MK XXII - Honeywell MK XXII EGPWS Installation Manual CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO:...

CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-250 REV: E SHEET 1 OF 324

Airlines & Avionics Products

Honeywell International, Inc.

15001 N.E. 36th Street

Redmond, WA 98052

MK XXII Enhanced Ground Proximity Warning System

(TSO C194 HTAWS) for

Rotorwing Aircraft

Installation Manual 060-4314-250 Rev E

Part Numbers: 965-1595-020 965-1595-021 965-1595-022 965-1595-024 965-1595-026 965-1595-028 965-1595-030

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Honeywell MK XXII EGPWS Installation Manual

CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 060-4314-250 REV: E SHEET 2

This document is an unpublished work. Copyright 2003-2008, 2009, 2010, 2012 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.



Typed names constitute approval signatures. Actual signatures are on file at Honeywell in Redmond, WA.

DRAWN Larry Matter 12/01/2003

CHECK Larry Matter 12/01/2003

ENGR Jim Mulkins 12/01/2003

MFG

QA

APVD Noel Paterson 12/01/2003

APVD

REVISION STATUS OF SHEETS INDEX

ADDED SHEETS ADDED SHEETS

SHEET

NUMBER

REV

LTR

SHEET

NUMBER

REV

LTR

SHEET

NUMBER

REV

LTR

SHEET

NUMBER

REV

LTR

SHEET

NUMBER

REV

LTR

SHEET

NUMBER

REV

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ALL E

REVISIONS

SH REV DESCRIPTION DATE APPROVED

ALL A Updated for –021 and –022 software.

Reason: 01 Severity: 10

12/05/2004 Larry Matter

Jim Mulkins

ALL B Updated for -024 and -026 software.



N. Paterson

ALL C UPDATE PER ECO 0067930

Updated to add TSO-C194 effectivity.



G. Ostrom

ALL D UPDATE PER ECO 0095872

Updated to add new aircraft and display type. Also revised table in

CAT 17 and CAT 18, and updated miscellaneous information.

EFF PT: 14A


G. Ostrom

L. Ngo

ALL E UPDATE PER ECO 0146887

Updated to add new aircraft, Navigation type and CAT 19, updated

miscellaneous information.

EFF PT: 14A


G. Ostrom

B. Friedrich



TABLE OF CONTENTS

SECTION I – GENERAL INFORMATION .................................................................................................................. 16

1.1 INTRODUCTION .......................................................................................................................................................... 16

1.2 APPLICABILITY .......................................................................................................................................................... 16

1.3 HOW TO USE THIS DOCUMENT .................................................................................................................................. 16

1.4 REFERENCE DOCUMENTS ........................................................................................................................................... 17

1.5 DESCRIPTION OF EQUIPMENT ..................................................................................................................................... 17

1.5.1 MK XXII EGPWS Computer ............................................................................................................................ 18

1.5.2 MK XXII EGPWS Configuration Module ........................................................................................................ 18

1.5.3 GPS Antenna ................................................................................................................................................... 19

1.5.4 OAT Sensor ...................................................................................................................................................... 20

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

1.7.2 Configuration Module ..................................................................................................................................... 22

1.7.3 Smart Cable (PCMCIA Interface) ................................................................................................................... 22

1.8 INSTALLATION AND ACCESSORIES KITS ..................................................................................................................... 22

1.8.1 MK XXII EGPWS Installation Kits .................................................................................................................. 23

1.8.2 RS-232 Cable ................................................................................................................................................... 23

1.8.3 Smart Cable ..................................................................................................................................................... 23

1.8.4 Terrain Database Cards .................................................................................................................................. 23

1.8.5 Flight History Card ......................................................................................................................................... 24

1.9 ACCESSORIES REQUIRED BUT NOT SUPPLIED ............................................................................................................. 24

1.9.1 ARINC 453 Terrain Display wiring ................................................................................................................. 24

1.9.2 GPS Antenna & cable ...................................................................................................................................... 24

1.9.3 Circuit Breaker ................................................................................................................................................ 25

1.9.4 Annunciators & Switch/Annunciators ............................................................................................................. 25

1.9.4.1 GPWS Warning (red) P/TEST; switch/annunciator assembly ................................................................................. 25

1.9.4.2 GPWS Caution (amber) G/S CANCLD switch/annunciator assembly. ................................................................... 25

1.9.4.3 LOW ALT / ON switch/annunciator assembly ........................................................................................................ 25

1.9.4.4 TERR INHIB / ON switch/annunciator assembly .................................................................................................... 25

1.9.4.5 AUDIO INHIBIT / ON switch/annunciator assembly ............................................................................................. 26

1.9.4.6 GPWS INOP / TERR INOP annunciator assemblies ............................................................................................... 26

1.9.4.7 TERR DISPLAY / ON switch/annunciator assemblies ............................................................................................ 26

1.10 COCKPIT SPEAKER (OPTIONAL) ............................................................................................................................... 26

1.11 TEMPERATURE PROBES ............................................................................................................................................ 26

1.12 TOOLS REQUIRED ..................................................................................................................................................... 26

1.12.1 Crimping Tool - P1, P2, P3 ............................................................................................................................ 26

1.12.2 Contact Positioner - P1, P2, P3 ...................................................................................................................... 27



1.12.3 Insertion/Removal Tool - P1, P2, P3 .............................................................................................................. 27

1.12.4 Spare Contacts - P1, P2, P3 ............................................................................................................................ 27

1.13 LICENSE REQUIREMENTS ......................................................................................................................................... 27

1.14 TSO-C194 DEVIATIONS ........................................................................................................................................... 28

1.14.1 Environmental Qualification Deviation ........................................................................................................... 28

1.14.2 Electronic Hardware Qualification Deviation ................................................................................................. 28

1.15 LIMITATIONS ............................................................................................................................................................ 29

1.15.1 a. Operating instructions and equipment limitations ...................................................................................... 29

1.15.2 b. Installation procedures and limitations ...................................................................................................... 29

1.15.3 c. Schematic drawings of the installation procedures ..................................................................................... 29

1.15.4 d. Wiring diagrams of the installation procedures ......................................................................................... 29

1.15.5 e. List of components ....................................................................................................................................... 29

1.15.6 f. Component Maintenance Manual (CMM) ................................................................................................... 29

1.15.7 g. Material and process specifications list ...................................................................................................... 29

1.15.8 h. Quality control system (QCS) description .................................................................................................. 29

1.15.9 i. Manufacturer’s TSO Qualification test report ............................................................................................. 30

1.15.10 j. Nameplate drawing .................................................................................................................................... 30

1.15.11 k. List of all drawings and processes ............................................................................................................ 30

1.15.12 l. Environmental qualifications form ............................................................................................................ 30

1.15.13 m. Plan for software aspects of certification (PSAC), software configuration index, and software

accomplishment summary (SAS) ................................................................................................................................. 30

1.15.14 n. Plan for hardware aspects of certification (PHAC), hardware verification plan, top-level drawing, and

hardware accomplishment summary .......................................................................................................................... 30

1.16 NON TSO FUNCTIONS .............................................................................................................................................. 33

1.16.1 Helicopter Mode 1 ........................................................................................................................................... 33

1.16.2 Helicopter Mode 2 ........................................................................................................................................... 33

1.16.3 Helicopter Mode 3 ........................................................................................................................................... 33

1.16.4 Helicopter Mode 4 ........................................................................................................................................... 33

1.16.5 Helicopter Mode 4C ......................................................................................................................................... 33

1.16.6 Helicopter Altitude Callouts ............................................................................................................................ 33

1.16.7 Bank Angle Callout .......................................................................................................................................... 33

1.16.8 Tail Strike Callout ............................................................................................................................................ 33

1.16.9 Externally Triggered Annunciation ................................................................................................................. 34

1.16.10 Radio Altimeter Test ...................................................................................................................................... 34

SECTION II - INSTALLATION .................................................................................................................................... 36

2.1 INTRODUCTION .......................................................................................................................................................... 36

2.2 UNPACKING AND INSPECTING THE EQUIPMENT ......................................................................................................... 36

2.3 EQUIPMENT INSTALLATION ........................................................................................................................................ 36

2.3.1 General ............................................................................................................................................................ 36

2.3.2 MK XXII Computer Location ........................................................................................................................... 37

2.3.3 MK XXII Computer Installation ...................................................................................................................... 37

2.3.4 Configuration Module Location ...................................................................................................................... 38



2.3.5 Configuration Module Installation .................................................................................................................. 38

2.3.6 GPS Antenna location ..................................................................................................................................... 46

2.3.7 GPS Antenna Installation ................................................................................................................................ 46

2.3.8 OAT Sensor Location ....................................................................................................................................... 46

2.3.9 OAT Sensor Installation .................................................................................................................................. 46

2.3.10 Cockpit Annunciators / Switches ..................................................................................................................... 47

2.3.10.1 Description ............................................................................................................................................................... 47

2.3.10.2 Location ................................................................................................................................................................... 48

2.3.10.3 Inhibit Switch Functions and Selection .................................................................................................................... 50

SECTION III – SYSTEM PLANNING .......................................................................................................................... 54

3.1 INTRODUCTION .......................................................................................................................................................... 54

3.2 SYSTEM WIRING/ ELECTRICAL INTERFACES .............................................................................................................. 54

3.2.1 Primary Power Input ....................................................................................................................................... 54

3.2.2 Chassis Ground ............................................................................................................................................... 54

3.2.3 GPS Antenna ................................................................................................................................................... 55

3.2.4 Analog and Digital Inputs ............................................................................................................................... 55

3.2.5 Discrete Inputs ................................................................................................................................................. 55

3.2.6 Serial Outputs .................................................................................................................................................. 55

3.2.7 Audio Output ................................................................................................................................................... 56

3.2.8 Discrete Outputs .............................................................................................................................................. 56

3.2.9 Configuration Module ..................................................................................................................................... 56

3.3 CONFIGURABLE INTERFACES ..................................................................................................................................... 56

3.3.1 Category 1 - Aircraft / Mode Type Select ........................................................................................................ 57

3.3.1.1 Aircraft / Mode Type ............................................................................................................................................... 57

3.3.1.2 Instructions ............................................................................................................................................................... 57

3.3.2 Category 2 – Air Data Input Select ................................................................................................................. 58

3.3.2.1 Instructions ............................................................................................................................................................... 58

3.3.2.2 Analog altitude and 500 ohm OAT .......................................................................................................................... 59

3.3.2.3 Digital – ARINC 429 (Cat. 2 ID 5, 1, 6) .................................................................................................................. 60

3.3.2.4 Digital –ARINC 575 (Cat. 2 ID 2) ........................................................................................................................... 61

3.3.2.5 Shadin 2000 (Cat. 2 ID 10) ...................................................................................................................................... 62

3.3.2.6 Digital – ARINC 429 Dual IOC Buses (Cat. 2. ID 253 and 254) ............................................................................. 63

3.3.3 Category 3 – Position Input Select .................................................................................................................. 64

3.3.3.1 Instructions ............................................................................................................................................................... 64

3.3.3.2 ARINC 743 Format .................................................................................................................................................. 64

3.3.3.3 GPS Altitude (Label 076) Reference ........................................................................................................................ 64

3.3.3.4 North-South East-West Velocity labels .................................................................................................................... 64

3.3.3.5 HT-1000 GPS Compatibility .................................................................................................................................... 64

3.3.3.6 ARINC 429 BUS (Cat. 3 ID 0,1,4,5,10-13) ............................................................................................................. 65

3.3.3.7 RS-232 Transmit-Receive, 9600 baud (Cat. 3 ID 3) ................................................................................................ 66

3.3.3.8 Dual ARINC 429 BUS (Cat. 3 ID 253 and 255) ...................................................................................................... 67

3.3.4 Category 4 – Altitude Callouts ........................................................................................................................ 68



3.3.4.1 Instructions ............................................................................................................................................................... 68

3.3.5 Category 5 – Audio Menu Select ..................................................................................................................... 69

3.3.5.1 Instructions ............................................................................................................................................................... 69

3.3.6 Category 6 – Terrain Display Select ............................................................................................................... 70

3.3.6.1 Instructions ............................................................................................................................................................... 70

3.3.6.2 TAD Selection ......................................................................................................................................................... 70

3.3.6.3 Terrain Display Configuration Group ...................................................................................................................... 71

3.3.6.4 Display Input Control Group .................................................................................................................................... 73

3.3.6.5 Output 429 Bus Group ............................................................................................................................................. 73

3.3.6.6 Sample Display Schematics ..................................................................................................................................... 73

3.3.7 Category 7 – Options Select Group #1 ............................................................................................................ 91

3.3.7.1 Instructions ............................................................................................................................................................... 91

3.3.7.2 Steep Approach (Not Available in the Mk XXII) .................................................................................................... 91

3.3.7.3 TA&D Alternate Pop-up .......................................................................................................................................... 91

3.3.7.4 Peaks Mode .............................................................................................................................................................. 91

3.3.7.5 Obstacle Awareness ................................................................................................................................................. 92

3.3.7.6 Bank Angle Callout Enabling .................................................................................................................................. 92

3.3.7.7 WOW Reversal ........................................................................................................................................................ 92

3.3.7.8 GPS Altitude Reference ........................................................................................................................................... 92

3.3.8 Category 8 – Radio Altitude Input Select ........................................................................................................ 93

3.3.8.1 Instructions ............................................................................................................................................................... 93

3.3.8.2 Digital Radio Altitude Interface (Cat. 8 ID 2) .......................................................................................................... 93

3.3.8.3 Analog Radio Altitude Interface (Cat. 8 ID 0,1,3,4,5) ............................................................................................. 94

3.3.8.4 Digital – ARINC 429 Dual IOC Buses (Cat. 8 ID 251 - 255) .................................................................................. 94

3.3.9 Category 9 – Navigation Inputs Select ............................................................................................................ 95

3.3.9.1 Instructions ............................................................................................................................................................... 95

3.3.9.2 Analog Glideslope Interface (Cat. 9 ID 0,1,5) ......................................................................................................... 96

3.3.9.3 Digital Glideslope/Localizer Interface (Cat. 9 ID 2,3,4) .......................................................................................... 97

3.3.9.4 Digital – ARINC 429 Dual IOC buses (Cat. 9 ID 249 - 255) ................................................................................... 97

3.3.10 Category 10 – Attitude Input Select ................................................................................................................. 98

3.3.10.1 Attitude Signals ........................................................................................................................................................ 98

3.3.10.2 Instructions ............................................................................................................................................................... 98

3.3.10.3 Analog Roll Angle (Synchro) (Cat. 10 ID 0,2,4,7) .................................................................................................. 99

3.3.10.4 Digital ARINC 429 High Speed (Cat. 10 ID 6) ..................................................................................................... 100

3.3.10.5 Digital – ARINC 429 Dual IOC buses (Cat. 10 ID 128, 253, 254) ........................................................................ 100

3.3.11 Category 11 – Heading Input Select .............................................................................................................. 100

3.3.11.1 Instructions ............................................................................................................................................................. 100

3.3.11.2 Magnetic Heading .................................................................................................................................................. 101

3.3.11.3 Analog Heading (Synchro) (CAT. 11 ID 0) ........................................................................................................... 101

3.3.11.4 Digital ARINC 429 High Speed ............................................................................................................................. 102

3.3.11.5 Digital – ARINC 429 Dual IOC buses (Cat. 10 ID 254 & 255) ............................................................................. 102

3.3.12 Category 12 – Windshear Input Select .......................................................................................................... 102

3.3.12.1 Instruction .............................................................................................................................................................. 102



3.3.13 Category 13 – Input / Output Discrete Type Select ....................................................................................... 103

3.3.13.1 Instruction .............................................................................................................................................................. 103

3.3.13.2 Input/Output Discretes ........................................................................................................................................... 103

3.3.13.3 Audio Inhibit Discrete ............................................................................................................................................ 103

3.3.13.4 Landing Gear Discrete ........................................................................................................................................... 103

3.3.13.5 Weight ON Wheels (WOW) Discrete .................................................................................................................... 104

3.3.13.6 Glideslope Cancel Discrete .................................................................................................................................... 104

3.3.13.7 Mode 6 Low Volume Discrete ............................................................................................................................... 104

3.3.13.8 Minimums/Check Height Silence Discrete ............................................................................................................ 105

3.3.13.9 Terrain Awareness Inhibit ...................................................................................................................................... 105

3.3.13.10 Self Test Discrete ................................................................................................................................................... 105

3.3.13.11 Glideslope Inhibit Discrete .................................................................................................................................... 105

3.3.13.12 Timed Audio Inhibit Discrete ................................................................................................................................ 106

3.3.13.13 Low Altitude Mode Select Discrete ....................................................................................................................... 106

3.3.13.14 ICS Audio On Discrete .......................................................................................................................................... 106

3.3.13.15 Output Discretes ..................................................................................................................................................... 106

3.3.13.16 Lamp Format .......................................................................................................................................................... 107

3.3.13.17 GPWS INOP Discrete ............................................................................................................................................ 107

3.3.13.18 TAD INOP Discrete ............................................................................................................................................... 107

3.3.13.19 GPWS Warning Discrete ....................................................................................................................................... 107

3.3.13.20 GPWS Alert Discrete ............................................................................................................................................. 107

3.3.13.21 Glideslope Cancel Discrete .................................................................................................................................... 107

3.3.13.22 TCAS Inhibit Discrete............................................................................................................................................ 108

3.3.13.23 Terrain Display Select #1 & #2 Discrete ................................................................................................................ 108

3.3.13.24 Timed Audio Inhibit Discrete ................................................................................................................................ 108

3.3.13.25 Low Altitude Mode Discrete .................................................................................................................................. 108

3.3.14 Category 14 – Audio Output Level ................................................................................................................ 110

3.3.14.1 Instructions ............................................................................................................................................................. 110

3.3.15 Category 15, Autorotation Threshold ............................................................................................................ 111

3.3.15.1 Instruction .............................................................................................................................................................. 111

3.3.16 Category 16, Torque Input Select .................................................................................................................. 112

3.3.16.1 Instructions ............................................................................................................................................................. 112

3.3.17 Category 17 – Options Select Group #2 ........................................................................................................ 114

3.3.17.1 Instructions ............................................................................................................................................................. 114

3.3.17.2 Helo Normal Pop-Up Range .................................................................................................................................. 114

3.3.17.3 Helo Low Altitude Pop-Up Range ......................................................................................................................... 114

3.3.17.4 Autorotation Callout Option Select ........................................................................................................................ 114

3.3.17.5 Mode 6B Always ON Enable ................................................................................................................................. 115

3.3.17.6 Normal Terrain Airspeed Select ............................................................................................................................. 115

3.3.17.7 Low Altitude Airspeed Select ................................................................................................................................ 115

3.3.17.8 Low Altitude No VFOM Select ............................................................................................................................. 115


3.3.18.1 Instructions ............................................................................................................................................................. 116



3.3.18.2 Audio Inhibit Time ................................................................................................................................................. 116

3.3.18.3 Inhibit All Except Minimum Type Callout and 100 Ft Callout Select ................................................................... 117

3.3.18.4 Inhibit All Except Minimum Type Callout Select .................................................................................................. 117

3.3.18.5 Inhibit Includes Too Low Gear Select.................................................................................................................... 117

3.3.18.6 Inhibit Altitude Callouts 50 ft and Below Over Runway Select ............................................................................. 117

3.3.18.7 Lower MDA/DH Value Select ............................................................................................................................... 117


3.3.19.1 Instructions ............................................................................................................................................................. 118

3.3.19.2 Low Altitude Mode ................................................................................................................................................ 118

3.3.19.3 Mode 2 Terrain Inhibit ........................................................................................................................................... 118

SECTION IV – CONFIGURATION MODULE PROGRAMMING AND TERRAIN DATABASE LOADING ......... 121

4.1 INTRODUCTION ........................................................................................................................................................ 121

4.2 HARNESS CHECKOUT AND POWER CHECK ............................................................................................................... 121

4.3 UNIT INSTALLATION ................................................................................................................................................ 121

4.4 EGPWC INITIALIZATION AND CONFIGURATION ...................................................................................................... 121

4.4.1 RS-232 Communication with the MK XXII EGPWS ........................................................................................ 121

4.4.2 EGPWC Front Panel Test Connector .............................................................................................................. 122

4.4.3 WinVIEWS ....................................................................................................................................................... 122

4.4.4 WinVIEWS Operation ...................................................................................................................................... 123

4.5 CONFIGURATION MODULE PROGRAMMING ............................................................................................................. 123

4.5.1 CUW and CMR Commands ............................................................................................................................. 124

4.5.2 Configuration Module Reprogramming ........................................................................................................... 125

4.5.3 Configuration Module RTC Update ................................................................................................................. 126

4.6 REGIONAL TERRAIN DATABASE LOADING ............................................................................................................... 127

4.6.1 Effectivity ......................................................................................................................................................... 127

4.6.2 Description ...................................................................................................................................................... 127

4.6.3 Approval .......................................................................................................................................................... 127

4.6.4 Material – Cost and Availability ...................................................................................................................... 127

4.6.5 Accomplishment Instructions ........................................................................................................................... 128

4.6.6 Verification of the Terrain Database Version .................................................................................................. 129

SECTION V – CERTIFICATION ................................................................................................................................ 132

5.1 INTRODUCTION ........................................................................................................................................................ 132

5.2 CERTIFICATION PROCEDURE .................................................................................................................................... 132

5.2.1 Equipment Compatibility ................................................................................................................................. 132

5.2.2 Equipment Location ......................................................................................................................................... 132

5.2.3 FAA Requirements ........................................................................................................................................... 132

5.2.4 Ground Test ..................................................................................................................................................... 132

5.2.5 Flight Manual Revision .................................................................................................................................... 132

5.2.6 Flight Test ........................................................................................................................................................ 133

5.2.7 Pilots Guide ..................................................................................................................................................... 133

5.2.8 Failure Modes, Effects, and Safety Analysis .................................................................................................... 133

5.2.9 Existing STC’s.................................................................................................................................................. 133



APPENDIX A - CUSTOMER WORKSHEET ............................................................................................................ 135

APPENDIX B - SAMPLE WIRING DIAGRAMS ...................................................................................................... 144

APPENDIX C – WINVIEWS OPERATION INSTRUCTIONS ................................................................................ 144

APPENDIX D – VENDOR DRAWINGS ..................................................................................................................... 148

D 1.0 VENDOR CONTACT INFORMATION .................................................................................................................. 148

D 1.1 EDMO ........................................................................................................................................................... 150

D 1.2 EMTEQ ......................................................................................................................................................... 151

D 1.3 AEROSPACE OPTICS ........................................................................................................................................ 156

D 1.4 STACOSWITCH ............................................................................................................................................... 157

APPENDIX E - INTERFACE DESCRIPTION DOCUMENT .................................................................................. 159

1.0 PART NUMBER ............................................................................................................................................... 159

2.0 PURPOSE ......................................................................................................................................................... 159

3.0 SYSTEM OVERVIEW ........................................................................................................................................ 159

4.0 ELECTRICAL INTERFACE ........................................................................................................................ 159

4.1 INTRODUCTION ............................................................................................................................................... 159

4.2 SIGNAL INTERFACES ....................................................................................................................................... 159

4.2.1 Grounds ......................................................................................................................................................... 159

4.2.2 Primary Power Input ..................................................................................................................................... 160

4.2.3 DC Analog Inputs .......................................................................................................................................... 160

4.2.3.1 Radio Altitude ........................................................................................................................................................ 160

4.2.3.2 Low Level Glideslope ............................................................................................................................................ 160

4.2.3.3 Localizer Deviation or Low Level Glideslope Validity ......................................................................................... 161

4.2.3.4 Barometric Altitude ................................................................................................................................................ 161

4.2.3.5 Outside Air Temperature ........................................................................................................................................ 161

4.2.3.6 TORQUE INPUTS - DC ........................................................................................................................................ 162

4.2.4 AC Analog Inputs........................................................................................................................................... 162

4.2.4.1 Synchro Roll Attitude ............................................................................................................................................ 162

4.2.4.2 Synchro Magnetic Heading .................................................................................................................................... 162

4.2.4.3 Synchro PITCH ATTITUDE ................................................................................................................................. 162

4.2.4.4 Synchro TORQUE ................................................................................................................................................ 163

4.2.5 Signal Timing Reference Inputs ..................................................................................................................... 163

4.2.6 ARINC 429/575 Digital Serial Bus Inputs ..................................................................................................... 163

4.2.7 RS-232 / RS-422 Digital Serial Bus Inputs .................................................................................................... 164

