Honeywell MKXXII Installation Manual MK II EGPWS For Rotorwing Aircraft User To The 9007811f 9995 4f22 9775 C9ea39d8fc10

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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
Honeywell
MK XXII EGPWS Installation Manual
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This document is an unpublished work. Copyright 2000 Honeywell, International, Inc. All
rights reserved.
This document and all information and expression contained herein are the property of Honeywell International
Inc., and is provided to the recipient in confidence on a “need to know” basis. Your use of this document is strictly
limited to a legitimate business purpose requiring the information contained therein. Your use of this document
constitutes acceptance of these terms.
Honeywell
MK XXII EGPWS Installation Manual
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Typed names constitute approval signatures. Actual signatures are on file at Honeywell in
Redmond, WA.
DRAWN Dennis Martin 12/8/00
CHECK Sara Stark 12/8/00
ENGR Dennis Martin 12/8/00
MFG
QA
APVD Dennis Martin 12/8/00
APVD
REVISIONS
SH REV DESCRIPTION DATE APPROVED
ALL A Added Software –008 Revisions.
Reason: 01 Severity: 10
8/9/01
8/9/01
S. Wright
D. Martin
ALL B Added Software –010 Revisions.
Reason: 01 Severity: 10
3/22/02
3/22/02
D. Martin
R Gilliland
ALL C Added Software –011 Revisions.
Reason: 01 Severity: 10
6/07/02
6/7/02
D Martin
T Curtis
Honeywell
MK XXII EGPWS Installation Manual
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TABLE OF CONTENTS
SECTION I – GENERAL INFORMATION............................................................................................ 16
1.1 INTRODUCTION.................................................................................................................................... 16
1.2 APPLICABILITY.................................................................................................................................... 16
1.3 HOW TOUSE 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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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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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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APPENDIX C.........................................................................................................................................................................143
WINVIEWS OPERATION INSTRUCTIONS ...................................................................................................................143
APPENDIX D............................................................................................................................................ 149
VENDOR DRAWINGS............................................................................................................................ 149
D 1-0 VENDOR CONTACT INFORMATION................................................................................................. 151
D1-1 EDMO................................................................................................................................. 153
D1-2 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 PART NUMBER..........................................................................................................................................................166
E 2 PURPOSE...................................................................................................................................................................166
E 3 SYSTEM OVERVIEW..................................................................................................................................................166
E 4 ELECTRICAL INTERFACE..................................................................................................................................167
E 4.1 Introduction .....................................................................................................................................................167
E 4.2 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 Discrete Inputs.............................................................................................................................................174
E 4.2.11 Configuration Module Interface ..................................................................................................................175
E 4.2.12 GPS Antenna Input ......................................................................................................................................175
E 4.2.13 OAT Voltage Reference Output....................................................................................................................176
E 4.2.14 Lamp Driver Outputs ...................................................................................................................................176
E 4.2.16 Audio Outputs ..............................................................................................................................................176
E 4.2.17 ARINC Digital Serial Output Busses ...........................................................................................................177
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E 4.2.17.1 ARINC 429 Output Bus................................................................................................. ...........................177
E 4.2.17.2 ARINC 453 Output Bus................................................................................................. ...........................178
E 4.2.18 FRONT PANEL TEST INTERFACE........................................................................................................................178
E 4.2.18.1 RS-232 MAINTENANCE PORT (SERIAL PORT 4).............................................................................................178
E 4.2.18.2 PCMCIA / SmartCable Port ....................................................................................................................179
E 4.2.18.3 GSE Present Discrete Input .....................................................................................................................179
E 4.2.19 FRONT PANEL STATUS INDICATORS .................................................................................................................179
E 5 AIRCRAFT APPLICATION DATA .......................................................................................................................180
E 5.1 CONFIGURATION TYPES........................................................................................................................................180
E 5.2 CONFIGURATION SELECTION ................................................................................................................................180
E 5.3 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 Category 10, Attitude Input Select ...............................................................................................................238
E 5.3.11 Category 11, Heading Input Select..............................................................................................................240
E 5.3.12 Category 12, Windshear Input Select...........................................................................................................241
E 5.3.13 Category 13, Input / Output Discrete Type Select .......................................................................................242
E 5.3.14 Category 14, Audio Output Level ................................................................................................................245
E 5.3.15 Category 15, Autorotation Threshold ..........................................................................................................246
E 6 CONNECTOR INTERFACE...................................................................................................................................247
E 6.1 PINOUT FOR FRONT CONNECTORS SORTED BY PIN NUMBER .................................................................................247
