected. Baro. Alt
Computed Airspeed
Static Air Temperature
Fault Designation: AIR DATA BUS
Bus Type: Basic
CHANNEL
429RX_2
A = J2-39
B = J2-38
Label
203
Sig. Bits
Range
Signal Type
Basic
Resolution
1.0
0.0625
0.25
Rate (ms)
31.3-62.5
62.5-125
250-500
17
14
11
±131,072 FT
±1024 KTS
±512 Degrees
206
Basic
213
Basic
Configuration Data
Type
Summary Data
Derive Baro Altitude Rate
Digital
Baro Altitude Rate is derived using
Uncorrected Barometric Altitude. Baro
Rate is not available with this air data
source.
TABLE E 3.1.2-10: AIR DATA INPUT SELECT #10
CONNECT TO:
CHANNEL
Fault Designation: AIR DATA BUS
Bus Type: Basic
ADC #1 (Low Speed)
429RX_2
Format: ARINC 429
A = J2-39
B = J2-38
Data
Label
203
204
206
212
Sig. Bits
17
17
14
Range
Signal Type
Basic
Basic
Basic
Basic
Resolution
1.0
1.0
0.0625
16.0
Rate (ms)
31.3-62.5
31.3-62.5
62.5-125
31.3-62.5
Uncorrected. Baro. Alt
Corrected Baro. Alt
Computed Airspeed
Barometric Rate
±131,072 FT
±131,072 FT
±1024 KTS
±32678 FPM
11
Outside Air Temp
Format: DC
Total Air Temperature
Input Type: Basic
Fault Designation: STATIC AIR TEMPERATURE FAULT
Probe element
Excitation:
5 V = J1-25
J1
25
(5 V Ref)
Temp Input
(probe element):
(+) = J1-63
(-) = J1-44
4.42 K Ohms
+
-
63
44
Temp In
Ground
GND = J1-53
Chassis Gnd
53
Note: Nominal 500 Ω Temperature Probe only.
Resistance @ 0°C: 500Ω 0.6Ω
Connection example:
CIC Temperature Sensor, P/N 05257 (2 wire). Connect positive lead
to both J1-25 and J1-63. Connect negative lead to both J1-44 and J1-
53 (Chassis Ground).
Other probes may have three contacts.
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TABLE E 3.1.2-11: AIR DATA INPUT SELECT #11
SIGNAL
CONNECTION
SUMMARY DATA
Uncorrected Barometric
Altitude
(+) = J1-62
(-) = J1-43
Format: DC with Validity Flag
Input Type: Basic
Fault Designation: BAROMETRIC ALTITUDE FAULT
Validity: Barometric Alt Valid (+28V)
Format: DC
Outside Air Temp
Total Air Temperature
Input Type: Basic
Fault Designation: STATIC AIR TEMPERATURE FAULT
Probe element
Excitation:
5 V = J1-25
J1
25
(5 V Ref)
Temp Input
(probe element):
(+) = J1-63
(-) = J1-44
4.42 K Ohms
+
-
63
44
Temp In
Ground
GND = J1-53
Chassis Gnd
53
Note: Nominal 500 Ω Temperature Probe only.
Resistance @ 0°C: 500Ω 0.6Ω
Connection example:
CIC Temperature Sensor, P/N 05257 (2 wire). Connect positive lead
to both J1-25 and J1-63. Connect negative lead to both J1-44 and J1-
53 (Chassis Ground).
Other probes may have three contacts.
Substitute Ground Speed for Airspeed (airspeed is not available with this air data
input).
Computed Airspeed
No Connection
N/A
CHANNEL
PIN FUNCTION
CONNECTION
PIN TYPE
Input
DESIGNATION
REFERENCE
28V_DISC_08
Polarity/Configuration
References
Barometric Altitude
Validity Discrete
(+28V)
J1-9
>+17V = Valid
< +4.4V = Invalid
6.6.19
4.2.7
Configuration Data
Derive Baro Altitude Rate
Type
Summary Data
Analog
Baro Altitude Rate is derived using
Uncorrected Barometric Altitude. Although
the AZ-241 provides Baro rate, the EGPWS
does not have an analog connection available.
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TABLE E 3.1.2-12: AIR DATA INPUT SELECT #12
SIGNAL
CONNECTION
SUMMARY DATA
Uncorrected Barometric
Altitude
(+) = J1-62
(-) = J1-43
Format: DC with Validity Flag
Input Type: Basic
Fault Designation: BAROMETRIC ALTITUDE FAULT
Validity: Barometric Alt Valid (+28V)
Format: Internal Constant 250C and Valid.
Input Type: Basic
Fault Designation: Static Air Temperature.
Substitute Ground Speed for Airspeed (airspeed is not available with this air data
input).
Outside Air Temp
No Connection
No Connection
Computed Airspeed
N/A
CHANNEL
PIN FUNCTION
CONNECTION
PIN TYPE
Input
DESIGNATION
REFERENCE
28V_DISC_08
Polarity/Configuration
References
Barometric Altitude
Validity Discrete
(+28V)
J1-9
>+17V = Valid
< +4.4V = Invalid
6.6.19
4.2.7
Configuration Data
Type
Summary Data
Derive Baro Altitude Rate
Analog
Baro Altitude Rate is derived using
Uncorrected Barometric Altitude. Although
the AZ-800 provides Baro rate, the EGPWS
does not have an analog connection available.
E 5.3.3
CATEGORY 3, POSITION INPUT SELECT
The following table provides identification of the Position source signal. Each entry in the Position Input Type column has a
corresponding table that provides detailed information on the configuration. For example, the details for Position Input Type
#0 are found in Table E 3.1.3-0.
In this category, only the following Position signals are defined:
•
•
•
•
•
•
Altitude
Date
Ground Speed
Horizontal Figure of Merit (HFOM)
Horizontal. Integrity Limit
Latitude Position
•
•
•
•
•
Longitude Position
Sensor Status
True Track Angle
Universal Time Correlation
Vertical Figure of Merit (VFOM)
TABLE E 3.1.3: POSITION INPUT SELECT FOR EGPWS MKXXII
Position
Input
Type
ID
Description
Effectivity
App. Cfg.
(TableE
3.1.3-x)
0
1
2
3
4
0
1
2
3
4
5
6
GPS, ARINC 429 low speed, 743A format
GPS, ARINC 429 low speed, 743 format
GPS, Internal (RS-232 GPS-PXPRESS format)
GPS, External (RS-232 GPS-PXPRESS format)
GPS, ARINC 429 high speed, 743A format
GPS, ARINC 429 high speed, 743 format
Dual GPS, ARINC 429 high speed, 743 format
-001
-001
-001
-001
-001
-001
-003
-001
-001
-001
-001
-001
-001
-003
5
255
Note 1: The GPS Altitude Reference in Category 7, Options 1 Select must be properly applied for the appropriate GPS
Position type. At the time of release of this document, all GPS sources except the Universal GPS1000 based systems are of
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MSL type. The Universal GPS1000 based GPS sources are of WGS-84 type. If the internal GPS source (ID=2) is defined,
the GPS altitude reference in Category 7 must be MSL.
Note 2: Universal GPS 1000 does not calculate VFOM and HFOM correctly which makes it an unacceptble position source
for helicopters.
TABLE E 3.1.3-0: POSITION INPUT TYPE 0 (LOW SPEED ARINC 743A GPS)
CONNECT TO:
Fault Designation: GPS BUS
Bus Type: Basic
CHANNEL
429RX_4
GPS (Low Speed)
per ARINC 743A-2
Data
A = J2-25
B = J2-8
Label
110
111
130
076
136
247
112
103
273
125
260
Sig. Bits
20
Range
Signal Type
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Resolution
0.00017166137695
0.00017166137695
0.00012207
0.125
*Rate (ms)
1000
1000
1000
1000
Latitude - Normal
Longitude - Normal
GPS Hor. Int. Limit
Altitude
±180 Degrees
±180 Degrees
16 nm
±131,072 FT
32768 ft
20
17
20
18
VFOM
0.125
1000
HFOM
18
16 nm
0.000061035
0.125
1000
1000
Ground Speed
True Track Angle
Sensor Status
**UTC
15
15
19
19
±4096 Knots
±180 Degrees
Discrete Wd
Discrete Wd
Discrete Wd
0.0054931640625
n/a
1000
1000
0.1 min
1000
**Date
19
1 day
1000
**This label is not required.
Data used if present
*Slowest acceptable update rate in milliseconds.
TABLE E 3.1.3-1: POSITION INPUT TYPE 1 (LOW SPEED ARINC 743 GPS)
CONNECT TO:
Fault Designation: GPS BUS
Bus Type: Basic
CHANNEL
429RX_4
GPS (Low Speed)
per ARINC 743
Data
Latitude - Normal
Longitude - Normal
GPS Hor. Int. Limit
Altitude
VFOM
HFOM
Ground Speed
True Track Angle
Sensor Status
**UTC
A = J2-25
B = J2-8
Label
110
111
130
076
136
247
112
103
273
125
260
Sig. Bits
20
20
17
20
15
15
15
15
Range
Signal Type
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Resolution
0.00017166137695
0.00017166137695
0.00012207
0.125
0.03125
0.03125
0.125
0.0054931640625
n/a
*Rate (ms)
1000
1000
1000
1000
1000
1000
1000
1000
±180 Degrees
±180 Degrees
16 nm
±131,072 FT
1024 meters
1024 meters
±4096 Knots
±180 Degrees
Discrete Wd
Discrete Wd
Discrete Wd
19
19
19
1000
1000
1000
0.1 min
1 day
**Date
**This label is not required.
Data used if present
*Slowest acceptable update rate in milliseconds.
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TABLE E 3.1.3-2: POSITION INPUT TYPE 2 (INTERNAL RS-232 GPS)
CHANNEL
GPS_RXA
GPS_TXA
Internal
Internal GPS
Fault Designation: INTERNAL GPS
Bus Type: Basic
[XPGPS_Int] = 1
(9600 baud)
Data
ID/byte
15/1-4
15/5-8
15/9-12
16/1-4
16/5-8
17/1-4
17/5-8
1C/0
Sig. Bits
Range
±180 Degrees
±180 Degrees
meters
Signal Type
Basic
Resolution
real single-precision
real single-precision
real single-precision
real single-precision
real single-precision
real single-precision
real single-precision
n/a
*Rate (ms)
1000
1000
1000
1000
1000
1000
1000
1000
Latitude
Longitude
HP Error
Altitude
32
32
32
32
32
32
32
8
Basic
Basic
Basic
Basic
Basic
Basic
Basic
meters
meters
VP Error
Ground Speed
True Track Angle
GPS State
Integrity State
Error Status
meters/sec
360 Degrees
Discrete Wd
Discrete Wd
Discrete Wd
1C/1
8
Basic
n/a
n/a
1000
1000
1C/6-7
8
Basic
* Slowest acceptable update rate in milliseconds.
Note: "MSL" reference must be selected when an internal GPS is utilized. Refer to Table 5.3.7
TABLE E 3.1.3-3: POSITION INPUT TYPE 3 (EXTERNAL RS232 GPS, PXPRESS FORMAT)
CHANNEL
GPS_RXA
GPS_TXA
External
J2-28 (cm)
J2-45 (Tx)
J2-29 (Rx)
Internal GPS
[XPGPS_Int] = 0
(9600 baud)
Data
Latitude
Fault Designation: GPS BUS
Bus Type: Basic
ID/byte
15/1-4
15/5-8
15/9-12
16/1-4
16/5-8
17/1-4
17/5-8
1C/0
Sig. Bits
Range
±180 Degrees
±180 Degrees
meters
Signal Type
Basic
Resolution
real single-precision
real single-precision
real single-precision
real single-precision
real single-precision
real single-precision
real single-precision
n/a
*Rate (ms)
1000
1000
1000
1000
1000
1000
1000
1000
32
32
32
32
32
32
32
8
Longitude
HP Error
Altitude
VP Error
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
meters
meters
Ground Speed
True Track Angle
GPS State
Integrity State
Error Status
meters/sec
360 Degrees
Discrete Wd
Discrete Wd
Discrete Wd
1C/1
1C/6-7
8
8
n/a
n/a
1000
1000
Basic
* Slowest acceptable update rate in milliseconds.
TABLE E 3.1.3-4: POSITION INPUT TYPE 4 (HIGH SPEED ARINC 743A GPS)
CONNECT TO:
Fault Designation: GPS BUS
Bus Type: Basic
CHANNEL
429RX_4
GPS (High Speed)
per ARINC 743A-2
Data
Latitude - Normal
Longitude - Normal
GPS Hor. Int. Limit
Altitude
VFOM
HFOM
Ground Speed
True Track Angle
Sensor Status
**UTC
A = J2-25
B = J2-8
Label
110
111
130
076
136
247
112
103
273
125
260
Sig. Bits
20
20
17
20
18
18
15
15
Range
Signal Type
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Resolution
0.00017166137695
0.00017166137695
0.00012207
0.125
0.125
0.000061035
0.125
*Rate (ms)
1000
1000
1000
1000
1000
1000
1000
1000
±180 Degrees
±180 Degrees
16 nm
±131,072 FT
32768 ft
16 nm
±4096 Knots
±180 Degrees
Discrete Wd
Discrete Wd
Discrete Wd
0.0054931640625
n/a
19
19
19
1000
1000
1000
0.1 min
1 day
**Date
**This label is not required.
Data used if present
*Slowest acceptable update rate in milliseconds.
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TABLE E 3.1.3-5: POSITION INPUT TYPE 5 (HIGH SPEED ARINC 743 GPS)
CONNECT TO:
Fault Designation: GPS BUS
Bus Type: Basic
CHANNEL
429RX_4
GPS (High Speed)
per ARINC 743
Data
Latitude - Normal
Longitude - Normal
GPS Hor. Int. Limit
Altitude
VFOM
HFOM
Ground Speed
True Track Angle
Sensor Status
**UTC
A = J2-25
B = J2-8
Label
110
111
130
076
136
247
112
103
273
125
260
Sig. Bits
20
20
17
20
15
15
15
15
Range
Signal Type
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Resolution
0.00017166137695
0.00017166137695
0.00012207
0.125
0.03125
0.03125
0.125
0.0054931640625
n/a
*Rate (ms)
1000
1000
1000
1000
1000
1000
1000
1000
±180 Degrees
±180 Degrees
16 nm
±131,072 FT
1024 meters
1024 meters
±4096 Knots
±180 Degrees
Discrete Wd
Discrete Wd
Discrete Wd
19
19
19
1000
1000
1000
0.1 min
1 day
**Date
**This label is not required.
Data used if present
*Slowest acceptable update rate in milliseconds.
TABLE E3.1.3-255: POSITION INPUT TYPE 255 (DUAL HIGH SPEED ARINC 743A GPS)
Fault Designation: GPS BUS 1
CONNECT TO:
GPS #1 (High Speed)
per ARINC 743A-2
CHANNEL
429RX_4
Bus Type: Basic
A = J2-25
B = J2-8
Data
Latitude - Normal
Longitude - Normal
GPS Hor. Int. Limit
Altitude
VFOM
HFOM
Ground Speed
True Track Angle
Sensor Status
**UTC
Label
110
111
130
076
136
247
112
103
273
125
260
Sig. Bits
20
20
17
20
18
18
15
15
Range
Signal Type
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Resolution
0.00017166137695
0.00017166137695
0.00012207
0.125
0.125
0.000061035
0.125
*Rate (ms)
1000
1000
1000
1000
1000
1000
1000
1000
±180 Degrees
±180 Degrees
16 nm
±131,072 FT
32768 ft
16 nm
±4096 Knots
±180 Degrees
Discrete Wd
Discrete Wd
Discrete Wd
0.0054931640625
n/a
19
19
19
1000
1000
1000
0.1 min
1 day
**Date
**This label is not required.
Data used if present
CONNECT TO:
GPS #2 (High Speed)
per ARINC 743A-2
Data
CHANNEL
429RX_7
Fault Designation: GPS BUS 2
Bus Type: Basic
A = J2-23
B = J2-6
Label
110
111
130
076
136
247
112
103
273
125
260
Sig. Bits
20
20
17
20
18
18
15
15
Range
Signal Type
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Basic
Resolution
0.00017166137695
0.00017166137695
0.00012207
0.125
0.125
0.000061035
0.125
*Rate (ms)
1000
1000
1000
1000
1000
1000
1000
1000
Latitude - Normal
Longitude - Normal
GPS Hor. Int. Limit
Altitude
VFOM
HFOM
Ground Speed
True Track Angle
Sensor Status
**UTC
±180 Degrees
±180 Degrees
16 nm
±131,072 FT
32768 ft
16 nm
±4096 Knots
±180 Degrees
Discrete Wd
Discrete Wd
Discrete Wd
0.0054931640625
n/a
19
19
19
1000
1000
1000
0.1 min
1 day
**Date
**This label is not required.
Data used if present
*Slowest acceptable update rate in milliseconds.
Note: This configuration may not be selected if an AHRS configuration is required for Attitude and Heading information
(refer to Category 10 type 1 and Category 11 type 1), due to the conflict with Channel 429RX-7.
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E 5.3.4
CATEGORY 4, ALTITUDE CALLOUTS
The following table provides identification of the Altitude Callouts Menu. Each entry in the ID column corresponds to a
particular menu selection.