4.2.7.1 GPS RS-232 Digital Serial Bus (serial port 3) ....................................................................................................... 165

4.2.7.2 GPS RS-422 Digital Serial Bus (serial port 3) ....................................................................................................... 165

4.2.7.3 Air Data RS-232 Digital Serial Bus (serial port 2) ................................................................................................. 165

4.2.7.4 Air Data RS-422 Digital Serial Bus (serial port 2) ................................................................................................. 165

4.2.7.5 SCI Range RS-422 Digital Serial Bus (serial port 1) ............................................................................................. 165

4.2.7.6 TORQUE INPUTS RS-422 Digital Serial Bus (serial port 1) ................................................................................ 166

4.2.8 Discrete Inputs ............................................................................................................................................... 166



4.2.9 Configuration Module Interface .................................................................................................................... 166

4.2.10 GPS Antenna Input ....................................................................................................................................... 167

4.2.11 OAT Voltage Reference Output .................................................................................................................... 167

4.2.12 Lamp Driver Outputs .................................................................................................................................... 167

4.2.12.1 Monitor Output Characteristics .............................................................................................................................. 167

4.2.12.2 Discrete Output Characteristics .............................................................................................................................. 168

4.2.13 Audio Outputs ............................................................................................................................................... 168

4.2.13.1 High Level (Speaker) Audio Output ...................................................................................................................... 168

4.2.13.2 Low Level (Interphone) Audio Output................................................................................................................... 168

4.2.14 ARINC Digital Serial Output Buses.............................................................................................................. 169

4.2.14.1 ARINC 429 Output Bus ......................................................................................................................................... 169

4.2.14.2 ARINC 453 Output Bus ......................................................................................................................................... 169

4.2.15 Front Panel Test Interface ............................................................................................................................ 169

4.2.15.1 RS-232 Maintenance Port (serial port 4) ................................................................................................................ 169

4.2.15.2 PCMCIA / SmartCable Port ................................................................................................................................... 170

4.2.15.3 GSE Present Discrete Input .................................................................................................................................... 170

4.2.15.4 Front Panel Status Indicators.................................................................................................................................. 170

5.0 AIRCRAFT APPLICATION DATA ............................................................................................................. 171

5.1 CONFIGURATION TYPES ................................................................................................................................. 171

5.2 CONFIGURATION SELECTION .......................................................................................................................... 171

5.3 CONFIGURATION SELECTION TABLES ............................................................................................................. 175

5.3.1 Category 1, Aircraft / Mode Type Select ....................................................................................................... 175

5.3.2 Category 2, Air Data Input Select ................................................................................................................. 177

5.3.3 Category 3, Position Input Select ................................................................................................................. 184

5.3.4 Category 4, Altitude Callouts ........................................................................................................................ 192

5.3.5 Category 5, Audio Menu Select ..................................................................................................................... 194

5.3.6 Category 6, Terrain Display Select ............................................................................................................... 201

5.3.7 Category 7, Options 1 Select ......................................................................................................................... 237

5.3.8 Category 8, Radio Altitude Input Select ........................................................................................................ 238

5.3.9 Category 9, Navigation Input Select .............................................................................................................. 244

5.3.10 Category 10, Attitude Input Select ................................................................................................................ 251

5.3.11 Category 11, Heading Input Select ................................................................................................................ 254

5.3.12 Category 12, Windshear Input Select ........................................................................................................... 255

5.3.13 Category 13, Input / Output Discrete Type Select ......................................................................................... 256

5.3.14 Category 14, Audio Output Level ................................................................................................................. 274

5.3.15 Category 15, Autorotation Threshold ........................................................................................................... 275

5.3.16 Category 16, Torque Input Select ................................................................................................................. 277

5.3.17 Category 17, Options 2 Select ....................................................................................................................... 287



6.0 OUTPUT DATA DEFINITION .................................................................................................................... 301

6.1. ARINC 429 OUTPUT DATA ............................................................................................................................ 301

6.1.1 Discrete Output Words .................................................................................................................................. 302



6.1.1.1 EGPWS Alert Discrete #1 (270) ............................................................................................................................ 303

6.1.1.2 EGPWC Logic Discretes (271) .............................................................................................................................. 303

6.1.1.3 Mode 6 Callouts Discrete #1 (272) ........................................................................................................................ 304

6.1.1.4 Mode 6 Callouts Discrete #2 (273) ........................................................................................................................ 304

6.1.1.5 EGPWS Alert Discrete #2 (274) ............................................................................................................................ 305

6.1.1.6 EGPWC Alert Discrete #3 (300) ............................................................................................................................ 305

6.1.2 Internal Data Outputs .................................................................................................................................... 306

6.1.2.1 Geometric Altitude VFOM (135) ........................................................................................................................... 306

6.1.2.2 Terrain Clearance (164) ......................................................................................................................................... 306

6.1.2.3 Geometric Altitude (261) ....................................................................................................................................... 306

6.1.2.4 Computed Terrain Clearance (067) ........................................................................................................................ 306

6.1.2.5 Latitude – Selected EGPWS (310) ......................................................................................................................... 306

6.1.2.6 Longitude – Selected EGPWS (311) ...................................................................................................................... 306

6.1.3 Terrain Display Outputs ................................................................................................................................ 307

6.1.3.1 Displayed Range (050) ........................................................................................................................................... 307

6.1.3.2 Terrain Display Status Word (051) ........................................................................................................................ 307

6.1.3.3 Message Word #1 (052) ......................................................................................................................................... 308

6.1.3.4 Message Word #2 (053) ......................................................................................................................................... 308

6.1.3.5 Message Word #3 (054) ......................................................................................................................................... 309

6.1.3.6 Message Word #4 (055) ......................................................................................................................................... 309

6.1.4 Equipment IDENTIFICATION ...................................................................................................................... 310

6.1.4.1 Equipment IDENTIFICATION WORD ................................................................................................................ 310

6.1.5 FAULT SUMMARY WORDS (for Proline 4/21) ............................................................................................ 310

6.1.5.1 FAULT DIAGNOSTIC Word #1 (350) ................................................................................................................. 310



6.1.6 PEAK BINARY LABELS ................................................................................................................................ 312

6.1.6.1 Peaks Upper Elevation (011) .................................................................................................................................. 312

6.1.6.2 Peaks Lower Elevation (012) ................................................................................................................................. 312

6.2 ARINC 708A OUTPUT ................................................................................................................................... 313

6.3 AUDIO OUTPUT .............................................................................................................................................. 313

6.4 DISCRETE OUTPUTS ........................................................................................................................................ 313

6.4.1 Ground Proximity Alerts Discrete (Lamp) Outputs ....................................................................................... 313

6.4.2 Audio On Discrete ......................................................................................................................................... 313

6.4.3 Monitor Discretes (GPWS, Terrain INOP & Terrain Not Available) ........................................................... 313

6.4.4 Terrain Display Switching Discretes (Wxr/EGPWS Display Select) ............................................................. 314

6.4.5 Glideslope Cancel Discrete ........................................................................................................................... 314

6.4.6 Terrain / Obstacle Awareness Alert Discretes............................................................................................... 314

6.4.6.1 Terrain / Obstacle Caution ..................................................................................................................................... 314

6.4.6.2 Terrain / Obstacle Warning .................................................................................................................................... 314

6.4.6.3 Terrain Pop Up (Helicopter) .................................................................................................................................. 314

6.4.7 Low Altitude Mode Discrete (Tactical) ......................................................................................................... 314

6.4.8 TCAS Inhibit Discrete .................................................................................................................................... 314



6.4.9 Timed Audio Inhibit Discrete ......................................................................................................................... 314

6.5 SYSTEM CONFIGURATION STATUS ................................................................................................................. 315

6.5.1 System Status Messages ................................................................................................................................. 316

7.0 CONNECTOR INTERFACE ........................................................................................................................ 317

7.1 PINOUT FOR FRONT CONNECTORS SORTED BY PIN NUMBER ........................................................................... 317

8.0 DEFINITIONS .............................................................................................................................................. 322



SECTION I GENERAL INFORMATION



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 965-1595-020 965-1595-024 965-1595-030 965-1595-021 965-1595-026 965-1595-022 965-1595-028

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 Information.

Appendix E Interface Description Document



1.4 Reference Documents

Following is a list of Honeywell reference documents:

965-1595-601 Product Specification for the MK XXII Enhanced Ground Proximity Warning System (EGPWS)

965-1595-201 Outline, MK XXII EGPWC

060-4314-002 Failures Modes, Effects, and Safety Analysis

060-4314-009 Generic RWFM Supplement For EGPWS (-020 thru -024)

Generic RWFM Supplement For EGPWS (-026)

060-4314-011 Line Maintenance Manual

060-4314-200 MK XXII Helicopter-Enhanced GPWS Pilot’s Guide

060-4314-251 Installation Ground Test Procedure for the Mk XXII EGPWS for Rotary Wing Aircraft

060-4314-252 General Flight Test Procedure

1.5 Description of Equipment

The MK XXII EGPWS is a rack mount ground proximity warning (GPWS) and terrain display (Class A 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 for helicopters

♦ Terrain map with runways

♦ Internal GPS card

♦ Front loading updateable database (requires Smart Cable)

♦ External Configuration Module (with Real Time Clock for use with Internal GPS)

♦ Internal heater blanket for operation outside of the heated area of the aircraft



Fig 1.0 MK XXII EGPWC

1.5.1 MK XXII EGPWS Computer

The MK XXII EGPWS computer is available under P/N 965-1595-0XX 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, Canada, South America, Europe, Eastern Europe, Africa, South Africa, Asia, Pacific, South Pacific, and Middle East regions and are comprised of terrain data (6 arc second where available), major airports, and man-made obstacles (for North America and limited other regions only).

1.5.2 MK XXII EGPWS Configuration Module

The MK XXII EGPWS Configuration Module is available under P/N 700-1710-020 (Included in Installation Kit, see section 1.8). The MK XXII EGPWS uses a Configuration Module installed in the aircraft wiring to store aircraft/EGPWS interface configuration and includes a Real Time Clock for EGPWS installations using internal GPS. The Configuration module 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. An optional Configuration Module is available under P/N 700-1710-001 for non-Internal GPS operation only.

The 700-1710-020 Configuration Module includes a GPS Real Time Clock (RTC) counter and position memory to aid in GPS initialization. A capacitor will keep the position memory retained and clock current for approximately 35 days. GPS initialization time should be less than 3 minutes with active RTC data. If the capacitor has discharged then GPS initialization time may be as long as 10 minutes.

1.5.3 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 (current draw less than 50mA) Qualification: TSO C129 or C129a or C144

Antenna gain is limited to 33dB gain, maximum. Antennas with 26dB gain are preferred. There are Active GPS antennas with higher gain. However, as the active antenna amplifiers amplify noise as well as the signal, this can overdrive the GPS input AGC circuitry and actually reduce performance.

The following GPS antennas are found to be compatible with the EGPWS internal GPS card. Other GPS antennas may be found compatible, contact EGPWS engineering for assistance. It is the responsibility of the OEM or owner/operator (and ultimately the regulatory authorities) to assess the antenna acceptance criteria relative to ARINC, MIL, or other specifications. Boeing has certified the Sensor Systems antenna S67-1575-133 (an ARINC 743A antenna with a 33dB gain) for use on all A/C. This antenna is certified for HIRF/EMI, Class 1 flight critical operation. As a result, it is very expensive (about 3X other versions).

Honeywell KA 96 P/N 071-01620-0001 TSO-C190 Obsolete ------- King KA 91 P/N 071-01545-0200 TSO-C129 Obsolete ------- King KA 92 P/N 071-01553-0200 TSO-C129

Sensor Systems P/N S67-1575-52 TSO-C129, ARINC 743A Sensor Systems P/N S67-1575-133 TSO-C129a, ARINC 743A

The EGPWS requires an input signal of no less than -106 dB (at the EGPWS-GPS coax connector). Installers need to calculate signal strength, plus antenna gain, minus cable line loss to ensure that the input signal does not exceed the -106 dB limit. To calculate signal strength at the EGPWS coax connector, assume a received signal strength of -118 dB at the antenna (this is average signal strength from a GPS satellite at zenith over the antenna). Add the gain of the antenna, then subtract the line loss of the coax cable, and insertion loss at each connector, except at the EGPWS. Assume 0.6dB insertion loss per connector.



EXAMPLE: Active GPS Antenna with 26dB gain. A 40 foot coax cable run with 1 coax connector (at the rack disconnect). The cable has a specified line loss of 0.25dB/foot. -118dB (received signal) + 26dB (antenna gain) -92dB -10dB (line loss) (0.25dB/foot x 40 foot run) - 0.6dB (rack coax connector insertion loss) = -102.6dB at EGPWS coax connector, better than required -106dB. This is an acceptable installation.

1.5.4 OAT Sensor

The EGPWS uses a separate OAT sensor (Outside Air Temperature) to measure outside air temperature on aircraft that do not have another compatible source of outside air temperature. Outside Air Temperature is used by the EGPWS along with pressure altitude in the Geometric Altitude computation. If Outside Air Temperature is not available, Geometric Altitude is computed using pressure altitude and GPS Altitude with a corresponding reduction in accuracy. Honeywell engineers have determined that the reduction in accuracy is small because the GPS Altitude is the strongest element in the computation.

Geometric Altitude is computed by the EGPWS to reduce or eliminate errors potentially induced in corrected barometric altitude by temperature extremes, non-standard altitude conditions, and altimeter miss-sets. Geometric Altitude also allows continuous EGPWS operation in QFE environments without crew intervention.

1.5.5 Smart Cable (PCMCIA Interface)

The EGPWS Smart Cable (part number 951-0386-001) is a removable PCMCIA card interface. The Smart Cable is compatible with any Honeywell supplied ATA style EGPWS PCMCIA 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 Cable loading operation will closely emulate that of an ARINC 615 Data Loader. (Reference Figure 1-1 MK XXII EGPWS SMART CABLE)



P3

POWER ON

IN PROG

CARD CHNG

XFER COMP

XFER FAIL

SMART CABLEPART NO.

951–0386– 0XX

USED WITH ENHANCEDGROUND PROXIMITY WARNING SYSTEM

SERNO: MFGDATE:

MOD STATUS12345

6789

10

FIGURE 1-1 MK XXII EGPWS SMART CABLE

1.6 Technical Characteristics

MK XXII EGPWS

TSO Compliance: TSO-C194, TSO-C151b, 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: TSO-C194, TSO-C151b Physical size: 2.68” x 1.51” x 0.32” (fits Positronic connector backshell) Weight: <1 pound with connector and backshell Mounting: Mounts to Positronic connector backshell Temperature (operational): same as MK 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 Section 1.5.3, ARINC 743A,TSO-C129A and Manufacturer’s specifications.

OAT Sensor

Nominal 500 ohm Temperature probe, resistance at 0°C 500-ohm ± 0.6 ohm, Range -70°C to +60°C (reference ARINC 575 Section 3.8 or ARINC 706 Section 4.8). See Manufacturer’s specifications.

1.7 Units Supplied

1.7.1 MK XXII EGPWS

The part number for the MK XXII EGPWS units is as follows:

965-1595-0XX 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 two versions. When ordering the Configuration Module, order part number:

700-1710-020 with Real Time Clock (recommended for all installations)

700-1710-001 without Real Time Clock (use only with non internal GPS applications)

1.7.3 Smart Cable (PCMCIA Interface)

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.

1.8 Installation and Accessories Kits

Honeywell recommends the Internal GPS kit for all installations and the External GPS kit as an alternate part.

NOTE: Not all installation kits are immediately available, contact Honeywell Order Administration

(800-757-8999) for availability.



1.8.1 MK XXII EGPWS Installation Kits

(A) EGPWS installation with Internal GPS This kit must be used when using the internal GPS and may be used when using an external GPS source. The MK XXII EGPWS Installation Kit, P/N 755-7013-010, contains the following parts: Vendor Name Vendor P/N Description QTY UM Honeywell P/N Positronic Ind. DD78F1OJVLC-15 P1 connector 1 EA 440-1158-009 Positronic Ind. RD50F1OJVLC-15 P2 connector 1 EA 440-1233-001 Honeywell 700-1710-020 Configuration Module 1 EA 700-1710-020 Bendix/King 071-04003-0002 Computer Mounting Tray 1 EA 405-0383-001 Note: For all parts in the installation kit the weight of each individual part is less than 0.25 pounds.

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

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 XXXNAM North America 1 EA 718-1447-xxx Honeywell XXXSAM South America 1 EA 718-1448-xxx Honeywell XXXEUR Europe 1 EA 718-1449-xxx Honeywell XXXEEU Eastern Europe 1 EA 718-1450-xxx Honeywell XXXAFR Africa 1 EA 718-1451-xxx Honeywell XXXPAC Pacific 1 EA 718-1452-xxx Honeywell XXXASI Asia 1 EA 718-1453-xxx Honeywell XXXSPA South Pacific 1 EA 718-1457-xxx Honeywell XXXMES Middle East 1 EA 718-1458-xxx Honeywell XXXCAN * Canada 1 EA 718-1647-xxx Honeywell XXXSAF * South Africa 1 EA 718-1654-xxx Honeywell 402-6083-xxx Label, TDB 1 EA 402-6083-xxx Honeywell SM9FLAPC256M1 PCMCIA Card, Blank 256Mb 1 EA 300-1314-004** XXX is the Database version number. * New distribution of regions for helicopter databases: In TDB 438 and later, new regions were created for Canada (CAN) which was part of North

America (NAM) region and South Africa (SAF) region which was part of Africa (AFR) region due to higher resolution data being available for those areas.

** The PCMCIA card can also be ordered through Smart Modular Technologies with CUxxxxx part number. See SIL EGPWS-MKV/MKVI/MKVII/MKVIII/XXII-34-39.



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 Honeywell

300-1151-0061

718-1593-0022 Flight History Download Flight History Download

1 1

EA EA

300-1151-0061

718-1593-002 Note 1: Unprogrammed (blank) 32 Mb ATA PCMCIA card. Note 2: Programmed 32 Mb ATA PCMCIA card.

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 bus wiring must meet the following requirements:

• Cable length must be less than 300 feet (91.4 meters). • Wire to wire capacitance must not exceed 50 pF/foot. • Shielded twisted pair with not less than one twist per inch. • Impedance of 78 ohms ±10% at 1 MHz.

Vendor Name Vendor P/N Description QTY UM 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 ECS

4122021 312402

ARINC 453 cable (2 shields) ARINC 453 cable (3 shields)

A/R A/R

EA EA

Emteq D70-022402T-01 ARINC 453 cable A/R EA

M17/176-00002 M83536/6-022M M12883/44-01

Military Specification Relay, 4PDT (Note 1) Relay, Socket (Note 1)

A/R A/R A/R

EA EA EA

Note 1: Recommended in EFS 40/50 Installation Manual.

1.9.2 GPS 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 Honeywell 071-01620-0001 KA 96 GPS Antenna (29dB) 1 EA 071-01620-0001 Honeywell 050-03729-0000 KA 96 Antenna Installation Kit 1 EA 050-03729-0000 Bendix/King 071-01553-0200 KA 92 GPS Antenna (26dB) OPT EA Obsolete * Bendix/King 050-03318-0000 KA 92 Antenna Installation Kit OPT EA Obsolete * Sensor Systems S67-1575-38 S67 GPS Antenna (29dB) OPT EA Sensor Systems S67-1575-52 S67 GPS Antenna (26dB) OPT EA Sensor Systems S67-1575-133 S67 GPS Antenna (33dB) OPT EA



Thermax M17/128-RG400 Coax Cable, RG400/U A/R EA Coax Cable, RG-142B/U A/R EA PIC S14293 Coax Cable A/R EA PIC S44191 Coax Cable A/R EA ECS 311901 Coax Cable A/R EA ECS 311601 Coax Cable A/R EA ECS 311201 Coax Cable A/R EA Amp 225554-6 TNC Angle Plug, Male OPT EA 440-1239-001 Amphenol 79075 TNC Angle Plug, Male OPT EA 440-1239-001 NOTE: If a satellite communication system is installed in the aircraft, or the GPS cable run is in the vicinity of a VHF transceiver

and/or cable, DO NOT USE R/G 142 or R/G 400 cable. * The KA 92 GPS antenna has been made obsolete by the manufacturer and replaced by the KA 96 GPS antenna. See

Honeywell Service Bulletin KA 92-34-01.

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 1 EA

Klixon (T.I.) 7277-2-1 1 Amp Circuit Breaker, lamp power +28

1 EA

1.9.4 Annunciators & Switch/Annunciators

The devices shown below are switch/annunciators and are representative of those used in some installations. However, there are other comparable devices on the market that may be substituted at the installer/customers choice. The installer/customer is cautioned to verify regulatory approval of the annunciation devices installed. See Appendix D for Vendors.

1.9.4.1 GPWS Warning (red) P/TEST; switch/annunciator assembly

The ‘GPWS’ annunciator provides visual indication of an EGPWS warning. The GPWS warning (red) annunciator also has a switch that is used to manually initiate EGPWS Self Test.

1.9.4.2 GPWS Caution (amber) G/S CANCLD switch/annunciator assembly.

The ‘GPWS caution annunciator provides visual indication of an EGPWS alert. The EGPWS caution (amber) annunciator also has a switch that is used to manually inhibit EGPWS Mode 5 glideslope alerts. The bottom half of the annunciator provides visual indication that the Mode 5 glideslope alerts have been canceled.

1.9.4.3 LOW ALT / ON switch/annunciator assembly

The LOW ALT / ON switch/annunciator provides for manual selection of low altitude mode and visual indication that the Mk XXII EGPWS is in low altitude mode.

1.9.4.4 TERR INHIB / ON switch/annunciator assembly

The ‘TERR INHIBIT’ switch/annunciator provides for manual selection of terrain inhibit mode and visual indication that the EGPWS Terrain functions have been inhibited.



1.9.4.5 AUDIO INHIBIT / ON switch/annunciator assembly

The ‘AUDIO INHIBIT’ switch/annunciator provides for manual selection of audio inhibit mode and visual indication that the EGPWS mode functions have been inhibited.

1.9.4.6 GPWS INOP / TERR INOP annunciator assemblies

The ‘GPWS INOP’ annunciator provides visual indication that the EGPWS GPWS modes have a disabled function. The ‘TERR INOP’ annunciator provides visual indication that the EGPWS Terrain modes have a disabled function.

1.9.4.7 TERR DISPLAY / ON switch/annunciator assemblies

The ‘TERR DISPLAY’ switch/annunciator provides for manual selection of the terrain display and visual indication that the EGPWS Terrain Display has been selected for the associated display.

1.10 Cockpit Speaker (Optional)

The MK XXII EGPWS can interface to an 8 ohm audio speaker for cockpit annunciation of aural alerts.

Vendor Name 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

1.11 Temperature Probes

The MK XXII EGPWS may be optionally interfaced to a dedicated 500-ohm temperature probe meeting the specifications of ARINC 575 Section 3.8. The installer may want to discuss availability of a dual-element probe compatible with the EGPWS and with other systems on the aircraft with the manufacturers. Vendor Name Vendor P/N Description QTY UM Kollsman CIC Norwich Norwich

05257* 103-00157-3 103-00034

Single element, unheated Single element, unheated Dual element, unheated

1 1 1

EA EA EA

Rosemount 102CT2CB 500-ohm 1 EA Rosemount 102AU1AF Single element, heated 1 EA Rosemount 102AU1AG Dual element, heated 1 EA Rosemount 102EH2BH Dual element, heated 1 EA Rosemount 102EH2EB Dual element, heated 1 EA Rosemount 102JE2FG Triple element, heated 1 EA Rosemount 129H-500 Single element, unheated 1 EA Rosemount 129G-500 Dual element, unheated 1 EA *Also available from Donel Systems (formerly CIC)

1.12 Tools Required

1.12.1 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

1.12.2 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 Daniels K42 (22-28 AWG) Contact Positioner, Pin P3 EA 1 Military M22520/2-09

1.12.3 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

1.12.4 Spare Contacts - P1, P2, P3

P/N Description UM QTY Vendor Name & Part Number 440-1223-002 15 pin male with hood EA 1 Positronic Ind. DD15M10YOC-15 440-1223-003 1 15 pin female EA 1 Positronic Ind. DD15F10OOC-15 440-1223-004 1 15 pin male EA 1 Positronic Ind. DD15M10OOC-15 400-5163-002 1 15 pin clamp kit EA 1 AMP 745854-3 male contacts for 15 pin 22-30 AWG EA 1 Positronic Ind. MC8022D male contacts for 15 pin 22-30 AWG EA 1 M39029/58-360 female contacts for 50 pin 20-24 AWG EA 1 Positronic Ind. FC6020D female contacts for 50 pin 20-24 AWG EA 1 M39029/63-368 female contacts for 78 pin 22-30 AWG EA 1 Positronic Ind. FC8022D female contacts for 78 pin 22-30 AWG EA 1 M39029/57-354 1 These parts are available in EGPWS kit PN 755-7013-090.