E 7 DEFINITIONS ........................................................................................................................................................252
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SECTION I
GENERAL INFORMATION
Honeywell
MK XXII EGPWS Installation Manual
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SECTION I – GENERAL INFORMATION
SECTION I – GENERAL INFORMATION............................................................................................ 16
1.1 INTRODUCTION.................................................................................................................................... 16
1.2 APPLICABILITY.................................................................................................................................... 16
1.3 HOW TOUSE 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
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1.12 LICENSE REQUIREMENTS................................................................................................................... 28
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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 Product Specification for the MK XXII Enhanced Ground Proximity
Warning System (EGPWS)
993-1176-401 Interface Control Document (ICD) for the MK VI/VIII/XXII Enhanced
Ground Proximity Warning System
965-1590-206 Outline, MK XXII EGPWC
060-4326-000 EGPWS Terrain Database Airport Coverage List
060-4314-009 Generic RWFM Supplement For EGPWS
060-4314-200 Mk XXII Helicopter-Enhanced GPWS Pilot’s Guide
060-4314-006 General Flight Test Procedure
060-4167-167 Installation Ground Test Procedure for the Mk XXII EGPWS for
Rotary Wing Aircraft
060-4314-002 Failures Modes, Effects, and Safety Analysis
060-4314-011 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: 1575.42 MHz
Impedance: 50 ohms
Gain: 33dB max, 26.5 dB preferred
Power: 5 VDC
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 TSO-C129
King KA 92 P/N 071-01553-0200 TSO-C129
Sensor Systems P/N S67-1575-52 TSO-C129, ARINC 743A
Sensor Systems P/N S67-1575-133 TSO-C129a, ARINC 743A
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: TSO-C92c, TSO-C151a, class A
Physical size (HxWxD): 6.20” x 3.04” x 10.30”
Weight: 3.9 pounds maximum
Mounting: Standard 3 inch King Radio rack
Temperature (operational): -55°C to +70°C (F2)
Altitude range: 55,000 feet (F2)
Cooling: No cooling necessary
Shock: No shock mounting required
Power Consumption (28 VDC): 3 Amps
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: 2.68” x 1.51” x 0.32” (fits Positronic connector backshell)
Weight: <1 pound with connector and backshell
Mounting: Mounts to Positronic connector backshell
Temperature (operational): same as MK XXII EGPWS
Altitude range: same as MK XXII EGPWS
Cooling: No cooling necessary
Shock: No shock mounting required
Power Consumption (5 VDC): from MK XXII EGPWS
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
Positronic Ind. DD78F1OJVLC-15 P1 connector 1 EA 440-1158-009
Positronic Ind. RD50F1OJVLC-15 P2 connector 1 EA 440-1233-001
Amphenol 79075 GPS Antenna connector 1 EA 440-1239-001
Honeywell 700-1710-001 Configuration Module 1 EA 700-1710-001
Bendix/King 071-04003-0002 Computer Mounting Tray 1 EA 405-0383-001
CIC 05257 OAT Sensor 1 EA 107-1049-001
CIC 05257-TOMK OAT mounting Kit 1 EA 107-1049-002
CIC 05257-TPIK OAT Connector Kit 1 EA 107-1049-003
(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
Positronic Ind. DD78F1OJVLC-15 P1 connector 1 EA 440-1158-009
Positronic Ind. RD50F1OJVLC-15 P2 connector 1 EA 440-1233-001
Amphenol 79075 GPS Antenna connector 1 EA 440-1239-001
Honeywell 700-1710-001 Configuration Module 1 EA 700-1710-001
Bendix/King 071-04003-0002 Computer Mounting Tray 1 EA 405-0383-001
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 Vendor P/N Description QTY UM Honeywell P/N
Honeywell 704-2617-001 RS-232 Cable 1 EA 704-2617-001
1.8.3 Smart Cable
The MK XXII EGPWS Smart Cable can be ordered using the following part numbers:
Vendor Name Vendor P/N Description QTY UM Honeywell P/N
Honeywell 951-0386-001 Smart Cable 1 EA 951-0386-001
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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 Vendor P/N Description QTY UM Honeywell P/N
Honeywell 424NAM North America 1 EA 718-1447-xxx
Honeywell 424SAM South America 1 EA 718-1448-xxx
Honeywell 424EUR Europe 1 EA 718-1449-xxx
Honeywell 424EEU Eastern Europe 1 EA 718-1450-xxx
Honeywell 424AFR Africa 1 EA 718-1451-xxx
Honeywell 424PAC Pacific 1 EA 718-1452-xxx
Honeywell 424ASI Asia 1 EA 718-1453-xxx
Honeywell 424SPA South Pacific 1 EA 718-1457-xxx
Honeywell 424MES Middle East 1 EA 718-1458-xxx
Honeywell 402-6075-xxx Label, TDB Front Panel 1 EA 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 Vendor P/N Description QTY UM Honeywell P/N
Honeywell * Flight History Download 1 EA *
* 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 ARINC 453 cable A/R EA
Pic Wire&Cable D5102QX Hi Temp Quadraxial A/R EA
Pic Wire&Cable D771553 MIL-STD 1553 Data Bus A/R EA
ECS 4122021 ARINC 453 cable A/R EA
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Vendor Name Vendor P/N Description QTY UM Honeywell P/N
Emteq D 07002-100 ARINC 453 Cable A/R EA
M17/176-00002 Military Specification A/R EA
1.9.2 GPS Antenna & cable
The GPS Antenna & cable can be ordered from their manufacturers using the following part
numbers:
Vendor Name Vendor P/N Description QTY UM Honeywell P/N
Bendix/King 071-01545-0200 KA 91 GPS Antenna 1 EA
Bendix/King 071-01553-0200 KA 92 GPS Antenna 1 EA 300-1147-001
Comant CI 405-2 KA 92 GPS Antenna 1 EA 300-1147-001
Bendix/King 050-03318-0000 Antenna Installation Kit OPT EA 405-0432-001
Sensor Systems S67-1575-38 S67 GPS Antenna 1 EA
Sensor Systems S67-1575-52 S67 GPS Antenna 1 EA
Sensor Systems S67-1575-133 S67 GPS Antenna 1 EA
Thermax M17/128-RG400 Coax Cable, RG400 A/R EA
Coax Cable, RG-142 A/R EA
Amp 225554-6 TNC Angle Plug, Male 1 EA 440-1239-001
Amphenol 79075 TNC Angle Plug, Male 1 EA 440-1239-001
1.9.3 Circuit Breaker
The Circuit Breaker needs to be a 3 Amp delayed action circuit breaker.
Vendor Name Vendor P/N Description QTY UM Honeywell P/N
Klixon (T.I.) 7277-2-3 3 Amp Circuit Breaker,
EGPWS power +28
1EA
Klixon (T.I.) 7277-2-1 1 Amp Circuit Breaker,
lamp power +28
1EA
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/TES T; 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/annu nciator 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 a nnunciator 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 Vendor P/N Description QTY UM Honeywell P/N
Quam 30A05Z8 Audio Speaker 1 EA
Utah SP-3A Audio Speaker 1 EA
CTS 4AC3 Audio Speaker 1 EA 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
Hand Crimping Tool EA 1 Positronic Ind. 9507
Hand Crimping Tool EA 1 Daniels AFM8
Hand Crimping Tool EA 1 Military M22520/2-1
1.11.2 Contact Positioner - P1, P2, P3
Description UM QTY Vendor Name & Part Number
Contact Positioner, Socket P1 EA 1 Positronic Ind. 9502-3
Contact Positioner, Socket P1 EA 1 Daniels K41 (for 22 to 28 AWG)
Contact Positioner, Socket P1 EA 1 Military M22520/2-06
Contact Positioner, Socket P2 EA 1 Positronic Ind. 9502-5
Contact Positioner, Socket P2 EA 1 Daniels K13-1 (20-24 AWG)
Contact Positioner, Socket P2 EA 1 Military M22520/2-08
Contact Positioner, Pin P3 EA 1 Positronics 9502-4
Contact Positioner, Pin P3 EA 1 Daniles K42 (22-28 AWG)
Contact Positioner, Pin P3 EA 1 Military M22520/2-09
1.11.3 Insertion/Removal Tool - P1, P2, P3
Description UM QTY Vendor Name & Part Number
Removal Tool P1, P3 EA 1 Daniels DRK 95-22M
Removal Tool P1, P3 EA 1 Military M81969/8-02
Removal Tool P2 EA 1 Daniels DRK145
Insertion Tool P1, P3 EA 1 Daniels DAK 95-22M
Insertion Tool P1, P3 EA 1 Military M81969/8-01
Insertion Tool P2 EA 1 Daniels DAK145
Insertion/Removal Tool P1, P3 EA 1 Military M81969/1-04
Insertion/Removal Tool P2 EA 1 Military M81969/1-02
1.11.4 Spare Contacts - P1, P2, P3
Description Mil Spec Part Number
Contacts (P1) socket M39029/57-354 22-28 GA Wire
Contacts (P2) socket M39029/63-368 20-24 GA Wire
Contacts (P3) Pin M39029/58-360 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 P2 pin #
Violet P2-17
Blue P2-16
Orange P2-33
Wire Color P2 pin #
Black P2-50
White P2-49
Red P2-32
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D. Position Slide Lock and Spring Clip onto connector.