The Altitude Callouts menu consists of standard callout options and Autorotation Mode reversion callout options. ID’s 0
through 127 consist of standard callouts while ID’s 128 through 255 include standard callouts and reversion to a set of
Autorotation callouts. Selecting ID 0 – 8 will result in the callouts listed being enunciated whether the aircraft is in
autorotation or not. Selecting ID 128 – 137 will result in the identified standard callouts if the aircraft is not in autorotation
and the autorotation callouts listed if the aircraft is in autorotation. The Autorotation Mode is defined by logic within the
EGPWC for helicopter types identified in Category 1.
Smart Callout activation (TRUE) is reflected by a “500” callout being spoken at the end of the selected callout menu
sequence in the Long Level 1 Self-Test. In addition, the Callout menu ID number and the “Smart Callout Selected”
configuration message, will both be given during level 3 Self-Test and in the RS232 Present Status display.
TABLE E 3.1.4: ALTITUDE CALLOUTS FOR EGPWS MKXXII
3
Smart Callout
Selected
Autorotation
ID
MENU
Effectivity
Callout Enable
App.
Cfg.
MINIMUMS-MINIMUMS,
“Smart 500”, 200, 100, 50, 40, 30, 20 ,10
MINIMUMS-MINIMUMS,
“Smart 500”, 200
0
1
False
False
True
True
-001
-001
-001
-001
MINIMUMS-MINIMUMS,
“Smart 500”, 100, 50, 40, 30, 20,10
MINIMUMS-MINIMUMS, “Smart 500”
MINIMUMS-MINIMUMS,
200, 100, 50, 40, 30, 20 ,10
MINIMUMS-MINIMUMS, 200
MINIMUMS-MINIMUMS,
100, 50, 40, 30, 20 ,10
MINIMUMS-MINIMUMS
MINIMUMS-MINIMUMS,
“Smart 500”, 200, 100, 50, 40, 30, 20 ,10
MINIMUMS-MINIMUMS,
“Smart 500”, 200
2
3
False
False
False
False
False
False
True
True
True
False
False
False
False
-001
-001
-001
-001
-001
-001
-003
-001
-001
-001
-001
-001
-001
-003
4
5
6
8
4
128
True
4
129
130
True
-003
-003
True
MINIMUMS-MINIMUMS,
“Smart 500”, 100, 50, 40, 30, 20 ,10
4
True
True
True
True
True
-003
-003
-003
-003
-003
-003
-003
-003
-003
-003
True
4
131 MINIMUMS-MINIMUMS, “Smart 500”
True
MINIMUMS-MINIMUMS,
200, 100, 50, 40, 30, 20 ,10
133 MINIMUMS-MINIMUMS, 200
132
False
False
False
MINIMUMS-MINIMUMS,
100, 50, 40, 30, 20 ,10
134
MINIMUMS-MINIMUMS,
100
135
True
False
-006
-006
136 MINIMUMS-MINIMUMS, 200, 100
137 MINIMUMS-MINIMUMS
True
True
False
False
-006
-006
-006
-006
3
4
The AUTOROTATION callouts consists of: 200, 100 during Autorotation, if Autorotation Callout Enabled is True.
The Smart Callout function will not be given if in autorotation.
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Note: Selecting an Altitude Callout ID without a minimums callout can be accomplished by leaving the Decision Height
input discrete open or connected to +28VDC.
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E 5.3.5
CATEGORY 5, AUDIO MENU SELECT
The following table provides identification of the Voice Menu type. Each entry in the Voice Menu column has a
corresponding table that provides detailed information on the configuration. For example, the details for Voice Menu # are
found in Table E 3.1.5-128.
TABLE E 3.1.5: AUDIO MENU TYPE
ID
Audio Menu Type
(Table E 3.1.5.-x)
128
Description
Effectivity
App
Cfg.
.
128
Basic Helicopter Menu
-006
-006
TABLE E 3.1.5-128: AUDIO MENU TYPE 128 (BASIC HELICOPTER)
ALERT/WARNING CONDITION
MODE 1 PULL UP
AUDIO MENU
NOTES
PULL UP
1
MODE 2 PULL UP PREFACE
MODE 2 PULL UP
TERRAIN TERRAIN
PULL UP
1, 2
1
TERRAIN AWARENESS PREFACE
TERRAIN AWARENESS WARNING
OBSTACLE AWARENESS PREFACE WARNING! OBSTACLE
OBSTACLE AWARENESS WARNING WARNING! OBSTACLE
WARNING! TERRAIN
WARNING! TERRAIN
1, 2
1, 3
1, 2
1, 3
MODE 2 TERRAIN
TERRAIN
MODE 6 MINIMUMS
SELECTED CALLOUTS (See 5.3.4)
MODE 6 ALTITUDE
ALTITUDE ALTITUDE (See 5.3.4)
TERRAIN AWARENESS CAUTION
OBSTACLE AWARENESS CAUTION CAUTION OBSTACLE (PAUSE) CAUTION OBSTACLE
CAUTION TERRAIN (PAUSE) CAUTION TERRAIN
4
4
MODE 4 TOO LOW TERRAIN
TCF TOO LOW TERRAIN
MODE 6 ALTITUDE CALLOUTS
MODE 4 TOO LOW GEAR
MODE 1 SINKRATE
TOO LOW TERRAIN
TOO LOW TERRAIN
SELECTED CALLOUTS (See 5.3.4)
TOO LOW GEAR
SINKRATE
5
Note: The basic warning is “SINKRATE (PAUSE) SINKRATE”.
However, if the Mode 1 Pullup curve is violated only a single “Sinkrate”
may occur prior to the pull up voice.
DON’T SINK (PAUSE) DON’T SINK
GLIDESLOPE
SELECTED CALLOUTS (See 5.3.4)
BANK ANGLE (PAUSE) BANK ANGLE,
BANK ANGLE BANK ANGLE (AlliedSignal Algorithm at low
altitudes)
MODE 3 DON’T SINK
MODE 5 GLIDESLOPE
MODE 6 APPROACHING DH
MODE 6 BANK ANGLE
MODE 6 TAIL STRIKE
TA&D INVALID ALERT
TAIL TOO LOW
BE ALERT TERRAIN INOP
Note 1: These are the only voices that can interrupt.
Note 2: The preface voices will always be given prior to the warning voice.
Note 3: Voice message is continuous.
Note 4: Voice message will repeat every 10 seconds.
Note 5: Long Self-Test will only issue a single 'Sinkrate".
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E 5.3.6
CATEGORY 6, TERRAIN DISPLAY SELECT
Section Overview
The following table (5.3.6) has an identification number (ID) associated with each Terrain Display configuration. Each of the
ID rows has a group number for the Display Configuration, the Input Control. The TA&D Pop Up Disable function is
defined by a Boolean. The ID groups will completely identify a particular Terrain Display Interface.
In this category the following signals are configured by the ID number:
Signal Name
Terrain Display Bus:
Range Bus:
Signal Type
KCPB* or ARINC
ARINC 429 or RS-422
Boolean
Defined By
Display Configuration Group
Display Input Control Group
Defined directly in Table
TA&D Alternate Pop Up
*KCPB is also known as AlliedSignal Picture Bus (ASPB)
TABLE E 3.1.6: TERRAIN DISPLAY SELECT FOR EGPWS MKXXII
TAD
and
ID
Type
Effectivity
Application Notes
KC Picture Bus (KCPB) (Note 1)
No Display
TAD And TCF Enabled
E 3.1.6-x- TCF Disable
x
-006
-006
0
False
1
False
2
3
4
5
True
False
False
False
False
TA&D / TCF Disabled
-006
-006
-006
-006
-006
Collins ProLine II (4x4) (Note 3)
Bendix PPI-4A/4B (Note 2)
Collins ProLine II (5x6) (Note 3)
Collins ProLine II (5x4,5x5) (Note 3)
6
Reserved
Reserved
9
-006
-006
-006
False
False
False
Non-Integrated EFIS 40/50 (Honeywell/Bendix)
Integrated EFIS 40/50 (Honeywell/Bendix)
Collins WXI-701/711, without Auto Range
Integrated Honeywell P880/660/440
(WXPD w/ SCI range)
10
12
-006
-006
-006
13
14
15
False
False
False
Bendix PPI-4A/4B without Auto Range (Note 2)
Integrated Honeywell P880/660/440
(WXPD w/ SCI range and aircraft symbol on overlay)
Bendix, IN182A, IN812A, (RDR 2000)
Bendix, IN842A, IN862A, (RDR 2100)
KC Picture Bus (KCPB) w/o presentation of Terrain
Awareness Corrected Altitude (Note 1, Note 7)
Collins ProLine 4 (Non-Intergrated)
-010
-010
16
17
False
False
-010
18
False
-011
-011
-006
-006
235
236
242
246
False
False
False
False
Collins ProLine 4 (Intergrated)
KC Picture Bus (KCPB) (Note 1, Note 6)
Non-Integrated EFIS 10 (Bendix/Honeywell)
Honeywell EDZ705 (5x5), EDZ756 (5x6) with DC-811
range push button control
-006
250
255
False
False
-006
Honeywell SPZ8000 (w/SCI range) (Note 4)
Note 1: For a description of the KCPB features implemented in a particular software release, see Appendix B: KCPB Phased
Implementation in the EGPWS Interface Methodology document 060-4303-000.
Note 2: This configuration is applicable to RDR-4B with a mod that makes it capable of displaying blue.
Note 3: Refer to Rockwell Collins Service Information Letter, EFIS 84/85/86 SIL 2-99 Dated March 16/99 or later revision,
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for information describing the requirements to interface an EGPWS to the Collins Pro Line II system equipped with EFIS
84/85/86 Displays and WXR-350/840/700 or TWR-850 Weather Radar systems.
Note 4: This interface only supports the SG-810 and SG-811 SPZ-8000. This display is defined for the –001 & -003 releases
but can cause periodic resets of the EGPWS due to an internal SCI range problem. The –001 & -003 release should not be
used for this display.
Note 5: Peaks Enable is always true regardless of the selection from Category 7 Table 5.3.7.
Note 6: This configuration is applicable to the Aircraft Type 133 (MD900/902) only. It is the only display configuration
supported for that Aircraft Type.
Note-7 With this configuration the EGPWC shall not overlay Terrain Awareness Corrected Altitude.
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Table E 3.1.6-0
KC Picture Bus
DISPLAY CONFIGURATION GROUP 0 (KC PICTURE BUS2)
Value
Function
Display Type
Sweep Type
Auto Pop Up
KC Picture Bus (KCPB)
Curtain (Vertical or Horizontal scan)
Category 7, Options Select Group #1
TA&D Alternate Pop Up: False
TA&D Alternate Pop Up: True
Pop Up On Caution or Warning
Never Pop Up
Peaks Mode
Category 7, Options Select Group #1
(Elevations via overlay)
Peaks Enable: False
Peaks Off
Peaks Enable: True
Peaks On
Manual select
Manual deselect
Auto Range
None (Display Control Selection)
None (Display Control Selection)
Controlled by display response (if selected a 10 nm range will be used)
Moving Marker
Overlay Page
Display bus type
None
Controlled by display
KCPB
DISPLAY BUS #1
453TX_1
CONNECT TO:
A = J1-58
B = J1-59
DISPLAY BUS #2
453TX_2
Terrain Display data
CONNECT TO:
A = J1-56
Terrain Display data
B = J1-57
DISPLAY INPUT CONTROL GROUP 0
CHANNEL
429_422RX_1
CONNECT TO:
KCPB-IND 429 out (range)
Bus 1 (Low Speed)
Fault Designation: KCPB BUS 1
Bus Type: Basic
A = J2-37
B = J2-36
Data
*Range
Query/Continuous Response
DSU Status Data (DSU only)
*Key Press/Display Mode
Label Sig. Bits
Range
0.5-1023.5NM
N/A
N/A
N/A
Signal Type Resolution
Rate (ms)
250
1000
1000
250
271
011
350
012
11
Basic
Basic
Basic
Basic
0.5
Discrete
Discrete
Discrete
N/A
N/A
N/A
CHANNEL
429RX_3
CONNECT TO:
Fault Designation: KCPB BUS 2
Bus Type: Basic
KCPB-IND 429 out (range)
Bus 2 (Low Speed)
Data
A = J2-41
B = J2-40
Label Sig. Bits
Range
0.5-1023.5NM
N/A
Signal Type Resolution
Rate (ms)
250
1000
1000
250
*Range
271
011
350
012
11
Basic
Basic
Basic
Basic
0.5
Query/Continuous Response
DSU Status Data (DSU only)
*Key Press/Display Mode
Discrete
Discrete
Discrete
N/A
N/A
N/A
N/A
N/A
OUTPUT 429 BUS GROUP 0
Channel
Pins
Comments
429TX_1 (Low Speed)
429TX_2
A = J2-43 B = J2-42
A = J2-26 B = J2-9
Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x and 7.1.4.x
No Connection (No Data Output)
Integration notes:
•
•
KCPB is also known as ASPB (AlliedSignal Picture Bus).
Label 012 is optional. The current fault and fault history message “RANGE” for label 271 (Range) is not shown if
Range Keys are requested on label 012 (Key Press/Display Mode).
•
When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels.
This prevents the EGPWS from reporting an external bus fault on the second channel.
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Table Table E 3.1.6-1 No Display – TAD and TCF Enabled
OUTPUT 429 BUS GROUP 0
Channel
Pins
Comments
429TX_1 (Low Speed)
429TX_2
A = J2-43 B = J2-42
A = J2-26 B = J2-9
Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x and 7.1.4.x
No Connection (No Data Output)
Table Table E 3.1.6-2 TA&D / TCF Disabled
OUTPUT 429 BUS GROUP 0
Channel
Pins
Comments
429TX_1 (Low Speed)
429TX_2
A = J2-43 B = J2-42
A = J2-26 B = J2-9
Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x and 7.1.4.x
No Connection (No Data Output)
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Table Table E 3.1.6-3 Collins ProLine II (4x4)
DISPLAY CONFIGURATION GROUP 6 (COLLINS PRO-LINE II, 4X4)
Function
Value
Display Type
Sweep Type
Auto Pop Up
Collins Pro-Line II (4x4) Display
Standard with +/-60 degree limit
Category 7, Options Select Group #1
TA&D Alternate Pop Up: False
TA&D Alternate Pop Up: True
Pop Up On Caution or Warning
Never Pop Up
Peaks Mode
Category 7, Options Select Group #1
(Elevations via overlay)
Peaks Enabled: False
Peaks Enabled: True
Peaks Off
Peaks On
Auto Range
Moving Marker
Overlay Page
No
No
Yes; “TERR” located on the left side of display.
Peaks Elevations located on the upper left side of Terrain image.
Standard ARINC 453
Display bus type
DISPLAY BUS #1
453TX_1
CONNECT TO:
A = J1-58
B = J1-59
Terrain Display data to switching relay/Symbol Generator
CONNECT TO:
DISPLAY BUS #2
453TX_2
A = J1-56
Terrain Display data to switching relay/Symbol Generator
B = J1-57
DISPLAY INPUT CONTROL GROUP 1
CHANNEL
429_422RX_1
CONNECT TO:
WX-IND 429 out (range)
Bus 1 (Low Speed)
Fault Designation: DISPLAY BUS 1
Bus Type: Basic
A = J2-37
B = J2-36
Data
Label Sig. Bits
Range
5-320NM
Signal Type Resolution
Basic N/A
Rate (ms)
100
Range (Display Word 2)
271
Discrete
CHANNEL
429RX_3
CONNECT TO:
WX-IND 429 out (range)
Bus 2 (Low Speed)
Data
Fault Designation: DISPLAY BUS 2
Bus Type: Basic
A = J2-41
B = J2-40
Label Sig. Bits
271 Discrete
PIN FUNCTION
Range
5-320NM
Signal Type Resolution
Basic N/A
Rate (ms)
100
Range (Display Word 2)
CONN PIN #
J1-32
REFERENCE NAME
GND_DISC_12
Polarity/Configuration
Type 1 (Momentary)
Display Select Discrete #1
Gnd = Display Select Toggle
<not> Gnd = Normal
J1-31
GND_DISC_13
Display Select Discrete #2
Type 1 (Momentary)
Gnd = Display Select Toggle
<not> Gnd = Normal
OUTPUT 429 BUS GROUP 0
Channel
Pins
Comments
429TX_1 (Low Speed)
429TX_2
A = J2-43 B = J2-42
A = J2-26 B = J2-9
Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x and 7.1.4.x
No Connection (No Data Output)
Integration note:
When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This
prevents the EGPWS from reporting an external bus fault on the second channel.
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MK XXII EGPWS Installation Manual
Table Table E 3.1.6-4 Bendix PPI-4A/4B
DISPLAY CONFIGURATION GROUP 1 (BENDIX RDR 4A/B PPI WITH MOD )
Function
Display Type
Sweep Type
Value
Bendix PPI-4A/4B (MAP-MODE)
Standard
Auto Pop Up
Category 7, Options Select Group #1
TA&D Alternate Pop Up: False
TA&D Alternate Pop Up: True
Pop Up On Caution or Warning
Never Pop Up
Peaks Mode
Category 7, Options Select Group #1
(Elevations via overlay)
Peaks Enable: False
Peaks Enable: True
Peaks Off
Peaks On
Manual select
Manual deselect
Auto Range
Moving Marker
Overlay Page
Anytime
Anytime
Yes 10NM
No
Without Peaks: “TERR” located in the lower right corner.
With Peaks: Peaks numbers located in the lower right corner.