1.13 License Requirements

There are no Radio license requirements for the MK XXII EGPWS.



1.14 TSO-C194 Deviations

The MK XXII EGPWS and its Configuration Module have two (2) deviations to TSO-C194. Honeywell has shown that the system maintains an equivalent level of safety and the FAA has evaluated and approved the deviations.

1.14.1 Environmental Qualification Deviation

TSO-C194 states in Section 3 (Requirements), paragraph d (Environmental Qualification) “Test the equipment according to RTCA/DO-160F, Environmental Conditions and Test Procedures for Airborne Equipment, dated December 6, 2007.”

Deviation:

The original qualification testing for the MK XXII EGPWS, part number 965-1595-[ ], and Configuration Module, part number 700-1710-020, was performed in 2003 at which time RTCA/DO-160D was the current version. The appropriate categories were tested for helicopter applications. Honeywell has compared DO-160D to DO-160F, while DO-160F contains several test procedures updates DO-160D remains a valid series of minimum standard environmental test conditions. The appropriateness and FAA acceptance of this qualification basis has been shown by TSO-C151a/b authorization as well as the numerous MK XXII STC and TC approvals in helicopter applications.

Approval Status:

Honeywell has demonstrated an equivalent level of safety as required by TSO-C194 in Section 3 (Requirements), paragraph g (Deviation). The FAA has approved this deviation.

See Environmental Qualification Form, Table I.

1.14.2 Electronic Hardware Qualification Deviation

TSO-C194 states in Section 3 (Requirements), paragraph f (Electronic Hardware Qualification). “If the article includes a complex custom micro-coded component, develop the component to the guidance in FAA Advisory Circular (AC) 20-152, RTCA, Inc. Document RTCA/DO-254, Design Assurance Guidance for Airborne Electronic Hardware" The hardware design assurance level should be consistent with the failure condition classification in paragraph 3b of this TSO.”

Deviation:

The MK XXII EGPWS hardware was developed in 2002 which predates FAA Advisory Circular (AC) 20-152 issue date of 6/30/05. The MK XXII EGPWS contains one programmable logic device (PLD) and two ARINC 429 Receiver chips that are considered complex electronic hardware. The Configuration Module includes two PLDs.

Honeywell followed an FAA agreed upon complex electronic hardware approval method for TSO submittals. The design assurance method included DER review and approval, with FAA form 8110-3, of the programmable logic device lifecycle data. This approval process occurred each time minor changes were made to the EPLD to support board updates.



Approval Status:

Honeywell has demonstrated an equivalent level of safety as required by TSO-C194 in Section 3 (Requirements), paragraph g (Deviation). The FAA has approved this deviation.

1.15 Limitations

TSO-C194 paragraph 5. Application Data Requirements.

1.15.1 a. Operating instructions and equipment limitations

The Honeywell MK XXII Helicopter EGPWS Pilot Guide HPN 060-4314-200 including section MK XXII

System Limitations / Constraints is available upon request from Honeywell Technical Publications to Honeywell authorized installers and dealers. Installers will provide a Flight Manual Supplement as part of their STC submittal.

1.15.2 b. Installation procedures and limitations

The installer will provide detailed installation drawings as part their STC submittal noting any limitations in their submittal package.

The conditions and tests for TSO approval of this article are minimum performance standards. Those installing this article, on or in a specific type or class of aircraft, must determine that the aircraft installation conditions are within the TSO standards. TSO articles must have separate approval for installation in an aircraft. The article may be installed only according to 14 CFR part 43 or the applicable airworthiness requirements.

1.15.3 c. Schematic drawings of the installation procedures

Section 2 of this document provides specific installation guidance for computer mounting, configuration module installation, optional GPS antenna mounting, and required cockpit annunciators.

1.15.4 d. Wiring diagrams of the installation procedures

Section 3 of this document provides specific installation guidance for known aircraft interfaces.

1.15.5 e. List of components

Section 1 of this document details required and optional items used for installation.

1.15.6 f. Component Maintenance Manual (CMM)

ATA No. 34-45-42 (HPN 012-0714-001) available to Honeywell authorized installers and dealers from Honeywell Technical Publications.

1.15.7 g. Material and process specifications list

Data provided to the FAA.

1.15.8 h. Quality control system (QCS) description

Honeywell is an authorized Production Approval Holder (PAH).



1.15.9 i. Manufacturer’s TSO Qualification test report

This item is included in the Plan for Software Aspects of Certification (PSAC) and is available upon request from Honeywell Technical Publications to Honeywell authorized installers and dealers.

1.15.10 j. Nameplate drawing

Honeywell drawing number 402-6083 is available upon request from Honeywell Technical Publications to Honeywell authorized installers and dealers.

1.15.11 k. List of all drawings and processes

Data provided to the FAA.

1.15.12 l. Environmental qualifications form

Honeywell drawing number 904-0178-401 Qualification by Test and Similarity Report is available upon request to Honeywell authorized installers and dealers from Honeywell Technical Publications.

1.15.13 m. Plan for software aspects of certification (PSAC), software configuration index, and software accomplishment summary (SAS)

The Plan for Software Aspects of Certification (PSAC), Software Configuration Index, and Software Accomplishment Summary (SAS) are available upon request from Honeywell Technical Publications to Honeywell authorized installers and dealers.

1.15.14 n. Plan for hardware aspects of certification (PHAC), hardware verification plan, top-level drawing, and hardware accomplishment summary

All hardware related data is covered in the Plan for Software Aspects of Certification (PSAC), and is available upon request from Honeywell Technical Publications to Honeywell authorized installers and dealers.



Environmental Qualification Form

NOMENCLATURE: EGPWS MK XXII

TYPE/MODEL/PART NO: 965-1595- [ ] TSO NUMBER C194, C151b

MANUFACTURER’S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION: 965-1595-601

Product Specification for the Helicopter Enhanced Ground Proximity Warning System (EGPWS) Rev D

MANUFACTURER: HONEYWELL INTERNATIONAL INC.

ADDRESS: 21111 N. 19th Ave., Phoenix, AZ 85027

REVISION & CHANGE NUMBER OF DO-160: NEW DATE TESTED: March – April 2003

CONDITIONS SECTION DESCRIPTION OF TESTS CONDUCTED

Temperature and Altitude 4.0 Equipment tested to Categories F2,

Low Temperature -55C Operation High Temperature +70C Operation In-Flight Loss of Cooling NA

4.5.1 4.5.2 & 4.5.3 4.5.4

Category F2 for Temperature and Altitude No cooling necessary

Altitude: 55,000 Ft Decompression: 8,000 ft to -55,000 ft Overpressure: -15,000 ft

4.6.1 4.6.2 4.6.3

Category A2 for Decompression and Overpressure

Temperature Variation 5.0 Equipment tested to Category B

Humidity 6.0 Equipment tested to Category A

Operational Shock and Crash safety 7.0 Equipment tested to Category B

Vibration 8.0 Equipment tested to Category U: Helicopter unknown frequencies. Curves F and F1.

Explosive Atmosphere 9.0 Equipment tested to Category E

Waterproofness 10.0 X, (no test required)

Fluids Susceptibility 11.0 X, (no test required)

Sand and Dust 12.0 X, (no test required)

Fungus 13.0 F, (no test, non-nutrient material certification)

Salt Fog Test 14.0 X, (no test required)

Magnetic Effect 15.0 Equipment tested to Category Z



CONDITIONS SECTION DESCRIPTION OF TESTS CONDUCTED

Power Input 16.0 Equipment tested to Category A

Voltage Spike 17.0 Equipment tested to Category A

Audio Frequency Susceptibility 18.0 Equipment tested to Category Z

Induced Signal Susceptibility 19.0 Equipment tested to Category C

Radio Frequency Susceptibility 20.0 Equipment tested for conducted susceptibility to Category R and for radiated susceptibility to Category RR

Radio Frequency Emission 21.0 Equipment tested to Category M

Lightning Induced Transient Susceptibility 22.0 Equipment tested to Category A3E3

Lightning Direct Effects 23.0 X, (no test required)

Icing 24.0 X, (no test required)

Electrostatic Discharge 25.0 Equipment tested to Category A

Fire, Flammability 26.0 Not Applicable

Other Tests

REMARKS

Table I – Environmental Qualification Form



1.16 Non TSO functions

A non-TSO function is one that is not covered by a TSO-approved minimum performance standard (MPS), does not support or affect the hosting article’s TSO function(s), and could technically be implemented outside of the TSO article.

Honeywell’s MK XXII EGPWS includes optional features that meet the non-TSO definition. The following tables briefly describe existing non-TSO functions included in the MK XXII EGPWS. The Mode envelopes are similar to the fixed wing TSO C92c Mode envelopes but adjusted for helicopters.

1.16.1 Helicopter Mode 1

Helicopter Mode 1 provides alerts when the aircraft has excessive descent rate close to the terrain. This envelope is not part of TSO C194.


Helicopter Mode 2 provides alerts when the aircraft is closing with the terrain at an excessive rate. This envelope is not part of TSO C194.


Helicopter Mode 3 provides alerts when the aircraft loses a significant amount of altitude immediately after takeoff or during a missed approach. This envelope is not part of TSO C194.


Helicopter Mode 4 provides alerts for insufficient terrain clearance with respect to phase of flight and speed. This envelope is not part of TSO C194.

1.16.5 Helicopter Mode 4C

Helicopter Mode 4C provides a Mode 4 “Too Low Terrain” warning if the aircraft exhibits insufficient climb performance during take-off. This envelope is not part of TSO C194.

1.16.6 Helicopter Altitude Callouts

The Altitude Callouts option, enabled via a configuration module selection, aurally annunciates various altitude callouts and descent below minimum selected decision height during final approach. Other sets of callouts are also provided during autorotation and cruise to provide altitude awareness to the rotor wing pilot. Pre-defined callout menus are selected with configuration module option. This function is not part of TSO C194.

1.16.7 Bank Angle Callout

The Bank Angle option, enabled via a configuration module selection, provides an aural advisory for excessive bank angles. This function is not part of TSO C194.

1.16.8 Tail Strike Callout

Tail Strike provides an aural advisory for excessive pitch angles when the aircraft is low to the ground and there is danger of tail rotor strike.



1.16.9 Externally Triggered Annunciation

The EGPWC responds to the external commands by generating aural annunciations prioritized with respect to other ground proximity alerts. This function is not part of TSO C194.

“Low Rotor” “Fire Engine 1/2" “Engine 1/2 Failure” “Fire APU” “Airspeed”

“Smoke In Baggage” “Hover Altitude” “Swash Plate Temperature” “Level Off” “Decouple”

“Hover Altitude” “Gearbox Pressure” “Check Power” “Smoke In Cabin” “Gear Box Oil Out”

1.16.10 Radio Altimeter Self Test

A maintenance DH voice advisory call is provided from the EGPWC during an on ground Radio Altimeter test. This function is not part of TSO C194.

Honeywell MK XXII EGPW Installation Manual


SECTION II

INSTALLATION



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.



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 computer has an internal heater blanket allowing the computer to be mounted outside the heated area of the aircraft. The computer has been qualified for operation up to 50,000 feet and -55°C using the heater blanket. The computer has been vibration tested to 3-axis allowing mounting orientation in any direction.

All mechanical installation drawings 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. Follow aircraft manufacturer’s, sub-system manufacturer’s or ARINC specifications for shield grounding.

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).



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 700-1710-020 (optional part number 700-1710-001). The Configuration Module is installed as one side of the P2 (50 pin) mating connector backshell and contains electrically reprogrammable memory for configuration storage. The Configuration Module when installed is wired directly to the appropriate pins in the P2 connector.

2.3.5 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

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. (Note: Ground wire is not applicable to 700-1710-020 Configuration Modules.)

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 700-1710-020 * 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

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



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.


Note: The Ground wire (used for ESD discharge) is Not Applicable to Configuration Module PN 700-1710-020.



STEP 3 Position item 1.7 (Slide lock) onto wired connector as shown in figure 2.1-3 below:




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. (See Note par. 2.3.5.E)


Note: The Ground wire (used for ESD discharge) is Not Applicable to Configuration Module PN 700-1710-020.



STEP 5 Install item 1.6 (Spring Clip) as shown figure 2.1-5 below:




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.




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.




2.3.6 GPS Antenna location

The antenna must be mounted on top of the fuselage in the centerline of the aircraft. 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 GPS antenna baseplate must be level within ± 5° in both axis when the aircraft is level (level is defined as the aircraft attitude required when weighing the aircraft for weight and balance). If the GPS antenna is tilted more than 5° or is mounted close to other objects that shadow it, loss of some of the satellites will occur and system performance may be degraded. See manufacturer for specifications of GPS antenna, antenna cables, and connector information. Some GPS Antenna cable and connector information, including vendor information, is listed below.

Cable Length Cable Part Number (VPN)

EGPWS TNC Connector (VPN)

Antenna TNC Connector (VPN)

Max Loss*

0 to 40 ft RG142B/U RG400/U

TED Mfg. 5-10-30 TED Mfg. 5-30-102-1 8.0

0 to 80 ft ECS 311601 TED Mfg. 5-10-307 TED Mfg. 5-10-307 8.0 0 to 100 ft ECS 311201 TED Mfg. 5-10-306 TED Mfg. 5-10-306 8.0 100 to 165 ft Contact TED, ECS or PIC for complete cable/connector assembly * Maximum Allowable Loss (dB) @ 1575 MHz for cable and connector using nominal 26.5 dB gain.

TED Manufacturing Corp. 11415 Johnson Drive Shawnee, Kansas 66203 Tel: (913) 631-6211

Electronic Cable Specialists (ECS) 5300 W. Franklin drive Franklin, Wisconsin 53132 Tel: (800) 327-9473

PIC Wire & Cable N63 W 22619 Main Street Sussex, Wisconsin 53089 Tel: (800) 742-3191

2.3.7 GPS Antenna Installation

Refer to manufacturer’s procedures or applicable STC documentation.

2.3.8 OAT Sensor Location

The OAT sensor should be mounted on the underside (belly) of the aircraft or other convenient location meeting the following conditions. Avoid mounting the sensor where it can be affected by direct sunlight, or exhaust gases from engines or heaters. The probe tip should extend beyond the aircraft boundary layer into the turbulent airflow. See manufacturer for specifications.

2.3.9 OAT 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 965-1595-601 for additional information and for electrical loads specification.

NOTE: When using the Bendix/King Multifunction Display (MFD) KMD 550/850 most of the annunciation and switch functions described below are available on screen text and as softkeys.

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, blue, or green 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.

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 2-8. For panel cutouts and assembly options see the manufacturer’s specifications. 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 at least one 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.



FIGURE 2-8 MK XXII EGPWS Annunciators/Switches Location



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. Note that Modes 1, 2, 3, and 4 are still enabled.

2.3.10.3.2 Audio Inhibit (Timed) The Timed Audio Inhibit will inhibit most audio output for a configurable period. The default inhibit time is 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. Configuration options in the Options 3 (Category 18) menu provide a variety of inhibit selections.

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 RECOMMENDED.

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 1 is inhibited and, 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.

2.3.10.3.5 ICS Audio On This discrete input or Command Word bit is to be used with Central Aural Warning Systems to provide handshaking for priority management. When the ICS Audio On is set true, all audio messages that are prioritized below the Warning Terrain and Warning Obstacle messages will be inhibited allowing priority messages to be broadcast. See Category 13 ID’s 137 – 139.

2.3.10.3.6 Minimums/Check Height Silence This discrete input will inhibit a Mode 6 "Minimums Minimums" or "Check Height Check Height" callout for 3 minutes. The momentary action switch is normally mounted in the Cyclic lever and is usually found on Eurocopter aircraft. See Category 13 ID’s 137 – 139.



FIGURE 2-2 MK XXII EGPWS OUTLINE



FIGURE 2-3 MK XXII EGPWS MOUNTING TRAY

Honeywell P/N 405-0383-001



SECTION III

SYSTEM PLANNING



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 5.3 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 3. Use this table along with Appendix B Fig A1.1, 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 7.1 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 *Pin pairs J1-40/J1-60 and

J1-40, J1-60 * +28 VDC Input J1-41/J1-61 are internally

J1-41, J1-61 * +28 VDC Return shorted to each other.

Recommended EGPWC Power Control Device: 3 Amp Delayed Action Circuit Breaker

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



Pins J1-42 and J1-53 are both connected to chassis ground internally. It is not necessary to tie them

both to ground in the aircraft wiring. Pin J1-53 was made available to provide a convenient way to

supply a ground to external equipment. If the OAT probe is not present, nothing needs to be tied to J1-

53.

3.2.3 GPS Antenna

A GPS antenna connector is available on the front of the MK XXII EGPWS 965-1595-0XX.

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 are 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.



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

annunciators via a EFIS display. 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 3.3.13.14. Output

discretes are intended to operate with +28 VDC lamp sources and will not operate with +5 VDC

lamp sources.

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 700-1710-020. The

configuration module is installed as part of the P2 mating connector backshell and contains electrically

reprogrammable memory for configuration storage. By this method the aircraft configuration is stored in

the configuration module on the aircraft and each newly installed EGPWS computer does not require

operator assisted programming before or during installation. The aircraft configuration in the

Configuration Module can be changed at any time by use of the WinViews software, as explained in

Section IV.

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, fixed or retractable gear, tail strike warning selection and

terrain approach speed regime. Note: Category 16 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 5.3.1 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). Note that with the part number 965-

1595-020, all of the Aircraft Types have been renumbered from earlier versions.

3.3.1.2 Instructions

1. Using Appendix E Table 5.3, under Step/category 1 select Aircraft type. Using Table 5.3.1 and the

instructions below to select ID number for your aircraft type and record that number on Table 5.3

under Ident No. This number will be used for programming the configuration module.

2. Select the aircraft first by gear type, retractable or fixed. Then select the tail strike warning profile

from Table 3.3.1.2-1 below. Tail strike options are Type 0 (No Tail Strike Warning), Type 1 (higher

tail profile), Type 2 (lower tail profile), Type 3 (S-92 tail profile) and Type 4 (AW 139 tail profile).

Tail Strike Type Description Aircraft Models

0 No Warning MD 900, MD 902

1 High Tail Profile S-76, AS-332, Bell 407, Bell 212/412, , EH-101, US-101,

Agusta 109

2 Low Tail Profile EC-135, EC-155B, , AS-350, AS-355, AS-365, HH-65, Bell

427, Bell 430

3 High Tail Profile S-92

4 High Tail Profile AW 139

Table 3.3.1.2-1 Helo Tail Strike Warning Selection

3. Finally select the operational speed profile for your aircraft and it's normal mission. This sets two

approach speed profile values. The first (approach) is the higher end speed an approach will start

at. The second (hover), is the lower approach speed of an approach. The Terrain function will

inhibit all warnings below this speed. Two speed options are available, fast and slow. The fast

profile, which fits most applications and is Honeywell's recommended selection, sets Approach to

100 knots and Hover to 70 knots. The slow profile sets Approach to 90 knots and Hover to 60

knots. The slower range should only be used by aircraft flying slower and who prefer a more

conservative warning protection.

Speed Profile Cruise Approach Hover

Fast >100 Kts 100-70 Kts <70 Kts

Slow >90 Kts 90-60 Kts <60 Kts

Table 3.3.1.2-2 Helo Operational Speed Profile



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 7 digital air

data types.


1. Using Appendix E Table 5.3, under Step/category 2 select Air Data Source. Using Table 5.3.2 and

5.3.2-x select the ID number for your air data source and record that number on Table 5.3 under

Ident No. for step 2. This number will be used during programming of the configuration module.

2. Using Appendix E Tables 5.3.2-x, where x is the Air Data Type number, define the electrical

interfaces required to support your Air Data Type. Using Table 5.3.2-x, determine the wiring

interconnects and record it on Appendix A Fig A1-2.



3.3.2.2 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

(+)

(-)

UncorrectedBarometric

Altitude

Baro Altitude Valid +28V

(+)

(-)Temp. Input

Chassis Ground

+5V Excitation

500 ohmTemperature

Probe

Analog-ADC.vsd

Cat 2 Uncorrected Baro Altitude

Vendor Model ID Altitude Out Common BIT Out

Kollsman CIC 04077 0 J1-F J1-G J1-E

Collins ADS-65 3 J1-12 J1-13 J1-5

Kollsman CIC 02702 4 J1-A J1-B J1-E

Honeywell AZ-241 11/12 J1-63 J1-11 J1-12

Honeywell AZ-242/244 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

Honeywell AZ-252 11/12 J1A-17 J1B-11 J1B-13

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: ID 12 does not require an OAT input, instead a constant temperature of 25 deg C is assumed.

NOTE: Honeywell AZ-242 with part numbers 4013242-708, -709, -710, -712, -713 and –742 have DC Altitude out at pin J1B-17. Part numbers 4013242-709 and -711 have DC Altitude out at pin J1A-40.



3.3.2.3 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.


labels 203, 204, 206, 212, and 213.


labels 203, 206, and 213.

Air Data Type 13 is a low speed, digital ARINC 429 signal having the air data label 203 only.

Air Data Type 14 is a high speed, digital ARINC 429 signal having air data labels 203, 206, 212, and

213.

If the hardware is capable of transmitting all label sets, the preferred Air Data Type is 5. If only label 204

is missing, use Air Data Type 1, and if both labels 204 and 212 are missing use Air Data Type 6.

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 SpeedAir Data Bus

Digital-ADC.vsd

Cat 2 Bus 1 Bus 2

Vendor Model ID A B A B

Sperry AZ-6XX,-8XX 5* J1B-26 J1B-27 J1B-70 J1B-71

Kollsman CIC 04471 5* J1-12 J1-13

Kollsman CIC 02702

mod 6

1* J2-J J2-K

KDC 281 1* P2811-5 P2811-6

KDC 481 5* P4811-U P4811- i

B&D 90004 5* J1-27 J1-9

B&D 2600 6** 6 8

B&D 2601 6** 14 13

B&D 2800 5* P201-11 P201-28

Collins ADC 85/86/850 5* P2-9 P2-10 P2-29 P2-30

Shadin ADC-2000 (s/w mod 71.73.01)

5* J1-40 J1-22

Thommen AC/AD32*** 5* B C q r


* Category 2, ID 5, 1 or 6 depending on availability of labels 204 and 212. ID 5 is the preferred selection, 1 is next, and 6 is last. CIC air data computers installed without Baro Set pots should be configured as Cat 2 ID 1.

** EGPWS installations with the B&D 2600 ADC should be configured for Cat 2 ID 6 because the B&D 2600 Altitude Rate ARINC 429 label 212 has a poor response to altitude changes and causes nuisance alerts.

*** Configure for Low speed ARINC 429 transmitting labels 203, 204, 206, 212, and 213.



3.3.2.4 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 575Air Data Bus

ARINC575-ADC.vsd

Cat 2 Bus 1 Bus 2


Collins ADC-80( )

Collins ADC-82A

2 P3-35 P3-36

B&D 90004 2 J1-27 J1-9




3.3.2.5 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

J2ARINC 429 Air Data

ARINC 429 Bus - Hi

ARINC 429 Bus - Lo

EGPWS MK XXII

A

B

ARINC 429 Low SpeedAir Data Bus

(+)

(-)Temp. Input

Chassis Ground

+5V Excitation

500 ohmTemperature

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




3.3.2.6 Digital – ARINC 429 Dual IOC Buses (Cat. 2. ID 253 and 254)

Air Data Type 253 (IOC bus or equivalent) is a dual, high speed, digital ARINC 429 signal having the air

data labels 203, 206, 212, and 213. Air Data Type 254 (IOC bus or equivalent) is a dual, high speed,

digital ARINC 429 signal having the air data labels 203, 204, 206, 212, and 213.

37*

36*

A

B

J2 IOC Buses

IOC Bus 1

EGPWS MK XXII

A

B

ARINC 429High Speed

41*

40*

A

B

IOC Bus 2A

B

ARINC 429High Speed

ARINC429-IOC-1.vsd

Cat 2 IOC Bus 1 IOC Bus 2


253*

254


* For ID 253 the MK XXII connections at connector J2 are J2-39/38 and J2-21/04.