E. Install Backshell Housing onto connector. The Ground wire (used for ESD discharge) is terminated
with shielded pigtails inside the backshell to the P2 connector.
F. Organize and dress wire exiting from the backshell, route Configuration Module wires in a coil. Install
Cable Clamp, do not tighten Cable Clamp screws.
G. Secure the Configuration Module to the connector using screws provided. Tighten Cable Clamp
screws as required.
CONFIGURATION MODULE ASSEMBLY
REQUIRED: Two items as follows:
ITEM 1.0 Connector (P2) Positronic Ind. RD50F10JVLC-15 *
ITEM 2.0 Configuration Module Honeywell 700-1710-001
* This item may be available from Honeywell under Part No. (440-1233-001)
ITEM 1 DESCRIPTION:
Connector P2 (Positronic Ind. PN RD50F10JVLC-15) is a packaged kit consisting of the following parts:
1.1 Connector, 50 socket D-Sub Qty - 1
1.2 Contacts, size 20 crimp Qty - 50
1.3 Backshell housing Qty - 1
1.4 Backshell plate Qty - 1
1.5 Screws, Phillips CSK Qty - 2
1.6 Spring Clip Qty - 1
1.7 Slide Lock Qty - 1
1.8 Screws, Slotted Qty - 2
1.9 Cable Clamp Qty - 1
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INSTALLATION ASSEMBLY SEQUENCE
STEP 1 Install all MK 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 +28 VDC Input
J1-41, J1-61 +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
62
43
9
25
63
44
53
J1
Altitude Out
Signal Common
BIT Out
Analog Air Data ComputerEGPWS MK XXII
(+)
(-)
Uncorrected
Barometric
Altitude
Baro Altitude Valid +28V
(+)
(-)
Temp. Input
Chassis Ground
+5V Excitation
500 ohm
Temperature
Probe
Analog-ADC.vsd
Cat 2 Uncorrected Baro Altitude
Vendor Model ID Altitude Out Common BIT Out
CIC 04077 0 J1-F J1-G J1-E
Collins ADS-65 3 J1-12 J1-13 J1-5
CIC 02702 4 J1-A J1-B J1-E
Honeywell AZ-241 11/12 J1-63 J1-11 J1-12
Honeywell AZ-242 11/12 J1A-40 J1A-11 J1A-12
Honeywell AZ-648 11/12 J1-J J1-G J1-U
Honeywell AZ-800 11/12 J1A-78 J1A-10 J1A-34
Honeywell AZ-810 11/12 J1A-78 J1A-10 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.
39
38
A
B
J2 ARINC 429 Air Data
ARINC 429 Bus - Hi
ARINC 429 Bus - Lo
EGPWS MK XXII
A
B
ARINC 429 Low Speed
Air Data Bus
Digital-ADC.vsd
Cat 2 Bus 1 Bus 2
Vendor Model ID A B A B
Sperry AZ-8XX 5* J1B-26 J1B-27 J1B-70 J1B-71
CIC 04471 5* J1-12 J1-13
CIC 02702 mod 6 * J2-J J2-K
KDC 281 * P2811-5 P2811-6
KDC 481 * P4811-U P4811- i
B&D 90004 5* J1-27 J1-9
B&D 2600 * 6 8
B&D 2601 * 14 13
B&D 2800 * P201-11 P201-28
Collins ADC 85/86 5* P2-9 P2-10 P2-29 P2-30
Shadin ADC-2000
(s/w mod 71.73.01) 5* J1-40 J1-22
NOTE: The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS
engineering. Please contact the manufacturer’s customer service to confirm your installation.
* Category 2, ID 5, 1 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.
39
38
A
B
J2 ARINC 575 Air Data
ARINC 575 Bus - Hi
ARINC 575 Bus - Lo
EGPWS MK XXII
A
B
ARINC 575
Air Data Bus
ARINC575-ADC.vsd
Cat 2 Bus 1 Bus 2
Vendor Model ID A B A B
Collins ADC-80( )
Collins ADC-82A
2 P3-35 P3-36
B&D 90004 2 J1-27 J1-9
NOTE: The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS
engineering. Please contact the manufacturer’s customer service to confirm your installation.
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3.3.2.6 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.
39
38
A
B
J2 ARINC 429 Air Data
ARINC 429 Bus - Hi
ARINC 429 Bus - Lo
EGPWS MK XXII
A
B
ARINC 429 Low Speed
Air Data Bus
(+)
(-)
Temp. Input
Chassis Ground
+5V Excitation
500 ohm
Temperature
Probe
25
63
44
53
J1
Shadin2000.vsd
Cat 2 Bus 1 Bus 2
Vendor PN ID A B A B
962830-1,2,3 10 J2-7 J2-8
962830A-1,2,3
962830A-X-S-4
962830A-X-S-5
962830A-1-S-7(B212/412)
10 J1-40 J1-22
NOTE: The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS
engineering. Please contact the manufacturer’s customer service to confirm your installation.
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3.3.2.7 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.
39
38
A
B
J2 IOC Buses
IOC Bus 1
EGPWS MK VI / MK VIII
A
B
ARINC 429
High Speed
41
40
A
B
IOC Bus 2
A
B
ARINC 429
High Speed
ARINC429-IOC.vsd
Cat 2 IOC Bus 1 IOC Bus 2
Vendor Model ID A B A B
BD 100 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)
25
8
A
B
J2 ARINC 429 GPS
ARINC 429 Bus - Hi
ARINC 429 Bus - Lo
EGPWS MK XXII
A
B
ARINC 429
GPS Bus
ARINC429-GPS.vsd
429 GPS Alt ARINC Bus 1 Bus 2
Vendor Model Speed Ref. 743/743A A B A B
GNS-XLS (17960-0203-)
or (17960-0102-) SM06 Low MSL 743A J101-N5 * J101-N6 *
GNS-XL (18355-) SM06 Low MSL 743A J101-N5 J101-N6
HG2021GBXX H/L** MSL 743 J1-38 J1-39 J1-24 J1-25
HG2021GDXX H/L** MSL 743A J1-38 J1-39 J1-24 J1-25
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)
45
29
J2 RS-232 GPS
RX – Receive In
TX – Transmit Out
EGPWS MK XXII
TX
RX
RS – 232
GPS Bus
28CM GND
NC
RS232-GPS.vsd
GPS Alt ARINC RS-232
Vendor Model Ref. 743/743A RX TX GND
GARMIN GNS430
Software Version 2.21 MSL N/A P4001-56 Chassis
KLN 900
066-04034-0104 or 066-04034-0204
MSL N/A P9002-13 Chassis
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.