Standard ARINC 453
Display bus type
DISPLAY BUS #1
453TX_1
CONNECT TO:
A = J1-58
B = J1-59
DISPLAY BUS #2
453TX_2
Terrain Display data to switching relay/Symbol Generator
CONNECT TO:
A = J1-56
Terrain Display data to switching relay/Symbol Generator
B = J1-57
DISPLAY INPUT CONTROL GROUP 1
CHANNEL
429_422RX_1
CONNECT TO:
WX-IND 429 out (range)
Bus 1 (Low Speed)
Fault Designation: DISPLAY BUS 1
Bus Type: Basic
A = J2-37
B = J2-36
Data
Label Sig. Bits
Range
5-320NM
Signal Type Resolution
Basic N/A
Rate (ms)
100
Range (Display Word 2)
271
Discrete
CHANNEL
429RX_3
CONNECT TO:
WX-IND 429 out (range)
Bus 2 (Low Speed)
Data
Fault Designation: DISPLAY BUS 2
Bus Type: Basic
A = J2-41
B = J2-40
Label Sig. Bits
271 Discrete
PIN FUNCTION
Range
5-320NM
Signal Type Resolution
Basic N/A
Rate (ms)
100
Range (Display Word 2)
CONN PIN #
J1-32
REFERENCE NAME
GND_DISC_12
Polarity/Configuration
Type 1 (Momentary)
Display Select Discrete #1
Gnd = Display Select Toggle
<not> Gnd = Normal
J1-31
GND_DISC_13
Display Select Discrete #2
Type 1 (Momentary)
Gnd = Display Select Toggle
<not> Gnd = Normal
OUTPUT 429 BUS GROUP 0
Channel
Pins
Comments
429TX_1 (Low Speed)
429TX_2
A = J2-43 B = J2-42
A = J2-26 B = J2-9
Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x and 7.1.4.x
No Connection (No Data Output)
Integration note:
When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This
prevents the EGPWS from reporting an external bus fault on the second channel.
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MK XXII EGPWS Installation Manual
Table E 3.1.6-5
Collins ProLine II (5x6)
DISPLAY CONFIGURATION GROUP 2 (COLLINS PROLINE II, 5X6)
Function
Value
Display Type
Sweep Type
Auto Pop Up
Collins ProLine II (5x6)
Standard with +/-60 degree limit
Category 7, Options Select Group #1
TA&D Alternate Pop Up: False
TA&D Alternate Pop Up: True
Pop Up On Caution or Warning
Never Pop Up
Peaks Mode
Category 7, Options Select Group #1
(Available as of -003)
Peaks Enabled: False
Peaks Enabled: True
Peaks Off
Peaks On
Manual select
Manual deselect
Auto Range
Anytime
Anytime
No
Moving Marker
Overlay Page
No
Yes; “TERR” is located on the right side of display.
“TERR” and Peaks Elevations located on upper left side of Terrain
image as of –003.
Display bus type
Standard ARINC 453
DISPLAY BUS #1
453TX_1
CONNECT TO:
A = J1-58
B = J1-59
Terrain Display data to switching relay/Symbol Generator
CONNECT TO:
DISPLAY BUS #2
453TX_2
A = J1-56
Terrain Display data to switching relay/Symbol Generator
B = J1-57
DISPLAY INPUT CONTROL GROUP 1
CHANNEL
429_422RX_1
CONNECT TO:
WX-IND 429 out (range)
Bus 1 (Low Speed)
Fault Designation: DISPLAY BUS 1
Bus Type: Basic
A = J2-37
B = J2-36
Data
Label Sig. Bits
Range
5-320NM
Signal Type Resolution
Basic N/A
Rate (ms)
100
Range (Display Word 2)
271
Discrete
CHANNEL
429RX_3
CONNECT TO:
WX-IND 429 out (range)
Bus 2 (Low Speed)
Data
Fault Designation: DISPLAY BUS 2
Bus Type: Basic
A = J2-41
B = J2-40
Label Sig. Bits
271 Discrete
PIN FUNCTION
Range
5-320NM
Signal Type Resolution
Basic N/A
Rate (ms)
100
Range (Display Word 2)
CONN PIN #
J1-32
REFERENCE NAME
GND_DISC_12
Polarity/Configuration
Type 1 (Momentary)
Display Select Discrete #1
Gnd = Display Select Toggle
<not> Gnd = Normal
J1-31
GND_DISC_13
Display Select Discrete #2
Type 1 (Momentary)
Gnd = Display Select Toggle
<not> Gnd = Normal
OUTPUT 429 BUS GROUP 0
Channel
Pins
Comments
429TX_1 (Low Speed)
429TX_2
A = J2-43 B = J2-42
A = J2-26 B = J2-9
Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x and 7.1.4.x
No Connection (No Data Output)
Integration note:
When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This
prevents the EGPWS from reporting an external bus fault on the second channel.
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MK XXII EGPWS Installation Manual
Table E 3.1.6-6
Collins ProLine II (5x4,5x5)
DISPLAY CONFIGURATION GROUP 3 (COLLINS PROLINE II, 5X4, 5X5)
Function
Value
Display Type
Sweep Type
Auto Pop Up
Collins ProLine II (5x4, 5x5) Display
Standard with +/-60 degree limit
Category 7, Options Select Group #1
TA&D Alternate Pop Up: False
TA&D Alternate Pop Up: True
Pop Up On Caution or Warning
Never Pop Up
Peaks Mode
Category 7, Options Select Group #1
(Available as of –003)
Peaks Enabled: False
Peaks Enabled: True
Peaks Off
Peaks On
Auto Range
Moving Marker
Overlay Page
No
No
Yes; “TERR” is located on the right side of display.
“TERR” or Peaks Elevations located on upper left side of Terrain image
as of -003.
Display bus type
DISPLAY BUS #1
453TX_1
Standard ARINC 453
CONNECT TO:
A = J1-58
B = J1-59
Terrain Display data to switching relay/Symbol Generator
CONNECT TO:
DISPLAY BUS #2
453TX_2
A = J1-56
Terrain Display data to switching relay/Symbol Generator
B = J1-57
DISPLAY INPUT CONTROL GROUP 1
CHANNEL
429_422RX_1
CONNECT TO:
WX-IND 429 out (range)
Bus 1 (Low Speed)
Fault Designation: DISPLAY BUS 1
Bus Type: Basic
A = J2-37
B = J2-36
Data
Label Sig. Bits
Range
5-320NM
Signal Type Resolution
Basic N/A
Rate (ms)
100
Range (Display Word 2)
271
Discrete
CHANNEL
429RX_3
CONNECT TO:
WX-IND 429 out (range)
Bus 2 (Low Speed)
Data
Fault Designation: DISPLAY BUS 2
Bus Type: Basic
A = J2-41
B = J2-40
Label Sig. Bits
271 Discrete
PIN FUNCTION
Range
5-320NM
Signal Type Resolution
Basic N/A
Rate (ms)
100
Range (Display Word 2)
CONN PIN #
J1-32
REFERENCE NAME
GND_DISC_12
Polarity/Configuration
Type 1 (Momentary)
Display Select Discrete #1
Gnd = Display Select Toggle
<not> Gnd = Normal
J1-31
GND_DISC_13
Display Select Discrete #2
Type 1 (Momentary)
Gnd = Display Select Toggle
<not> Gnd = Normal
OUTPUT 429 BUS GROUP 0
Channel
Pins
Comments
429TX_1 (Low Speed)
429TX_2
A = J2-43 B = J2-42
A = J2-26 B = J2-9
Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x and 7.1.4.x
No Connection (No Data Output)
Integration note:
When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This
prevents the EGPWS from reporting an external bus fault on the second channel.
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MK XXII EGPWS Installation Manual
Table E 3.1.6-9
Non-Integrated EFIS 40/50 (Honeywell/Bendix)
DISPLAY CONFIGURATION GROUP 7 (NON-INTEGRATED EFIS 40/50)
Function
Value
Bendix Non-Integrated EFIS 40/50
Sweep range +/- 60 degrees
Category 7, Options Select Group #1
TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True
Display Type
Sweep Type
Auto Pop Up
Pop Up when display is in the
proper mode.
Never Pop Up
Peaks Mode (Peaks
Category 7, Options Select Group #1
Elevations are in Terrain
Image, replacing “TERR”)
Peaks Enabled: False
Peaks Enabled: True
Peaks Off
Peaks On
Manual select
Manual deselect
Auto Range
Anytime WXR is on and display is in proper Mode
Anytime
No
Moving Marker
Overlay Page
Display bus type
No
Yes; “TERR” at upper right corner of display.
Standard ARINC 453
DISPLAY BUS #1
453TX_1
CONNECT TO:
A = J1-58
Terrain Display data to switching relay/Symbol Generator
B = J1-59
DISPLAY BUS #2
453TX_2
CONNECT TO:
A = J1-56
Terrain Display data to switching relay/Symbol Generator
B = J1-57
DISPLAY INPUT CONTROL GROUP 2
CHANNEL
429_422RX_1
CONNECT TO:
Fault Designation: DISPLAY BUS 1
Bus Type: Basic
WX-IND 429 out (range)
Bus 1 (Low Speed)
Data
Mode (Display Word 1)
Range (Display Word 2)
Discrete Word (VP)
A = J2-37
B = J2-36
Label Sig. Bits
Range
Signal Type Resolution Rate
270
271
273
Discrete
Discrete
Discrete
Mode, Tilt, Gain
5-320NM
VP Mode, Bit 11
Basic
Basic
Basic
N/A
N/A
N/A
100 ms
100 ms
100 ms
CHANNEL
429RX_3
CONNECT TO:
Fault Designation: DISPLAY BUS 2
Bus Type: Basic
WX-IND 429 out (range)
Bus 2 (Low Speed)
Data
Mode (Display Word 1)
Range (Display Word 2)
Discrete Word (VP)
A = J2-41
B = J2-40
Label Sig. Bits
Range
Signal Type Resolution Rate
270
271
273
Discrete
Discrete
Discrete
Mode, Tilt, Gain
5-320NM
VP Mode, Bit 11
Basic
Basic
Basic
N/A
N/A
N/A
100 ms
100 ms
100 ms
CONN PIN #
J1-32
REFERENCE NAME
GND_DISC_12
PIN FUNCTION
Display Select Discrete #1
Polarity/Configuration
Type 1 (Momentary)
Gnd = Display Select Toggle
<not> Gnd = Normal
J1-31
GND_DISC_13
Display Select Discrete #2
Type 1 (Momentary)
Gnd = Display Select Toggle
<not> Gnd = Normal
OUTPUT 429 BUS GROUP 0
Channel
Pins
Comments
429TX_1 (Low Speed)
429TX_2
A = J2-43 B = J2-42
A = J2-26 B = J2-9
Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x and 7.1.4.x
No Connection (No Data Output)
Integration note:
When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This
prevents the EGPWS from reporting an external bus fault on the second channel.
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MK XXII EGPWS Installation Manual
Table E 3.1.6-10
Integrated EFIS 40/50 (Honeywell/Bendix)
DISPLAY CONFIGURATION GROUP 8 (INTEGRATED EFIS 40/50)
Function
Display Type
Sweep Type
Value
Bendix Integrated EFIS 40/50
Sweep range +/- 90 degrees
Auto Pop Up
Category 7, Options Select Group #1
TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True
Pop Up on Terrain Caution or
Warning.
Never Pop Up
Peaks Mode
Peaks Always Enabled
The EFIS display supplies the Peak Elevations as stroked characters.
The EFIS can be configured to place the Elevations on the bottom left
or right side of the display.
Manual select
Manual deselect
Auto Range
Anytime
Anytime
Yes, to 10 nm on Terrain Caution or Warning.
Moving Marker
Overlay Page
Display bus type
No
No, the display supplies a “TERR” mode annunciation.
Standard ARINC 453
DISPLAY BUS #1
453TX_1
CONNECT TO:
A = J1-58 B = J1-59
Terrain Display data to switching relay/Symbol Generator
DISPLAY BUS #2
453TX_2
CONNECT TO:
A = J1-56 B = J1-57
Terrain Display data to switching relay/Symbol Generator
DISPLAY INPUT CONTROL GROUP 2
CHANNEL
429_422RX_1
CONNECT TO:
WX-IND 429 out (range)
Bus 1 (Low Speed)
Fault Designation: DISPLAY BUS 1
Bus Type: Basic
A = J2-37
B = J2-36
Data
Label Sig. Bits
Range
Mode, Tilt, Gain
5-320NM
Signal Type Resolution Rate
Mode (Display Word 1)
Range (Display Word 2)
Discrete Word (VP)
270
271
273
Discrete
Discrete
Discrete
Basic
Basic
Basic
N/A
N/A
N/A
100 ms
100 ms
100 ms
VP Mode, Bit 11
CHANNEL
429RX_3
CONNECT TO:
Fault Designation: DISPLAY BUS 2
Bus Type: Basic
WX-IND 429 out (range)
Bus 2 (Low Speed)
Data
Mode (Display Word 1)
Range (Display Word 2)
Discrete Word (VP)
A = J2-41
B = J2-40
Label Sig. Bits
Range
Signal Type Resolution Rate
270
271
273
Discrete
Discrete
Discrete
Mode, Tilt, Gain
5-320NM
VP Mode, Bit 11
Basic
Basic
Basic
N/A
N/A
N/A
100 ms
100 ms
100 ms
CONN PIN #
J1-32
REFERENCE NAME
GND_DISC_12
PIN FUNCTION
Display Select Discrete #1
Polarity/Configuration
Type 1 (Momentary)
Gnd = Display Select Toggle
<not> Gnd = Normal
J1-31
GND_DISC_13
Display Select Discrete #2
Type 1 (Momentary)
Gnd = Display Select Toggle
<not> Gnd = Normal
OUTPUT 429 BUS GROUP 0
Channel
Pins
Comments
429TX_1 (Low Speed)
429TX_2
A = J2-43 B = J2-42
A = J2-26 B = J2-9
Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x and 7.1.4.x
No Connection (No Data Output)
Integration note:
•
Peaks Elevations are transmitted digitally to the display via Label 025 on the ARINC453 bus; they are then display as
stroked charters on the bottom left or right of the display (depending on EFIS strapping).
•
To Pop Up for a Terrain Caution or Warning it is necessary for the EFIS to receive two discrete signals from the EGPWS
(one to indicate that Terrain is selected and one to indicate that selection was due to an alert). The EFIS needs to
distinguish between manual selection and alert conditions so it will know when it should autorange. Both EFIS and
EGPWS start to autorange on a Caution or Warning to minimize any latency problem displaying status during an alert.
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MK XXII EGPWS Installation Manual
•
When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels.
This prevents the EGPWS from reporting an external bus fault on the second channel.
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MK XXII EGPWS Installation Manual
Table E 3.1.6-12
Collins WXI-701/711, without Auto Range
DISPLAY CONFIGURATION GROUP 10 (COLLINS WXI 701/711 PPI, WITHOUT AUTO RANGE)
Function
Display Type
Sweep Type
Auto Pop Up
Value
Collins WXI-701/711 PPI
Fan
Category 7, Options Select Group #1
TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True
Pop Up On Caution or Warning
Never Pop Up
Peaks Mode
Category 7, Options Select Group #1
Peaks Enable: False
Peaks Enable: True
Peaks Off
Peaks On
Manual select
Manual deselect
Auto Range
Anytime
Anytime
No
Moving Marker
Overlay Page
No
Without Peaks: “TERR” located at the bottom left of display.
With Peaks: Peaks numbers lower left.
Display bus type
DISPLAY BUS #1
453TX_1
Standard ARINC 453
CONNECT TO:
A = J1-58
B = J1-59
DISPLAY BUS #2
453TX_2
Terrain Display data to switching relay/Symbol Generator
CONNECT TO:
A = J1-56
Terrain Display data to switching relay/Symbol Generator
B = J1-57
DISPLAY INPUT CONTROL GROUP 1
CHANNEL
429_422RX_1
CONNECT TO:
WX-IND 429 out (range)
Bus 1 (Low Speed)
Fault Designation: DISPLAY BUS 1
Bus Type: Basic
A = J2-37
B = J2-36
Data
Label Sig. Bits
Range
5-320NM
Signal Type Resolution
Basic N/A
Rate (ms)
100
Range (Display Word 2)
271
Discrete
CHANNEL
429RX_3
CONNECT TO:
WX-IND 429 out (range)
Bus 2 (Low Speed)
Data
Fault Designation: DISPLAY BUS 2
Bus Type: Basic
A = J2-41
B = J2-40
Label Sig. Bits
271 Discrete
PIN FUNCTION
Range
5-320NM
Signal Type Resolution
Basic N/A
Rate (ms)
100
Range (Display Word 2)
CONN PIN #
J1-32
REFERENCE NAME
GND_DISC_12
Polarity/Configuration
Type 1 (Momentary)
Display Select Discrete #1
Gnd = Display Select Toggle
<not> Gnd = Normal
J1-31
GND_DISC_13
Display Select Discrete #2
Type 1 (Momentary)
Gnd = Display Select Toggle
<not> Gnd = Normal
OUTPUT 429 BUS GROUP 0
Channel
Pins
Comments
429TX_1 (Low Speed)
429TX_2
A = J2-43 B = J2-42
A = J2-26 B = J2-9
Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x and 7.1.4.x
No Connection (No Data Output)
Integration note:
•
•
Left/Right shift keys on the display are not to be used when displaying terrain.
When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels.