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 Pxpress format, and Internal GPS card.


1. Using Appendix E Table 5.3, Under Step/category 3 select Position Input Source. Using Table 5.3.3

and 5.3.3-x select ID number for your position input source and record that number on Table 5.3

under Ident No. for step 3. This number will be used during programming of the configuration

module.

2. Appendix E Tables 5.3.3-x, where x is the position input type number, define the electrical interfaces

required to support the position input type. Using Tables 5.3.3-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 derived from VDOP and HDOP signals and are in meters. Note:

Universal UNS-1 C/D/K/M GPS only, output is in ARINC 743 format. NOTE: in -030 software update

HDOP (101) and VDOP (102) were added as required labels for Category 3 ID’s 0, 1, 4, 5, 10, 11,

12, 13, 252, 253 and 255.

3.3.3.3 GPS Altitude (Label 076) Reference

The GPS Altitude (label 076) may be referenced to mean sea level or WGS-84. Determine which

reference your GPS position uses and program the GPS Altitude Reference accordingly in Category 7.

Note: Universal UNS-1 C/D/K/M GPS only, output the Altitude Label 076 referenced to WGS-84.

3.3.3.4 North-South East-West Velocity labels

ID’s 10-13 and 253 are provided to support GPS interfaces that do not provide North-South East-West

Velocity labels 166 & 174. ID’s 0,1,4,5, and 255 are preferred.

3.3.3.5 HT-1000 GPS Compatibility

ID 14 is provided to support HT-1000 GPS interfaces that do not provide HDOP, VDOP and Sensor

Status labels.



3.3.3.6 ARINC 429 BUS (Cat. 3 ID 0,1,4,5,10-13)

25

8

A

B

J2 ARINC 429 GPS

ARINC 429 Bus - Hi

ARINC 429 Bus - Lo

EGPWS MK XXII

A

B

ARINC 429GPS Bus

ARINC429-GPS.vsd

Cat 3 429 GPS Alt ARINC Bus 1 Bus 2

Vendor Model ID Speed Ref. 743/743A A B A B

Collins GNLU-910A Note 4 High MSL 743A LMP-2J LMP-2K

Collins GPS-4000 0/42 H/L2 MSL 743A MP-11A MP-11B

UNS 764-2

UNS GPS-1000 (1075-( )) 1 Low WGS-84 743 TP-12A TP-12B TP-11A TP-11B

UNS GPS-1000A (1078-( ))

UNS GPS-1200 (1080-( )) 0 Low MSL 743A TP-12A TP-12B TP-11A TP-11B UNS-1C (1017-3X-( )) or (1017-4X-( ))

1 Low WGS-84 743 P1-a P1-b

UNS-1CSP (1019-3X-( ))

(1019-4X-( ))

UNS-1D (1192-00-( )) or (1192-30-( ))

1 Low WGS-84 743 MP-10J MP-10K

UNS-1F(w), -1E (2192-00-( ))

0 Low MSL 743A MP-10J MP-10K MP-4J MP-4K

UNS-1ESP (2019-4X-( )) UNS-1K, -1L (1116-3X-( )) or (1116-4X-( ))

1 Low WGS-84 743 MP-4C MP-4D

UNS-1M (1013-4X-( )) 1 Low WGS-84 743 P2-K P2-L UNS-1MSP (1114-4X-( )) (1114-5X-( ))

GNS-XLS (17960-0203-) SM04

(17960-0102-) SM07 0 Low MSL 743A J101-N5 1 J101-N6 1

GNS-XL (18355-) SM07 0 Low MSL 743A J101-N5 J101-N6 GNS-X / CDU-XLS (NMU) (14141-0624-) SM04

0 Low MSL 743A JA-A01 JA-A02

HG2021GBXX/ABXX 1/5 2 H/L2 MSL 743 J1-38 J1-39 J1-24 J1-25

HG2021GC/GDXX 0/4 2 H/L2 MSL 743A J1-38 J1-39 J1-24 J1-25

HT1000/HT9100 10/12 H/L MSL 743A MP-C02 MP-C01 FreeFlight (Trimble) 2101 I/O Approach Plus (81440-XX software ver. 241G)

1 Low MSL 743A5 J2-16 J2-23 J2-58 J2-57

FreeFlight Systems 1203 GPS/WAAS (84327-0X-XXXX)

0/4 2 H/L2 MSL 743A J1-14 J1-13 J1-18 J1-17

NOTE: The connector pin numbers and software versions given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer’s customer service to confirm your installation.

1 The Enhanced GNS-XLS ARINC 429 bus also contains Range label 2 HG2021G: Pin 21 open = high speed; Pin 21 GND = Low speed; GPS-4000: MP-4C = HiSpd/LoSpd select; FFS 1203:

Pin 11 = HiSpd/LoSpd select 3 NOT COMPATIBLE with MK XXII EGPWS

a. Honeywell HT-9000 / KLN-89 / KLN-90 / KLN-670 / GNS-XES b. IIMorrow Apollo 2101



c. Trimble 2100 / 2101 / TNL8100 d. Universal GPS-950, UNS-1A (1161-X-X), UNS-1B (1190-X-X), UNS 764-1

4 Check manufacturer for compatibility with North-South, East-West Velocities. 5 If ARINC 743 is selected (ID 1) the EGPWS computes HFOM/VFOM from HDOP/VDOP. This is done to improve the

value of HFOM/VFOM that the EGPWS uses for GPS (743 or 743A) that still assume selective availability is on.

3.3.3.7 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

RXRS – 232

GPS Bus

28CM GND

NC

RS232-GPS.vsd

GPS Alt ARINC NS RS-232

Vendor Model Ref. 743/743A EW RX TX GND

GARMIN GNS430 Software Version 2.21

MSL N/A Note P4001-56 Chassis

KLN 900 066-04034-0XXX

MSL N/A OK P9002-13 Chassis

KLN 94 MSL N/A OK P941-6 Chassis

NOTE: The connector pin numbers and software versions 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.

Check manufacturer for compatibility with North-South, East-West Velocities.



3.3.3.8 Dual ARINC 429 BUS (Cat. 3 ID 253 and 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. Non-IOC aircraft can use ID 255 to activate dual GPS inputs for

redundancy and improved system availability, but the interface must have dual, High Speed,

ARINC 743A GPS, and this cannot be used if using Category 10 ID 5 or Category 11 ID 2.

25*

8*

A

B

J2 ARINC 429 GPS

ARINC 429 Bus 1

Lo

EGPWS MK XXII

A

B

ARINC 429GPS Bus

23*

6*

A

B

A

B

ARINC 429GPS Bus

Hi

ARINC 429 Bus 2

Lo

Hi

ARINC429-DualGPS-1.vsd

Cat. 3 GPS Alt ARINC Bus 1 Bus 2

Aircraft Model ID Ref. 743/743A A B A B

253* 743A

255 743A


* For ID 253 the MK XXII connections at connector J2 are J2-37/36 and J2-41/40.



3.3.4 Category 4 – Altitude Callouts

Category 4 defines the Altitude Callout menu choices and Smart ‘500’ Callout selection.

Appendix E Table 5.3.4 defines the Altitude Callout Menu options and identifies the first MK XXII

EGPWS version in which the option was available (see the Effectivity entry).

The Altitude callout menus have selected combinations of “Minimums-Minimums” or "Check Height",

Smart “500”, “200”, “100”, “50”, “40”, “30”, “20”, and “10”. No altitude callouts may also be selected.

Recommended selections are ID 5, 14 or 15.

NOTE: For applications that use Category 16 Torque Type ID 0 (No Torque Input), 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 5 or 15.

NOTE: Auto-rotation selection has moved to Category 17.

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. Since normal helicopter operation may include flight at or below 500 feet, a Smart

“500” callout is not recommended.

“Minimums-Minimums” or "Check Height" callout can be selected or deselected from these

combinations by connecting or not connecting the Decision Height (DH) discrete (J1-33) of Category 8.

The AVAD compliant callout menu selections are available for altitudes of 100 feet thru 160 feet

although only 100 is normally used. AVAD compliant callouts are required for North Sea Offshore

operation and are unique in that they do not latch and so can be retriggered with succeeding transitions

thru the callout altitude.


1. Using Appendix E Table 5.3.4 , select the preferred Altitude Callout Menu Type (ID) that

matches the feature preferences and version (part number) being installed. Using Table 5.3.4

select ID number for your Altitude callouts and record that number on Table 5.3 under Ident No.

for step 4. This number will be used during programming of the configuration module.

2. If the “Minimums-Minimums” or "Check Height" callout will be used, use the electrical interfaces

(pin-outs) for Radio Altitude Input Select Type (Category 8) shown in Appendix E Table 5.3.8-x

to generate the installation wiring diagrams.



3.3.5 Category 5 – Audio Menu Select

Category 5 defines a basic Audio Menu (ID 128 or ID 129) for most Helicopters and a special Audio

Menus (ID 251 or ID 254) for S-76 factory installations and (ID 252, ID 253 and ID 255) designed to

support S-92 Helicopters.


1. Using Appendix E Table 5.3, Under Step/category 5 select Audio Menu. Using Table 5.3.5, select

ID number for your audio menu and record that number on Table 5.3 under Ident No. This number

will be used for programming the configuration module.

2. Audio Menu has no bearing on Aircraft wiring interface.



3.3.6 Category 6 – Terrain Display Select

Category 6 defines the Terrain Display options available.

Appendix E Table 5.3.6 defines the Terrain Display Select options (Display Configuration Group

Tables, Display Input Control Group Tables and Output 429 Bus Group Tables) and identifies the

first MK 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.


1. Using Appendix E Table 5.3.6 and 5.3.6-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 5.3 under the Ident No.

heading for Step (Category) 6.

2. Using the ID number Table 5.3.6 as “x”, go to the Table 5.3.6-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 5.3.6-x are used to generate the installation wiring diagrams.

Determine the wiring interconnects and record it on Appendix A Fig A1-1.

Figure 3.3.6-1 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 5.3.6 for “TAD Disable” indicates that TA&D is ENABLED (the

“Disable” is disabled).



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 3.3.6.3-1 Definition of Display Configuration Group Tables (Appendix E Section 5.3.6)



WX

Sys

tem

R/T

J2-3

7J2

-36

J1-5

8J1

-59

J1-5

1

J1-3

2

A B A BA

RIN

C 4

53 T

ER

RA

IN B

US

#1

AR

INC

429

RA

NG

E B

US

J1-5

4T

erra

in D

ispl

ay S

elec

t #1

Dis

cret

e O

utpu

t

Ter

rain

Pop

-Up

Dis

cret

e O

utpu

t

Dis

play

Sel

ect

Dis

cret

e #1

Inp

utD

SD

#1

Gnd

Gnd

Ran

ge #

1 Gnd

TE

RR

ON

Mo

me

nta

ry

28 V

DC

DIS

PL

AY

RE

LA

Y

429

IN45

3 O

UT

453

#1

J1-5

6J1

-57

A B45

3 #2

J2-4

1J2

-40

A BR

ange

#2

J1-3

1D

SD

#2

Gnd

Wx/

TE

RR

Dis

pla

yS

yste

m

453

WX

/T

ER

R B

US

A B A B TE

RR

AIN

PO

P-U

P

TE

RR

AIN

SE

LEC

TE

D

429

Ran

geO

utpu

t B

us

BR

T/

DIM

/T

ES

T

FIG

UR

E 3

.3.6

-1 S

ingl

e T

ube

Wx/

Ter

rain

Dis

play

* D

isp

lay

re

lay

sp

ec

ific

ati

on

s:

- 4

PD

T

-

Co

ntin

uo

us

Du

ty C

ycle

- P

icku

p V

olta

ge

: 13

.5 V

dc

Ma

x.

-

Dro

po

ut V

olta

ge

: 7.5

- 2

.0 V

dc

- C

oil

Re

sist

an

ce: n

om

ina

l 50

0 O

hm

s (~

10

0m

A @

28

Vd

c)-

Co

il R

atin

g: 2

6.0

Vd

c (n

om

ina

l) 3

4 V

dc

(ma

x.)

- C

on

tact

V d

rop

: < 1

25

mV

@ r

ate

d lo

ad

- C

on

tact

cu

rre

nt r

atin

g: 2

Am

ps

resi

stiv

e @

28

Vd

c



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 Sample Display Schematics

Honeywell GNS-XLS

Honeywell KMD 540 / 550 / 850

Honeywell Grimes TRA-45A

Honeywell Grimes MFRD

Universal MFD-640

Honeywell Primus UDI with Avtech DSU

Collins IND-300 UDI with Avtech DSU

Honeywell Bendix PPI-4B

Garmin MX-20

Collins Pro-Line II

Honeywell Bendix EFS-40/50

Collins WXI-701/711

Honeywell Primus 440/660/880 Integrated

Honeywell Bendix RDR 2000 / IN182A

Collins Pro-Line IV

Honeywell Bendix EFS-10

Honeywell SPZ 7600 / SG-705

Honeywell SPZ 8000 / SG-811



HONEYWELLMK XXII

H-EGPWS965-1595-0XX

P1

ARINC 453 OUTPUT (A)

ARINC 453 OUTPUT (B)

58

59

P

P P

P

12

13

J3001

Ben

dix

KM

D-5

40

N

OTE

5

29

30

(A)

(B)

(A)

(B) ARINC 429 TX

KCPB BUS

(A)

(B)

37

36

Hon

eyw

ell T

RA

-45A

01

03

J1

28

13

Hon

eyw

ell G

NS

-XLS

NO

TE 7

Q4

Q6

J101

N5

N6

31

11

Shield (*= Chassis)

Shield (*= Chassis)

02 Un-terminatedQ5

P P

(A)

(B) ARINC 429 RX

Shield

(A)

(B)

43

42ARINC 429 OUTPUT

RANGE INPUT

Hon

eyw

ell M

FRD

38

09

J2

33

34

39

MK XXIICATEGORY 6ID 0, 18-20, 230, 242 (KCPB) All Aircraft

NOTES:1. All stranded wire shall conform to MIL-W-22759/16 or equivalent. All shielded wire shall conform to MIL-C-27500 spec. or equivalent. All wires are 22 gauge unless otherwise noted.2. Connect the shield to aircraft chassis or unit pin with as short a conductor as practical.3. Use M17/00002 wire per MIL-C-17/176D spec. or equivalent for KCPB interface.4. Refer to the appropriate Installation Manual for configuration setup instructions.5. The KMD 540 must have the KAC 502 EGPWS card installed for the Terrain Display function.6. The Avidyne FlightMax is not compatible with MK XXII computers.7. GNS-XLs Enhanced PN 17960-0203-XXXX SM04 or later.8. The Universal MFD 640 has configurable inputs & outputs. See Universal Installation Manual for details.

NOTE 3

J3

P2

* * *

* * *

Uni

vers

al M

FD-6

40

See

Not

e 8

See

Not

e 8

See

Not

e 8

P

(A)

(B)

41

40RANGE INPUT



HONEYWELLMK XXII

H-EGPWS965-1595-0XX

P1



58

59

TERR

ON

MomentaryAction

0704

10

08

0501

1112

06

0302

AnnunciatorPress To Test

P

P P

P

47

48

J1 J2

BRT/DIM ANN. POWER

8

9

2

(H)

(C)

(A)

(B)

Terrain Select

ARINC 453

ARINC 429RANGE INPUT (A)

RANGE INPUT (B)

37

36

AVTECH DSU 6001-1-1

32 Terrain Status

J1 1312111037363534 243231302928272625236

P P P P

P P P P

90, 100, 200, 300, 300SL, 400, 500, AVQ30

450, 650 w/o Lightening, 800

440, 650 w/ Lightening, 660, 700, 870, 880

2 19 13 6 18 9 3 16 12 1 10 4 8 15 17 11 5 NC 7

N J E S U T D H R F M K L A C P B V G

2 19 13 6 18 9 3 16 12 1 10 4 8 15 17 11 5 14 7

HONEYWELL PRIMUS SERIES WXR INDICATOR (UDI PORT)U

DI

GN

D

RA

NG

E3

-IN

RA

NG

E2

-IN

RA

NG

E1

-IN

RA

NG

E0

-IN

SH

R -

SH

R+

SV

R -

SV

R+

SE

L -

SE

L+

BLU

E -

BLU

E+

GR

N+

GR

N -

RE

D -

RE

D+

UD

I S

HL

D

ST

BY

MK XXIICATEGORY 6ID 0, 18, 230, 242(KCPB) Primus radar

NOTES:1. All stranded wire shall conform to MIL-W-22759/16 or equivalent. All shielded wire shall conform to MIL-C-27500 spec. or equivalent. All wires are 22 gauge unless otherwise noted.2. Connect the shield to aircraft chassis or unit pin with as short a conductor as practical.3. Use M17/00002 wire per MIL-C-17/176D spec. or equivalent for KCPB interface.4. Refer to the appropriate Installation Manual for configuration setup instructions.

NOTE 3

P2

P

RANGE INPUT (A)

RANGE INPUT (B)

41

40



HONEYWELLMK XXII

H-EGPWS965-1595-0XX

P1



58

59

TERR

ON

MomentaryAction

0704

10

08

0501

1112

06

0302

P

P P

P

47

48

J1 J2

BRT/DIMANN. POWER

8

9

2

(H)

(C)

(A)

(B)

Terrain Select

ARINC 453

ARINC 429RANGE INPUT (A)

RANGE INPUT (B)

37

36

AVTECH DSU 6001-1-2

32 Terrain Status

J1 1312111037363534 24

4847

302928272625236

P P P P

P

14 13 9 10 7 6 21 20 25 27 26 33 32 1 2 3 NC 4

39

COLLINS IND-220, IND-270, IND-270A, IND-300

UD

I GN

D

RA

NG

E3

-IN

RA

NG

E2

-IN

RA

NG

E1

-IN

RA

NG

E0

-IN

SH

R -

SH

R+

SV

R -

SV

R+

TG

T E

NA

BLE

ALP

HA

_B

LN

K

BLU

E -

BLU

E+

GR

N+

GR

N -

RE

D -

RE

D +

SH

LD

SS

BY

31

46

16

RA

DA

R B

LK

10S

HLD

2J2 5150

28 30 29

2.58

MH

z L

2.58

MH

z H

50-Pin DSUB

37-Pin DSUB

P PPP

MK XXIICATEGORY 6ID 0, 18, 230, 242 (KCPB) Collins Radar

NOTES:1. All stranded wire shall conform to MIL-W-22759/16 or equivalent. All shielded wire shall conform to MIL-C-27500 spec. or equivalent. All wires are 22 gauge unless otherwise noted.2. Connect the shield to aircraft chassis or unit pin with as short a conductor as practical.3. Use M17/00002 wire per MIL-C-17/176D spec. or equivalent for KCPB interface.4. Refer to the appropriate Installation Manual for configuration setup instructions.5. GPS Ground Speed required before Collins radar display will show EGPWS terrain picture.

NOTE 3

P

RANGE INPUT (A)

RANGE INPUT (B)

41

40



Co

llin

s P

roL

ine

IIw

ith W

XP

-84

0/8

50

Cat

. 6

-ID

's 3

,5,&

6

J2

15

16

18

19

36

37

58

59

Lam

p Te

st

28V

Lam

p D

imm

ing

Bus

EG

PW

S

Co

llin

s W

x P

nl

WX

P-8

40

/850

A BA

RIN

C 4

29 R

ange

#1

A BA

RIN

C 4

53

Vid

eo #

1

MK

XX

II 9

65-1

590

-003

or

late

r.M

K X

XII

965

-159

5-0

20 o

r la

ter.

A BA B

AR

INC

42

9 R

ang

e

AR

INC

45

3 P

ictu

re

Not

e:

Fo

r in

terf

ace

an

d o

pera

tion

of

the

Co

llin

s P

rolin

e II

disp

lays

se

e C

olli

ns

SIL

2-9

9

Col

linsP

2.v

sd

TE

RR

ON

mo

me

nta

ry

31

Ter

rain

Dis

pla

y S

ele

ct (

in)

Ter

rain

Dis

pla

y S

ele

ct (

out

)

28V

EG

PW

S

PW

R B

us

11

Rem

ote

ON

J1

40

41

56

57

A BA

RIN

C 4

29 R

ange

#2

A BA

RIN

C 4

53

Vid

eo #

2

J1

18

19

Co

llin

s W

x P

nl

WX

P-8

40

/850

A BA

RIN

C 4

53

Pic

ture

28V

EG

PW

S

PW

R B

us

11

Rem

ote

ON

15

16

A BA

RIN

C 4

29

Ran

ge

54

49

Ter

rain

Dis

pla

y S

ele

ct (

out

)

TE

RR

ON

mo

me

nta

ry

32

Ter

rain

Dis

pla

y S

ele

ct (

in)

To

WX

R/T T

o W

X

R/T



AR

T 20

00/2

100

RTA

-4A

/B

RS

-181

A/8

11A

RS

-841

A/8

61A



96

5-1

17

6-0

03

MA

RK

VI

EG

PW

S

96

5- 1

20

6-0

03

MA

RK

VII

I E

GP

WS

4.

3.

1.NO

TE

S:

2.

WE

AT

HE

R R

AD

AR

S.

IS T

HE

PR

EF

ER

RE

D C

ON

FIG

UR

AT

I ON

.

IS T

HE

RE

QU

IRE

D C

ON

FIG

UR

AT

ION

.

CO

MP

UT

ER

PA

RT

NU

MB

ER

S:

TH

E C

AT

EG

OR

Y 1

3 I

/O D

ISC

RE

TE

TY

PE

ID 1

(L

AM

P F

OR

MA

T 2

)

TH

E C

AT

EG

OR

Y 6

DIS

PL

AY

TY

PE

ID

10

(I N

TE

GR

AT

ED

EF

IS 4

0/5

0)

TH

IS C

ON

FIG

UR

AT

ION

IS

NO

T S

UP

PO

RT

ED

PR

IOR

TO

EG

PW

S

(3.1

3)

FO

R T

HE

CO

MP

LE

TE

IN

TE

RF

AC

E T

O T

HE

BE

ND

IX/K

ING

RE

FE

R T

O T

HE

WE

AT

HE

R R

AD

AR

SE

CT

ION

OF

TH

IS M

AN

UA

L

QU

AD

RA

X C

AB

LE

FO

R T

HE

45

3 D

AT

A B

US

AN

D T

HE

KC

PB

.

US

E M

17

/17

6-0

00

2 S

HIE

LD

ED

WIR

E O

R 0

24

-00

06

4-0

00

0

96

5-1

18

6-0

03

MA

RK

VI

EG

PW

S W

/IN

TE

RN

AL

GP

S

96

5-1

21

6-0

03

MA

RK

VII

I E

GP

WS

W/I

NT

ER

NA

L G

PS

BU

S

(MO

ME

NT

AR

Y)

AN

NU

NC

IAT

OR

ON

TE

RR

AIN

EG

PW

S F

AIL

BU

S

AN

NU

NC

IAT

OR

AN

NU

NC

IAT

OR

DIM

ME

R

PR

ES

S-T

O-T

ES

T

(AL

TE

RN

AT

E A

CT

ION

)

TE

RR

AIN

IN

HIB

IT

32

12

TE

RR

AIN

IN

HIB

IT S

WIT

CH

IN

TE

RR

AIN

SE

LE

CT

SW

ITC

H I

N

55

TE

RR

AIN

IN

OP

PR

ES

S-T

O-T

ES

TA

NN

UN

CIA

TO

R D

IMM

ER

TE

RR

AIN

SE

LE

CT

ED

DIS

CR

ET

E I

N

TE

RR

AIN

PO

P-U

P D

ISC

RE

TE

IN

1A

P4

65

22

37

P4

65

1B

45

3 D

AT

A B

US

A I

N4

53

DA

TA

BU

S B

IN

R/T

TR

AN

SM

ITT

ER

42

9 B

OU

T

R/T

TR

AN

SM

ITT

ER

42

9 A

OU

T

MF

D S

YM

BO

L G

EN

ER

AT

OR

BE

ND

IX/K

ING

SG

46

5

SE

E N

OT

E 1

.

2B 49

22

P4

65

81

68

SE

E N

OT

E 1

.

SE

E N

OT

E 1

.

EG

PW

S

SE

E N

OT

E 1

.

+2

8V

DC

AV

ION

ICS

PO

WE

R

SE

E N

OT

E 1

.

SE

E N

OT

E 1

.