25
8
A
B
J2 ARINC 429 GPS
ARINC 429 Bus 1
Lo
EGPWS MK XXII
A
B
ARINC 429
GPS Bus
23
6
A
B
A
B
ARINC 429
GPS Bus
Hi
ARINC 429 Bus 2
Lo
Hi
ARINC429-DualGPS.vsd
429 GPS Alt ARINC Bus 1 Bus 2
Aircraft Model Speed Ref. 743/743A A B A 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
Display manufacturer, model, etc.
Sweep Type
The type of sweep used for terrain data (fan, standard, etc.)
Auto Pop Up Category 7, Options Select Group #1
TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True
The TA&D Alternate Pop Up is set to
False or True in Category 7. If False,
Pop Up behavior for the terrain
display is described here.
The TA&D Alternate Pop Up is set to
False or True in Category 7. If True,
Pop Up behavior for the terrain
display is described here.
Peaks Mode Category 7, Options Select Group #1
See Note 1 Peaks Enable: False Peaks Enable: True
Peaks Enable is set to False or True
in Category 7. The effect of setting it
to False is described here.
Peaks Enable is set to False or True
in Category 7. The effect of setting it
to True is described here.
Manual select
Describes if/when terrain display(s) can be manually selected
Manual deselect
Describes if/when terrain display(s) can be manually deselected
Auto Range
Defines if the display data is automatically scaled and, if so, the scale used
(such as 10 nautical miles)
Moving Marker
Indicates whether or not a moving marker is provided
Overlay Page
Describes where “TERR” and Peaks Elevations overlays will be located on the
display screen.
Display Priority
Indicates the priority for displaying terrain data. For example:
Standard (PWS Warn, Terrain Warn, PWS Caution, Terrain Caution)
Searchlights
Display bus type
Defines the display bus type ‘KC Picture Bus (ASPB), ‘Honeywell Picture Bus’
or ‘ARINC 453’.
CHANNEL
TX453-1 CONNECT TO:
A = J1-58
B = J1-59
Indicates the correct connection for these pins
CHANNEL
TX453-2 CONNECT TO:
A = J1-56
B = J1-57
Indicates the correct connection for these pins
Notes: 1 Peaks Mode “(Not Available)” or “(Elevations via overlay)” shown here. Peaks mode “Not Available” means
that this display type cannot display Peaks Mode.
Table 0-1 Definition of Display Configuration Group Tables (Appendix E Section 5.3.6)
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WX System R/T
J2-37
J2-36
J1-58
J1-59
J1-51
J1-32
A
B
A
BARINC 453 TERRAIN BUS #1
ARINC 429 RANGE BUS
J1-54 Terrain Display Select #1 Discrete Output
Terrain Pop-Up Discrete Output
Display Select
Discrete #1 Input
DSD #1 Gnd
Gnd
Range #1
Gnd
TERR
ON
Momentary
28 VDC
DISPLAY RELAY
429 IN 453 OUT
453 #1
J1-56
J1-57
A
B
453 #2
J2-41
J2-40
A
B
Range #2
J1-31DSD #2 Gnd
Wx/TERR
Display
System
453 WX /
TERR BUS
A
B
A
B
TERRAIN
POP-UP
TERRAIN
SELECTED
429 Range
Output Bus
BRT/
DIM/
TEST
FIGURE 3.3.6-1 Single Tube Wx/Terrain Display
* Display relay specifications:
- 4PDT - Continuous Duty Cycle
- Pickup Voltage: 13.5 Vdc Max. - Dropout Voltage: 7.5 - 2.0 Vdc
- Coil Resistance: nominal 500 Ohms (~100mA @ 28 Vdc)
- Coil Rating: 26.0 Vdc (nominal) 34 Vdc (max.)
- Contact V drop: < 125mV @ rated load
- Contact current rating: 2 Amps resistive @ 28 Vdc
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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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Honeywell Grimes
TRA-45A
J2
J1
J1
J1
28
13
1
3
28
13
1
3
37
36
41
40
58
59
56
57
TERR
INHIB
TERR
INOP
Lamp Test 28V Lamp Dimming Bus
Alternate Action
12
55
EGPWS TRA-45A
TRA-45A
A
B
ARINC 429 Range #1 In
A
B
ARINC 429 Range #2 In
A
B
KCPB Video #1 Out
A
B
KCPB Video #2 Out
Terrain Inhibit (in)
Terrain INOP (out)
MK XXII 965-1590-006 or later
A
B
A
B
A
B
A
B
Range out
KCPB Video in
Range out
KCPB Video in
80-5145-X-2
Note:
For interface and operation of the Honeywell Grimes TRA-45A see
Honeywell TRA-45A Equipment Installation Manual P/N 34-40-01
80-5145-X-2
TRA45.vsd
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Honeywell GNS-XLS
J2
J1
J101
J101
N5
N6
Q4
Q6
N5
N6
Q4
Q6
37
36
25
8
41
40
58
59
56
57
TERR
INHIB
TERR
INOP
Lamp Test 28V Lamp Dimming Bus
Alternate Action
12
55
EGPWS GNS-XLS
GNS-XLS
A
B
ARINC 429 Range #1 In
A
B
ARINC 429 GPS In
A
B
ARINC 429 Range #2 In
A
B
KCPB Video #1 Out
A
B
KCPB Video #2 Out
Terrain Inhibit (in)
Terrain INOP (out)
MK XXII 965-1590-006 or later.
A
B
A
B
A
B
A
B
Range & GPS out
KCPB Video in
Range out
KCPB Video in
17960-0203-XXXX
17960-0203-XXXX
Note:
GNS-XLS will not perform auto pop-up during Alert.
For interface and operation of the GNS-XLS see Honeywell
GNS-XLS System Installation Manual 006-10528-0000
GNS-XLS.vsd
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AVIDYNE FSD
J2
J1
J5
J5
17
35
4
22
17
35
4
22
37
36
41
40
58
59
56
57
TERR
INHIB
TERR
INOP
Lamp Test 28V Lamp Dimming Bus
Alternate Action
12
55
EGPWS AVIDYNE FSD
AVIDYNE FSD
A
B
ARINC 429 Range #1 In
A
B
ARINC 429 Range #2 In
A
B
KCPB Video #1 Out
A
B
KCPB Video #2 Out
Terrain Inhibit (in)
Terrain INOP (out)
MK XXII 965-1590-006 or later.