This prevents the EGPWS from reporting an external bus fault on the second channel.
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MK XXII EGPWS Installation Manual
Table E 3.1.6-13
Integrated Honeywell P880/660/440 (WXPD w/ SCI range)
Display Configuration Group 11 (Honeywell Integrated P880/660/440).
Function
Display Type
Sweep Type
Value
Honeywell Integrated P880/660/440 radar displays
Honeywell
Auto Pop Up
Category 7, Options Select Group #1
TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True
Pop Up On Caution or Warning
Never Pop Up
Peaks Mode
Category 7, Options Select Group #1
Peaks Enable: False
Peaks Enable: True
Peaks Off
Peaks On
Manual select
Manual deselect
Auto Range
Anytime
Anytime
No
Moving Marker
Overlay Page
Display bus type
TERRAIN DISPLAY BUS #1
453TX_1
Yes (across bottom of display)
Yes, for Peaks Elevations only
Honeywell picture bus
CONNECT TO:
A = J1-58
Terrain Display data to switching relay/Symbol Generator #1
B = J1-59
TERRAIN DISPLAY BUS #2
453TX_2
CONNECT TO: Not supported for this display type
DISPLAY INPUT CONTROL GROUP 3
CHANNEL
429_422RX_1
CONNECT TO:
SCI Bus 1
1.1.1.1.1.1 Fault Designation: DISPLAY BUS 1
(RS-422 - 12K baud)
Bus Type: Basic
A = J2-36
B = J2-37
Data
Label Sig. Bits
Range
2000NM
Signal Type Resolution
Basic N/A
Rate (ms)
100
Range (Mode/Range Word)
80
4 Discrete
CONN PIN #
J1-32
REFERENCE NAME
GND_DISC_12
PIN FUNCTION
Display Select Discrete #1
Polarity/Configuration
Type 1 (Momentary)
Gnd = Display Select Toggle
<not> Gnd = Normal
OUTPUT 429 BUS GROUP 0
Channel
Pins
Comments
429TX_1 (Low Speed)
429TX_2
A = J2-43 B = J2-42
A = J2-26 B = J2-9
Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x and 7.1.4.x
No Connection (No Data Output)
Integration note:
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MK XXII EGPWS Installation Manual
Table E 3.1.6-14
Bendix PPI-4A/4B without Auto Range
DISPLAY CONFIGURATION GROUP 12 (BENDIX RDR 4A/B PPI WITHOUT AUTORANGE, WITH MOD )
Function
Display Type
Sweep Type
Value
Bendix PPI-4A/4B (MAP-MODE)
Standard
Auto Pop Up
Category 7, Options Select Group #1
TA&D Alternate Pop Up: False
TA&D Alternate Pop Up: True
Pop Up On Caution or Warning
Never Pop Up
Peaks Mode
Category 7, Options Select Group #1
(Elevations via overlay)
Peaks Enable: False
Peaks Enable: True
Peaks Off
Peaks On
Manual select
Manual deselect
Auto Range
Anytime
Anytime
No
Moving Marker
Overlay Page
No
Without Peaks: “TERR” located in the lower right corner.
With Peaks: Peaks numbers located in the lower right corner.
Standard ARINC 453
Display bus type
TERRAIN DISPLAY BUS #1
453TX_1
CONNECT TO:
A = J1-58
B = J1-59
TERRAIN DISPLAY BUS #2
453TX_2
Terrain Display data to switching relay/Symbol Generator
CONNECT TO:
A = J1-56
Terrain Display data to switching relay/Symbol Generator
B = J1-57
DISPLAY INPUT CONTROL GROUP 1
CHANNEL
429_422RX_1
CONNECT TO:
WX-IND 429 out (range)
Bus 1 (Low Speed)
Fault Designation: DISPLAY BUS 1
Bus Type: Basic
A = J2-37
B = J2-36
Data
Label Sig. Bits
Range
5-320NM
Signal Type Resolution
Basic N/A
Rate (ms)
100
Range (Display Word 2)
271
Discrete
CHANNEL
429RX_3
CONNECT TO:
WX-IND 429 out (range)
Bus 2 (Low Speed)
Data
Fault Designation: DISPLAY BUS 2
Bus Type: Basic
A = J2-41
B = J2-40
Label Sig. Bits
271 Discrete
PIN FUNCTION
Range
5-320NM
Signal Type Resolution
Basic N/A
Rate (ms)
100
Range (Display Word 2)
CONN PIN #
J1-32
REFERENCE NAME
GND_DISC_12
Polarity/Configuration
Type 1 (Momentary)
Display Select Discrete #1
Gnd = Display Select Toggle
<not> Gnd = Normal
J1-31
GND_DISC_13
Display Select Discrete #2
Type 1 (Momentary)
Gnd = Display Select Toggle
<not> Gnd = Normal
OUTPUT 429 BUS GROUP 0
Channel
Pins
Comments
429TX_1 (Low Speed)
429TX_2
A = J2-43 B = J2-42
A = J2-26 B = J2-9
Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x and 7.1.4.x
No Connection (No Data Output)
Integration note:
•
When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels.
This prevents the EGPWS from reporting an external bus fault on the second channel.
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MK XXII EGPWS Installation Manual
Table E 3.1.6-15
Integrated Honeywell P880/660/440
(Honeywell Integrated P880/660/440 with A/C symbol)
Value
Honeywell Integrated P880/660/440 radar displays with A/C symbol
Honeywell
Function
Display Type
Sweep Type
Auto Pop Up
Category 7, Options Select Group #1
TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True
Pop Up On Caution or Warning
Never Pop Up
Peaks Mode
Category 7, Options Select Group #1
Peaks Enable: False
Peaks Enable: True
Peaks Off
Peaks On
Manual select
Manual deselect
Auto Range
Anytime
Anytime
No
Moving Marker
Overlay Page
Display bus type
TERRAIN DISPLAY BUS #1
453TX_1
Yes (across bottom of display)
Yes, for Peaks Elevations only
Honeywell picture bus
CONNECT TO:
A = J1-58
Terrain Display data to switching relay/Symbol Generator #1
B = J1-59
TERRAIN DISPLAY BUS #2
453TX_2
CONNECT TO: Not supported for this display type
TABLE 5.3.6.2-3 DISPLAY INPUT CONTROL GROUP 3
CHANNEL
429_422RX_1
CONNECT TO:
SCI Bus 1
1.1.1.1.1.2 Fault Designation: DISPLAY BUS 1
(RS-422 - 12K baud)
Bus Type: Basic
A = J2-36
B = J2-37
Data
Label Sig. Bits
Range
2000NM
Signal Type Resolution
Basic N/A
Rate (ms)
100
Range (Mode/Range Word)
80
4 Discrete
CONN PIN #
J1-32
REFERENCE NAME
GND_DISC_12
PIN FUNCTION
Display Select Discrete #1
Polarity/Configuration
Type 1 (Momentary)
Gnd = Display Select Toggle
<not> Gnd = Normal
TABLE 5.3.6.3-0 OUTPUT 429 BUS GROUP 0
TRACEABILITY
5.3.6.3-0:
Channel
Pins
Comments
429TX_1 (Low Speed)
429TX_2
A = J2-43 B = J2-42
A = J2-26 B = J2-9
Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x and 7.1.4.x
No Connection (No Data Output)
Integration Notes:
This display type overlays an inverted T aircraft symbol
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Table E 3.1.6-16
Bendix IN182A/IN812A Radar display (RDR 2000)
Function
Display Type
Value
Bendix IN182A/IN812A color Radar Display (RDR-2000 radar
system)
Reference section
Sweep Type
Auto Pop Up
Sweep range +/- 50 degrees
Category 7, Options Select Group #1
TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True
Pop Up when the display is in the
proper mode.
Never Pop Up
Peaks Mode
Category 7, Options Select Group #1
(Available -003)
Peaks Enabled: False
Peaks Enabled: True
Peaks Off
Peaks On
Manual select
Manual deselect
Auto Range
Anytime WXR is on and display is in proper Mode
Anytime
No
Moving Marker
Overlay Page
No
Yes; “TERR” centered at top of display.
“TERR” or Peaks Elevation located on upper right side of Terrain
image as of –003.
Display bus type
Standard ARINC 453
TERRAIN DISPLAY BUS #1
453TX_1
CONNECT TO:
A = J1-58
B = J1-59
Terrain Display data to switching relay/Symbol Generator
TERRAIN DISPLAY BUS #2
453TX_2
CONNECT TO:
A = J1-56
B = J1-57
Terrain Display data to switching relay/Symbol Generator
Note :
•
This config group is similar to config group 4 except warning inhibited message not seen on the overlay
Display Input Control Group 2
CHANNEL
429_422RX_1
CONNECT TO:
Fault Designation: DISPLAY BUS 1
Bus Type: Basic
WX-IND 429 out (range)
Bus 1 (Low Speed)
Data
Mode (Display Word 1)
Range (Display Word 2)
Discrete Word (VP)
A = J2-37
B = J2-36
Reference
6.2.25
6.2.18
Label Sig. Bits
Range
Mode, Tilt, Gain
5-320NM
Signal Type Resolution Rate
270
271
273
Discrete
Discrete
Discrete
Basic
Basic
Basic
N/A
N/A
N/A
100 ms
100 ms
100 ms
6.2.26
VP Mode, Bit 11
CHANNEL
429RX_3
CONNECT TO:
Fault Designation: DISPLAY BUS 2
Bus Type: Basic
WX-IND 429 out (range)
Bus 2 (Low Speed)
Data
Mode (Display Word 1)
Range (Display Word 2)
Discrete Word (VP)
A = J2-41
B = J2-40
Reference
6.2.25
6.2.18
Label Sig. Bits
Range
Signal Type Resolution Rate
270
271
273
Discrete
Discrete
Discrete
Mode, Tilt, Gain
5-320NM
VP Mode, Bit 11
Basic
Basic
Basic
N/A
N/A
N/A
100 ms
100 ms
100 ms
6.2.26
CONN PIN #
J1-32
REFERENCE NAME
GND_DISC_12
PIN FUNCTION
Display Select Discrete #1
Polarity/Configuration
Type 1 (Momentary)
Gnd = Display Select Toggle
<not> Gnd = Normal
Reference
4.2.7
6.6.18
J1-31
GND_DISC_13
Reference
4.2.7
6.6.19
Display Select Discrete #2
Type 1 (Momentary)
Gnd = Display Select Toggle
<not> Gnd = Normal
*
When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels.
This prevents the EGPWS from reporting an external bus fault on the second channel.
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Output 429 Bus Group 0
Comments
Channel
Pins
429TX_1 (Low Speed)
A = J2-43
B = J2-42
Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, 7.1.4.x, and
7.1.6.x1
429TX_2
A = J2-26
B = J2-9
No Connection (No Data Output)
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Table E 3.1.6-17
Function
Display Type
Bendix IN842A/IN862A Radar display (RDR 2100)
Value
Bendix IN842A/IN862A color Radar Display (RDR-2100 radar
system)
Reference section
Sweep Type
Auto Pop Up
Sweep range +/- 60 degrees
Category 7, Options Select Group #1
TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True
Pop Up when display is in the
proper mode.
Never Pop Up
Peaks Mode
Category 7, Options Select Group #1
(Available -003)
Peaks Enabled: False
Peaks Enabled: True
Peaks Off
Peaks On
Manual select
Manual deselect
Auto Range
Anytime WXR is on and display is in proper Mode
Anytime
No
Moving Marker
Overlay Page
No
Yes; “TERR” centered at top of display.
“TERR” or Peaks Elevation located on upper right side of Terrain
image as of –003.
Display bus type
Standard ARINC 453
TERRAIN DISPLAY BUS #1
453TX_1
CONNECT TO:
A = J1-58
B = J1-59
Terrain Display data to switching relay/Symbol Generator
TERRAIN DISPLAY BUS #2
453TX_2
CONNECT TO:
A = J1-56
B = J1-57
Terrain Display data to switching relay/Symbol Generator
Note :
•
This config group is similar to config group 5 except warning inhibited message not seen on the overlay
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Display Input Control Group 2
CHANNEL
429_422RX_1
CONNECT TO:
Fault Designation: DISPLAY BUS 1
Bus Type: Basic
WX-IND 429 out (range)
Bus 1 (Low Speed)
Data
Mode (Display Word 1)
Range (Display Word 2)
Discrete Word (VP)
A = J2-37
B = J2-36
Reference
6.2.25
6.2.18
Label Sig. Bits
Range
Mode, Tilt, Gain
5-320NM
Signal Type Resolution Rate
270
271
273
Discrete
Discrete
Discrete
Basic
Basic
Basic
N/A
N/A
N/A
100 ms
100 ms
100 ms
6.2.26
VP Mode, Bit 11
CHANNEL
429RX_3
CONNECT TO:
Fault Designation: DISPLAY BUS 2
Bus Type: Basic
WX-IND 429 out (range)
Bus 2 (Low Speed)
Data
Mode (Display Word 1)
Range (Display Word 2)
Discrete Word (VP)
A = J2-41
B = J2-40
Reference
6.2.25
6.2.18
Label Sig. Bits
Range
Signal Type Resolution Rate
270
271
273
Discrete
Discrete
Discrete
Mode, Tilt, Gain
5-320NM
VP Mode, Bit 11
Basic
Basic
Basic
N/A
N/A
N/A
100 ms
100 ms
100 ms
6.2.26
CONN PIN #
J1-32
REFERENCE NAME
GND_DISC_12
PIN FUNCTION
Display Select Discrete #1
Polarity/Configuration
Type 1 (Momentary)
Gnd = Display Select Toggle
<not> Gnd = Normal
Reference
4.2.7
6.6.18
J1-31
GND_DISC_13
Reference
4.2.7
6.6.19
Display Select Discrete #2
Type 1 (Momentary)
Gnd = Display Select Toggle
<not> Gnd = Normal
*
When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels.
This prevents the EGPWS from reporting an external bus fault on the second channel.
Output 429 Bus Group 0
Channel
Pins
Comments
429TX_1 (Low Speed)
A = J2-43
B = J2-42
Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, 7.1.4.x, and
7.1.6.x1
429TX_2
A = J2-26
B = J2-9
No Connection (No Data Output)
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Table E 3.1.6-18
KC PictureBus w/opresentation ofTerrain AwarenessCorrected
Altitude
Function
Value
Reference section
Display Type
KC Picture Bus (KCPB)
Sweep Type
Auto Pop Up
Curtain (Vertical or Horizontal scan)
Category 7, Options Select Group #1
TA&D Alternate Pop Up: False
TA&D Alternate Pop Up: True
Pop Up On Caution or Warning
Never Pop Up
Peaks Mode
Category 7, Options Select Group #1
(Elevations via overlay)
Peaks Enable: False
Peaks Off
Peaks Enable: True
Peaks On
Manual select
Manual deselect
Auto Range
None (Display Control Selection)
None (Display Control Selection)
Controlled by display response (if selected a 10 nm range will be used)
Moving Marker
Overlay Page
Display bus type
None
Controlled by display
KCPB
TERRAIN DISPLAY BUS #1
453TX_1
CONNECT TO:
A = J1-58
Terrain Display data
B = J1-59
TERRAIN DISPLAY BUS #2
453TX_2
CONNECT TO:
A = J1-56
Terrain Display data
B = J1-57
Integration Notes:
•
•
KCPB is also known as ASPB (AlliedSignal Picture Bus).
This Display Group is configured by the Display using response labels on its ARINC 429 data bus.
Display Input Control Group 0
CHANNEL
429_422RX_1
CONNECT TO:
Fault Designation: KCPB BUS 1
Bus Type: Basic
KCPB-IND 429 out (range)
Bus 1 (Low Speed)
Data
A = J2-37
B = J2-36
Reference
6.2.35
6.2.23
6.2.36
6.2.24
Label Sig. Bits
Range
0.5-1023.5NM
N/A
Signal Type Resolution
Rate (ms)
250
1000
1000
250
*Range
271
011
350
012
11
Basic
Basic
Basic
Basic
0.5
Query/Continuous Response
DSU Status Data (DSU only)
*Key Press/Display Mode
Discrete
Discrete
Discrete
N/A
N/A
N/A
N/A
N/A
CHANNEL
429RX_3
CONNECT TO:
Fault Designation: KCPB BUS 2
Bus Type: Basic
KCPB-IND 429 out (range)
Bus 2 (Low Speed)
Data
A = J2-41
B = J2-40
Reference
6.2.35
6.2.23
6.2.36
6.2.24
Label Sig. Bits
Range
0.5-1023.5NM
N/A
Signal Type Resolution
Rate (ms)
250
1000
1000
250
*Range
271
011
350
012
11
Basic
Basic
Basic
Basic
0.5
Query/Continuous Response
DSU Status Data (DSU only)
*Key Press/Display Mode
Discrete
Discrete
Discrete
N/A
N/A
N/A
N/A
N/A
*
*
Label 012 is optional. The current fault and fault history message “RANGE” for label 271 (Range) is not shown if
Range Keys are requested on label 012 (Key Press/Display Mode).
When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels.
This prevents the EGPWS from reporting an external bus fault on the second channel.