60

40

+2

8V

DC

PO

WE

R I

N+

28

VD

C P

OW

ER

IN

59 51

TE

RR

AIN

PO

P-U

P O

UT

KC

PB

B O

UT

SE

E N

OT

E 3

.

J140

37

36

J2

45

3 D

AT

A B

US

B O

UT

41

NO

. 2

DIS

PL

AY

RA

NG

E 4

29

B I

NN

O.

1 D

ISP

LA

Y R

AN

GE

42

9 B

IN

NO

. 1

DIS

PL

AY

RA

NG

E 4

29

A I

NN

O.

2 D

ISP

LA

Y R

AN

GE

42

9 A

IN

PR

OX

IMIT

Y W

AR

NIN

G C

OM

PU

TE

RM

AR

K V

I/V

III

EN

HA

NC

ED

GR

OU

ND

58

KC

PB

A O

UT

42

9 C

ON

TR

OL

BU

S 1

B I

N4

29

CO

NT

RO

L B

US

1A

IN

SE

E N

OT

E 2

.

WE

AT

HE

R R

AD

AR

R/T

BE

ND

IX/K

ING

45

3 D

AT

A B

US

A O

UT

TE

RR

AIN

SE

LE

CT

RE

LA

Y O

UT

54



HONEYWELLMK XXII

H-EGPWS965-1595-0XX

P1

TERRAIN SELECT (IN) 32

WX RTSYSTEM



58

59

RADARIND

RDR TERR

MomentaryAction

NC

NO

RELAY

D3

D1

C3

C1

B3

B1

A3

A1

D2

C2

B2

A2

X1

X2

0704

10

08

0501

1112

06

0302


P

P P

P

5

6

J1

WX

I-701

BRT/DIM ANN. POWER

10

11

15

(H)

(L)

(A)

(B)

RT On/Off 1

T/R Data Bus

Control Bus A

TERRAIN RELAY (OUT) 54

RANGE INPUT (A)

RANGE INPUT (B)

37

36

P

P

+28 VDCRELAY POWER

SEE NOTE 3,5

(P)

(N)

(A)

(B)

T/R Data Bus

Control Bus A

70-Ohm termination12

8

9

59J1

WR

T-X

XX

?

?

Collins WXI-701 RADAR INDCPN 2041222-XXXX

MK XXIICATEGORY 6ID 12Collins WXI-701

NOTES:1. All stranded wire shall conform to MIL-W-22759/16 or equivalent. All shielded wire shall conform to MIL-C-27500 spec. or equivalent. All wires are 22 gauge unless otherwise noted.2. Connect the shield to aircraft chassis or unit pin with as short a conductor as practical.3. Use M17/00002 wire per MIL-C-17/176D spec. or equivalent for ARINC 453 interface.4. Refer to the appropriate Installation Manual for configuration setup instructions.5. Some installations may require a 75-ohm resistor for termination of the ARINC 453 video bus.

RANGE INPUT (A)

RANGE INPUT (B)

41

40

P2

6B RT On/Off 1

P



HONEYWELLMK XXII

H-EGPWS965-1595-0XX

P1


WX RTSYSTEM



58

59

RADARIND

RDR TERR

MomentaryAction

NC

NO

RELAY

D3

D1

C3

C1

B3

B1

A3

A1

D2

C2

B2

A2

X1

X2

0704

10

08

0501

1112

06

0302


P

P P

P

M

L

63J1

WI-8

80/6

60/6

50/4

40

BRT/DIM ANN. POWER

F

G

X

(P)

(N)

(P)

(N)

EGPWS SELECT

WXPD BUS

SCI BUS


RANGE INPUT (A)

RANGE INPUT (B)

37

36

P

P

+28 VDCRELAY POWER

SEE NOTE 3,5

(P)

(N)

(P)

(N)

CENTER WXPD BUS

LEFT SCI BUS

ShieldW

3

4

59J1

WU

-880

/660

/440

71

72

T Shield

HONEYWELL PRIMUS RADAR INDHPN 7007700-X1X

MK XXIICATEGORY 6ID 13 and 15WI-440/660/880

NOTES:1. All stranded wire shall conform to MIL-W-22759/16 or equivalent. All shielded wire shall conform to MIL-C-27500 spec. or equivalent. All wires are 22 gauge unless otherwise noted.2. Connect the shield to aircraft chassis or unit pin with as short a conductor as practical.3. Use M17/00002 wire per MIL-C-17/176D spec. or equivalent for ARINC 453 interface.4. Refer to the appropriate Installation Manual for configuration setup instructions.5. Some installations may require a 75-ohm resistor for termination of the ARINC 453 video bus.6. Radar Indicators must be modified from part number 7007700-x0x to -x1x for EGPWS Terrain display.7. Not Compatible with Category 2 RS-422 Air Data interface.

RANGE INPUT (A)

RANGE INPUT (B)

41

40

P2



HONEYWELLMK XXIIEGPWS

965-1595-0XXJ2



58

59

P P

RANGE INPUT (A)

RANGE INPUT (B)

37

36

PP

P1

3*

4*

#1 - IOC (ICC-4000)

non-Integrated PROLINE 4 INTERFACEMK XXII EGPWS Category 6, ID 235

P1

8D

10D

#1 - MFD

H - ARINC 453

L - (70 ohm terminated)

4

29

#1 - WXR

H

L

P

P1

P P

RANGE INPUT (A)

RANGE INPUT (B)

41

40

P1

3*

4*

#2 - IOC (ICC-4000)



56

57

PP

P1

8D

10D

#2 - MFD

H - ARINC 453

J1

LA-GP-5 bus (Label 155)

RA-GP-5 bus (Label 155)

* ICC-851A pins 13 & 14

* ICC-851A pins 13 & 14

11D L - (unterminated)

11D L - (unterminated)

L - (70 ohm terminated)

TERR RLY SELECT #1 54

TERR

+28 VDC

MOM TERR SELECT #1 32

TERR

+28 VDC

TERR RLY SELECT #2 49

MOM TERR SELECT #2 31

ARINC 453 OUT

+28 VDC

+28 VDC

70Ω*

* In the OEM installations a single weather radar 453 bus enters the left MFD, passes through, and is terminated (70 ohm) at the right MFD. For EGPWS installations break the 453 radar bus between the MFDs, install switching relays, and wire one relay to each MFD. The right MFD connection is moved to remove the 70 ohm termination at that MFD. To allow proper radar termination when EGPWS is passing through the relays, the radar picture bus has a 70 ohm resistor (added externally).



HONEYWELLMK XXII

H-EGPWS965-1595-0XX

P1


WX RT SYSTEM

(A)

(B)

58

59

RADARIND

RDR TERR

MomentaryAction

NC

NO

RELAY

D3

D1

C3

C1

B3

B1

A3

A1

D2

C2

B2

A2

X1

X2

0704

10

08

0501

1112

06

0302


P

P P

P

P1A-48

P1A-49

SG

-101

A

SG

-101

B

BRT/DIM ANN. POWER

P1B-52

P1B-04

(H)

(C)

(A)

(B)

ARINC 453

ARINC 429


(A)

(B)

37

36

P

P

+28 VDCRELAY POWER

42

43

P5001

AR

T 20

00/2

100

RTA

-4A

/B

2

3

(H)

(C)

(A)

(B)

ARINC 453

ARINC 429

BP

2D

3D

3B

4B

8

9

P1001

RS

-181

A/8

11A

RS

-841

A/8

61A

19

20

P1001

X

A

ZA

G

EFIS 10B/K SG 101A/B SYM GEN

P5003-22

P5003-23

P7004-17

P7004-40

MK XXIICATEGORY 6ID 246EFIS 10

NOTES:1. All stranded wire shall conform to MIL-W-22759/16 or equivalent. All shielded wire shall conform to MIL-C-27500 spec. or equivalent. All wires are 22 gauge unless otherwise noted.2. Connect the shield to aircraft chassis or unit pin with as short a conductor as practical.3. Use M17/00002 wire per MIL-C-17/176D spec. or equivalent for ARINC 453 interface.4. Refer to the appropriate Installation Manual for configuration setup instructions.5. Some installations may require a 75-ohm resistor for termination of the ARINC 453 video bus.6. NO TRAFFIC AVAILABLE WITH EFIS 10.

NOTE 3, 5PICTURE OUTPUT

RANGE INPUT

P

(A)

(B)

41

40RANGE INPUT

P2



34

23

35 1

H L

J1L

EF

T D

ISP

LAY

C

ON

TR

OL

LER

Co

ntro

ller

Se

rial D

ata

'WX

/ T

ER

R' p

ush

bu

tton

GN

D

DC

-811

34 2335 1

H L

J1R

IGH

T D

ISP

LAY

C

ON

TR

OLL

ER

Con

trol

ler

Ser

ial D

ata

GN

D

DC

-811

89

90

Co

ntro

ller

Se

rial D

ata

J1A

LEF

T S

YM

BO

L G

EN

ER

AT

OR

SG

-811

H L89 90

H L

J1A

RIG

HT

SY

MB

OL

GE

NE

RA

TO

R

Con

trol

ler

Ser

ial D

ata

SG

-811

1 2J1B

H L

9

WX

/TE

RR

PIC

TU

RE

BU

S IN

DO

UT

#0

4 5

H L

22

23

H L

1 2J1B 9

H L

4 5

H L

22 23

H L

R-E

FIS

+28

VD

CL-

EF

IS+

28 V

DC

J2

H L

58

59

H L

43 42

H L

H LH L

H L

EG

PW

S A

RIN

C 4

29*

CH

AN

. 7

Ra

dar

Se

rial D

ata

98

PG

M P

IN G

ND

42

PR

OG

PIN

110

EG

PW

S IN

ST

ALL

ED

J2A

3 5+

28V

GN

D

L-E

FIS

+28

VD

C

98 J2A 42 3 5

R-E

FIS

+28

VD

C

Rad

ar S

eria

l Dat

a

PG

M P

IN G

ND

PR

OG

PIN

110

EG

PW

S IN

ST

ALL

ED

+28

VG

ND

H L

56

57

H L

WX

/TE

RR

PIC

TU

RE

BU

S IN

DO

UT

#0

PN

700

4544

-314

PN

700

4544

-314

51J1J1

J2

H L

36 37

J_

J_R

adar

Con

trol

ler

Rad

ar R

/T

MK

XX

II E

GP

WS

DIS

PLA

Y

BU

S #

1D

ISP

LAY

B

US

#2

TE

RR

AIN

P

OP

UP

AR

INC

429

O

UT

PU

T B

US

SE

RIA

L B

US

R

AN

GE

INP

UT

*P

RO

G P

IN 1

112

1

* E

FIS

AR

INC

42

9 IN

PU

T F

RO

M

EG

PW

S C

AN

BE

PR

OG

RA

MM

ED

F

OR

CH

1 (

J2A

-64

/65)

OR

CH

7

(J1

B-4

/5).

E

GP

WS

AR

INC

429

CH

AN

. 7

*

PR

OG

PIN

111

*21

*O

PE

N =

CH

7

G

ND

= C

H 1

* E

FIS

AR

INC

429

IN

PU

T F

RO

M

EG

PW

S C

AN

BE

PR

OG

RA

MM

ED

F

OR

CH

1 (

J2A

-64/

65

) O

R C

H 7

(J

1B

-4/5

).

*O

PE

N =

CH

7

G

ND

= C

H 1

TE

RR

AIN

PO

P U

P31

TE

RR

AIN

PO

P U

P3

1

i jL M

Left

Pic

ture

B

usR

ight

Pic

ture

B

us

gP

ictu

re B

us S

hiel

d

A TLe

ft E

FIS

C

ontr

ol B

usV B

Rig

ht E

FIS

C

ontr

ol B

us

* **

WI-

870

Ind

icat

or

pin

s J1

-F/G

(

HP

N 7

007

70

0-X

XX

)*

WC

-87

0 C

ontr

olle

r p

ins

J4-A

/B

(H

PN

70

084

71

-XX

X )

* W

C-8

74

Con

trol

ler

pin

s J4

-A/B

(

HP

N 7

006

92

1-X

XX

)

WR

-80

0(H

PN

MI-

585

35

0)

(HP

N 9

65-1

59

5-0

XX

)

NO

TE

: S

erv

ice

Bu

lletin

70

04

544

-34

-48

m

od

ifie

s 7

004

544

-31

2 t

o -3

14

an

d a

dds

EG

PW

S in

terf

ace

.

NO

TE

: S

erv

ice

Bu

lletin

70

045

44

-34-

48

mod

ifies

70

045

44

-31

2 to

-3

14

a

nd

ad

ds

EG

PW

S in

terf

ace

.

'WX

/ T

ER

R' p

ush

but

ton

h

HO

NE

YW

ELL

SP

Z 8

000

Cat

. 6 -

ID 2

55



3.3.7 Category 7 – Options Select Group #1

Category 7 enables/disables the following Options: Steep Approach (not available in MK XXII), TA&D

Alternate Pop Up, Peaks Mode, Obstacle Awareness, Bank Angle, WOW Reversal, and GPS Altitude

Reference.

Appendix E Table E 5.3.7 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 and for Helicopters Steep Approach and

TA&D Alternate Pop Up should always be set to False.


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 Table 5.3.7, 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 5.3 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 TA&D Alternate Pop Up. For Helicopters TA&D Alternate Pop Up should

always be set to False.

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.

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 at least 100 feet taller

than the surrounding terrain and continuously computes obstacle clearance envelopes ahead of the aircraft,

issuing alerts if the boundaries of these envelopes conflict with obstacle elevation data in the obstacle

database (similar to the Terrain Awareness function). Obstacle data is currently available for North America

and parts of Europe and 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 Awareness for helicopters.

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 each installation.

3.3.7.7 WOW Reversal (Weight-On-Wheels)

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 (J1-37) active position:

WOW Reversal

WOW Discrete (Category 13) False True

WOW Discrete = +28V WOW Not WOW

WOW Discrete = Open (or GND) Not WOW WOW

Ground seeking WOW discrete (J1-18) active position:

WOW Reversal

WOW Discrete (Category 13) False True

WOW Discrete = GND WOW Not WOW

WOW Discrete = Open (or +28V) Not WOW WOW

3.3.7.8 GPS Altitude Reference

The GPS Altitude (ARINC 429 label 076, Category 3) may be referenced to mean sea level (MSL) or WGS-

84. Determine which reference the GPS position uses and set the GPS Altitude Reference accordingly in this

Category. If using the internal GPS card select MSL.



3.3.8 Category 8 – Radio Altitude Input Select

Category 8 defines the Radio Altitude and Decision Height interface.


1. Using Appendix E Tables 5.3, under Step/category 8 select Radio Altitude Type. Using Table 5.3.8 and

5.3.8-x select ID number for your Radio Altimeter and record that number on Table 5.3 under Ident No.

for step 8. This number will be used during programming of the configuration module.

2. Appendix E Tables 5.3.8-x, where x is the Radio Altimeter Type number, define the electrical interfaces

required to support each Radio Altimeter. Using Table 5.3.8-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 5.3.8-x determine the wiring interconnects for

Decision Height and record it on Appendix A Fig A1-1.

3.3.8.2 Digital Radio Altitude Interface (Cat. 8 ID 2)

21

4

J2Radio 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



3.3.8.3 Analog Radio Altitude Interface (Cat. 8 ID 0,1,3,4,5)

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 Cat. Indicator R/T

R/T Indicator ID DH + - Valid

Collins ALT 55 (3) ALI-55 1 P1-V P1-57 P1-59 P1-49

Collins ALT 50 5 P1-57 P1-59 P1-49

Honeywell HG7502 JG1072( ) 0 P1-e P4-47 P4-46 P4-27

Honeywell RT-221/300(1) RA-315 0 P1-F P1-X P1-N P1-Y

Honeywell RT-220/300(2) RA-215 3 P1-F P1-N P1-W P1-Y

Honeywell KRA-405 KNI-415/416 4 M P1-B P1-g S

Honeywell KRA 405B KNI-415/416 4 M E X j

KRA 405B (2)

066-01153-0101 3 G Z j

KRA 405B 066-01153-0202

0 Z G j

Honeywell ALA-51A INA-51( ) 0 P2-e P1B-47 P1B-46 P1B-12

Collins 860F-1/4 339H-1/-2 0 P1-e P1B-47 P1B-46 P1B-12

TRT AHV-530 0 P1B-47 P1B-46 P1B-12

Honeywell APN-209

RT-1115/ID-1917

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-221’s are also compatible, consult your Honeywell representative.

NOTE 2: This is the precision output from the R/T. Note the + and – signals are swapped to convert the –4mV to +4mV. RT-300 (-9X1, -9X3,-904, -9X5) should also use the Precision Output, same as the RT-220.

NOTE 3: The ALT-55 provides compromised EGPWS performance due to the average altitude tracking algorithm employed.

3.3.8.4 Digital – ARINC 429 Dual IOC Buses (Cat. 8 ID 251 - 255)

Radio Altitude Type 251 (IOC bus or equivalent) is a dual high speed, digital ARINC 429 signal having labels

164 and 170. Radio Altitude Type 253 (IOC bus or equivalent) is a dual high speed, digital ARINC 429

signal having label 164 and a analog discrete DH input. Radio Altitude Type 254 (IOC bus or equivalent) is a

dual high speed, digital ARINC 429 signal having labels 164, 170 and 370. Radio Altitude Types 252 & 255

(IOC bus or equivalent) are a dual high speed, digital ARINC 429 signal having labels 164 and 370. For

interface description see paragraph 3.3.2.6 Air Data Type.



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 5.3.9 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).


1. Using Appendix E Tables 5.3, 5.3.9 and 5.3.9-x as described above, select the Navigation Input Select

Type that matches the aircraft configuration, feature preferences, and version (part number) being

installed.

2. Record the ID number for the Navigation Inputs Select Type from Appendix E Table 5.3 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 5.3.9 as “x”, go to Appendix E Table

5.3.9-x. .The electrical interfaces (pin-outs) for the Navigation Inputs Select Type are shown in Appendix

E Table 5.3.9-x and are used to 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 analog and digital formats.

Glideslope Validity

Glideslope Validity (+28V Super Flag) is required for Navigation Inputs Select 0 or 5 at pin J1-11. Glideslope

Validity (Low Level) is required for Navigation Inputs Select 1 at pins J1-30 (+) and J1-10 (-). Digital ARINC

429 Glideslope interfaces (Navigation Inputs 2 & 3) do not require Glideslope Validity input.

Localizer Validity

Localizer Validity (+28V Super Flag) is required for Navigation Inputs Select 5 at pin J1-48.

Digital ARINC 429 Localizer interfaces do not require Localizer 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.



3.3.9.2 Analog Glideslope Interface (Cat. 9 ID 0,1,5)

J1 ILS ReceiverEGPWS MK XXII

GS Valid +28 11

+

-

Low LevelGS Valid

+28

GNDILS Tuned

+

-GS Deviation

65

46

30

10

39

20

Super Flag +28V

+-

Delayed ILS ModeILS Energize

GS Flag(Low Level)

+Up

+DnGS Deviation

Analog-ILS-2.vsd

LOC Valid +28 48 LOC Val +28V

+

-LOC Deviation

30

10

+R

+LLOC Deviation

GS Inhibit (BC) +28 38 Backcourse

GS Inhibit (BC) GND 19 Backcourse

GS Valid LOC Valid ILS Tuned Deviation

Vendor Model Cat. 9

ID SuperFlag

+28V Low Level

Flag SuperFlag

+28V GND GS +up

+dn LOC +R

+L Honeywell KNR 6030 5 J1003-27

J1003-21 J1003-22 J1002-50 J1002-18

J1003-8 J1003-9

J1002-39 J1002-40

Honeywell KNR 660 1

P1-e P1-q

P1-k

P1-T P1-V

Honeywell KNR 634 1 5 P6342-50

P6342-34 P6342-18 P6342-49 P6341-17

P6342-36 P6342-35

P6342-23 P6342-7

Honeywell KGM-691 0 P692-W

P692-S P692-T

P692-a

P692-B P692-C

Honeywell KNR 600A 1

P601-e P601-q P601-A P601-k

P601-r P601-s

P601-m P601-n

Collins 51RV-1, 51RV-4( ) 5 TP-27 2

TP-21 TP-22 BP-50 BP-18

TP-8 TP-9

BP-39 BP-40

Collins VIR-30, -31, -32 5 P1-17

P1-9 P1-13 P2-18 P2-40

P1-5 P1-1

P2-10 P2-13

Honeywell VNS 41A 5 P1001-60

P1001-101 J1001-56

J1001-90 J1001-23

J1001-38 J1001-92

Honeywell RNA-34A 5 TP-27 TP-21 BP-50 BP-18

TP-8 TP-9

BP-39 BP-40

Honeywell KN 53 1

P2-13 P2-R

P2-12

P2-P P2-14

Honeywell KN 72

P1-2 P1-10

Honeywell RNZ 850 5 P1-A74

P1-B60 P1-B106 P1-B91 P1-B64

P1-B79 P1-B75

P1-B78 P1-B75

Honeywell KX-155/165 1

P901-U P901-R P401-14 P401-8

P901-S P901-T

P901-s (KX-165) P901-k (only

NOTE: The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. ePlease contact the manufacturer’s customer service to confirm your installation.

1 066-1078-00, -01, -04, -05, -10, -11, -14 and –15 only.

2 51RV-4( ) only.



3.3.9.3 Digital Glideslope/Localizer Interface (Cat. 9 ID 2,3,4)

22

5

J2ILS Bus

A

B

EGPWS MK VI / MK VIII

A

BARINC 429 ILS ARINC 429

Low Speed

Vendor Model Cat 9 ARINC 429 Bus 1 ARINC 429 Bus 2 ID A B A B

Chelton VNS 411A 2,3 P1-C P1-D

Chelton VNS 411B 2,3 P1001-62 P1001-103

Honeywell RNA-34A 2,3 P1024-24 P1024-28 P1024-21 P1024-25

Honeywell KNR 634A 4 P6342-41 P6342-42 P6342-44 P6342-45

Honeywell KN 40A(B) 4 P401(403)-41 P401(403)-42 P401(403)-44 P401(403)-45

Collins VIR-432 2,3 P1-35 P1-36 P1-22 P1-23

Garmin GNS-430 2,3 P4006-24 P4006-23


3.3.9.4 Digital – ARINC 429 ILS bus (Cat. 9 ID 6)

Navigation Input Select Type 6 (ILS bus or equivalent) is a single low speed, digital ARINC 429 bus including

Vertical Deviation (117), Lateral Deviation (116) and Mode 5 Control (163) labels for Precision Approach

landings.

See Primus APEX for interface description.

3.3.9.5 Digital – ARINC 429 Dual IOC buses (Cat. 9 ID 248 - 255)

Navigation Input Select Type 249 - 255 (IOC bus or equivalent) are dual high speed, digital ARINC 429

signal having labels 173, and 174 along with combinations of Selected Course and PFD Mode Select Word.

Navigation Input Select Type 249 & 252 are designed to use ARINC 429 receive channels 2 & 5.

Navigation Input Select Type 248 (IOC bus or equivalent) is a dual high speed, digital ARINC 429 bus

including Vertical Deviation (117), Lateral Deviation (116) and Mode 5 Control (163) labels for Precision

Approach landings.

For interface description see paragraph 3.3.2.6 Air Data Type.



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 5.3.10 defines the Attitude Input Select type and identifies the first MK XXII EGPWS

version in which the option was available (see the Effectivity entry).


1. Using Appendix E Tables 5.3 and 5.3.10 ,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 5.3.10 under the Ident No.

heading for Step (Category) 10 on Table 5.3. This number will be used for programming the

configuration module

3. Using the Attitude Input Select ID number from Appendix E Table 5.3.10 as “x”, go to Appendix E Table

5.3.10-x. The electrical interfaces (pin-outs) for the Attitude Input Select Type are used to determine the

wiring interconnects and record it on Appendix A Fig A1-3.



3.3.10.3 Analog Roll Angle (Synchro) (Cat. 10 ID 0,2,4,7)

576

1

212

J1 Vertical Gyro

X

Y

EGPWS MK XXII

Roll Angle

Z

X

YRoll SynchroZ

X

YPitch SynchroZ

X

YZ

Pitch Angle

Vendor Model Attitude Pitch Synchro (Note 1) Roll Synchro (Note 1)

V/G Valid +28 X Y Z X Y Z

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 HG1075/95 J1B-G3 J1B-C9 J1B-C10 J1B-C11 J1B-D9 J1B-D10 J1B-D11

Honeywell AH-600 J1B-11 J1B-52 J1B-53 J1B-54 J1B-49 J1B-50 J1B-51

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.