A
B
A
B
A
B
A
B
Range out
KCPB Video in
Range out
KCPB Video in
D98-00001-5X
Note:
For interface and operation of the Avidyne FSD
see Avidyne FSD Installation Manual P/N 600-0067
D98-00001-5X
Avidyne.vsd
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Integrated
Primus 440/660/880
J2
J1
F
G
M
L
37
36
41
40
58
59
56
57
TERR
INHIB
TERR
INOP
Lamp Test
28V Lamp Dimming Bus
Alternate Action
12
55
EGPWS
Honeywell
Radar Indicator
A
B
RS-422 Serial Range #1 In
A
B
Range #2 In
A
B
ARINC 453 Video #1 Out
A
B
ARINC 453 Video #2 Out
Terrain Inhibit (in)
Terrain INOP (out)
MK XXII 965-1590-006 or later.
P
N
P
N
SCI Bus
WXPD Bus
Note:
For interface and operation of the Honeywell Weather Radar Indicator
WI-440, 660, 880 see Honeywell Service Bulletin 7007700-34-15
WI-440, 660, 880
7007700-X1X
IntP880.vsd
NC
NC
Honeywell WRX R/T
WU-440, 660, 880
71 72 3 4
TERR
ON
momentary
32
54
Terrain Display Select (in)
Terrain Display Select (out)
28V EGPWS PWR Bus
XEGPWS Selected
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AVTECH DSU
Primus WXR UDI
J2
J1
J1
8
9
47
48
37
36
41
40
58
59
56
57
TERR
INHIB
TERR
INOP
Lamp Test
28V Lamp Dimming Bus
Alternate Action
12
55
EGPWS
AVTECH DSU
A
B
ARINC 429 Range #1 In
A
B
ARINC 429 Range #2 In
A
B
KCPB Video #1 Out
A
B
KCPB Video #2 Out
Terrain Inhibit (in)
Terrain INOP (out)
MK XXII 965-1590-006 or later.
A
B
A
B
Range out
KCPB Video in
Note:
For interface and operation of the Avtech 6001 DSU see Avtech
DSU Installation and Operation Procedure P/N 6001-1680
P/N 6001-1
PrimusUDI.vsd
PRIMUS SERIES
90, 100, 200, 300,
300SL, 400, 500, AVQ30
450, 650 w/o Lightning,
800
440, 650 w/ Lightning,
660, 670, 700, 880 21913 618 931612 10 4815 11
17 14
5
7
21913 618 931612 10 4815 11
17
NC
5
7
1
N JESUTDHR MKLA PCVBGF
49
open
7
2
TERR
ON
momentary 32
Display Invalid
Terrain Select
Terrain Status
J2
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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
Alternate Pop-Up
Defines whether EGPWC visual alerts will “pop-up” on displays not
currently displaying terrain data. The entries are:
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) Not Selected Selected
WOW Discrete = +28V WOW Not WOW
WOW Discrete = Open Not WOW WOW
Ground seeking WOW discrete active position:
WOW Reversal
WOW Discrete (Category 13) Not Selected Selected
WOW Discrete = GND WOW Not WOW
WOW Discrete = Open Not WOW 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
21
4
J2 Radio Altimeter R/T
A
B
EGPWS MK XXII
A
B
ARINC 429
Radio Altitude ARINC 429
DH Discrete (Gnd) 33
Radio Altimeter Indicator
DH
J1
Vendor Model Indicator R/T
R/T Indicator SCALE DH A B
Collins RAC-870 ALI-55 ARINC 429 P1-V P1-2 P1-3
Honeywell ALA-52A ARINC 429 MP-B2 MP-B3
Honeywell KRA 405B KNI-415/416 ARINC 429 M B C
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3.3.8.4 Analog Radio Altitude Interface
64
45
29
J1 Radio Altimeter R/T
+
-
EGPWS MK XXII
(+)
(-)
Analog Radio Altitude ARINC 552, ALT 55,
RT-200/300
Radio Altitude Valid +28V Valid
DH Discrete (Gnd) 33
Radio Altimeter Indicator
DH
Vendor Model Indicator R/T
R/T Indicator SCALE DH + - Valid
Collins ALT 55 (3) ALI-55 ALT55 P1-V P1-57 P1-59 P1-49
Collins ALT 50 -20 to 2100 ft P1-57 P1-59 P1-49
Honeywell HG7502 JG1072( ) ARINC 552 P1-e P4-47 P4-46 P4-27
Honeywell RT-300 (1) RA-315 ARINC 552 P1-F P1-X P1-N P1-Y
Honeywell RT-200 (2) RA-215 -.4mV/ft P1-F P1-N P1-W P1-Y
Honeywell KRA-405 KNI-415/416 ALT55 M P1-B P1-g S
Honeywell KRA 405B KNI-415/416 ALT55 M E X j
KRA 405B (2)
066-01153-0101
-4mV/ft G Z j
KRA 405B
066-01153-0202
ARINC 552A Z G j
Honeywell ALA-51A INA-51( ) ARINC 552 P2-e P1B-
47
P1B-46 P1B-27
Collins 860F-1 339H-1/-2 ARINC 552 P1-e P1B-
47
P1B-46 P1B-27
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)
J2 ILS Receiver
EGPWS MK XXII
GS Valid +28 11
+
-
Low Level
GS Valid
+28
GND
ILS Tuned
+
-
GS Deviation 65
46
30
10
39
20
Super Flag +28V
+
-
Delayed ILS Mode
ILS Energize
GS Flag
(Low Level)
+Up
+Dn GS Deviation
Valid ILS Tuned Deviation
Vendor Model SuperFlag
+28V
Low Level
Flag
+28V GND GS
+up/+dn
Honeywell
KNR 630
J1003-27 J1003-21
J1003-22
J1002-18 J1003-8
J1003-9
Honeywell
KNR 634
P6342-50 P6342-34
P6342-18
P6341-17 P6342-36
P6342-35
Honeywell
KGM-691
P692-S
P692-T
P692-a P692-B
P692-C
Honeywell
KNR 600A
P601-e
P601-q
P601-k P601-r
P601-s
Collins
51RV-1
TP-22
TP-21
BP-18 TP-8
TP-9
Collins
VIR-30, -31, -32
P1-17 J1-9
J1-13
P2-40 P1-5
P1-1
Honeywell
VNS 41A
P1001-60 J1001-56 J1001-90
J1001-23
Honeywell
RNA-34A
TP-27 TP-21 BP-18 TP-8
TP-9
Honeywell
KN 53
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
22
5
J2
ILS Bus
A
B
EGPWS MK VI / MK VIII
A
B
ARINC 429 ILS
ARINC 429
Low Speed
Vendor Model ARINC 429 Bus 1 ARINC 429 Bus 2
ABAB
Honeywell KNR 634A P6342-41 P6342-42 P6342-44 P6342-45
Honeywell VNS 41A P1001-62 P1001-103
Honeywell RNA-34A P1024-24 P1024-28 P1024-21 P1024-25
Honeywell KN 40A(B) P401 (403) –41 P401 (403) –42 P401 (403)-44 P401 (403)-45