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Output 429 Bus Group 0
Comments
Channel
Pins
429TX_1 (Low Speed)
A = J2-43
B = J2-42
Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, 7.1.4.x, and
7.1.6.x1
429TX_2
A = J2-26
B = J2-9
No Connection (No Data Output)
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Table E 3.1.6-235
Display Configuration (Collins ProLine II, 5x6, and ProLine 4)
Function
Display Type
Sweep Type
Value
Collins ProLine II (5x6)
Standard with +/-60 degree limit
Category 7, Options Select Group #1
Reference section
Auto Pop Up
TA&D Alternate Pop Up: False
TA&D Alternate Pop Up: True
Pop Up On Caution or Warning
Never Pop Up
Peaks Mode
Category 7, Options Select Group #1
(Available as of -003)
Peaks Enabled: False
Peaks Enabled: True
Peaks Off
Peaks On
Manual select
Manual deselect
Auto Range
Anytime
Anytime
No
Moving Marker
Overlay Page
No
Yes; “TERR” is located on the right side of display.
“TERR” or Peaks Elevations located on upper left side of Terrain image
as of -003.
Display bus type
TERRAIN DISPLAY BUS #1
453TX_1
Standard ARINC 453
CONNECT TO:
A = J1-58
B = J1-59
Terrain Display data to switching relay/Symbol Generator
TERRAIN DISPLAY BUS #2
453TX_2
CONNECT TO:
A = J1-56
B = J1-57
Terrain Display data to switching relay/Symbol Generator
Integration Notes:
1. Peaks Elevation numbers have been re-positioned to improve their presentation/visibility as of –010 release.
Display Input Control Group
CHANNEL
CONNECT TO:
429_422RX_1
IOC #1 Bus (High Speed)
Format: ARINC429
Fault Designation: IOC BUS 1
Bus Type: Basic
A = J2-37
B = J2-36
Data
Label Sig. Bits
Range
5-640NM
Signal Type Resolution
Basic N/A
Rate (ms)
50
Range (Mode/Range Word)
155
Discrete
CHANNEL
429RX_3
CONNECT TO:
IOC #2 Bus (High Speed)
Format: ARINC429
Fault Designation: IOC BUS 2
BUS TYPE: BASIC
A = J2-41
B = J2-40
Data
Label Sig. Bits
Range
Signal Type Resolution
Basic N/A
Rate (ms)
50
Range (Mode/Range Word)
155
Discrete
5-640NM
*
When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels.
This prevents the EGPWS from reporting an external bus fault on the second channel.
Output 429 Bus Group
Channel
Pins
Comments
429TX_1 (Low Speed)
A = J2-43
B = J2-42
Transmits
429TX_2
A = J2-26
B = J2-9
No Connection (No Data Output)
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Table E3.1.6-236
Display Configuration (Collins ProLine IV, 5x6)
Function
Display Type
Sweep Type
Value
Collins ProLine IV (5x6)
Standard with +/-60 degree limit
Category 7, Options Select Group #1
Auto Pop Up
TA&D Alternate Pop Up: False
No Effect
TA&D Alternate Pop Up: True
No Effect
Pop Up Controlled by Display
Pop Up Controlled by Display
Peaks Mode
Category 7, Options Select Group #1
(Available as of -011)
Peaks Enabled: False
Peaks Enabled: True
Peaks Off
Peaks On
Pop Down
Never Automatically pop down
Manual select
Manual deselect
Auto Range
Anytime
Anytime
No
Moving Marker
Overlay Page
No
Yes; “TERR” is located on the right side of display.
“TERR” and Peaks Elevations located on upper left side of Terrain
image as of -011.
Display Priority
Display bus type
Standard
Standard ARINC 708
Terrain Mode Annunciation Standard
TERRAIN DISPLAY BUS #1
453TX_1
CONNECT TO:
A = J1-58
B = J1-59
Terrain Display data to switching relay/Symbol Generator
TERRAIN DISPLAY BUS #2
453TX_2
CONNECT TO:
A = J1-56
B = J1-57
Terrain Display data to switching relay/Symbol Generator
Display Input Control
CHANNEL
429_422RX_1
CONNECT TO:
IOC #1 Bus (High Speed)
Fault Designation: IOC BUS 1
Format: ARINC429
Bus Type: Basic
A = J2-37
B = J2-36
Data
Label Sig. Bits
Range
5-640NM
Signal Type Resolution
Basic N/A
Rate (ms)
50
Range (Mode/Range Word)
155
Discrete
CHANNEL
429RX_3
CONNECT TO:
IOC #2 Bus (High Speed)
Format: ARINC429
Fault Designation: IOC BUS 2
BUS TYPE: BASIC
A = J2-41
B = J2-40
Data
Label Sig. Bits
Range
Signal Type Resolution
Basic N/A
Rate (ms)
50
Range (Mode/Range Word)
155
Discrete
5-640NM
*
When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels.
This prevents the EGPWS from reporting an external bus fault on the second channel.
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Output 429 Bus Group
Comments
Channel
Pins
429TX_1 (Low Speed)
A = J2-43
B = J2-42
Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x, 7.1.4.x, and
7.1.6.x1
429TX_2
A = J2-26
B = J2-9
No Connection (No Data Output)
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Table E 3.1.6-242
KC Picture Bus
Display Configuration Group 0 (KC Picture Bus1)
Function
Value
Display Type
KC Picture Bus (KCPB)
Sweep Type
Auto Pop Up
Curtain (Vertical or Horizontal scan)
Category 7, Options Select Group #1
TA&D Alternate Pop Up: False
TA&D Alternate Pop Up: True
Pop Up On Caution or Warning
Never Pop Up
Peaks Mode
Category 7, Options Select Group #1
(Elevations via overlay)
Peaks Enable: False
Peaks Off
Peaks Enable: True
Peaks On
Manual select
Manual deselect
Auto Range
None (Display Control Selection)
None (Display Control Selection)
Controlled by display response (if selected a 10 nm range will be used)
Moving Marker
Overlay Page
Display bus type
None
Controlled by display
KCPB
TERRAIN DISPLAY BUS #1
453TX_1
CONNECT TO:
A = J1-58
B = J1-59
TERRAIN DISPLAY BUS #2
453TX_2
Terrain Display data
CONNECT TO:
A = J1-56
Terrain Display data
B = J1-57
Display Input Control Group 245
CHANNEL
429RX_8
CONNECT TO:
KCPB-IND 429 out (range)
Bus 1 (Low Speed)
Fault Designation: KCPB BUS 1
Bus Type: Basic
A = J2-24
B = J2-07
Data
*Range
Query/Continuous Response
DSU Status Data (DSU only)
*Key Press/Display Mode
Label Sig. Bits
Range
0.5-1023.5NM
N/A
N/A
N/A
Signal Type Resolution
Rate (ms)
250
1000
1000
250
271
011
350
012
11
Basic
Basic
Basic
Basic
0.5
Discrete
Discrete
Discrete
N/A
N/A
N/A
CHANNEL
429RX_3
CONNECT TO:
Fault Designation: KCPB BUS 2
Bus Type: Basic
KCPB-IND 429 out (range)
Bus 2 (Low Speed)
Data
A = J2-41
B = J2-40
Label Sig. Bits
Range
0.5-1023.5NM
N/A
Signal Type Resolution
Rate (ms)
250
1000
1000
250
*Range
271
011
350
012
11
Basic
Basic
Basic
Basic
0.5
Query/Continuous Response
DSU Status Data (DSU only)
*Key Press/Display Mode
Discrete
Discrete
Discrete
N/A
N/A
N/A
N/A
N/A
OUTPUT 429 BUS GROUP 0
Channel
Pins
Comments
429TX_1 (Low Speed)
429TX_2
A = J2-43 B = J2-42
A = J2-26 B = J2-9
Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x and 7.1.4.x
No Connection (No Data Output)
Integration Notes:
•
•
•
KCPB is also known as ASPB (AlliedSignal Picture Bus).
This Display Group is configured by the Display using response labels on its ARINC 429 data bus.
Label 012 is optional. The current fault and fault history message “RANGE” for label 271 (Range) is not shown if
Range Keys are requested on label 012 (Key Press/Display Mode).
•
When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels.
This prevents the EGPWS from reporting an external bus fault on the second channel.
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Table E 3.1.6-246
Non-Integrated EFIS 10 (Bendix/Honeywell)
DISPLAY CONFIGURATION GROUP 246 (BENDIX EFIS 10 DISPLAY, EFS86 RADAR SYSTEM)
Function
Display Type
Sweep Type
Value
Bendix EFIS 10
Normal, Sweep range +/- 90 degrees
Category 7, Options Select Group #1
Auto Pop Up
TA&D Alternate Pop Up: False
Pop Up On Terrain Caution or
Warning.1
TA&D Alternate Pop Up: True
Never Pop Up
Peaks Mode
Category 7, Options Select Group #1
Peaks Enable: False
Peaks Enable: True
Peaks Off
Peaks On
Manual select
Manual deselect
Auto Range
Anytime1
Anytime1
No
Moving Marker
Overlay Page
No
Yes; Without Peaks: “TERR” is located at the bottom left of the display.
With Peaks: Peaks numbers are located at the lower left of the display.
Standard ARINC 708/453
Display bus type
TERRAIN DISPLAY BUS #1
453TX_1
CONNECT TO:
A = J1-58
B = J1-59
Terrain Display data to switching relay/Symbol Generator #1
CONNECT TO:
TERRAIN DISPLAY BUS #2
453TX_2
A = J1-56
Terrain Display data to switching relay/Symbol Generator #2
B = J1-57
DISPLAY INPUT CONTROL GROUP 246
CHANNEL
429_422RX_1
CONNECT TO:
WX-IND 429 out (range)
Bus 1 (Low Speed)
Fault Designation: DISPLAY BUS 1
Bus Type: Basic
A = J2-37
B = J2-36
Data
Label Sig. Bits
Range
Mode, Tilt, Gain
5-320NM
Signal Type Resolution
Rate
100 ms
100 ms
Mode (Display Word 1)
Range (Display Word 2)
270
271
Discrete
Discrete
Basic
Basic
N/A
N/A
CHANNEL
429RX_3
CONNECT TO:
Fault Designation: DISPLAY BUS 2
Bus Type: Basic
WX-IND 429 out (range)
Bus 2 (Low Speed)
Data
Mode (Display Word 1)
Range (Display Word 2)
A = J2-41
B = J2-40
Label Sig. Bits
Range
Signal Type Resolution
Rate
100 ms
100 ms
270
271
Discrete
Discrete
Mode, Tilt, Gain
5-320NM
Basic
Basic
N/A
N/A
CONN PIN #
J1-32
REFERENCE NAME
GND_DISC_12
PIN FUNCTION
Display Select Discrete #1
Polarity/Configuration
Type 1 (Momentary)
Gnd = Display Select Toggle
<not> Gnd = Normal
J1-31
GND_DISC_13
Display Select Discrete #2
Type 1 (Momentary)
Gnd = Display Select Toggle
<not> Gnd = Normal
OUTPUT 429 BUS GROUP 0
Channel
Pins
Comments
429TX_1 (Low Speed)
429TX_2
A = J2-43 B = J2-42
A = J2-26 B = J2-9
Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x and 7.1.4.x
No Connection (No Data Output)
Integration note:
•
Either weather or a weather test pattern must be displayed before Terrain can be viewed. The white weather
annunciation “WX” will still be present when terrain is displayed.
•
When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels.
This prevents the EGPWS from reporting an external bus fault on the second channel.
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Table E 3.1.6-250
Honeywell EDZ705 (5x5), EDZ756 (5x6) with DC-811 range push button control
DISPLAY CONFIGURATION GROUP 250 HONEYWELL SPZ8000, EDZ705 (5X5), EDZ756 (5X6), EDZ605, EDZ805, AND EDZ806)
Function
Display Type
Sweep Type
Auto Pop Up
Value
Honeywell (SPZ8000 new style - every fourth display line is blanked)
Honeywell
Category 7, Options Select Group #1
TA&D Alternate Pop Up: False
TA&D Alternate Pop Up: True
Pop Up On Caution or Warning
Never Pop Up
Peaks Mode
Category 7, Options Select Group #1
Peaks Enable: False
Peaks Off
Peaks Enable: True
Peaks On
Manual select
Manual deselect
Auto Range
Controlled by display system
Controlled by display system
Yes (10NM)
Moving Marker
Overlay Page
Display bus type
TERRAIN DISPLAY BUS #1
453TX_1
Yes (Honeywell type)
Yes for Peaks Elevations only.
Honeywell picture bus
CONNECT TO:
A = J1-58
Terrain Display data to switching relay/Symbol Generator #1 and MFD left channel
B = J1-59
TERRAIN DISPLAY BUS #2
453TX_2
CONNECT TO:
A = J1-56
B = J1-57
Terrain Display data to switching relay/Symbol Generator #2 and MFD right channel
DISPLAY INPUT CONTROL GROUP 251
CHANNEL
CONNECT TO:
429_422RX_1
DC811 #1
1.1.1.1.1.3 Fault Designation: DISPLAY BUS 1
Bus Type: (RS-422 – 7.8125K baud)
Label Sig. Bits
N/A
A = J2-36
B = J2-37
Data
Range
Signal Type Resolution Rate (ms)
Basic N/A 100
Range (Up/Down)
CHANNEL
422RX_2
CONNECT TO:
DC811 #2
1.1.1.1.1.4 Fault Designation: DISPLAY BUS 2
BUS TYPE: (RS-422 – 7.8125K BAUD)
A = J2-10
B = J2-11
Data
Label Sig. Bits
N/A
Range
Signal Type Resolution Rate (ms)
Basic N/A 100
Range (Up/Down)
OUTPUT 429 BUS GROUP 0
Channel
Pins
Comments
429TX_1 (Low Speed)
429TX_2
A = J2-43 B = J2-42
A = J2-26 B = J2-9
Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x and 7.1.4.x
No Connection (No Data Output)
Integration Notes:
•
•
The EGPWS ARINC 429 Output Bus must be connected to the display.
This display uses the following ARINC 429 labels from the EGPWS for annunciation:
The Terrain display will annunciate:
“TERR" in green or cyan (depending on the program) when the Terrain is selected and valid.
“TERR” in amber if Terrain is selected and any of the following conditions are TRUE:
•
•
•
The EGPWS ARINC 429 output bus is missing or labels 050 and 051 are absent or unreadable for 2 seconds.
EGPWS ARINC label 051 bit 13 = 0 (“Terrain Display Valid” bit FALSE)
EGPWS ARINC label 050 bit 17 = 1 (“Terrain Inhibit” bit TRUE)
Note - Per customer request for EDZ705 and EDZ756, the display does not go blank when Terrain is Inhibited,
nor is an amber TERR presented. This change is part of the EFIS system
•
EGPWS ARINC labels are valid, but range in label 050 disagrees with range via SCI bus label 80 (Label 050 bits
11-14 contain the left display range and bits 15-18 contain the right).
The display will be blanked when the amber “TERR” is present.
The Terrain display will Pop Up to Terrain mode as follows:
•
If all the conditions indicated by for the amber “TERR” above are FALSE.
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•
If the display is in normal MFD mode (not HSI backup, or SG backup) AND if Label 051 bit 11 transitions from 0
to 1 (rising edge), AND Checklist is not selected on the MFD, and TCAS Auto Pop Up is not occurring.
The display will change to Map mode.
The display will energize the Terrain selection relays.
The display will annunciate “TERR”.
•
•
•
•
The display will change to the range indicated by the EGPWS ARINC 429 Label 050.
•
•
When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels.
This prevents the EGPWS from reporting an external bus fault on the second channel.
Note that the Channel 429_422RX_1 polarity is shown reversed from ARINC 429 application.
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Table E 3.1.6-255
Honeywell SPZ8000 (w/ SCI range)
Display Configuration Group 255 (Honeywell SPZ8000 older style)
Function
Value
Display Type
Honeywell (5x6) (SPZ8000) older style; does not blank every fourth
weather radar display line. This interface supports SG-810 and SG-
811 SPZ8000 systems only.
Sweep Type
Auto Pop Up
Honeywell
Category 7, Options Select Group #1
TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True
Pop Up On Caution or Warning
Never Pop Up
Peaks Mode
Category 7, Options Select Group #1
(Elevations via overlay)
Peaks Enable: False
Peaks Off
Peaks Enable: True
Peaks On
Manual select
Manual deselect
Auto Range
Controlled by SPZ8000 display system
Controlled by SPZ8000 display system
Yes (10 NM)
Moving Marker
Overlay Page
Display bus type
Yes (Honeywell type)
Yes, for Peaks Elevations (located on lower right side)
Honeywell picture bus
TERRAIN DISPLAY BUS #1
453TX_1
CONNECT TO:
A = J1-58
Terrain Display data to switching relay/Symbol Generator #1
B = J1-59
TERRAIN DISPLAY BUS #2
453TX_2
CONNECT TO:
A = J1-56
B = J1-57
Terrain Display data to switching relay/Symbol Generator #2
(NOTE: Range setting always follows Display Bus #1).
Display Input Control Group 255
CHANNEL
429_422RX_1
CONNECT TO:
SCI Bus 1
(RS-422 - 12K baud)
Fault Designation: DISPLAY BUS 1
Bus Type: Basic
A = J2-36
B = J2-37
Data
Label Sig. Bits
Range
2000NM
Signal Type Resolution
Basic N/A
Rate (ms)
100
Range (Mode/Range Word)
80
4 Discrete
OUTPUT 429 BUS GROUP 0
Channel
Pins
Comments
429TX_1 (Low Speed)
429TX_2
A = J2-43 B = J2-42
A = J2-26 B = J2-9
Transmits (Section 7) Label sets: 7.1.1.x, 7.1.2.x, 7.1.3.x and 7.1.4.x
No Connection (No Data Output)
Integration Notes:
•
•
The EGPWS ARINC 429 Output Bus must be connected to the SPZ8000 display.