3.3.10.4 Digital ARINC 429 High Speed (Cat. 10 ID 6 and 128)

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 429HS

Roll PitchAngle

Vendor Model Cat 10 ARINC 429 Bus 1 ARINC 429 Bus 2 ID A B A B

Collins AHC-85(D/E only) 6* P1-16 P1-14 P1-24 P1-22

Litef LTR-81 AHRS 6* MP-G7 MP-G8 MP-E5 MP-E6

Litef LCR-92/LCR-93 AHRS 6* J4-08 J4-29 J4-49 J4-07

Honeywell HG1075/1095 IRU 6* J1B-G7 J1B-G8 J1B-E5 J1B-E6


* ID 6 is preferred with Category 2 Air Data with ARINC 429 Barometric Altitude Rate (label 212), otherwise ID 5. ID 6 cannot be used with analog Air Data interfaces.

3.3.10.5 Digital – ARINC 429 Dual IOC buses (Cat. 10 ID 253, 254)

Attitude Input Select Type 253 and 254 (IOC bus or equivalent) are dual high speed, digital ARINC 429

signal having labels 324, 325, 326 and 327. Attitude Input Select Type 253 also includes Inertial Vertical

Speed (365) and Inertial Altitude (361). For interface description see paragraph 3.3.2.6 Air Data Type.

3.3.11 Category 11 – Heading Input Select

Category 11 defines the Magnetic Heading interface.

Appendix E Table 5.3.11 defines the Heading Input Select types and identifies the first MK XXII EGPWS



1. Using Appendix E Tables 5.3, 5.3.11 and 5.3.11-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 5.3.11 under the Ident

No. heading for Step (Category) 11 on Table 5.3. This number will be used for programming the

configuration module.



3. Using the Heading Input Select number from Appendix E Table 5.3.11 as “x”, go to Appendix E

Table 5.3.11-x. The electrical interfaces (pin-outs) for the Heading Input Select Type are shown in

Appendix E Table 5.3.11-x 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.

3.3.11.3 Analog Heading (Synchro) (CAT. 11 ID 0)

22

233

J1 Directional Gyro

X

Y

EGPWS MK XXII

X

YHeading Synchro Heading

Z Z

H

C

424

26 VACReference

H

CHeading Ref

28Mag Hdg Validity +28V = ValidAnalog-HDG.vsd

Vendor Model Heading Heading Reference Heading Synchro (Note 1)

D/G Valid 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 AH-600 J1B-37 J1B-38 J1B-39 J1B-40 J1B-41 J1B-42

Honeywell KSG 105 P1-V P1-P P1-d P1-Z P1-W P1-T

Honeywell KI-525 3 J2-P J2-R J2-U J2-S J2-V J2-T

Jet DN-104 P2-31 P2-9 P2-10 P2-1 P2-2 P2-3

Litef LTR-81 MP-E15 MP-B12 MP-B13 MP-B9 MP-B10 MP-B11

Litef LCR 92/LCR-93 Note 2 J3-05 J3-20 J3-13 J3-42 J3-28

Sperry C-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: The KI-525 must have the proper mod for HEADING TRANSMITTER output. The Heading Valid output at J2-P needs to be converted from ground active to +28V active output using an external relay for use with EGPWS.



3.3.11.4 Digital ARINC 429 High Speed (CAT. 11 ID 2 and 3)

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 429HS

Heading

Vendor Model 429 High Speed

AHRS A B

Litef LCR 92S

3.3.11.5 Digital – ARINC 429 Dual IOC buses (Cat. 10 ID 254 & 255)

Heading Input Select Type 254 & 255 (IOC bus or equivalent) are dual high speed, digital ARINC 429 signal

having labels True Heading (314) or Magnetic Heading (320). For interface description see paragraph

3.3.2.6 Air Data Type.

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.



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 5.3.13 defines the Input/Output discretes options and identifies the first MK XXII EGPWS



1. Using Appendix E Tables 5.3, 5.3.13, and 5.3.13-x, select the Input/Output Discrete Type number that

matches the aircraft configuration, feature preferences and version (part number) being installed.

Note: Normal 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 5.3. This number will be used for

programming the configuration module.

3. Using the Input/Output Discrete Type number from Appendix E Table 5.3.13 as “x”, the ICD Table 5.3.13-

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 5.3.13-x, use

only the one that matches the aircraft wiring (use only the +28V and 0V or the Ground and Open definitions).

3.3.13.2 Input/Output Discretes

Additional information for the discretes is provided below.

3.3.13.3 Audio Inhibit Discrete

Honeywell does not recommend the use of this input for Helicopters.

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” 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

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.




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.


WOW +28 On Ground = +28V

In Air = Gnd/Open

J1-37

WOW Gnd On Ground = Gnd

In Air = +28V /Open

J1-18

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).


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.




Mode 6 Low Volume Low Volume = Gnd

Not Low Volume = Open

J1-13

3.3.13.8 Minimums/Check Height Silence Discrete

The Minimum/Check Height Silence discrete will silence a "Minimum Minimums" or “Check Height Check

Height" message for 3 minutes.

This discrete is normally connected to a momentary action switch mounted on the Cyclic column. This is the

same switch that would have previously been used to silence callouts from the AVAD system.


Minimums/Check

Height Silence

Silence = Gnd

Normal = Open

J1-13

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 normally 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.


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.


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.




Glideslope Inhibit +28 Inhibit = +28V

Not Inhibit = Gnd/Open

J1-38

Glideslope Inhibit Gnd Inhibit = Gnd

Not Inhibit = +28V /Open

J1-19

3.3.13.12 Timed Audio Inhibit Discrete

The Timed Audio Inhibit will cause the inhibiting of most audio messages for a configurable period. See

Options 3 (Category 18). The default inhibit period is 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.


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 ICS Audio On Discrete

The ICS Audio On discrete will inhibit all audio messages prioritized below the Warning Terrain and Warning

Obstacle messages. Self Test messages are excluded. This discrete is designed to be used in handshaking

with a Central Aural Warning System in conjunction with the Audio On output discrete.

3.3.13.15 Output Discretes

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.

All EGPWS Output Discretes have corresponding bit assignments in the EGPWS ARINC 429 output data.

3.3.13.16 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.

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.

3.3.13.17 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.

3.3.13.18 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.

3.3.13.19 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.

3.3.13.20 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.

3.3.13.21 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.



3.3.13.22 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.

3.3.13.23 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.

3.3.13.24 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.

3.3.13.25 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.



Table 3.3.13-1 MK XXII EGPWS – Example Cockpit Lights



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 5.3.14 defines the Audio Output Level options and identifies the first MK XXII EGPWS



1. Using Appendix E Tables 5.3 and 5.3.14 as described above, select the Audio Output Level ID number

that matches the feature preferences and version (part number) being installed.

2. Record the ID number for the Audio Output Level from Appendix E Table 5.3.14 under the Ident No.

heading for Step (Category) 14 in Appendix E Table 5.3.

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

AudioPanel

Low level audio

J1-70HJ1-71L

J1-75HJ1-74L

8 ohm

FIGURE 3.14-1 Audio Interface

Note: Because most helicopters use a full muff headset, cockpit speakers are not applicable.



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 3.3.15-1 below.

Appendix E Table 5.3.15 defines the Autorotation threshold options.


1. Using Table 3.3.15-1 below and Appendix E Tables 5.3 and 5.3.15 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 5.3.15 or Table 3.1.15-

1 below under the Ident No. heading for Step (Category) 15 in Appendix E Table 5.3.

Table 3.3.15-1: AUTOROTATION THRESHOLD

Aircraft Model Threshold % Threshold ID

Agusta 109E 2 4

AS 365N3 7.5 15

Bell 212 6 12

Bell 412 6 12

Bell 430 7.5 15

Bell 427 TBD

EC-135P TBD

EC-155B 7.5 15

HH-65 7.5 15

MD900/902 7.5 15

S-76 Series 7.5 15

BK-117 TBD

Bell 222 TBD

EH-101 7.5 15

S-92 7.5 15

AW-139 7.5 15



3.3.16 Category 16, Torque Input Select

Torque data is primarily used to detect an Autorotation. Category 16 defines the Torque interface. Interface

is provided for ARINC 429 and RS 422 digital inputs and 4 DC Torque inputs as shown below. Many DC

Torque signals are very high impedance and are not compatible with the MK XXII. In these cases two

options are available.

A DC to ARINC 429 Torque Converter may be used, as described below and in Appendix D, for aircraft

whose torque indications systems use a DC signal and have no DC reference (such as S-76A, A+, A++, and

C autopilot output) or those who have a 10.0 VDC reference. Note that some Eurocopter aircraft provide a

DC torque signal but use an AC reference (AS350, AS355, AS365N/N1/N2). These may not be compatible

with the DC to 429 Torque Converter and may need to chose the second option below.

The MK XXII may be configured for no torque input. This type does not detect autorotation and thus do not

provide the autorotation altitude callouts or advanced gear warnings. Mode 1 is inhibited in these types.


1. Using Appendix E Table 5.3, under Step/category 16 select Torque Source. Using the guide below and

Tables 5.3.16 and 5.3.16-x select the ID number for your Torque source and record that number on

Table 5.3 under Ident No. for step 16. This number will be used during programming of the configuration

module.

2. Using Appendix E Tables 5.3.16-x, where x is the Torque Type number, define the electrical interfaces

required to support your Torque Type. Using Table 5.3.16-x determine the wiring interconnects and

record it on Appendix A Fig A1-2.

Table 3.3.16-1: Torque Application Guide

ID Signal Type Aircraft Application

0 No Torque AS-350, AS-355N, AS-365N/N1/N2, EC-130

1 ARINC 429 S76B/C+

4 Synchro Bell 212/412

5 ARINC 429 BNR EC-155B, AS-365N3

6 RS-422 MD900/902, Agusta 109E, EC-135P1

7 DC AS 332

9 ARINC 429 BCD EC-155B, AS-365N3

10 ARINC 429 BNR Bell 430, 427

12 DC Bell 212/412

15 DC HH-65

16 DC BK117A/B-2/C-1(Note 1)

17 ARINC 429 DC to ARINC 429 Torque Converter

S76A, A+, A++ and C, BK117A/B-2/C-1 (Note 1)

18 ARINC 429 S-92, AW-139



ID Signal Type Aircraft Application

19 ARINC 429 EH-101

20 RS 422 MD 902 (PW206E)

21 RS 422 EC-135P1 (PW026B V27)

22 RS 422 EC-135P1 (PW026B V28)

23 DC H-60 Blackhawk

24 RS 422 Maintenance Port (8000 Hex Sync)

25 RS 422 Maintenance Port (8FFF Hex Sync)

26 RS 422 A-109E (PW206C V27)

27 RS 422 A-109E (PW206C V28)

28 RS 422 Maintenance Port (8000 Hex Sync)

29 RS 422 Maintenance Port (8FFF Hex Sync)

30 ARINC 429 Late model EC-227, EC 725, EC-135, EC-145,

EC-155/A

31 DC EC-145

32 ARINC 429 EC-120, EC-130, AS-350B2 and B4

33 ARINC 429 AS-355

Note 1: BK-117 series can use the CSAS output or the DC to ARINC 429 Torque Converter interface.

If your aircraft is not listed or for help in selecting the correct Torque type, contact the Honeywell Avionics

Technical Assistance line 1 800 601-3099 (or 602-365-3099 from outside the USA).

DC to ARINC 429 Torque Converter

For aircraft with a DC Torque signal system such as S-76A, A+, A++, and C or many Bell Aircraft the DC

Torque signal is not compatible with the MK XXII. For these aircraft it is recommended that a DC to ARINC

429 converter be used. At the time of this writing a certifiable source for a DC to ARINC 429 Torque

converter has not been identified. Contact Honeywell for recommendations.




Category 17 enables/disables the following Options: Helo Normal Pop-Up Range, Helo Low Altitude Pop-Up

Range, Autorotation Callout Option Select, Mode 6B Always ON Enable, Normal Terrain Airspeed Select,

Low Altitude Airspeed Select, Low Altitude No VFOM Select.

Appendix E Table 5.3.17 defines the Options Select group and identifies the first MK XXII EGPWS version in

which the option was available (see the Effectivity entry).


1. Review the sections below for information on Helo Normal Pop-Up Range, Helo Low Altitude Pop-Up

Range, Autorotation Callout Option Select.





3.3.17.2 Helo Normal Pop-Up Range

If the display type selected via Category 6 supports Auto Pop-Up and Auto-Ranging then the Helo Normal

Pop-Up Range Select chooses the Terrain Display Range to be forced during a non-Low Altitude Mode Pop-

Up. The 5 NM range selection is recommended if the selected display type supports a 5 NM range.

Otherwise select an option using a 10 NM range.

3.3.17.3 Helo Low Altitude Pop-Up Range

If the display type selected via Category 6 supports Auto Pop-Up and Auto-Ranging then the Helo Low

Altitude Pop-Up Range Select chooses the Terrain Display Range to be forced during a Low Altitude Mode

Pop-Up. The 2.5 NM range selection is recommended if the selected display type supports a 2.5 NM range.

Otherwise select the lowest range above 2.5 NM that the display will support.

3.3.17.4 Autorotation Callout Option Select

The Autorotation feature was previously (up to 965-1590-011) activated via Category 4. Now this category

selects the Auto-rotation callouts via one of the following options:

Autorotation Callout Option Select 0: No Auto-rotation callouts selected (the callout menu selected via

category 4 will remain active in auto-rotation).

Auto-rotation Callout Option Select 1: Selects “200” and “100” for Auto-rotation.

Auto-rotation Callout Option Select 2: Selects “200”, “100”, “80”, “60”, “40”, “20” and “10” for Auto-

rotation.



3.3.17.5 Mode 6B Always ON Enable

Selecting this option enables the "Altitude Altitude" or "Check Height Check Height" callout (Mode 6B) at all

times. The significant difference in this function is that the call out will be spoken for each transition thru the

DH Bug or setting. This option is often selected for Offshore operation.

3.3.17.6 Normal Terrain Airspeed Select

This option configures the system to use airspeed instead of ground speed to enable/disable the Terrain

Look Ahead function during normal (not Low Altitude) operations. A special consideration should be made

before selecting this option as it can lead to nuisance alerts when landing or taking off into strong headwind.

(See commentary below)

Aircraft operating in strong head winds will see a resulting decrease in ground speed. Depending on

speed this may reduce ground speeds below look ahead enabling speeds thus turning the terrain look

ahead function off. With this option selected, the Terrain Look Ahead function is enabled with airspeed

allowing the look ahead alert to be active in some circumstances when it otherwise would not. However,

based on customer feedback, this selection can increase the risk of nuisance alerts when landing or taking

off into headwinds.

3.3.17.7 Low Altitude Airspeed Select

This option configures the system to use airspeed instead of ground speed to enable/disable the Terrain

Look Ahead function during Low Altitude operations when the Low Altitude Mode is selected. A special

consideration should be made before selecting this option as it can lead to nuisance alerts when landing or

taking off into strong headwind. (See commentary in section 3.3.17.6)

3.3.17.8 Low Altitude No VFOM Select (was SAR select)

This option removes the addition of VFOM from the Terrain Floor when Low Altitude is selected. This is

necessary to allow SAR operations at 200 feet AGL. This option should only be selected on aircraft whose

mission requires operation down to 200 feet AGL.




Category 18 enables/disables the following Options: Audio Inhibit Time, Inhibit All Except Minimums Type

Callout and 100 Ft Callout select, Inhibit All Except Minimums Type Callout select, Inhibit Includes Too Low

Gear Select, Inhibit Altitude Callouts 50 ft and Below Over Runway select, Lower MDA/DH Value select.




1. Review the sections below for information on Audio Inhibit Time, Inhibit All Except Minimums Type

Callout and 100 Ft Callout select, Inhibit All Except Minimums Type Callout select, Inhibit Includes Too

Low Gear Select, Inhibit Altitude Callouts 50 ft and Below Over Runway select, Lower MDA/DH Value

select.





3.3.18.2 Audio Inhibit Time

This option allows selection of the Timed Audio Inhibit time. Options provide 2 to 2.5 minute increments from

3 to 20 seconds. An additional state is provided that allows the Audio Inhibit to be toggled ON and OFF.

Timed Audio Inhibit will inhibit all audio except the following.

Too Low Gear Minimums Minimums Minimums Check Height Check Height Altitude Altitude Altitude

Selected Altitude Callouts Glideslope Tail Too Low Bank Angle* Be Alert Terrain INOP

For the S-92 the following externally triggered messages are added to the list:

Low Rotor Fire Engine 1/2 Engine 1/2 Failure Gear Box Pressure Swash Plate Temperature Fire APU Smoke In Cabin

Smoke In Baggage Hover Altitude Airspeed Check Altitude Check Power Decouple Level Off



3.3.18.3 Inhibit All Except Minimum Type Callout and 100 Ft Callout Select

This option alters the above list to inhibit all audio messages except the following messages and the 100 foot

callout.

Minimums Minimums Minimums Check Height Check Height

Altitude Altitude Altitude

This option is most often used on aircraft operating offshore and combined with audio menus and callout

options using Check Height.

3.3.18.4 Inhibit All Except Minimum Type Callout Select

This option alters the inhibit list in 3.3.18.2 to inhibit all audio messages except the following message.

Minimums Minimums Minimums Check Height Check Height

Altitude Altitude Altitude

This option is most often used on aircraft operating onshore and combined with audio menus and callout

options using Check Height.

3.3.18.5 Inhibit Includes Too Low Gear Select

This option adds the Too Low Gear message to those messages inhibited by the Timed Audio inhibit. This

option is intended for those aircraft that perform low altitude rescue operations with landing gear up.

3.3.18.6 Inhibit Altitude Callouts 50 ft and Below Over Runway Select

This option will inhibit selected altitude callouts at 50 feet and below when the aircraft is over an airport with a

published instrument approach. This silences altitude callouts during final approach when ATC

communications traffic maybe high.

3.3.18.7 Lower MDA/DH Value Select

This option is effective when Category 8 (Radio Altitude Input) ID 251, ID 252, ID 254 or ID 255 are

configured. These allow the input of two sources of MDA or DH. Normally the higher of the two values is

selected for use. This option allows the selection of the lower of the two values for use by the Mode 6

functions.




Category 19 selects the Low Altitude Mode of operation (Land, SAR, or Offshore transport).




1. Review the sections below for information on Low Altitude Mode options.


matches the aircraft operation, system response, and version (part number) being installed. Record the

ID number for the Options Select Group #4 from Appendix E Table 5.3 under the Ident No. heading for

Step (Category) 19. This number will be used for programming the configuration module

3.3.19.2 Low Altitude Mode

“Low Altitude Mode” is selected with the use of the Low Altitude Mode Select (Tactical) discrete. This

discrete is sourced from an analog switch or digital ARINC 429 bits. Prior to the -030 release when “Low

Altitude Mode” was activated GPWS classic modes and the forward looking terrain alert function were

modified to allow flight in congested areas, low altitude routes or while performing special operations.

In release -030 and on, this option category allows tailoring of the MK XXII system response to the Low

Altitude Mode Select (Tactical) discrete.

When Low Altitude Mode Select is true the HTAWS provides a “Reduced Protection Mode” allowing

operations below the defined alert envelopes without issuing alerts. Low Altitude Mode Select affects the

following modes regardless of the configuration option selected below (see table for further changes in

operation):

GPWS Mode 2 inhibited.

GPWS Mode 3 inactive above 100 feet AGL.

Mode 6 provides the message “Altitude Altitude” or “Check Height” for each transitioning below the

selected decision height1.

Forward Looking Terrain Alerting Threat Detection is biased to allow closer proximity to terrain. 1 For S-92 “Altitude Altitude” callout is always active.

Low Altitude

Option Suggested Operations

See Appendix E for MK XXII

system response 0 Low level operations over land1 SAR over water 2 Offshore transport

3.3.19.3 Mode 2 Terrain Inhibit

Many HTAWS installations provide a Terrain Inhibit switch that allows the pilot to disable (or inhibit) Terrain

Awareness Alerts. When this switch is active the Forward Looking Terrain Alerting function is inhibited



however, the radio altimeter based, classic GPWS Mode 2 alerts are not. This can lead to pilot

dissatisfaction. The following is a scenario to illustrate the potential for confusion: Pilot is flying VFR and is

intentionally close to terrain; Forward Looking Terrain Alert activates providing “Caution! Terrain” aural and

alert visual; pilot inhibits terrain by selecting the Terrain Inhibit switch; Forward Looking Terrain Alert ceases

but due to close proximity to terrain the GPWS Mode 2 alert activates providing the “Terrain Terrain” aural

and alert visual. In this scenario the pilot has made the decision and commanded the system to inhibit terrain

alerts but the system continues to provide them albeit from a different mode. In the -030 release the Mode 2

Terrain Inhibit option allows the Terrain Inhibit switch to affect the Mode 2 function.

Mode 2 Terrain Inhibit = False; Terrain Inhibit does not affect Mode 2 (pre -030 release behavior).

Mode 2 Terrain Inhibit = True; Terrain Inhibit will also inhibit the Mode 2 alert function.



SECTION IV

CONFIGURATION MODULE PROGRAMMING

AND

TERRAIN DATABASE LOADING



SECTION IV – CONFIGURATION MODULE PROGRAMMING AND 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 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

M39029/63-368

PCOM

Connector, AMP 204513-2*

Pin Contact, 204370-2, QTY 4*

M39029/58-360

Backshell, AMP 745854-5

Jackscrew, AMP 747784-3

Grommet Set, AMP 747746-1

P3

* Alternate part number 748364-1 connector and 748333-4 or –7 pin contact.

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. WinVIEWS

software can be downloaded from the internet website (www.egpws.com)

3

2

5

3

4

1Length as required (5' to 50')



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 3,

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 3), create a command

string with the following structure:

CUW 0/19 # # # # # # # # # # # # # # # # # # #/

- 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).

- /19 indicates the beginning of the data string (/) with 19 being the number of categories to follow.

- <space><Cat 1 ID#><space><Cat 2 ID #>…<Cat 19ID#>/ each Cat ID# is the chosen ID for the

category from the Appendix E Table 3. The ending slash (/) indicates the end of the data string.

Note: If 19 ID’s do not follow “/19”, 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 19 (e.g., “/8 # … #/” with eight ID’s

defined), then the remaining categories (9 through 19) 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 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 0/19 128 3 2 134 128 3 29 1 0 2 0 0 129 0 15 1 0 18 0/

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: 2 (All Callouts) Category 5 Audio Menu: 128 (Basic menu) Category 6 Display Type: 3 Category 7 Options Select Group #1: 29 (Selections shown at end of list) 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 Category 16 Torque Type 1 Category 17 Options Select Group #2 123 (Selections shown at end of list) Category 18 Options Select Group #3 18 (Selections shown at end of list) Category 19 Options Select Group #4 0 (Selections shown at end of list) Peaks Mode Enable Obstacle Awareness Enabled GPS Altitude Ref. MSL Auto Rotation Callout Option 1 Selected Normal Pop Up Range 5 Selected Low Altitude Pop Up Range 2.5 Selected Normal Terrain With Airspeed Selected SAR Low Altitude Selected Audio Inhibit Time 5

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: 2 Category 5 ID: 128 Category 6 ID: 3 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 Category 16 ID: 1 Category 17 ID: 123 Category 18 ID: 18 Category 19 ID: 0 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 060-4314-250.

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 29) - <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 29 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 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.

4.5.3 Configuration Module RTC Update

To improve the EGPWS GPS card Time-to-first-fix performance a new configuration module has been made

available which includes a Real Time Clock and battery back up (super cap) RAM. Additional commands are

added for this function to initialize the RTC and the position data stored in the RAM during installation.

1. “RDT” – Read Date and Time returns the stored date and time from the configuration module and the

GPS card in Zulu time as follows:

RTC: hh:mm:ss_YYMMDD example: RTC: 20:15:30_040216

GPS: 20:15:31_040216

2. “RLL” – Read Latitude and Longitude returns the stored latitude and longitude from the configuration

module and the GPS card in the following format:

CFG MOD POS: (<Latitude>, <Longitude>) example: CFG MOD POS: 47.12345, -122.12345

INT GPS POS: 47.12345, -122.12345

3. “WDT” – Write Date and Time enters a date and time to be stored in the configuration module in Zulu

time as follows:



WDT hh:mm:ss_YYMMDD example: WDT 20:15:30_040216

4. “WLL” – Write Latitude and Longitude enters a latitude and longitude to be stored in the configuration

module in the following format:

WLL <Latitude>, <Longitude> example: WLL 47.12345, -122.12345

4.6 Regional Terrain Database Loading

4.6.1 Effectivity

The MK XXII EGPWS (965-1595-0XX) are shipped from the factory with the Regional Terrain Database

requested by the customer installed. Aircraft operating outside of the installed 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.