Collins VIR-432 P1-35 P1-36 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)
5
7
6
1
21
2
J1 Vertical Gyro
X
Y
EGPWS MK XXII
Roll Angle
Z
X
Y
Roll Synchro
Z
X
Y
Pitch Synchro
Z
X
Y
Z
Pitch Angle
Vendor Model Attitude Pitch Synchro Roll Synchro
V/G Valid +28 XYZXYZ
Aeronetics RVG 801 P1-U P1-A P1-B P1-C P1-D P1-E P1-F
Collins AHC-85( ) P1-13 P2-50 P2-51 P2-52 P2-42 P2-43 P2-44
Collins 332D-11 N A B C D E F
Honeywell HG1075 J1B-C9 J1B-C10 J1B-C11 J1B-D9 J1B-D10 J1B-D11
Jet VG-208 P1-U P1-A P1-B P1-C P1-D P1-E P1-F
King KVG-350 HH X Y Z P Q R
Litef LTR-81 MP-A11 MP-B1 MP-B2 MP-B3 MP-B4 MP-B5 MP-B6
Litef LCR-92& 93 Note 2 J3-11 J3-40 J3-26 J3-16 J3-39 J3-25
Sperry VG-14A Note 3 X Y Z P Q R
Sperry VG-311 P1-45 P1-5 P1-4 P1-6 P1-7 P1-8 P1-9
Note 1: The connector pin numbers given in the table above are to the best knowledge of Honeywell
EGPWS engineering. Please contact the manufacturer’s customer service to confirm your
installation.
Note 2: See LCR installation manual.
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.
23
6
J2 AHRS
A
B
EGPWS MK XXII
A
B
AHRS 429
HS Roll Pitch
Angle
Vendor Model 429 High Speed
AHRS A B
Litef LCR 92S 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. 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.
2. 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.
3. 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)
22
23
3
J1 Directional Gyro
X
Y
EGPWS MK XXII
X
Y
Heading Synchro Heading
ZZ
H
C
4
24
26 VAC Reference H
CHeading Ref
Vendor Model Heading Reference Heading Synchro
V/G H C X Y Z
Aeronetics Model 9100 P1-28 P1-6 P1-7 P1-8 P1-9 P1-10
Collins AHC-85( ) P2-57 P2-57 P2-34 P2-35 P2-36
Collins DGS-65 P1-50 P1-6 P1-3 P1-25 P1-40 P1-24
Honeywell HG 1075 J1B-G2 J1B-F13 J1B-G13 J1B-E10 J1B-E11 J1B-E12
Honeywell KSG 105 P1-V P1-P P1-d P1-Z P1-W P1-T
Jet DN-104 P2-31 P2-9 P2-10 P2-1 P2-2 P2-3
Litef LTR-81 MP-E15 MP-B12 MP-B13 MP-B9 MP-B10 MP-B11
Litef LCR 92/LCR-93 Note 2 J3-05 J3-20 J3-13 J3-42 J3-28
Sperry C-14A P1-e P1-H P1-J P1-L P1-M P1-K
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.
23
6
J2 AHRS
A
B
EGPWS MK XXII
A
B
AHRS 429
HS Heading
Vendor Model 429 High Speed
AHRS A B
Litef LCR 92S
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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 Connector Pin
Audio Inhibit +28 Inhibit = +28V
Not Inhibit = Gnd/Open
J1-36
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 Connector Pin
Landing Gear +28 Down = +28V
Not Down = Gnd/Open
J1-35
Landing Gear Gnd Down = Gnd
Not Down = +28V /Open
J1-16
For fixed gear 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 Connector Pin
WOW +28 On Ground = +28V
In Air = Gnd/Open
J1-37
WOW Gnd On Ground = Gnd
In Air = +28V /Open
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 Connector Pin
Glideslope Cancel Cancel = Gnd
Normal = Open
J1-15
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 Connector Pin
Mode 6 Low Volume Low Volume = Gnd
Not Low Volume = Open
J1-13
3.3.13.8 Autopilot Engaged Discrete
For helicopters this discrete is currently not used.
Discrete Position / Status Connector Pin
Autopilot Engaged Engaged = +28V
Not Engaged = Open
J1-8
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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 Connector Pin
TA Inhibit Inhibit = Gnd
Not Inhibit = Open
J1-12
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 Position / Status Connector Pin
Self Test Self Test = Gnd
Normal = Open
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 Connector Pin
Glideslope Inhibit +28 Inhibit = +28V
Not Inhibit = Gnd/Open
J1-38
Glideslope Inhibit Gnd Inhibit = Gnd
Not Inhibit = +28V /Open
J1-19
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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 Connector Pin
Timed Audio Inhibit Momentary Toggle = Gnd
Normal = Open
J1-17
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.
High level audio
600 ohm
Audio
Panel
Low level audio
J1-70
HJ1-71
L
J1-75H J1-74L
8 ohm
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. 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.
2. 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 Threshold % Threshold ID
128 S-76 B/C+ 7.5 15
129 S-76C/A++ 7.5 15
130 S-76A/A+ 7.5 15
131 Bell 212 6 12
131 Bell 412 6 12
132 EC-155B 7.5 15
133 MD900 7.5 15
133 MD902 7.5 15
134
135
136 AS 365N3 7.5 15
137
138
139
140
141 Bell 412, DC Torque 6 12
142
143
144
145
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) Pin 3 Pin 4 Pin 1
Standard (PC)* DB9 Connector Pin 3 Pin 2 Pin 5
*NOTE: Some PC Comm Ports have Pins 2 & 3 reversed from what is described above.
Connector, AMP 205161-1
Socket Contact, AMP 205090-1, QTY 3
PCOM
Connector, AMP 748364-1
Pin Contact, 204370-2, QTY 4
Backshell, AMP 745854-5
Jackscrew, AMP 747784-3
Grommet Set, AMP 747746-1
P3
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.