This display type may also be used for an integrated P880/660/440 display, but requires Auto Pop Up to be disabled and
relay selection to be controlled directly from an alternate action switch (for new installations of P880/660/440 use ID
13).
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E 5.3.7
CATEGORY 7, OPTIONS 1 SELECT
The following table provides identification of the Options Select Group #1. Each entry in the ID column corresponds to a
particular combination of TA&D Alternate Pop Up, Obstacle Awareness Enabled, Peaks Mode Enabled, Bank Angle Enable,
Steep Approach Enabled, Flap / WOW Reversal and GPS Altitude Reference selection. Refer to section 7.5 for configuration
messages that will be present for each option selected.
Note: Peaks Mode Enable is always True regardless of the option selected.
TABLE E 317: OPTIONS SELECT GROUP #1
ID
TA&D
Alternate
Pop Up
Peaks
Mode
Enabled
Obstacle
Awareness
Enabled
Bank Angle
Enable
Weight On
Wheels
Reversal
GPS
Altitude
Reference
Effectivity
5
6
App Cfg.
.
0
1
2
3
4
5
6
7
False
False
False
False
False
False
False
False
False
False
False
False
False
False
False
False
False
False
False
False
False
False
False
False
False
False
False
False
False
False
False
False
True
False
False
False
False
False
False
False
False
False
False
False
False
False
False
False
False
True
True
True
True
True
True
True
True
True
True
True
True
True
True
True
True
False
False
False
False
False
False
False
False
False
False
True
True
True
True
True
True
True
True
False
False
False
False
False
False
False
False
True
True
True
True
True
True
True
True
False
False
False
False
False
False
True
True
True
True
False
False
False
False
True
True
True
True
False
False
False
False
True
True
True
True
False
False
False
False
True
True
True
True
False
False
False
False
True
True
False
False
True
True
False
False
True
True
False
False
True
True
False
False
True
True
False
False
True
True
False
False
True
True
False
False
True
True
False
False
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
WGS-84
MSL
True
5
6
Enables PEAKS mode display if display supports
"MSL" reference must be selected when an internal GPS is utilized.
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ID
TA&D
Alternate
Pop Up
Peaks
Mode
Enabled
Obstacle
Awareness
Enabled
Bank Angle
Enable
Weight On
Wheels
Reversal
GPS
Altitude
Reference
Effectivity
5
6
App Cfg.
.
34
35
36
37
38
39
40
41
42
43
44
45
46
47
48
49
50
51
52
53
54
55
56
57
58
59
60
61
62
63
True
True
True
True
True
True
True
True
True
True
True
True
True
True
True
True
True
True
True
True
True
True
True
True
True
True
True
True
True
True
False
False
False
False
False
False
False
False
False
False
False
False
False
False
True
True
True
True
True
True
True
True
True
True
True
True
True
True
True
True
False
False
False
False
False
False
True
True
True
True
True
True
True
True
False
False
False
False
False
False
False
False
True
True
True
True
True
True
True
True
False
False
True
True
True
True
False
False
False
False
True
True
True
True
False
False
False
False
True
True
True
True
False
False
False
False
True
True
True
True
True
True
False
False
True
True
False
False
True
True
False
False
True
True
False
False
True
True
False
False
True
True
False
False
True
True
False
False
True
True
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
WGS-84
MSL
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
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E 5.3.8
CATEGORY 8, RADIO ALTITUDE INPUT SELECT
The following table provides identification of the Radio Altitude type. The entry in the Radio Altitude Type corresponds to a
table that provides detailed information on the configuration. For example, the details for Radio Altitude Type #1 are found
in Table 0-1. ARINC 552, ALT 55 and digital ARINC 429 compatible Radio Altimeters are supported. ALT 50 Radio
Altimeters are not supported due to the maximum 2000-foot operation
CAUTION:
ALT 55 radio altimeters use an avarage altitude tracking technique that does not track the nearest terrain. This can
produce errors up to 200 to 300 feet in high bank turns and mountainous terrain. This characteristic may degrade
EGPWS performance for Modes 1 thru 6.
In this category, only the following signals are defined:
•
Radio Altitude source selection, input scaling, and associated validities.
TABLE E 3.1.8: RADIO ALTITUDE INPUT SELECT FOR EGPWS MKXXII
Radio Altitude
Type
ID
Description
Effectivity
(Table E 3.1.8-
App.
Cfg.
x)
0
1
2
3
4
5
0
1
2
3
4
5
Analog Radio Altitude (ARINC 552)
Analog (ALT 55)
Digital Radio Altitude (ARINC 429) (Note 2)
Analog Radio Altitude (RT-200/300)
Analog (KRA 405)
-001
-001
-001
-001
-003
-010
-001
-001
-001
-001
-003
-010
Analog (Alt 50)
Note 2: Digital Radio Altimeters can not be used on two engine Helicopters with Digital Torque.
TABLE E 3.1.8-0: RADIO ALTITUDE INPUT SELECT TYPE 0 (ARINC 552)
SIGNAL
Radio Altimeter #1
CONNECTION
(+) = J1-64
SUMMARY DATA
Format: ARINC 552 with Validity Flag
(-) = J1-45
Input Type: Basic
Fault Designation: RADIO ALTIMETER FAULT
Validity: Radio Altitude Valid Discrete #1 (+28V)
PIN FUNCTION
CONNECTION
J1-29
PIN TYPE
Input
Input
CHANNEL DESIGNATION
REFERENCE
28V_DISC_07
Polarity/Configuration
Radio Altitude Validity
Discrete #1 (+28V)
DH Discrete (Gnd)
>+17V = Valid
<+4.4V = Invalid
Gnd = Below DH
<not> Gnd = Above DH
J1-33
GND_DISC_11
CONFIGURATION DATA
Description
Value
Out of Track Maximum
Out of Track Minimum
Pseudo Altitude Type
Field Enable Type
Pseudo altitude is only allowed to operate within
these limits.
Selects parameters for pseudo altitude engage logic
Selects pseudo altitude field elevation
2800
-20
3
2
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TABLE E 3.1.8-1: RADIO ALTITUDE INPUT SELECT TYPE 1 (ALT 55)
SIGNAL
CONNECTION
SUMMARY DATA
Radio Altimeter #1
(+) = J1-64
(-) = J1-45
Format: Alt 55 with Validity Flag
Input Type: Basic
Fault Designation: RADIO ALTIMETER FAULT
Validity: Radio Altitude Valid Discrete #1 (+28V)
PIN FUNCTION
CONNECTION
J1-29
PIN TYPE
Input
Input
CHANNEL DESIGNATION
REFERENCE
28V_DISC_07
Polarity/Configuration
Radio Altitude Validity
Discrete #1 (+28V)
DH Discrete (Gnd)
>+17V = Valid
<+4.4V = Invalid
Gnd = Below DH
<not> Gnd = Above DH
J1-33
GND_DISC_11
CONFIGURATION DATA
Description
Value
Out of Track Maximum
Out of Track Minimum
Pseudo Altitude Type
Field Enable Type
Pseudo altitude is only allowed to operate within
these limits.
Selects parameters for pseudo altitude engage logic
Selects pseudo altitude field elevation
2800
-20
4
2
TABLE E 3.1.8-2: RADIO ALTITUDE INPUT SELECT TYPE 2 (ARINC 429)
CONNECT TO:
Left ( #1) LRRA
(Low Speed)
Fault Designation: RADIO ALTIMETER BUS
Bus Type: Basic
CHANNEL
429RX_5
A = J2-21
B = J2-4
PIN FUNCTION
Data
Label
164
Sig. Bits
16
Range
±8192 FT
Signal Type
Basic
Polarity/Configuration
Resolution
0.125
Rate (ms)
25-50
Radio Altitude
CONNECTION
PIN TYPE
Input
CHANNEL DESIGNATION
REFERENCE
GND_DISC_11
DH Discrete (Gnd)
J1-33
Gnd = Below DH
<not> Gnd = Above DH
TABLE E 3.1.8-3: RADIO ALTITUDE INPUT SELECT TYPE 3 (RT-200/300)
CONNECTION SUMMARY DATA
Format: DC with Validity Flag (RT-200/300)
SIGNAL
Radio Altimeter #1
(+) = J1-64
(-) = J1-45
Input Type: Basic
Fault Designation: RADIO ALTIMETER FAULT
Validity: Radio Altitude Valid Discrete #1 (+28V)
PIN FUNCTION
CONNECTION
J1-29
PIN TYPE
Input
Input
CHANNEL DESIGNATION
REFERENCE
28V_DISC_07
Polarity/Configuration
Radio Altitude Validity
Discrete #1 (+28V)
DH Discrete (Gnd)
>+17V = Valid
<+4.4V = Invalid
Gnd = Below DH
<not> Gnd = Above DH
J1-33
GND_DISC_11
CONFIGURATION DATA
Description
Value
Out of Track Maximum
Out of Track Minimum
Pseudo Altitude Type
Field Enable Type
Pseudo altitude is only allowed to operate within
these limits.
Selects parameters for pseudo altitude engage logic
Selects pseudo altitude field elevation
2800
-20
3
2
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TABLE E 3.1.8-4: RADIO ALTITUDE INPUT SELECT TYPE 4 (KRA 405)
SIGNAL
CONNECTION
SUMMARY DATA
Radio Altimeter #1
(+) = J1-64
(-) = J1-45
Format: Alt 55 with Validity Flag
Input Type: Basic
Fault Designation: RADIO ALTIMETER FAULT
Validity: Radio Altitude Valid Discrete #1 (+28V)
PIN FUNCTION
CONNECTION
J1-29
PIN TYPE
Input
Input
CHANNEL DESIGNATION
REFERENCE
28V_DISC_07
Polarity/Configuration
Radio Altitude Validity
Discrete #1 (+28V)
DH Discrete (Gnd)
>+17V = Valid
<+4.4V = Invalid
Gnd = Below DH
<not> Gnd = Above DH
J1-33
GND_DISC_11
CONFIGURATION DATA
Description
Value
Out of Track Maximum
Out of Track Minimum
Pseudo Altitude Type
Field Enable Type
Pseudo altitude is only allowed to operate within
these limits.
Selects parameters for pseudo altitude engage logic
Selects pseudo altitude field elevation
2800
-20
3
2
Table E 3.1.8-5: Radio Altitude Input Select Type 5 (ALT 50)
SIGNAL
CONNECTION
REFERENCE
SUMMARY DATA
Radio Altimeter #1
(+) = J1-64
(-) = J1-45
Format: Alt 50 with Validity Flag
Input Type: Basic
Fault Designation: RADIO ALTIMETER FAULT
Validity: Radio Altitude Valid Discrete #1 (+28V)
PIN FUNCTION
CONNECTION
J1-29
PIN TYPE
Input
CHANNEL DESIGNATION
REFERENCE
28V_DISC_07
Polarity/Configuration
Radio Altitude Validity
Discrete #1 (+28V)
DH Discrete (Gnd)
>+17V = Valid
<+4.4V = Invalid
Gnd = Below DH
<not> Gnd = Above DH
J1-33
Input
GND_DISC_11
CONFIGURATION DATA
Description
Value
Out of Track Maximum
Out of Track Minimum
Pseudo Altitude Type
Field Enable Type
Pseudo altitude is only allowed to operate within
these limits.
Selects parameters for pseudo altitude engage logic
Selects pseudo altitude field elevation
2100
-20
4
2
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E 5.3.9
CATEGORY 9, NAVIGATION INPUT SELECT
The following table provides identification of the Navigation type. The entry in the Navigation Type corresponds to a table
that provides detailed information on the configuration. For example, the details for Navigation Type #1 are found in Table
0-1. In this category, only the following signals are defined:
•
•
Glideslope source selection.
Localizer source selection. (optional for digital only)
TABLE E 3.1.9: NAVIGATION INPUT SELECT FOR EGPWS MKXXII
I
D
Navigation
Inputs Select
Description
Effectivity
(Table E 3.1.9-
App.
Cfg.
-001
-001
x)
0
0
1
Analog Glideslope (ARINC 547) with +28V
Validity Flag
Analog Glideslope (ARINC 547) with Low Level
Validity
-001
-001
1
2
3
4
2
3
4
Digital Glideslope (ARINC 429)
Digital Glideslope and Localizer (ARINC 429)
Digital KN40 Glideslope and Localizer (ARINC
429)
-001
-001
-003
-001
-001
-003
5
5
Analog Glideslope/Localizer (ARINC 547) with
+28V Validity Flags
-008
-008
TABLE E 3.1.9-0: NAVIGATION INPUTS SELECT 0
SIGNAL
Glideslope Deviation
PIN FUNCTION
CONNECTION
SUMMARY DATA
Format: ARINC 547 with Validity Flag & ILS Select
Input Type: Basic
Fault Designation: GLIDESLOPE FAULT
Validity: Glideslope Validity Discrete #1 (+28V)
(+) = J1-65
(-) = J1-46
CONNECTION
J1-11
PIN TYPE
Input
CHANNEL DESIGNATION
REFERENCE
Polarity/Configuration
Glideslope Validity
Discrete #1
28V_DISC_06
>+17V = Valid
< +4.4V = Not Valid
+28V ILS Tuned
Discrete #1
GND ILS Tuned
Discrete #1
J1-39
Input
28V_DISC_01
GND_DISC_01
>+17V = ILS Tuned
< +4.4V = ILS Not Tuned
Gnd = ILS Tuned
J1-20
Input
<not> Gnd = ILS Not Tuned
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TABLE E 3.1.9-1: NAVIGATION INPUTS SELECT 1
SIGNAL
CONNECTION
SUMMARY DATA
Format: ARINC 547 with Low Level Validity & ILS Select
Input Type: Basic
Fault Designation: GLIDESLOPE FAULT
Validity: Low Level Glideslope Deviation Validity
Format: DC
(+) = J1-65
(-) = J1-46
Glideslope Deviation
Input Type: Basic
Low Level Glideslope
Deviation Validity
(+) = J1-30
(-) = J1-10
Fault Designation: GLIDESLOPE LOW LEVEL VALIDITY FAULT
> 0.145V = Valid (typical active range is 0.16V to 0.84V)
<= 0.145V = Invalid
PIN FUNCTION
CONNECTION
J1-39
PIN TYPE
Input
CHANNEL DESIGNATION
REFERENCE
28V_DISC_01
Polarity/Configuration
+28V ILS Tuned
Discrete #1
>+17V = ILS Tuned
< +4.4V = ILS Not Tuned
GND ILS Tuned
Discrete #1
J1-20
Input
GND_DISC_01
Gnd = ILS Tuned
<not> Gnd = ILS Not Tuned
TABLE E 3.1.9-2: NAVIGATION INPUTS SELECT 2
Fault Designation: ILS BUS
Bus Type: Basic
CHANNEL
429RX_6
CONNECT TO:
ILS #1 (Low Speed)
A = J2-22
B = J2-5
Data
Glideslope
Label
174
Sig. Bits
12
Range
Signal Type
Basic
Resolution
0.0001953125
Rate (ms)
33.3-66.6
±0.8 DDM
TABLE E 3.1.9-3: NAVIGATION INPUTS SELECT 3
Fault Designation: ILS BUS
Bus Type: Basic
CHANNEL
429RX_6
CONNECT TO:
ILS #1 (Low Speed)
A = J2-22
B = J2-5
Data
Glideslope
Localizer
Label
174
Sig. Bits
12
Range
Signal Type
Basic
Resolution
0.0001953125
0.00009765625
Rate (ms)
33.3-66.6
33.3-66.6
±0.8 DDM
±0.4 DDM
173
12
Basic
TABLE E 3.1.9-4: NAVIGATION INPUTS SELECT 4
Fault Designation: ILS BUS
Bus Type: Basic
CHANNEL
429RX_6
CONNECT TO:
ILS #1 (Low Speed)
A = J2-22
B = J2-5
Data
Glideslope
Localizer
Label
174
Sig. Bits
12
Range
±0.8 DDM
±0.4 DDM
n/a
Signal Type
Basic
Resolution
0.0001953125
0.00009765625
Bit 14 = ILS
Rate (ms)
33.3-66.6
33.3-66.6
167-333
173
034
12
Discrete
Basic
Basic
ILS Select (VOR/ILS Freq)
Configuration Data
Type
Reference Section
KN40 Nav Source
True
SRD 5.9.2.1.R61, 5.9.3.R41
TABLE E 3.1.9-5: NAVIGATION INPUTS SELECT 5
SIGNAL
Glideslope Deviation
CONNECTION
(+) = J1-65
(-) = J1-46
SUMMARY DATA
Format: ARINC 547 with Validity Super Flag & ILS Select
Input Type: Basic
Fault Designation: GLIDESLOPE FAULT
Validity: Glideslope Validity Discrete #1 (+28V)
Format: ARINC 547 with Validity Flag & ILS Select
Input Type: Basic
Localizer Deviation
(+) = J1-30
(-) = J1-10
Fault Designation: LOCALIZER FAULT
Validity: Localizer Validity Discrete #1 (+28V)
PIN FUNCTION
CONNECTION
J1-48
PIN TYPE
Input
CHANNEL DESIGNATION
REFERENCE
28V_DISC_11
Polarity/Configuration
Localizer Validity
Discrete #1
>+17V = Valid
< +4.4V = Not Valid
Glideslope Validity
Discrete #1
+28V ILS Tuned
Discrete #1
GND ILS Tuned
Discrete #1
J1-11
Input
28V_DISC_06
28V_DISC_01
GND_DISC_01
>+17V = Valid
< +4.4V = Not Valid
>+17V = ILS Tuned
< +4.4V = ILS Not Tuned
Gnd = ILS Tuned
J1-39
Input
J1-20
Input
<not> Gnd = ILS Not Tuned
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E 5.3.10
CATEGORY 10, ATTITUDE INPUT SELECT
The following table provides identification of the Roll Attitude Angle type. The entry in the Attitude Input Select
corresponds to a table that provides detailed information on the configuration. For example, the details for Attitude Input
Select #1 are found in 0-1.