4.6.4 Material – Cost and Availability

Regional Terrain Database PCMCIA cards are available for Operators that will be operating outside of the

installed database region. To order a regional terrain database send a purchase order or request to

[email protected] or [email protected] listing the part number and quantity required:

Vendor Name Vendor P/N Description QTY UM Honeywell P/N

Honeywell XXXNAM North America 1 EA 718-1447-XXX

Honeywell XXXSAM South America 1 EA 718-1448-XXX

Honeywell XXXEUR Europe 1 EA 718-1449-XXX

Honeywell XXXEEU Eastern Europe 1 EA 718-1450-XXX

Honeywell XXXAFR Africa 1 EA 718-1451-XXX

Honeywell XXPAC Pacific 1 EA 718-1452-XXX

Honeywell XXXSPA South Pacific 1 EA 718-1457-XXX

Honeywell XXXMES Middle East 1 EA 718-1458-XXX

Honeywell XXXCAN Canada 1 EA 718-1647-XXX

Honeywell XXXSAF South Africa 1 EA 718-1654-XXX

Honeywell XXXASI Asia 1 EA 718-1453-XXX



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

(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 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 965-1595-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/regions 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



SECTION V

CERTIFICATION



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 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 Complete Customer Care Center (800-601-2099), for

information regarding the compatibility of equipment not listed in Section III or interface into any

airframe not listed in Appendix E Table 5.3.1.

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 060-4167-251.

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 for part number 965-1595-020 thru -024 and 060-4314-065 for part number 965-1595-

026.



5.2.6 Flight Test

Honeywell has developed a generic Flight Test procedure for the MK XXII EGPWS, drawing number 060-

4314-252. 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



APPENDIX A

CUSTOMER WORKSHEET

MK XXII EGPWS

ENHANCED GROUND PROXIMITY WARNING SYSTEM


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. 060-4314-250, Installation Manual for the MK XXII For product description information, refer to Honeywell document No. 965-1595-601, 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):

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

MK XXII EGPWS



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)

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.

MK XXII EGPWS



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

GENERIC MODEL INFORMATION

Aircraft Tail Geometry:

Manufacturer:

Model:

(be specific)

Engine(s):

He

igh

to

f Ta

il

Tip of Tail to CG

MK XXII EGPWS



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)

SYSTEM Number of Engines DATA FORMAT

(ARINC 429, RS 422, RS

232, synchro, DC, AC

Signal Scale Factor

In % Torque

NOTES

Engine

Torque



APPENDIX B

SAMPLE WIRING DIAGRAMS



DIS

PLAY

TER

R

ON

TER

RD

ISPL

AYO

N

AVIO

NIC

SW

ITC

H U

NIT

(CU

STO

MER

OPT

ION

)

DIS

PLA

Y C

ON

FIG

UR

AT

ION

AU

DIO

GLI

DE

SL

OP

EA

ND

/OR

LOC

AL

IZE

R

RA

DIO

AL

TIT

UD

E

G/S

DEV

LOW

LEV

ELVA

LID

ITY

250m

VDC

WX

IN #

245

3 (B

)

WX

IN #

245

3 (A

)

WX

IN #

145

3 (B

)

WX

IN #

145

3 (A

)

OR

DC

SIG

NAL

SIG

RET

UR

N

OR

P1P2

522IL

S BU

S IN

PUT

ARIN

C 4

29 L

S

SH

(B)

(A)

SH

1030

OR

421

(B)

(A)

RAD

IO A

LTIT

UD

E IN

PUT

ARIN

C 4

29 L

S

SHP1P2

CAT

. 6ID

#

CAT

. 14

ID #

CAT

. 9ID

#

CAT

. 8ID

#

AUAU

SHSHSH

AVIO

NIC

SW

ITC

H U

NIT

(CU

STO

MER

OPT

ION

)

UN

-SW

ITC

HED

AUD

IO IN

CH

ASSI

S G

ND

CO

PILO

T IC

S

P1

POW

ERIN

PUT:

28 V

DC

(RET

UR

N)

(RET

UR

N)

(+)

(+)

CH

ASSI

S G

ND

UN

-SW

ITC

HED

AUD

IO IN

PILO

T IC

S(C

)

(H)

7475

29R

AD A

LT V

ALID

ITY:

+2

8 VD

C

4564

ESS

BUS

AIR

CR

AFT

+28

VDC

GPW

S

CH

ASSI

S G

RO

UN

D

GR

OU

ND

CH

ASSI

S/SI

GN

ALAI

RC

RAF

T

3 AM

P

4261416040 20

GN

D =

BEL

OW

DH

DH

DIS

CR

ETE

33

DW

G T

ITLE

REV

.FI

GU

RE

B1-1

MK

XXII

EG

PWS

P1

RAD

IO A

LTIM

ETER

R/T

UN

IT

RAD

ALT

IND

ICAT

OR

(+)

(-)AR

INC

552

/ AL

T55

Mk

XXII

ENH

ANC

ED G

PWS

WIR

ING

DIA

GR

AM,

WO

RKS

HEE

T

Hon

eyw

ell I

nter

natio

nal I

nc.

Red

mon

d, W

asin

gton

980

73-9

701

CKT

BKR

PN

L

DC

53G

RO

UN

D

DC

HI

LO

VALI

D

RAD

ALT

DH

G/S

DEV

(+U

P)

G/S

DEV

(+D

N)

GLI

DES

LOPE

RC

VR N

O.2

G/S

VAL

ID

G/S

DEV

(+U

P)G

/S D

EV (+

DN

)

GLI

DES

LOPE

RC

VR N

O.1

G/S

VAL

ID

TTL

NO

.2IL

S SE

L (G

ND

)

TTL

NO

.1IL

S SE

L (G

ND

)

FLT

DIR

CTR

L PN

L N

O.2

BAC

KCO

UR

SE

BAC

KCO

UR

SEFL

T D

IR C

TRL

PNL

NO

.1

65 46

G/S

DEV

(+U

P)

G/S

DEV

(+D

N)

G/S

VAL

IDIT

Y+2

8 VD

C11

+ --+

VAL

TTL

DN

UP

(GR

N)

(GR

N)

CO

PILO

T IN

STR

UM

ENT

PAN

EL

(GR

N)

(GR

N)

PILO

T IN

STR

UM

ENT

PAN

EL

ANN

UN

CIA

TOR

BO

X

SEE

SHEE

T 2,

ZO

NE

D3

22 22 22 22

ARIN

C 2

DAT

A(–

)(+

)

J2B

WX

VID

EO IN

1A

WX

VID

EO IN

1B

DC

-811

DAT

A(–

)(+

)

J1AJ1

CO

PLT

SYM

BOL

GEN

ERAT

OR

TER

R S

EL O

UT

J1

DC

-811

DAT

A(+

)(–

)J1

A

ARIN

C 2

DAT

A(–

)(+

)

J2B

WX

VID

EO IN

1A

WX

VID

EO IN

1B

4243(A

)EG

PWS

OU

TPU

TAR

INC

429

(B)

TER

RAI

N D

ISPL

AYO

UTP

UT

DAT

A #2

ARIN

C 4

53(B

)

(A)

TER

RAI

N D

ISPL

AYO

UTP

UT

DAT

A #1

ARIN

C 4

53(B

)

(A)

57565958

+–– +

P2 3736(A

)D

ISPL

AY

RAN

GE

#142

2 IN

PUT

(B)

P2

51

P1

TER

R D

ISPL

AY

POPU

P D

ISC

RET

EO

UTP

UT

1110(A

)D

ISPL

AY

RAN

GE

#242

2 IN

PUT

(B)

TER

RAI

N S

ELEC

TPO

P-U

P

J1C

OPL

T D

SPLY

CTL

(DC

-811

)

POP-

UP

TER

RAI

N S

ELEC

T

J1PL

T D

SPLY

CTL

(DC

-811

)

PLT

SYM

BOL

GEN

ERAT

OR

SH SH

TER

R S

EL O

UT

MO

M.

MO

M.

C/S

SH

SH

DC

GN

D+2

8 VD

CIL

S FR

EQSE

LEC

T39

OR

ILS

BAC

KCO

UR

SE38

OR

DC

GN

D+2

8 VD

C19

DED

ICAT

EDG

PWS

SPEA

KER

8 O

HM

, 4 W

ATTS

70 71(H

)

(C)

HIG

H L

EVEL

SPEA

KER

OU

TPU

T8

OH

MS

NO

MIN

ALAU

LOW

LEV

ELPR

E-AM

P O

UTP

UT

600

OH

MS

NO

MIN

AL

CO

CKP

ITSP

EAKE

R

TYP,

2 P

LCS

CO

PLT

PILO

T

C

815 38

3

3

DO

NO

T C

ON

NEC

T "S

IGN

AL R

ETU

RN

" WIR

E TO

AN

Y G

RO

UN

D

4

4

EXAM

PLE:

ID

250

(SPZ

7600

/ ED

Z705

)

LOC

DEV

(+LT

)LO

C D

EV (+

RT)

LOC

VAL

ID

PILO

TLO

CAL

IZER

RC

VR N

O.1

SH+2

8 VD

CLO

C V

ALID

ITY

LOC

DEV

(+LT

)

LOC

DEV

(+R

T)

SH

OR

30 10 48

RAD

IO A

LTIT

UD

E IN

PUT



INO

P

FIG

UR

E B

1-2

LO

W A

LT

IN

PU

TLO

W A

LT

= G

ND

LOW

AL

T O

UT

PU

TG

ND

= L

AM

P O

N

GP

WS

WA

RN

OU

TP

UT

GN

D =

LA

MP

ON

G/S

CA

NC

EL

INP

UT

CA

NC

EL

= G

ND

GP

WS

CA

UT

OU

TP

UT

GN

D =

LA

MP

ON

G/S

CA

NC

EL

LE

DLA

MP

OU

TP

UT

GN

D =

LA

MP

ON

SE

LF

TE

ST

INP

UT

SE

LF

TE

ST

= G

ND

943

62

AIR

DA

TA

VA

LID

ITY

DIS

CR

ET

E (

+2

8V

DC

)

(+)

(-)

AIR

DA

TA

IN

PU

TA

NA

LO

G D

C

P1

SH

Mk

XX

II E

NH

AN

CE

D G

PW

S

WIR

ING

DIA

GR

AM

, W

OR

KS

HE

ET

18

A1

A

AL

T.

MO

M.

MO

M.

MO

M.

AL

T.

MO

M.

MO

M.

MO

M.

PIL

OT

/CO

PIL

OT

INS

TR

PA

NE

LS

HE

ET

1, Z

ON

E B

2

C/S

GP

WS

INO

PG

ND

= L

AM

P O

N

55

TA

D/T

CF

IN

OP

GN

D =

LA

MP

ON

TE

RR

AW

AR

EN

ES

S &

TC

F IN

HIB

IT I

NP

UT

INH

IBIT

= G

ND

12

3839

AU

DIO

IN

HIB

IT 2

TC

AS

TP

T-6

6A

TC

AS

IN

HIB

IT O

UT

69

GN

D

14

1312

EG

PW

S M

ON

ITO

RR

S2

32

C4

(TX

)

(RX

)3

J3P1

P2

AR

INC

42

9 O

UT

PU

T(B

)

(A)

(B)

(A)

AIR

DA

TA

IN

PU

TA

RIN

C 4

29

PIT

OT

76 147315

77

3478

RE

V.

AIR

DA

TA

CO

MP

UT

ER

ST

AT

IC

MK

XX

II E

GP

WS

CO

M1

(GR

N)

(RE

D)

GP

WS

P/T

ES

T

(GR

N)

(AM

BE

R)

GP

WS

(GR

N)

(GR

N)

ON

(AM

BE

R)

(GR

N)

ON

INH

IBA

UD

IO

PIL

OT

IN

ST

RU

ME

NT

PA

NE

L

CO

PIL

OT

IN

ST

RU

ME

NT

PA

NE

L

DW

G T

ITLE

Ho

ney

wel

l Int

ern

atio

na

l In

c.R

ed

mo

nd

, Wa

sin

gto

n 9

80

73-9

701

P1

(AM

BE

R)

(AM

BE

R)

GP

WS

INO

PT

ER

R

CE

NT

ER

IN

ST

RU

ME

NT

PA

NE

L

72

SH

TE

RR

INH

IBO

N

(GR

N)

(AM

BE

R)

AL

T.

AU

DIO

IN

HIB

ITIN

PU

TIN

HIB

IT =

GN

D

17

CA

T. 2

ID #

CA

T.

13

ID #

AIR

CR

AF

T +

28

VD

CN

O.

2 A

VIO

NIC

S B

US

S

GP

WS

LIG

HT

S

1 A

MP

SH

25 63 44 53

+5

VD

C R

EF

AIR

TE

MP

(+

)

AIR

TE

MP

(-

)

GR

OU

ND

OA

T

PR

OB

EIN

PU

T

OA

TP

RO

BE

OR

RE

FO

NL

Y

AIR

DA

TA

INP

UT

/OU

TP

UT

DIS

CR

ET

EF

UN

CT

ION

S

C

DE

AD

FA

CE

LE

GE

ND

PW

R(+

28V

DC

DA

Y/+

16

VD

C N

IGH

T)

VIS

IBL

E W

HIT

E L

EG

EN

D P

WR

(0V

DC

DA

Y/+

16

VD

C N

IGH

T)

PR

ES

S-T

O-T

ES

T O

UT

PU

T(G

RO

UN

D =

TE

ST

)

AN

NU

NC

IAT

OR

BO

X

G/S

CA

NC

LD

LO

WA

LT

GP

WS

(RE

D)

(GR

N)

P/T

ES

T

GP

WS

(AM

BE

R)

(GR

N)

G/S

CA

NC

LD

ON

(GR

N)

(GR

N)

LO

WA

LT

ON

(GR

N)

(AM

BE

R)

AU

DIO

INH

IB

38

158

4

OP

TIO

NA

LT

ER

R I

NH

IBIT

SE

E B

EL

OW

AT

TIT

UD

E/M

AG

NE

TIC

HE

AD

ING

CA

T.

11

ID #

CA

T.

10

ID #

HE

AD

ING

SY

NC

HR

O

HE

AD

ING

VA

LID(X

)

(Y)

(Z)

NO

.1 V

G o

r A

HR

S

AT

TIT

UD

E V

ALI

D

SY

NC

HR

O

AT

TIT

UD

E

SY

NC

HR

O

AT

TIT

UD

E

PIT

CH

RO

LL

(X)

(Y)

(Z)

(X)

(Z)

(Y)

22

(X)

MA

G H

EA

DIN

G V

AL

IDIT

YD

ISC

RE

TE

(+

28

VD

C)

SH

OR

P2

623

(B)

(A)

23 283

(Y)

(Z)

AR

INC

42

9 H

SA

HR

S B

US

IN

PU

T

4

MA

GN

ET

ICH

EA

DIN

G

SY

NC

HR

O

DIS

CR

ET

E (

+2

8 V

DC

)

(X)

5

(Y)

7 6 68

(Z)

1 221

(Z)

(Y)

(X)

AT

TIT

UD

E

SY

NC

HR

O

AT

TIT

UD

E V

ALI

DIT

Y

PIT

CH

SY

NC

HR

OA

TT

ITU

DE

R

OLL

NO

.1 D

G o

r A

HR

S

P1 2

44(H

)

(L)

26

VA

C R

EF

AR

INC

429

GP

S #

1 O

UT

PU

T

AN

TE

NN

AG

PS

CA

T.

3ID

#

AR

INC

743

(A)

GP

S

PO

SIT

ION

(B)

(A)

SH

OR

OR

GP

S I

NP

UT

AR

INC

429

GP

S I

NP

UT

GP

S A

NT

.

TN

C8 45 29

2825

SH

TX RX

CO

MR

S2

32

(A)

(B)

P2

26

VA

C R

EF

(H)

(L)

AU

DIO

ON

/

AR

INC

743

(A)

GP

S

GP

S #

2 O

UT

PU

T

AR

INC

429

(A)

(B)

SH

SH

23 6

AR

INC

429

GP

S I

NP

UT

(B)

(A)

OR

DU

AL

NC

TIM

ED

AU

DIO

IN

HIB

ITL

AM

P O

UT

PU

TG

ND

= L

AM

P O

N5

2



APPENDIX C

WinViews OPERATION INSTRUCTIONS

Honeywell MK XXII Installation Manual


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



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. Command file updates are available at

http://www.egpws.com.

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.



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



APPENDIX D

VENDOR DRAWINGS



APPENDIX D – VENDOR DRAWINGS

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

Donel Systems Don Wilen (516) 876-8400

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: [email protected]

FreeFlight Systems 3700 Interstate 35 Waco, TX 76706 254-662-0000

Todd Ellison, Sales Engineer

Hollingsead International Sante Fe Springs, CA 213 921-3436

IDD Aerospace Redmond, WA 425 885-4353

ITT Cannon Santa Ana, CA 714 557-4700

Kollsman CIC Kollsman @ 603-889-2500 Cheryl Colby @ 603-886-2298



Korry Electronics 901 Dexter Avenue North Seattle, WA Attention: Airline Sales 206 281-1300 800 257- 8921

For orders and AOG requirements, contact: Sonya Cordova

206 281-3567 email: [email protected] fax: 206 281-3576 SITA: SEAKEXD

For engineering inquiries, contact: Bob Jacques

Airline Business Manager 206 281-3584 email: [email protected] fax: 206 273-4128

Tom Howard Airline Business Manager 206 281-1458 email: [email protected] 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 [email protected]

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 [email protected] 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



D 1.1 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



D 1.2 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.



TABLE 1

Table 1.A. (Teflon ® Jacketed RF Coax) (High Temp)

Cable Type

P/N

Loss @ 1600 Mhz

Per 100 ft

O.D.

(inches)

Bend Radius

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

P/N

Loss @ 1600 Mhz

Per 100 ft

O.D.

(inches)

Bend Radius

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”



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



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



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

Installation Considerations:

Meeting the specifications when faced with a long cable run could be challenging at some times. Solutions

typically are found when combining a Low Loss Cable (large OD) for the majority of the run with a “pig tail” at

the box or antenna sides. The “pig tail” cable will have a small OD, and will be very flexible to make the

installation in difficult areas easier. Please use the Tables above for additional information. You can also

call EMTEQ’s knowledgeable staff at the below numbers to help in the configuration and meet your

requirements.

EMTEQ, Inc.

S84 W18693 Enterprise Drive

Muskego, WI 53150

(888) 679-6170 Toll Free

(262) 679-6170

Fax: (262) 679-6175

e-mail: [email protected]



D 1.3 Aerospace Optics

Aerospace Optics Inc.

Aerospace Optics Inc. is pleased to support the Honeywell EGPWS/TAWS team with our line of Vivisun LED

lighted switches and indicators. We would welcome the opportunity to assist with your installation and

address your Honeywell EGPWS/TAWS lighting requirements.

LED Lighting

The Honeywell EGPWS/TAWS systems offer state-of-the-art performance. Accordingly, several recent

innovations in LED cockpit lighting have emerged which truly complement the performance of the Honeywell

Systems. Traditionally, lighted cockpit switches have used incandescent lamps which are known for the

excessive face cap temperatures they generate. The lamps are also subject to high failure rates which

degrades sunlight readability and creates reliability concerns. LED lighting resolves each of these limitations

as they consume less than half the power of typical incandescent lamps and offer life-of-the-aircraft

reliability. However, the use of LED lighting also has a number of additional challenges, which can quickly

dilute their utility.

When using LED lighting in the past, sunlight readability and viewing angles were limited and uniform

dimming required special pulse width modulation. Additionally, unprotected LEDs were susceptible to

damage from transients and voltage spikes from severe electrical environments as defined in RTCA/DO-

160D. However, today, with the evolution of LED technology and innovative design techniques, it is possible

to take advantage of the efficiencies afforded by LEDs while continuing to meet the lighting and

environmental requirements of aircraft design.

The Vivisun LED resolves each of these challenges including DO-160D compliance and standard voltage

controlled dimming. LEDs are the lighting source for the future and the ideal compliment to the Honeywell

EGPWS/TAWS Systems.

Please feel free to contact the Aerospace Optics Technical Sales Team for assistance in addressing the use

of LED lighted switches and indicators.

Aerospace Optics Inc.

3201 Sandy Lane

Fort Worth TX, 76016

1-(888)VIVISUN- (848-4786) Toll Free

Fax (817) 654-3405

www.vivisun.com

e-mail : [email protected]



D 1.4 StacoSwitch

StacoSwitch

As a supplier of high reliability switches and indicators for avionics since 1958, StacoSwitch is proud to be

integrated with many Honeywell products and divisions. Through our relationship with EDMO Distributors in

Spokane, WA, we supply AV17 kits that include all the switches, annunciators, and crimp pins needed to

complete the installation of your Honeywell EGPWS (TAWS) system. These kits meet all lighting and color

requirements in the shortest and lightest switch and indicator units available on the market. EDMO stocks

these kits and can even generate customized legend and color combinations with extremely fast delivery,

usually within a couple days.

StacoSwitch can also provide solutions to most switch needs that may arise, such as LED lighting, Night

Vision (NVIS) compatibility, EMI/RFI shielding, watertight seals, Digital Dimming Modules that can dim both

incandescent and LED lights with consistency, pushbutton guards, and customized-legend switch and

indicator assemblies that can be packaged into impressive matrix mounts.

Please check out our full line of products at www.stacoswitch.com. It includes all the detailed information to

help answer any questions you may have during an installation and also a link to EDMO.

Contact Information:

Dan Sugg – Vice President of Sales [email protected] StacoSwitch

1139 Baker Street Costa Mesa, CA 92626

Phone: (714) 549-3041 Fax: (714) 549-0930 www.stacoswitch.com



APPENDIX E

INTERFACE DESCRIPTION DOCUMENT



APPENDIX E - INTERFACE DESCRIPTION DOCUMENT

1.0 PART NUMBER

This document is the Interface Description for the MKXXII Helicopter Enhanced Ground Proximity Warning System (EGPWS) part number 965-1595-0XX. The MK XXII EGPWC 10 digit part number will identify the configuration of the EGPWC as follows:

965-1595-XXX (example 965-1595-020)

XXX = Application Software (including Configuration Software)

The Terrain Database (including the Envelope Modulation Database) Version is not identified in the 10-digit part number but with a separate identifier on the nameplate. All modification changes not affecting form, fit or function will be identified via “mod dots”. The digits identifying the Application software will match the respective version number of the Application software.

2.0 PURPOSE

This Appendix describes all of the system external interfaces for the MK XXII Enhanced Ground Proximity Warning System (EGPWS).

3.0 SYSTEM OVERVIEW

For more information please refer to the EGPWS Product Specification document 965-1595-601.

4.0 ELECTRICAL INTERFACE

4.1 INTRODUCTION

The MK XXII EGPWS provides electrical interfaces for aircraft systems and to support maintenance functions. The interfaces are made via the front panel aircraft interface connectors, front panel maintenance/test port and front panel LED’s. A TNC coaxial connector is located on the front panel for the internal GPS receiver in the 965-1595-0XX MK XXII EGPWC. The following sections describe the types of electrical interfaces provided in the EGPWC. See Section E 5 for the specific interface configuration capabilities of the MK XXII EGPWS.

4.2 SIGNAL INTERFACES

This section identifies and describes the number and characteristics of each interface type provided in the front panel aircraft interface connectors. The aircraft interface connectors are defined as P1 (78 pins) and P2 (50 pins). Section E 7 identifies the connector pin assignments. The signal mnemonic for each signal in Section E 7 is included in the following sections. All synchro inputs are brought in as three or five wire devices. No two wire absolute AC signals are available. All analog inputs provide broken wire detection on all input signal legs. Unless otherwise stated, the “Maximum reverse fault current” is defined as the current resulting from an internal component failure, with the input signal at zero volts.

4.2.1 GROUNDS

Chassis Ground Used for redundant metal connection. This pin is internally connected to DC Ground.

Pin Assignment (Signal Mnemonic): J1-42, J1-53 (GND)

DC Ground For discrete inputs and lamp driver outputs. These pins are also internally connected to Chassis Ground.