3
2
5
3
4
1
12
Length as required (5’ to 50’)
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To obtain a copy of the WinVIEWS software, contact:
Honeywell
Aerospace Electronic Systems
PO Box 97001
Redmond, WA 98073-9701 USA
Attn: Order Administration M/S 33
Phone: (425) 885-8719
FAX: (425) 885-8988
or Honeywell
Aerospace Electronic Systems
PO Box 97001
Redmond, WA 98073-9701 USA
Attn: EGPWS Applications Engineering
Phone: (425) 885-3711
FAX: (425) 885-2994
GPWS Hotline: (800) 813-2099
WinVIEWS can be sent via e-mail when an e-mail address is provided 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: 128
Category 2 Air Data Type: 3
Category 3 Position Type: 2
Category 4 Altitude Callouts Menu: 134 (All Callouts)
Category 5 Audio Menu: 128 (Basic menu)
Category 6 Display Type: 3
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: 1
Category 9 Navigation Type: 0
Category 10 Attitude Type: 2
Category 11 Heading Type: 0
Category 12 Windshear select Type: 0
Category 13 Discrete I/O Type: 129
Category 14 Audio Output Level Type: 0
Category 15 Autorotation Threshold 15
CWR list: (based on the above configuration)
CFG > CMR<Enter>
CONFIGURATION MODULE:
Format Version: 0
Category 1 ID: 128
Category 2 ID: 3
Category 3 ID: 2
Category 4 ID: 134
Category 5 ID: 128
Category 6 ID: 3
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Category 7 ID: 29
Category 8 ID: 1
Category 9 ID: 0
Category 10 ID: 2
Category 11 ID: 0
Category 12 ID: 0
Category 13 ID: 129
Category 14 ID: 0
Category 15 ID: 15
CRC: 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
Airlines & Avionics Products
Order Administration M/S 33
PO Box 97001
Redmond, WA 98073-9701
Phone: 425-885-8719
Fax: 425-885-8988
Honeywell Aerospace
Toulouse Office
Centreda, Avenue Didier Daurat
31700 Blagnac, France
Phone: (33) 5-6171-0079
Fax: (33) 5-6130-0497
Vendor Name Vendor P/N Description QTY UM Honeywell P/N
Honeywell 424NAM North America 1 EA 718-1447-XXX
Honeywell 424 SAM South America 1 EA 718-1448-XXX
Honeywell 424EUR Europe 1 EA 718-1449-XXX
Honeywell 424EEU Eastern Europe 1 EA 718-1450-XXX
Honeywell 424AFR Africa 1 EA 718-1451-XXX
Honeywell 424PAC Pacific 1 EA 718-1452-XXX
Honeywell 424SPA South Pacific 1 EA 718-1457-XXX
Honeywell 424MES Middle East 1 EA 718-1458-XXX
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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 Pin Nomenclature
J1-40, J1-60 28 VDC (+)
J1-41, J1-61 28 VDC (-)
J1-42, J1-53 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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MK XXII EGPWS
ENHANCED GROUND PROXIMITY WARNING SYSTEM
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The purpose for this work sheet is to obtain the necessary aircraft data for determining the specific interface configuration for the MK XXII Enhanced Ground
Proximity Warning System (EGPWS). For defined MK XXII EGPWS interface data, refer to Honeywell document No. 060-4314-225,
Installation Manual for the
MK XXII
For product description information, refer to Honeywell document No. 965-1590-601,
Product Specification for the MK XXII Enhanced Ground
Proximity Warning System
. Contact Honeywell EGPWS Applications Engineering for assistance.
Aircraft Operator:
Contact: Phone:
Installer:
Contact: Phone:
Aircraft Type (be specific):
Model S/N N #
Engine Type (model number):
COCKPIT DISPLAYS:
Please provide the following information for intended EGPWS display purposes (include any new displays planned):
SYSTEM QTY MANUFACTURER MODEL NO. PART NO. SOFTWARE NO.
EFIS Symbol Generator
EFIS Display
EFIS Display Control Panel
Multifunction Display (MFD)
Weather Radar Indicator
Weather Radar R/T
Weather Radar Controller
Other (specify)
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AIRCRAFT SYSTEMS INFORMATION: Please provide the manufacturer, model number, part number, software part number, quantity per aircraft, and
output data information for:
SYSTEM MFGR. MODEL NO. PART NO. S/W PART NO. QTY
OUTPUT DATA FORMAT – NOTES
(ARINC 429, 547, 552, 575, DC, synchro, potentiometer,
discrete, etc. Identify available ARINC 429 labels)
Air Data
Computers
GPS *
Radio
Altimeters
ILS
Receivers
AHRS / IRU
/ INU
VG
DG
Engine
Torque
* GPS Altitude Reference: WGS-84 MSL Use “N/A” if Not Applicable
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DISCRETE INPUTS:
Please check applicable boxes for both up and down positions.
PARAMETER GND OPEN +28 VDC
DH >°>°
WOW <°<°
Landing Gear Down
Landing Gear Up
Notes: ________________________________________________________________________________________________________________________
________________________________________________________________________________________________________________________
______________________________________________________________________________________________________________________________
Listed below are typical parameters from each system, which are required to implement the EGPWS functions. Note that this list is a
typical example. Actual source systems may vary depending on aircraft configuration and selected options.
SYSTEM PARAMETERS
RADIO ALTIMETER radio altitude, decision height
ADC barometric altitude, corrected baro altitude, baro rate, computed airspeed, static air temperature or total air
temperature
IRS / AHRS magnetic heading, vertical velocity, pitch, roll
ILS / NAV receiver glideslope deviation / flag , localizer deviation / flag
FMS / GPS altitude, latitude, longitude, ground speed, true track, true heading, mag variation, Nav mode, horizontal figure of
merit, horizontal integrity limit, vertical figure of merit
Engine 1 and 2 or FADEC Torque
Display Range
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GENERIC MODEL INFORMATION
Aircraft Tail Geometry:
Height of Nominal CG above ground
Distance from CG to Tail (Lowest point of tail or skid)
Distance from CG to center of Tail Rotor
Distance from lowest point of tail or tail-skid to ground
Distance from tail rotor blade (lowest point) to ground
Rotational Frequencies:
Main Rotor RPM No. Of Blades (Main Rotor)
Height
of Tail
Tip of Tail to CG
Manufacturer:
Model:
(be specific)
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SYSTEM Number of Engines DATA FORMAT
(ARINC 429, RS 422, RS
232, synchro, DC, AC
Signal Scale Factor
In % Torque
NOTES
Engine
Torque
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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 1
Standard DB9 Connector (for a PC)* Pin 3 Pin 2 Pin 5
*NOTE:Some PC Comm Ports have Pins 2 & 3 reversed from what is described above.