In this category, only the following signals are defined:
•
•
•
•
Roll Attitude
Pitch Attitude
TABLE E 3.1.10: ATTITUDE INPUT SELECT FOR EGPWS MK XXII
Attitude Input
ID
Description
Effectivity
Select
(Table 0-x)
App.
Cfg.
-001
-003
-003
0
2
4
0
2
4
Analog Roll (3-Wire Synchro) without validity
Analog Pitch and Roll (3-Wire Synchro)
Analog Roll(3-Wire Synchro) with validity (Note 1)
Digital Pitch, Roll, Pitch Rate and Roll Rate (High
Speed ARINC 429) (Note 3)
-001
-003
-003
128
128
-006
-006
Note 1: ID 4 may not be used with Category 13 (I/O Discrete Type) ID’s 2, or 3. This is due to a conflict with the validity
discrete. ID 0 may be used instead with the Validity discrete left unconnected. Also, ID 4 are intended to be used with
helicopter types that do not have the tail strike functionality (currently the MD-900 only).
Note 2: ID 128 may only be used in conjunction with Category 11 (Magnetic Heading) ID 2.
TABLE E 3.1.10-0: ATTITUDE INPUT SELECT TYPE 0
SIGNAL
CONNECTION
SUMMARY DATA
Format: 3 Wire Synchro
Input Type: Basic
Fault Designation: ROLL FAULT
Validity: None
(X) = J1-1
(Y) = J1-21
(Z) = J1-2
Roll Attitude
Reference: None
TABLE E 3.1.10-2: ATTITUDE INPUT SELECT TYPE 2
SUMMARY DATA
SIGNAL
CONNECTION
Format: 3 Wire Synchro with Validity Flag
Input Type: Basic
Fault Designation: ROLL FAULT
Validity: Attitude Validity Discrete #1
Reference: None
(X) = J1-1
(Y) = J1-21
(Z) = J1-2
Roll Attitude
Format: 3 Wire Synchro with Validity Flag
Input Type: Basic
Fault Designation: PITCH FAULT
Validity: Attitude Validity Discrete #1
Reference: None
(X) = J1-5
(Y) = J1-7
(Z) = J1-6
Pitch Attitude
PIN FUNCTION
CONNECTION
PIN TYPE
CHANNEL DESIGNATION
REFERENCE
Polarity/Configuration
References
Attitude Validity
Discrete #1
J1-68
Input
28V_DISC_12
>+17V = Valid
<+4.4V = Invalid
6.6.24
4.2.7
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TABLE E 3.1.10-4: ATTITUDE INPUT SELECT TYPE 4
SIGNAL
CONNECTION
SUMMARY DATA
Format: 3 Wire Synchro with Validity Flag
Input Type: Basic
Fault Designation: ROLL FAULT
Validity: Attitude Validity Discrete #1
Reference: None
(X) = J1-1
(Y) = J1-21
(Z) = J1-2
Roll Attitude
PIN FUNCTION
CONNECTION
PIN TYPE
CHANNEL DESIGNATION
REFERENCE
Polarity/Configuration
Summary Data
Attitude Validity
Discrete #1
J1-68
Input
28V_DISC_12
>+17V = Valid
<+4.4V = Invalid
6.6.24
4.2.7
TABLE E 3.1.10-128: ATTITUDE INPUT SELECT TYPE 128
CONNECT TO:
AHRS
(High Speed)
Fault Designation: AHRS BUS
Bus Type: Basic
CHANNEL
429RX_7
A = J2-23
B = J2-6
Data
Roll Angle
Pitch Angle
Body Roll Rate
Body Pitch Rate
Label
325
324
327
326
Sig. Bits
Range
Signal Type
Basic
Resolution
Rate (ms)
10-20
10-20
10-20
10-20
14
14
13
13
±180 degrees
±180 degrees
±128 deg/sec
±128 deg/sec
0.010986328125
0.010986328125
0.01562500
Basic
Basic
Basic
0.01562500
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E 5.3.11
CATEGORY 11, HEADING INPUT SELECT
The following table provides identification of the Heading type. The entry in the Heading Input Select corresponds to a table
that provides detailed information on the configuration. For example, the details for Magnetic Heading Input Select #1 are
found in 0-1.
In this category, only the following signals are defined:
•
Magnetic Heading
TABLE E 3.1.11: HEADING INPUT SELECT FOR EGPWS MK XXII
Heading Input
Select
ID
Description
Effectivity
(Table E 3.1.11-x)
App.
Cfg.
-001
-006
Analog Magnetic Heading (3-Wire Synchro with
reference and validity discrete)
High Speed ARINC 429 (Note 1)
0
2
0
2
-001
-006
Note 1: ID 2 is intended to be used in conjunction with Category 10 (Attitude) ID 128.
TABLE E 3.1.11-0: HEADING INPUT SELECT 0
SIGNAL
Magnetic Heading
PIN FUNCTION
CONNECTION
(X) = J1-22
(Y) = J1-23
(Z) = J1-3
Reference
(H) = J1-4
SUMMARY DATA
Format: 5 Wire Synchro with Validity Flag
Input Type: Basic
Fault Designation: MAGNETIC HEADING FAULT
Validity: Magnetic Heading Validity Discrete (+28V)
Reference: Nominal 26 VAC
(C) = J1-24
CONNECTION
PIN TYPE
CHANNEL DESIGNATION
REFERENCE
Polarity/Configuration
Magnetic Heading
Validity Discrete
J1-28
Input
28V_DISC_10
>+17V = Valid
< +4.4V = Invalid
TABLE E 3.1.11-2: HEADING INPUT SELECT 2
CONNECT TO:
Fault Designation: AHRS BUS
Bus Type: Basic
CHANNEL
429RX_7
AHRS
(High Speed)
Data
A = J2-23
B = J2-6
Label
320
Sig. Bits
15
Range
±180 degrees
Signal Type
Basic
Resolution
0.0054931640625
Rate (ms)
10-50
Magnetic Heading
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MK XXII EGPWS Installation Manual
E 5.3.12
CATEGORY 12, WINDSHEAR INPUT SELECT
The Windshear warning is not applicable to Helicopters.
The following table provides the definition of Windshear Input Select ID 0, which is used for helicopter installations.
TABLE E 3.1.12: WINDSHEAR INPUT SELECT
Windshear INOP Disable
Windshear Caution
Voice Disable
ID
Description
Effectivity
App.
Cfg.
0
No Windshear
TRUE
TRUE
-003
-003
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E 5.3.13
CATEGORY 13, INPUT / OUTPUT DISCRETE TYPE SELECT
The following table provides identification of the Input/Output Discrete Type. Each entry in the Input/Output Discrete Type
column has a corresponding table that provides detailed information on the configuration. For example, the details for
Input/Output Discrete Type #128 are found in Table E 3.1.13-128.
TABLE E 3.1.13: INPUT/OUTPUT DISCRETE TYPE SELECT FOR EGPWS MK XXII
Input/Output
Discrete Type
(Table E 3.1.13-
x)
ID
Description
Effectivity
App.
Cfg.
Helicopter Input / output discrete definitions (Lamp
Format 1)
Helicopter Input / output discrete definitions (Lamp
Format 2)
128
129
128
129
-003
-003
-003
-003
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TABLE E 3.1.13-128: INPUT/OUTPUT DISCRETE TYPE 128
CONN PIN #
CHANNEL
DESIGNATION
REFERENCE
28V_DISC_02
PIN TYPE
PIN FUNCTION
Polarity/Configuration
J1-38
J1-19
J1-37
J1-18
J1-36
J1-17
+28V Glideslope Inhibit Discrete
GND Glideslope Inhibit Discrete
+28V WOW Discrete
>+17V = Inhibit
<+4.4V = Not Inhibit
Gnd = Inhibit
<not> Gnd = Not Inhibit
>+17V = WOW
<+4.4V = Not WOW
Gnd = WOW
<not> Gnd = Not WOW
>+17V = Inhibit
<+4.4V = Not Inhibit
Gnd = Audio Inhibit Toggle
<not> Gnd = Audio Inhibit
Not Toggle
Input
Input
Input
Input
Input
GND_DISC_02
28V_DISC_03
GND_DISC_03
28V_DISC_04
GND_DISC_04
GND WOW Discrete
+28V Audio Inhibit Discrete
Timed Audio Inhibit Discrete
Input
J1-35
J1-16
J1-15
J1-14
28V_DISC_05
GND_DISC_05
GND_DISC_06
GND_DISC_07
+28V Landing Gear Discrete
>+17V = Gear Down
<+4.4V = Gear Up
Gnd = Gear Down
<not> Gnd = Gear Up
Gnd = Cancel Toggle
<not> Gnd = Normal
Gnd = Low Altitude Mode
Select
<not> Gnd = Normal
Gnd = Low Volume
<not> Gnd = Normal
>+17V = Engaged
<+4.4V = Not Engaged
Gnd = Inhibit
Input
Input
Input
GND Landing Gear Discrete
Glideslope Cancel Discrete (Note 1)
Low Altitude Mode Select (Tactical) (Note 1)
Input
Input
J1-13
J1-8
GND_DISC_08
28V_DISC_09
GND_DISC_09
GND_DISC_10
Mode 6 Low Volume Discrete
Autopilot Engaged Discrete #1
Terrain Awareness Inhibit Discrete (Note 2)
Self-Test Discrete (Note 1)
Input
Input
J1-12
J1-34
<not> Gnd = Not Inhibit
Gnd = Self-Test Toggle
<not> Gnd = Normal
Input
Output
Output
J1-72
J1-55
MON_OUT_1
MON_OUT_2
GPWS INOP Discrete
TAD INOP Discrete
Terrain Not Available
J1-78
DISC_OUT_1
GPWS Warning Discrete
Output
Terrain Awareness Caution or Warning
Obstacle Awareness Caution or Warning
GPWS Alert Discrete (Glideslope Only)
Glideslope Cancel Discrete
Low Altitude Mode Discrete (Tactical)
TCAS Inhibit discrete
Terrain Display Select #1 Discrete
Terrain Awareness Caution or Warning
Obstacle Awareness Caution or Warning
Terrain Display Select #2 Discrete
Timed Audio Inhibit
J1-77
J1-76
J1-73
J1-69
J1-54
J1-51
DISC_OUT_2
DISC_OUT_3
DISC_OUT_4
DISC_OUT_5
DISC_OUT_6
DISC_OUT_8
Output
Output
Output
Output
Output
Gnd = Terrain Pop Up
Gnd = Audio Inhibit
Output
J1-49
J1-52
J1-48
DISC_OUT_9
DISC_OUT_7
28V_DISC_11
Output
Output
Not Defined in this ID (Note 3).
Input
J1-67
J2-15
J2-31
J1-50
GND_DISC_14
28V_DISC_13
GND_DISC_15
MON_OUT_3
Input
Input
Input
Not Defined in this ID (Note 3).
Not Defined in this ID (Note 3).
Not Defined in this ID (Note 3).
Not Defined in this ID (Note 3).
Output
Configuration Data
Lamp Format
Flashing Lamps
Possible States
Type 1,Type 2
True, False
State
Type 1
False
Note 1: Provided by Momentary cockpit switch (non-latching)
Note 2: Provided by Alternate cockpit switch (Latching) with guard if inhibiting
Note 3: This discrete may be used in another category.
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TABLE E 3.1.13-129: INPUT/OUTPUT DISCRETE TYPE 129
CONN PIN #
CHANNEL
DESIGNATION
REFERENCE
28V_DISC_02
PIN TYPE
PIN FUNCTION
Polarity/Configuration
J1-38
J1-19
J1-37
J1-18
J1-36
J1-17
+28V Glideslope Inhibit Discrete
GND Glideslope Inhibit Discrete
+28V WOW Discrete
>+17V = Inhibit
<+4.4V = Not Inhibit
Gnd = Inhibit
<not> Gnd = Not Inhibit
>+17V = WOW
<+4.4V = Not WOW
Gnd = WOW
<not> Gnd = Not WOW
>+17V = Inhibit
<+4.4V = Not Inhibit
Gnd = Audio Inhibit Toggle
<not> Gnd = Audio Inhibit
Not Toggle
Input
Input
Input
Input
Input
GND_DISC_02
28V_DISC_03
GND_DISC_03
28V_DISC_04
GND_DISC_04
GND WOW Discrete
+28V Audio Inhibit Discrete
Timed Audio Inhibit Discrete
Input
J1-35
J1-16
J1-15
J1-14
28V_DISC_05
GND_DISC_05
GND_DISC_06
GND_DISC_07
+28V Landing Gear Discrete
>+17V = Gear Down
<+4.4V = Gear Up
Gnd = Gear Down
<not> Gnd = Gear Up
Gnd = Cancel Toggle
<not> Gnd = Normal
Gnd = Low Altitude Mode
Select
<not> Gnd = Normal
Gnd = Low Volume
<not> Gnd = Normal
>+17V = Engaged
<+4.4V = Not Engaged
Gnd = Inhibit
Input
Input
Input
GND Landing Gear Discrete
Glideslope Cancel Discrete (Note 1)
Low Altitude Mode Select (Tactical) (Note 1)
Input
Input
J1-13
J1-8
GND_DISC_08
28V_DISC_09
GND_DISC_09
GND_DISC_10
Mode 6 Low Volume Discrete
Autopilot Engaged Discrete #1
Terrain Awareness Inhibit Discrete (Note 2)
Self-Test Discrete (Note 1)
Input
Input
J1-12
J1-34
<not> Gnd = Not Inhibit
Gnd = Self-Test Toggle
<not> Gnd = Normal
Input
Output
Output
J1-72
J1-55
MON_OUT_1
MON_OUT_2
GPWS INOP Discrete
TAD INOP Discrete
Terrain Not Available
J1-78
J1-77
DISC_OUT_1
DISC_OUT_2
GPWS Warning Discrete
Output
Output
Terrain Awareness Warning
Obstacle Awareness Warning
GPWS Alert Discrete
Terrain Awareness Caution
Obstacle Awareness Caution
Glideslope Cancel Discrete
Low Altitude Mode Discrete (Tactical)
TCAS Inhibit discrete
Terrain Display Select #1 Discrete
Terrain Awareness Caution or Warning
Obstacle Awareness Caution or Warning
Terrain Display Select #2 Discrete
Timed Audio Inhibit
J1-76
J1-73
J1-69
J1-54
J1-51
DISC_OUT_3
DISC_OUT_4
DISC_OUT_5
DISC_OUT_6
DISC_OUT_8
Output
Output
Output
Output
Gnd = Terrain Pop Up
Gnd = Audio Inhibit
Output
J1-49
J1-52
J1-48
DISC_OUT_9
DISC_OUT_7
28V_DISC_11
Output
Output
Not Defined in this ID (Note 3).
Input
J1-67
J2-15
J2-31
J1-50
GND_DISC_14
28V_DISC_13
GND_DISC_15
MON_OUT_3
Input
Input
Input
Not Defined in this ID (Note 3).
Not Defined in this ID (Note 3).
Not Defined in this ID (Note 3).
Not Defined in this ID (Note 3).
Output
Configuration Data
Lamp Format
Flashing Lamps
Possible States
Type 1,Type 2
True, False
State
Type 2
False
Note 1: Provided by Momentary cockpit switch (non-latching)
Note 2: Provided by Alternate cockpit switch (Latching) with guard if inhibiting
Note 3: This discrete may be used in another category.
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E 5.3.14
CATEGORY 14, AUDIO OUTPUT LEVEL
The following table provides identification of the Audio Output Level Select. Each entry in the ID column corresponds to a
particular nominal alert output level selection (Max, -6 dB, -12 dB, -18dB and –24dB). The nominal output is 4 Wrms for the
8-ohm output and 100 mWrms for the 600-ohm output. The Audio Output Level can be additionally reduced by 6dB with the
Mode 6 Low Volume discrete (see Category 13). The output power level will be the nominal maximum output (4W or
100mW) reduced by the volume selection from Table 5.3.14 and the Mode 6 Low Volume discrete.
TABLE E 3.1.14: AUDIO OUTPUT LEVEL
ID
Volume Select
Effectivity
App Cfg.
-001 -001
-001 -001
-001 -001
-001 -001
-001 -001
0
1
2
3
4
Nominal
-6 dB
-12 dB
-18 dB
-24 dB
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E 5.3.15
CATEGORY 15, AUTOROTATION THRESHOLD
The following table provides identification of the Autorotation Threshold. Each entry in the ID column corresponds to an
engine torque threshold for autorotation. Each helicopter type has a unique engine torque percentage during autorotation
based on the aerodynamic qualities of the aircraft. This value is not typically published or well known, thus it has been
included as a configuration item in Table 10.3.15. Since a typical Autorotation Threshold value is between 5% and 10%, the
values have been chosen from 0% to 15% in increments of 0.5%.
TABLE E 3.1.15: AUTOROTATION THRESHOLD FOR EGPWS MK XXII
Effectivity
1.1.1.1
Autorotation
Threshold
App.
% of Torque
Cfg.
0
1
2
3
4
5
6
7
N/A
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
EM22 -006 EM22 -006
0.5 %
1.0 %
1.5 %
2.0 %
2.5 %
3.0 %
3.5 %
4.0 %
4.5 %
5.0 %
5.5 %
6.0 %
6.5 %
7.0 %
7.5 %
8.0 %
8.5 %
9.0 %
9.5 %
10.0 %
10.5 %
11.0 %
11.5 %
12.0 %
12.5 %
13.0 %
13.5 %
14.0 %
14.5 %
15.0 %
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
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E 6 CONNECTOR INTERFACE
E 6.1 PINOUT FOR FRONT CONNECTORS SORTED BY PIN NUMBER
TABLE E 4: PIN ASSIGNMENT FOR FRONT CONNECTORS SORTED BY PIN NUMBER
Channel
Designation
Reference
Connector -
Signal Usage Summary*
Roll Attitude Synchro (X leg)
Roll Attitude Synchro (Z leg)
Magnetic Heading Synchro (Z leg)
26VAC Reference #1 (H)
Spare Synchro (X leg)
Spare Synchro (Z leg)
Spare Synchro (Y leg)
Pin
J1-01
J1-02
J1-03
J1-04
J1-05
J1-06
J1-07
J1-08
J1-09
J1-10
J1-11
J1-12
J1-13
J1-14
J1-15
J1-16
J1-17
J1-18
J1-19
J1-20
J1-21
J1-22
J1-23
J1-24
J1-25
J1-26
J1-27
J1-28
J1-29
J1-30
J1-31
J1-32
J1-33
J1-34
J1-35
J1-36
J1-37
J1-38
J1-39
J1-40
J1-41
J1-42
J1-43
J1-44
J1-45
J1-46
J1-47
J1-48
J1-49
J1-50
J1-51
SYN_1X
SYN_1Z
SYN_2Z
26REF_1H
SYN_3X
SYN_3Z
SYN_3Y
28V_DISC_09
28V_DISC_08
GS_VAL_L
28V_DISC_06
GND_DISC_09
GND_DISC_08
GND_DISC_07
GND_DISC_06
GND_DISC_05
GND_DISC_04
GND_DISC_03
GND_DISC_02
GND_DISC_01
SYN_1Y
Autopilot Engaged Discrete (+28VDC)
Barometric Altitude Validity Discrete (+28VDC)
Glideslope Deviation Low Level Validity (-)
Glideslope Validity Discrete (+28VDC)
Terrain Awareness and TCF Inhibit Discrete (Ground)
Mode 6 Low Volume Discrete (Ground)
Reserved
Glideslope Cancel Discrete (Ground)
Landing Gear Discrete (Ground)
Audio Inhibit Discrete (Ground) or Timed Audio Inhibit Discrete
Reserved
Glideslope Inhibit Discrete (Ground)
ILS Tuned Discrete (Ground)
Roll Attitude Synchro (Y leg)
Magnetic Heading Synchro (X leg)
Magnetic Heading Synchro (Y leg)
26VAC Reference #1 (L)
Air Temperature Reference (+5VDC)
Engine Torque #1 (+)
Engine Torque #1 (-)
Magnetic Heading Validity Discrete (+28VDC)
Radio Altitude Validity Discrete (+28VDC)
Glideslope Deviation Low Level Validity (+)
Display Selected Discrete #2 (Ground)
Display Selected Discrete #1 (Ground)
DH Discrete (Ground)
SYN_2X
SYN_2Y
26REF_1L
OAT_REF
TORQUE_1H
TORQUE_1L
28V_DISC_10
28V_DISC_07
GS_VAL_H
GND_DISC_13
GND_DISC_12
GND_DISC_11
GND_DISC_10
28V_DISC_05
28V_DISC_04
28V_DISC_03
28V_DISC_02
28V_DISC_01
PWR_H
PWR_L
GND
ALT_L
OAT_L
RALT_L
GSDEV_L
TORQUE_2L
28V_DISC_11
DISC_OUT_9
MON_OUT_3
DISC_OUT_8
Self Test Discrete (Ground)
Landing Gear Discrete (+28VDC)
Audio Inhibit Discrete (+28VDC)
Reserved
Glideslope Inhibit Discrete (+28VDC)
ILS 1 Tuned Discrete (+28VDC)
Power Input: 28 VDC (+)
Power Input: 28 VDC (return)
Chassis Ground
Barometric Altitude (-)
Air Temperature (-)
Radio Altitude: ARINC 552 or ALT 55 (-)
Glideslope Deviation - Low Level (+ down)
Engine Torque #2 (-)
Spare +28VDC Discrete
Terrain Select Relay Output #2
Reserved
Spare Lamp Output
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Channel
Designation
Reference
Connector -
Pin
Signal Usage Summary*
J1-52
Spare Output/ Timed Audio Inhibit /Windshear Warning
Output**
DISC_OUT_7
J1-53
J1-54
J1-55
J1-56
J1-57
J1-58
J1-59
J1-60
J1-61
J1-62
J1-63
J1-64
J1-65
J1-66
J1-67
J1-68
J1-69
GND
Temperature Probe GND
DISC_OUT_6
MON_OUT_2
453TX_2A
453TX_2B
453TX_1A
453TX_1B
PWR_H
PWR_L
ALT_H
OAT_H
RALT_H
Terrain Select Relay Output #1
TAD / TCF INOP Output (monitor)
Terrain Display Output Data #2 (A leg)
Terrain Display Output Data #2 (B leg)
Terrain Display Output Data #1 (A leg)
Terrain Display Output Data #1 (B leg)
Power Input: 28 VDC (+)
Power Input: 28 VDC (return)
Barometric Altitude (+)
Air Temperature (+)
Radio Altitude: ARINC 552 or ALT 55 (+)
Glideslope Deviation - Low Level (+ up)
Engine Torque #2 (+)
GPWS Inhibit (GND) Discrete or Attitude Validity Discrete
Spare +28VDC Discrete
GSDEV_H
TORQUE_2H
GND_DISC_14
28V_DISC_12
Audio On (GND) Output or TCAS Inhibit Discrete (GND)
Output
DISC_OUT_5
J1-70
J1-71
J1-72
J1-73
J1-74
J1-75
J1-76
J1-77
J1-78
High Level Audio Output - 8Ω (+)
AUD_HL_H
AUD_HL_L
MON_OUT_1
DISC_OUT_4
AUD_LL_L
High Level Audio Output - 8Ω (-)
GPWS INOP Output (monitor)
Reserved
Low Level Audio Output – 600Ω (-)
Low Level Audio Output - 600Ω (+)
Glideslope Cancel Output
Glideslope Alert Output
AUD_LL_H
DISC_OUT_3
DISC_OUT_2
DISC_OUT_1
GPWS Warning Output
J2-01
J2-02
J2-03
J2-04
J2-05
J2-06
J2-07
J2-08
J2-09
J2-10
J2-11
J2-12
J2-13
J2-14
J2-15
J2-16
J2-17
J2-18
J2-19
J2-20
J2-21
J2-22
J2-23
J2-24
J2-25
SYN_4X
SYN_4Y
SYN_5Z
Configurable Synchro #1 (X leg)
Configurable Synchro #1 (Y leg)
Configurable Synchro #2 (Z leg)
Radio Altitude ARINC 429 Input (B leg)
ILS ARINC 429 Input (B leg)
Magnetic Heading/Roll ARINC 429 Input (B leg)
Spare ARINC 429 Input (B leg)
GPS ARINC 429 Input (B leg)
EGPWS ARINC 429 Output #2 (B leg)
Alt Display Display #2 or ADC RS-232 / 422 Input (B leg)
Alt Display Range #2 or ADC RS-232 / 422 Input (A leg)
GPS RS-232 / 422 Input (B leg)
429RX_5B
429RX_6B
429RX_7B
429RX_8B
429RX_4B
429TX_2B
422_232RX_2B
422_232RX_2A
GPS_RXB
GND
28V_DISC_13
GND
SC_PWR
SYN_4Z
SYN_5X
ADC RS-232 Common
Spare Discrete Input
Configuration Module Power Return (Ground)
Configuration Module Power (+5VDC)
Configurable Synchro #1 (Z leg)
Configurable Synchro #2 (X leg)
Configurable Synchro #2 (Y leg)
Radio Altitude ARINC 429 Input (A leg)
ILS ARINC 429 Input (A leg)
Magnetic Heading/Roll ARINC 429 Input (A leg)
Spare ARINC 429 Input (A leg)
GPS ARINC 429 Input (A leg)
SYN_5Y
429RX_5A
429RX_6A
429RX_7A
429RX_8A
429RX_4A
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Channel
Designation
Reference
429TX_2A
422_232TX_2A
GND
Connector -
Pin
Signal Usage Summary*
J2-26
J2-27
J2-28
J2-29
J2-30
J2-31
J2-32
J2-33
J2-34
J2-35
EGPWS ARINC 429 Output #2 (A leg)
ADC RS-232 / 422 Output (A leg)
GPS / ADC RS-232 / 422 Common
GPS RS-232 / 422 Input (A leg)
GPS_RXA
GND_DISC_15
SPICLK
SPIMISO
26REF_2H
26REF_2L
Spare Discrete Input
Configuration Module Serial Clock
Configuration Module Serial Input
26VAC Reference #2 (H)
26VAC Reference #2 (L)
Display Range #1
J2-36
J2-37
429_422RX_1
429_422RX_1
ARINC 429 (B leg)
RS-422 Input (A leg)
Display Range #1
ARINC 429 (A leg)
RS-422 Input (B leg)
J2-38
J2-39
J2-40
J2-41
J2-42
J2-43
J2-44
J2-45
J2-46
J2-47
J2-48
J2-49
J2-50
429RX_2B
429RX_2A
429RX_3B
429RX_3A
429TX_1B
429TX_1A
422_232TX_2B
GPS_TXA
GPS_TXB
Air Data ARINC 429 Input (B leg)
Air Data ARINC 429 Input (A leg)
Display Range #2 ARINC 429 Input (B leg)
Display Range #2 ARINC 429 Input (A leg)
EGPWS ARINC 429 Output #1 (B leg)
EGPWS ARINC 429 Output #1 (A leg)
ADC RS-232 / 422 Output (B leg)
GPS RS-232 / 422 Output (A leg)
GPS RS-232 / 422 Output (B leg)
SPISEL_CM#
SPIMOSI
Configuration Module Serial Select
Configuration Module Serial Output
J3-01
J3-02
J3-03
J3-04
J3-05
J3-06
J3-07
J3-08
J3-09
J3-10
J3-11
J3-12
J3-13
J3-14
J3-15
GND
CARD_PRES#
SmartCable Power Return (Ground)
PCMCIA Card Present
RS232RXD_MON EGPWS Monitor Port (RS232 Receive)
RS232TXD_MON EGPWS Monitor Port (RS232 Transmit)
Reserved
SC_PWR
SPICLK
SPIMISO
SPIMOSI
SPISEL_SC#
GSE_PRES#
GND
SmartCable Power (+5VDC)
SmartCable Serial Clock
SmartCable Serial Input
SmartCable Serial Output
SmartCable Serial Select
GSE Present
Ground
Ground
Ground
Reserved
GND
GND
GPS ANT
COAX
GPS COAX connection
*Refer to Category 13 where multiple uses are possible.
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Figure E 4, Front Panel Connector Orientation - J1, J2, J3, GPS ANT
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Figure E 4.1, Connector Pin References - J1, J2, J3
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MK XXII EGPWS Installation Manual
E 7 DEFINITIONS
The following acronyms are provided for use with this document:
Acronym
Interpretation
AAAS
ADC
ADS
Alternate Audio Alert Select
Air Data Computer
Air Data System
AGL
AHRS
AIC
Above Ground Level
Attitude Heading Reference System
Analog Input Controller
AIMS
AOA
ASA
Airplane Information Management System
Angle of Attack
AlliedSignal Aerospace
ASL
ATP
BCD
Above Sea Level
Acceptance Test Procedure
Binary Coded Decimal
BIST
BIT
Built in Self Test
Built In Test
BITE
BNR
BOSS
C/O
Built In Test Equipment
Binary
Batch Oriented Simulation System
Callouts
CAA
CAIMS
CFDS
CFIT
CFM
CISRD
CMC
COTS
CP
Civil Aviation Authority
Central Aircraft Information/Maintenance System
Centralized Fault Display System
Controlled Flight Into Terrain
Cubic Feet per Minute
CFDS Interface System Requirements Document
Central Maintenance Computer
Commercial Off the Shelf
Control Panel
CRS
CW
Course
Clockwise
DAA
DADC
DAU
DC
Digital/Analog Adapter
Digital Air Data Computer
Data Acquisition Unit
Digital Command
DDM
DEVN
DH
Difference in Depth of Modulation
Deviation
Decision Height
DITS
DME
DO
Digital Information Transfer System
Distance Measuring Equipment
Discrete Output
DSP
DSU
Digital Signal Processor
Display Switching Unit
DSWC
EEPROM
EFCP
EFIS
EGPWC
EGPWD
EGPWS
EICAS
EMI
Digital Stall Warning Computer
Electrically Erasable Programmable Read Only Memory
EFIS Control Panel
Electronic Flight Instrument System
Enhanced Ground Proximity Warning Computer
Enhanced Ground Proximity Warning Display
Enhanced Ground Proximity Warning System
Engine Indication and Crew Alert System
Electromagnetic Interference
Enabled
ENB
EPROM
Erasable Programmable Read Only Memory
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Acronym
Interpretation
F/T
Functional Test
F/W
F/W
Fail/Warning
Fail/Warning
FAA
FCC
FDR
FIAS
FMC
FMS
FPM
FSEU
FWC
G/S
Federal Aviation Administration
Flight Control Computer
Flight Data Recorder
Flight Inspection Aircraft System
Flight Management Computer
Flight Management System
Feet per Minute
Flaps/Slats Electronic Unit
Fault Warning Computer
Glideslope
GMT
GPS
GPW
GPWS
GT
Greenwich Mean Time
Global Position System
Ground Proximity Warning
Ground Proximity Warning System
Greater Than
H/W
HDG
HDOP
HSID
I/O
IAC
ICD
ILS
INOP
IOC
IRS
ISO
Hardware
Heading
Horizontal Dilution of Position
Hardware/Software Interface Document
Input/Output
Integrated Avionics Computer
Interface Control Document
Instrument Landing System
Inoperative
Input/Output Concentrator
Inertial Reference System
International Standards Organization
Inertial Vertical Speed
Knots
IVS
KT
KTS
LED
LRRA
LRU
LSB
Knots
Light Emitting Diode
Low Range Radio Altimeter
Line Replaceable Unit
Least Significant Bit
LT
Less Than
Mode Control Panel
MCP
MDA
MFD
MKII
MKV
MKVI
MKVII
MKVIII
MKXXII
MLS
MMU
MSB
N/A
Minimum Barometric Altitude
Multi-Functional Display
Mark Two Warning Computer
Mark Five Warning Computer
Mark Six Warning Computer
Mark Seven Warning Computer
Mark Eight Warning Computer
Mark Twenty Two Warning Computer
Microwave Landing System
Memory Management Unit
Most Significant Bit
Not Applicable
NCD
ND
NVM
OMS
P/N
No Computed Data
Navigation Display
Non Volatile Memory
Onboard Maintenance System
Part Number
PAR
Parity
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Acronym
Interpretation
PC
Personal Computer
PCMCIA
PFD
Personal Computer Memory Card Industry Association
Primary Flight Display
PMAT
PP
PVM
PWS
QFE
QNH
RA
Portable Maintanence Access Terminal
Program Pin
Processor/Voice/Memory
Predictive Windshear System
Corrected Baro Alt relative to field elevation
Corrected Baro Alt relative to sea level
Radio Altitude
RAM
RDOP
ROM
RTCA
RTS
RWY
S/T
Random Access Memory
Radar Display Output Processing
Read Only Memory
Requirements and Technical Concepts for Aviation
Ready to Transmit Signal
Runway
Self Test
S/W
Software
SDI
SDRD
SIG
Source/Destination Identifier
Software Design Requirements Document
Significant
SPC
Stall Protection Computer
System Requirements Document
Sign Status Matrix
SRD
SSM
ST
Self Test
SWC
TA&D
TACAN
TAD
TBD
TCAS
TCF
Stall Warning Computer
Terrain Awareness & Display
Tactical Air Navigation
Terrain Awareness Display
To Be Determined
Traffic Collision Avoidance System
Terrain Clearance Floor
United States’ Standards for Terminal Instrument Procedures
Track
TERPS
TK
TLB
TSO
TTL
Translation Lookaside Buffer
Technical Standing Order
Tuned To Localizer
UART
USM
UTC
UUT
VDC
VDOP
VHF
VLSI
VOR
W/S
Universal Asynchronous Receiver Transmitter
Unsigned Magnitude
Universal Time Correlation
Unit Under Test
Volts, DC
Vertical Dilution of Precision
Very High Frequency
Very Large Scale Integrated Circuit
VHF Omni-directional Range
Windshear
WC
Warning Computer
WX
Weather
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