The mating connector for the EGPWS J3 test connector is a male (pins) 15 pin double density D-
subminiature type, Positronics Industries (kit) part number ODD15M1OYOZ or the following
individual parts:
Nomenclature (AMP) Amp Part Number Military Part Number
Connector Shell (HDP-22 Crimp Snap In Contact) 748364-1 reference MIL-C-24308
Size 22 DM Crimp Snap In Contacts Pin 0.030 204370-2 M39029/58-360
Backshell (Shielded Cable Clamp Assembly) 745854-5
Jackscrews, 2 required (4-40 Male Jackscrew Kit) 747784-8
Grommet Sets 747746-1
The following tools will work with Positronics, Amp, and Mil Spec Connectors:
Insertion / Extraction Tool 91067-1 M81969/1-04
Hand Crimp Tool M22520/2-01
Positioner M22520/2-09
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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 VF
ARA1Val V
DHDsc V
RawBAlt1 VF
RawBaroRt1 VF
RawCAS1 VF
RawSAT1 VF
ILSTuned1 V
GnILSTuned1 V
RawAACGS1 VF
AGS1Val V
GPSLatude1 VF
GPSLngude1 VF
RawGLat1 VF
RawGLng1 VF
RawGAlt1 VF
RawVFOM1 VF
RawHFOM1 VF
RawGGSpd1 VF
RawHil1 VF
RawGTTk1 VF
RawRoll1 VF
RawPitch1 VF
AnAtt1Val V
RawAACMHD VF
AACMHDVal V
WOWDsc V
LandGrDsc V
GSCan V
AudInhDsc V
M6LwVolDsc V
GSInh V
GSlnhDsc V
TAWxRng1 VF
TAWxRng2 VF
TerrDis V
AnaTerrDis V
RawTorque1 VF
RawTorque2 VF
TacticalSel V
TAInop C
TAInop1 C
TAInop2 C
EngTorque1 VF
EngTorque2 VF
DispRngOut1 V
DispRngOut2 V
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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
Brighton, MA
616 787-1555
United Kingdom:
Surrey, England
44 (0932) 22-4122
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
and Electrical Conservation
Systems, Inc.
5300 W Franklin Drive
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: smatar@emteq.com
Hollingsead International Sante Fe Springs, CA
213 921-3436
IDD Aerospace Redmond, WA
425 885-4353
ITT Cannon Santa Ana, CA
714 557-4700
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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: scordova@korry.com
fax: 206 281-3576
SITA: SEAKEXD
For engineering inquiries, contact:
Bob Jacques
Airline Business Manager
206 281-3584
email: bjacques@korry.com
fax: 206 273-4128
Tom Howard
Airline Business Manager
206 281-1458
email: thoward@korry.com
fax: 206 273-4128
Master Specialties Co. Costa Mesa, CA
714 642-2427
Optima Wire 1120 Harpeth Industrial Ct.
Franklin, TN 37064
615 599-3770
Cathy Harper
cathy.h@mindspring.com
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. 8929 Fullbright Avenue
Chatsworth, CA 91311
818 341-5366
Fax: 818 341-9059
StacoSwitch 1139 Baker Street
Costa Mesa, CA 92626-4191
www.stacoswitch.com
714-549-3041
Fax: 714-549-0930
Dan Sugg
dsugg@stacoswitch.com
Also contact EDMO – Avionics
Distributor for StacoSwitch
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 O.D. Bend Radius
P/N Per 100 ft (inches) Minimum
TFLX130-100 21.60 dB 0.130 “ ½”
TFLX165-100 17.00 dB 0.161” 1 ¾”
TFLX205-100 13.90 dB 0.195 “ 1 ¾”
TFLX295-100 7.60 dB 0.205 “ 3.0 “
TFLX480-100 4.75 dB 0.480 “ 2.40 “
Table 1.B. (PE – Polyethylene Jacketed RF Coax) (85 C temp)
Cable Type Loss @ 1600 Mhz O.D. Bend Radius
P/N Per 100 ft (inches) Minimum
PFLX195-500 14.00 dB 0.195 “ ½
PFLX240-500 11.00dB 0.242 “ ¾”
PFLX340-500 7.59 dB 0.340 “ 1”
PFLX500-500 4.27 dB 0.500 “ 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 Antenna Straight TMS130-1 TMS165-1 TMS205-1
TNC male Antenna Right Angle TMR130-1 TMR165-1 TMR205-1
TNC female Disconnects Bulkhead Straight TFS130- 2 TFS165-2 TFS205-2
C male Antenna Straight CMS130-1 CMS165-1 CMS205-1
C male Antenna Right Angle CMR130-1 CMR165-1 CMR205-1
GPS
Connector
Type
Application Description TFLX295-100 TFLX480-100
TNC male Antenna Straight TMS295-1 TMS488-1
TNC male Antenna Right Angle TMR295-1 TMR488-1
TNC female Disconnects Bulkhead Straight TFS295-2 TFS488-2
C male Antenna Straight CMS295-1 CMS488-1
C male Antenna Right Angle CMR295-1 CMR488-1
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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 Antenna Straight TMS195-1 TMS240-1 TMS340-1
TNC male Antenna Right Angle TMR195-1 TMR240-1 TMR340-1
TNC female Disconnects Bulkhead Straight TFS195-2 TFS240-2 TFS340-2
C male Antenna Straight CMS195-1 CMS240-1 CMS340-1
C male Antenna Right Angle CMR195-1 CMR240-1 CMR340-1
GPS
Connector
Type
Application Description PFLX500-500
TNC male Antenna Straight TMS500-1
TNC male Antenna Right Angle TMR500-1
TNC female Disconnects Bulkhead Straight TFS500-2
C male Antenna Straight N/A
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Tool Frame and Die Part Numbers
Mil-Spec P/N Daniels
Cable Type for Hex Die P/N for Hex Die Tool Frame Die Hex
PFLX195 M22520/5-19 Y142 M22520/5-01 (HX4) B Hex
PFLX200 M22520/5-19 Y142 M22520/5-01 (HX4) B Hex
PFLX240 M22520/5-43 Y141 M22520/5-01 (HX4) A Hex
PFLX340 M22520/5-35 Y137 M22520/5-01 (HX4) A Hex
PFLX500 M22520/5-21 Y149 M22520/5-01 (HX4) A Hex
TFLX130 M22520/5-43 Y141 M22520/5-01 (HX4) A (ARINC) / B Hex
TFLX165 M22520/5-19 Y142 M22520/5-01 (HX4) B Hex
TFLX205 M22520/5-43 Y141 M22520/5-01 (HX4) A Hex
TFLX295 M22520/5-35 Y137 M22520/5-01 (HX4) A Hex
TFLX488 M22520/5-27 Y151 M22520/5-01 (HX4) 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: smatar@emteq.com
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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 the