Pin Assignment (Signal Mnemonic): (same as +28 VDC Return)

J1-41, J1-61

(PWR_L)

NOTE: All analog signals are differential input.



4.2.2 PRIMARY POWER INPUT

Nominal Input 28 VDC Normal Voltage Range 22.0 to 30.3 VDC Normal Surge Voltage Range 15 – 40VDC (30 msec) Abnormal Voltage Range 20.5 to 32.2 VDC Abnormal Surge Voltage Range 37.8 VDC (1sec); 46.3 VDC (100 msec) Normal Frequency Range not applicable Frequency Transients not applicable Power Requirements 9 Watts - No Warnings

+7 Watts with warning voice over 8 speaker +3 Watts with Internal GPS (includes antenna power)1 +49 Watts (typical) with heater blanket on2

Recommended Power Control Device 3 Amp delayed action circuit breaker. Pin Assignment (Signal Mnemonic):

+28 VDC Input +28 VDC Return

J1-40, J1-60 J1-41, J1-61

(PWR_H3) (PWR_L3)

1Based on the Honeywell GPS Pxpress card specification. 2The heater blanket turns on at temperatures -23 C and turns off at temperatures -20 C. 3Note that this is not a floating input. +28 VDC must be applied to both PWR_H and +28 VDC Return to

both PWR_L inputs.

4.2.3 DC ANALOG INPUTS

Unless otherwise specified, Input Signal accuracy is 1% linearity +0.1% full scale offset.

4.2.3.1 RADIO ALTITUDE

Quantity 1 Input Impedance, each leg > 83 K Maximum Reverse Fault Current < 200 A Signal Range 0 to 2500 feet Input Voltage Range (VRA) 37.7V VRA -2.5V Conversion Range (Vc) 29.7V Vc -0.4V Input Filter 0.1 Second Low Pass, 10% Broken Wire Detect Input will be biased to less than -50 feet Pin Assignment (Signal Mnemonic):

Signal (+) Return (-)

J1-64 J1-45

(RALT_H) (RALT_L)

4.2.3.2 LOW LEVEL GLIDESLOPE

Quantity 1 Input Impedance, each leg > 2.5 M Reverse Fault Current < 6.2 A Signal Range 12 Dots Input Voltage Range 0.9VDC Input Filter 0.1 Second Low Pass, 10% Input Type Differential Common Mode Voltage Range (VCM) 11V VCM -2V Broken Wire Detect Input will be biased less than -15 dots Pin Assignment (Signal Mnemonic):

+Up, Below Beam, Fly Up +Down, Above Beam, Fly Down

J1-65 J1-46

(GSDEV_H) (GSDEV_L)



4.2.3.3 LOCALIZER DEVIATION OR LOW LEVEL GLIDESLOPE VALIDITY

This input can be configured as either a low level glideslope valid, or as a localizer deviation input. Installations that only have the low level validity signal for glideslope cannot activate the analog localizer input. See section 5.3.9 for more information.

Quantity 1 Input Impedance, each leg > 2.5 M Reverse Fault Current < 6.2 A Input Filter 0.1 Second Low Pass, 10% Input Type Differential Common Mode Voltage Range (VCM) 11V VCM -2V

When used as a validity input: Pin Assignment (Signal Mnemonic):

+ Flag - Flag

J1-30 J1-10

(GS_VAL_H) (GS_VAL_L)

Active Voltage Range (Logic True) +160 to +840 mVDC Inactive Voltage Range (Logic False) 0 to 50 mVDC Broken Wire Detect Input will be biased less than -1 VDC

When used as a localizer input: Pin Assignment (Signal Mnemonic):

CRS DEV + Fly Right CRS DEV + Fly Left

J1-30 J1-10

(LCDEV_H) (LCDEV_L)

Signal Range Input Voltage Range

12 Dots 0.9VDC

Broken Wire Detect Input will be biased less than -15 dots

4.2.3.4 BAROMETRIC ALTITUDE

Quantity 1 Input Impedance, each leg > 83 K Reverse Fault Current < 200 A Input Voltage Range -0.18VDC to +15VDC Input Filter 0.1 Second Low Pass, 10% Input Type Differential Broken Wire Detect Input will be biased less than -3000 feet Pin Assignment (Signal Mnemonic):


J1-62 J1-43

(ALT_H) (ALT_L)

4.2.3.5 OUTSIDE AIR TEMPERATURE

Quantity 1 Input Impedance, each leg > 100 K Reverse Fault Current < 200 A Input Voltage Range +0.3 VDC to +0.6VDC Input Filter 0.1 Second Low Pass, 10% Input Type Differential Broken Wire Detect Input will be biased less than -80 C Pin Assignment (Signal Mnemonic):


J1-63 J1-44

(OAT_H) (OAT_L)

NOTE: For temperature probe voltage reference see section 4.2.11.



4.2.3.6 TORQUE INPUTS - DC

Quantity 2 Input Impedance, each leg > 83 K Reverse Fault Current < 200 A Input Voltage Range 5 VDC Input Filter 0.1 Second Low Pass, 10% Input Type Differential Broken Wire Detect Input will be biased less than -6 VDC Pin Assignment (Signal Mnemonic):

#1 Signal (+) #1 Return (-) #2 Signal (+) #2 Return (-)

J1-26 J1-27 J1-66 J1-47

(TORQUE_1H) (TORQUE _1L) (TORQUE _2H) (TORQUE _2L)

4.2.4 AC ANALOG INPUTS

Unless otherwise specified:

Input Impedance: X leg > 140 K Input Impedance: Y leg > 140 K Input Impedance: Z leg > 140 K Maximum Reverse Fault Current < 200 A Input Voltage Range 11.8 VACRMS ± 20% (leg to leg) Accuracy 2.5% linearity + 0.1% full scale offset

4.2.4.1 SYNCHRO ROLL ATTITUDE

Quantity 1 Synchro Angle Range ±80 deg Reference Voltages Not Required Pin Assignment (Signal Mnemonic):

X leg Y leg Z leg

J1-1 J1-21 J1-2

(SYN_1X) (SYN_1Y) (SYN_1Z)

4.2.4.2 SYNCHRO MAGNETIC HEADING

Quantity 1 Synchro Angle Range ±180 deg Reference Voltages 26 VACRMS ± 20% (see 4.2.5) Pin Assignment (Signal Mnemonic):

X leg Y leg Z leg

J1-22 J1-23 J1-3


4.2.4.3 SYNCHRO PITCH ATTITUDE

Quantity 1 Synchro Angle Range ±80 deg Reference Voltages Not Required Pin Assignment (Signal Mnemonic):

X leg Y leg Z leg

J1-5 J1-7 J1-6




4.2.4.4 SYNCHRO TORQUE

Quantity 2 Reference Voltages 26 VACRMS ± 20% (see 4.2.5) Pin Assignment (Signal Mnemonic):

#2 X leg #2 Y leg #2 Z leg #3 X leg #3 Y leg #3 Z leg

J2-1 J2-2 J2-18 J2-19 J2-20 J2-3

(SYN_4X) (SYN_4Y) (SYN_4Z) (SYN_5X) (SYN_5Y) (SYN_5Z)

4.2.5 SIGNAL TIMING REFERENCE INPUTS

These inputs accept 400 Hz AC signals, and detect the “zero crossings” of these signals. These zero crossings are used to time the conversion and input of AC signals. Absolute voltage level of these signals is not measured, but it must be within the range specified below. Voltage below the specified minimum value may result in intermittent or “jittery” zero cross detection.

Timing reference signals are required for input of most AC devices (not required for pitch and roll). These references can be brought into the appropriate timing reference input, or the system can be configured to derive a reference from the signal. Timing reference signals are specified for synchro inputs requiring a range greater than 80 degrees. Inputs requiring less (i.e., Roll Attitude) are configured to derive a reference from the synchro input signal and do not require a separate reference voltage input.

Quantity 2 Input Impedance > 140K each line to signal ground Maximum Reverse Fault Current < 120 A A/C Input Signal Frequency Range 400 Hz, 10% Maximum Input Voltage Swing (differential) 50V between input legs Maximum Input Voltage Swing (ref. to Gnd) 50V from any leg to signal ground Input Hardware Filtering None Minimum Input Voltage < 0.5 VAC Pin Assignment (Signal Mnemonic):

26VAC Reference #1 H 26VAC Reference #1 C 26VAC Reference #2 H 26VAC Reference #2 C

J1-4 J1-24 J2-34 J2-35

(26REF_1H) (26REF_1L) (26REF_2H) (26REF_2L)

4.2.6 ARINC 429/575 DIGITAL SERIAL BUS INPUTS

Quantity 8 Format DITS, ARINC 429/575 Low or High speed 1 Low Speed Data Rate 12.0 KBPS to 14.5 KBPS High Speed Data Rate 100 KBPS 1% Direction of Information Flow Type ‘A’ broadcast for ARINC 429/575 Word/Frame Structure Type ‘B’ 32 bit words consisting of 8 bits label

and 24 bits data/status Data definition Refer to Section 6 of the Interface Control

document

1 The bus speed is defined in the configuration selection, see Section 5 for details.



Channel Receive #1 A leg Receive #1 B leg Receive #2 A leg Receive #2 B leg Receive #3 A leg Receive #3 B leg Receive #4 A leg Receive #4 B leg Receive #5 A leg Receive #5 B leg Receive #6 A leg Receive #6 B leg Receive #7 A leg Receive #7 B leg Receive #8 A leg Receive #8 B leg

Pin Assignment J2-37 J2-36 J2-39 J2-38 J2-41 J2-40 J2-25 J2-8 J2-21 J2-4 J2-22 J2-5 J2-23 J2-6 J2-24 J2-7

(Signal Mnemonic) (429/422RX_1A) (429/422RX_1B) (429RX_2A) (429RX_2B) (429RX_3A) (429RX_3B) (429RX_4A) (429RX_4B) (429RX_5A) (429RX_5B) (429RX_6A) (429RX_6B) (429RX_7A) (429RX_7B) (429RX_8A) (429RX_8B)

SSM/SDI Definition:

Refer to Section 6 of this document

4.2.7 RS-232 / RS-422 DIGITAL SERIAL BUS INPUTS

Two full duplex RS-232 / RS-422 buses and a third RS-422 receiver are provided at the aircraft interface connectors. The RS-422 transceivers are electrically multiplexed with the RS-232 transceivers, and are selected through the configuration process. The third RS-422 receiver is electrically multiplexed with the ARINC 429 channel 1 receiver. The maintenance RS-232 bus is described in section 4.2.18.1. The specific characteristics (data rate, parity, data bits, stop bits) is defined in the configuration selection, see Section 5 and 6 for details. RS-422 cable termination will not be required for typical applications, see TIA/EIA-422-B Annex A.

The RS-232 bus meets the characteristics specified in RS232C and supports the following characteristics:

Data Rate 1200, 2400, 4800, 9600, 19200 or 38400 bits/Sec Parity None, Odd or Even Data bits 7 or 8 Stop bits 1 or 2 Maximum Recommended Cable Length 15 meters Data definition

Refer to Section 6 of this document

The RS-422 bus meets the characteristics of TIA/EIA-422-B and supports the following characteristics:

Data Rate 1200, 2400, 4800, 9600, 12000, 19200 or 38400 bits/Sec Maximum Transceivers on Bus 20 Receiver Input Impedance 12 K Word/Frame Structure Refer to Section 6 of this document Data definition Refer to Section 6 of this document



4.2.7.1 GPS RS-232 DIGITAL SERIAL BUS (SERIAL PORT 3)

One port is provided for use with external or internal RS-232 GPS interfaces. This port is common with the GPS RS-422 port described in Section 4.2.7.2 and can only function as a RS-232 interface or a RS-422 interface but not both.

Pin Assignment (Signal Mnemonic): Transmit Receive Common

J2-45 J2-29 J2-28

(GPS_TXA) (GPS_RXA) (GND)

NOTE: If the internal GPS configuration (Cat. 3 ID 2) is used then the receive input will be non-functional.

4.2.7.2 GPS RS-422 DIGITAL SERIAL BUS (SERIAL PORT 3)

One port is provided for use with external GPS interfaces. This port is common with the GPS RS-232 port described in Section 4.2.7.1 and can only function as a RS-232 interface or a RS-422 interface but not both.

Pin Assignment (Signal Mnemonic): Transmit A leg Transmit B leg Receive A leg Receive B leg

J2-45 J2-46 J2-29 J2-12

(GPS_TXA) (GPS_TXB) (GPS_RXA) (GPS_RXB)

NOTE: If the internal GPS configuration (Cat. 3 ID 2) is used then the receive input will be non-functional.

4.2.7.3 AIR DATA RS-232 DIGITAL SERIAL BUS (SERIAL PORT 2)

One port is provided for use with Air Data computer or Static Pressure Sensor interfaces. This port is common with the Air Data RS-422 port described in Section 4.2.7.4 and can only function as a RS-232 interface or a RS-422 interface but not both.

Pin Assignment (Signal Mnemonic): Transmit Receive Common

J2-27 J2-11 J2-28

(ADC_TXA) (ADC_RXA) (GND)

4.2.7.4 AIR DATA RS-422 DIGITAL SERIAL BUS (SERIAL PORT 2)

One port is provided for use with Air Data computer or Static Pressure Sensor interfaces. This port is common with the Air Data RS-232 port described in Section 4.2.7.3 and can only function as a RS-232 interface or a RS-422 interface but not both.

Pin Assignment (Signal Mnemonic): Transmit A leg Transmit B leg Receive A leg Receive B leg

J2-27 J2-44 J2-11 J2-10

(ADC_TXA) (ADC_TXB) (ADC_RXA) (ADC_RXB)

4.2.7.5 SCI RANGE RS-422 DIGITAL SERIAL BUS (SERIAL PORT 1)

Two ports are provided for use with the SCI range bus interfaces. Port 1 is common with the ARINC 429 channel 1 port described in Section 4.2.6 and can only function as a RS-422 interface or an ARINC 429 interface but not both. Port 2 is common with the RS-232 port described in Section 4.2.7.4 and can only function as a RS-422 interface or an RS-232 interface but not both.

Pin Assignment (Signal Mnemonic): Receive A leg Receive B leg Receive A leg Receive B leg

J2-37 J2-36 J2-11 J2-10

(429/422RX_1A) (429/422RX_1B) (429/422RX_2A) (429/422RX_2B)

Note: SCI Display Range RS-422 bus A and B legs are reversed from ARINC 429.



4.2.7.6 TORQUE INPUTS RS-422 DIGITAL SERIAL BUS (SERIAL PORT 1)

Two ports are provided for use with the Torque Input bus interfaces. Port 1 is common with the ARINC 429 channel 1 port described in Section 4.2.6 and can only function as a RS-422 interface or an ARINC 429 interface but not both. Port 2 is common with the RS-232 port described in Section 4.2.7.4 and can only function as a RS-422 interface or an RS-232 interface but not both.

Pin Assignment (Signal Mnemonic): Receive A leg Receive B leg Receive A leg Receive B leg

J2-37 J2-36 J2-11 J2-10

(429/422RX_1A) (429/422RX_1B) (429/422RX_2A) (429/422RX_2B)

Note: Torque Inputs RS-422 bus A and B legs are reversed from ARINC 429.

4.2.8 DISCRETE INPUTS

Discrete signals are intended for remote switching through the aircraft, and are therefore subject to being connected to other signals, and are also subject to transient voltage conditions. For these reasons, the following rules apply to each input, unless otherwise stated.

Each input is capable of withstanding voltage transients of 600VDC for 10 s and 50VDC continuously, without damage. The +28 VDC discrete(s) are internally biased via a pull down resistor, and are externally pulled up to +28VDC when active. The characteristics of each +28 VDC discrete input are as follows:

+28 VDC Discrete Characteristics

Quantity 13 Active Voltage Range (Logic True) > +17 VDC Inactive Voltage Range (Logic False) < +4.4 VDC Diode Isolation None Input Impedance > 95 K Maximum Fault Current < 60 A Pin Assignment (Signal Mnemonic):

See specific discrete in Category 13 (28V_DISC_xx)

The Ground discrete(s) are internally biased via a pull up resistor, and are externally pulled down to ground when active. The characteristics of each Ground discrete input are as follows:

Ground Discrete Characteristics

Quantity 15 Active Voltage Range (Logic True) < +3 VDC Inactive Voltage Range (Logic False) > 100 K (to ground) or > +4.5 VDC Diode Isolation Each input is diode isolated to prevent current sinking Input Impedance > 10 K Maximum Fault Current < 100 A (at +28 VDC input) Pin Assignment (Signal Mnemonic):

See specific discrete in Category 13 (GND_DISC_xx)

4.2.9 CONFIGURATION MODULE INTERFACE

System configuration is defined via a Configuration Module, which resides in the MK XXII EGPWS aircraft wiring harness backshell. The EGPWS Configuration Module contains the aircraft interface and functionality definitions specific to the installed aircraft. Refer to Section 5 for interface and functional definitions by category. Note that both Configuration Module part numbers, 700-1710-001 and 700-1710-020, have identical electrical interfaces.

Electrical Characteristics Refer to the EGPWS Configuration Module specification Data definition Refer to the EGPWS Configuration Module specification



Pin Assignment (Signal Mnemonic): Clock Master Data Out Master Data In Configuration Module Select Configuration Module +5VDC Configuration Module +5VDC Return

J2-32 (RED) J2-50 (BLK) J2-33 (ORN) J2-49 (WHT) J2-17 (VIO) J2-16 (BLU)

(SPICLK) (SPIMOSI) (SPIMISO) (SPISEL_CM#) (SC_PWR) (GND)

Output to Config Module Logic Low (nominal) Logic High (nominal) EMK 22 EMK 22 Clock Out 0 V 5 V Master Data Out 0 V 5 V Config Module Select 0 V 5 V

INTERFACE OF EGPWS OUTPUTS TO CONFIGURATION MODULE

4.2.10 GPS ANTENNA INPUT

A GPS input connector is available on the front of the MK XXII EGPWS (965-1595-0XX).

Quantity 1 Cable Length/Allowed Signal Loss Not more than 8 dB, at 1575.42 MHz, for cable and

connector loss from antenna to unit. Connector Type TNC Low Level DC on RF Output +5 VDC ±5%, 50 mAmps maximum, Shield Ground. Pin Assignment (Signal Mnemonic):

GPS ANT (COAX)

4.2.11 OAT VOLTAGE REFERENCE OUTPUT

This output is an accurate voltage source for 500 resistive temperature sensors.

Quantity 1 Output Voltage 5.000 VDC 10 mVDC (no load) Nominal Load 500 Pin Assignment (Signal Mnemonic):

J1-25 (OAT_REF)

NOTE: This output has a source impedance of 4.42 K, 0.1%.

4.2.12 LAMP DRIVER OUTPUTS

The MK XXII EGPWS supports two kinds of Ground/Open discrete outputs used to signal various discrete conditions. Monitor outputs are used to signal failure conditions for the MK XXII EGPWS. Monitor outputs default to an active state when there is a failure or if power is removed from the MK XXII EGPWS. The other Lamp Driver outputs are used to signal the alert or mode control status of the MK XXII EGPWS.

Short-term current limit protection is provided on all drivers for output shorting conditions. Ground going output discrete(s) may be connected together to produce a “wired OR” function for the active low state of the signals. If output discrete(s) are “wire OR’d” then diodes must be installed for isolation.

4.2.12.1 MONITOR OUTPUT CHARACTERISTICS

Quantity 3 Type of Output: Switch Closure to Ground Max. Open Circuit Voltage: 30 VDC Current Limit 1 A Potential Across “Closed” Switch: 2.5 VDC Max Pin Assignment (Signal Mnemonic): See specific output in Category 13 (MON_OUT_xx)

NOTE: Intended to operate with +28VDC lamp sources and will not operate with +5VDC lamp sources.



4.2.12.2 DISCRETE OUTPUT CHARACTERISTICS

Quantity 9 Type of Output: Switch Closure to Ground Max. Open Circuit Voltage: 30 VDC Current Limit 500 mA (typical) Potential Across “Closed” Switch: 1 VDC Max Pin Assignment (Signal Mnemonic): See specific output in Category 13 (DISC_OUT_xx)

NOTE: Intended to operate with +28VDC pullup external to the EGPWS.

4.2.13 AUDIO OUTPUTS

There are two audio outputs provided, one 8-ohm output and one 600-ohm output. There are several possible volume levels available with the MK XXII EGPWS as shown below, with maximum output being 2.45W (8) or 20mW (600). The actual audio level output by the EGPWS is dependent on several items:

Selection of nominal alert audio volume level (max, -6, -12, -18 or -24 dB) via Category 14. (see Section 5.3.14)

If a ‘soft’ Glideslope alert is being issued (given 6 dB below nominal alert volume level).

If a Self Test is in progress, alerts are given 6 dB below nominal alert volume level.

Selection of Mode 6 Low Volume Discrete lowers callout volume by 6 dB (see Section 5.3.13).

4.2.13.1 HIGH LEVEL (SPEAKER) AUDIO OUTPUT

The 8-ohm output is capable of driving a speaker directly but can also be used to drive other devices with equal or higher impedance.

Quantity 1 Maximum Power Output 2.45 Watts Nominal Nominal Output Impedance 8 Load Impedance 8 or greater Number of Available Power Output Levels 5 selectable levels excluding the Mode 6 Audio

Reduction function. Pin Assignment (Signal Mnemonic):


J1-70 J1-71

(AUD_HL_H) (AUD_HL_L)

4.2.13.2 LOW LEVEL (INTERPHONE) AUDIO OUTPUT

The 600-ohm output is capable of driving one 600-ohm load at the specified level (or at a reduced level). This output is primarily designed for headphones and interphone systems.

Quantity 1 Nominal Output Impedance 600 10% Maximum Single Channel Power Output 20 mW Nominal () Available Power Output Levels 5 Selectable levels excluding the Mode 6 Audio

Reduction function. Pin Assignment (Signal Mnemonic):


J1-75 J1-74

(AUD_LL_H) (AUD_LL_L)



4.2.14 ARINC DIGITAL SERIAL OUTPUT BUSES

4.2.14.1 ARINC 429 OUTPUT BUS

The ARINC 429 output buses are defined in the terrain display select Section 5.3.6, output 429 bus group.

Quantity 2 Format DITS, ARINC 429 Low Speed Data Rate 12.0 KBPS to 14.5 KBPS High Speed Data Rate 100 KBPS 1% Direction of Information Flow Type ‘A’ broadcast for ARINC 429 Word/Frame Structure Type ‘B’ 32 bit words consisting of 8 bits label and 24

bits data/status Data definition See Section E-6. Pin Assignment (Signal Mnemonic):

Bus #1 (A leg) Bus #1 (B leg) Bus #2 (A leg) Bus #2 (B leg)

J2-43 J2-42 J2-26 J2-9

(429TX_1A) (429TX_1B) (429TX_2A) (429TX_2B)

4.2.14.2 ARINC 453 OUTPUT BUS

Quantity 2 Format 1600 bit Manchester BI-phase per ARINC 708A Data Rate 1 Mb per second Word/Frame Structure See 060-4303-000 Data definition See 060-4303-000 Pin Assignment (Signal Mnemonic):

Bus #1 (A leg) Bus #1 (B leg) Bus #2 (A leg) Bus #2 (B leg)

J1-58 J1-59 J1-56 J1-57

(KCPB_1A) (KCPB_1B) (KCPB_2A) (KCPB_2B)

4.2.15 FRONT PANEL TEST INTERFACE

The MK XXII EGPWS provides a 15 pin (double density, D-Sub) test connector on the front panel, which supports interfaces for various test and maintenance functions. This connector provides the following interfaces.

4.2.15.1 RS-232 MAINTENANCE PORT (SERIAL PORT 4)

One port is provided which meets the characteristics specified in RS232C. This bus can be used to read internal data from the MK XXII EGPWS for both bench, and aircraft testing or transmitting configuration data for selected EGPWS interfaces and options.

Baud Rate 19,200 Parity None Data bits 8 Stop bits 1 Maximum Recommended Cable Length 15 meters Pin Assignment (Signal Mnemonic):

Transmit Receive Common

J3-4 J3-3 J3-1

(RS232TXD_MON) (RS232RXD_MON) (GND)



4.2.15.2 PCMCIA / SMARTCABLE PORT

One port is provided which meets the Motorola SPI characteristics. The PCMCIA / SmartCable interface allows for both the uploading, and downloading of internal MK XXII EGPWS information. Using this interface system, software and databases can be updated. Control of the upload/download process is accomplished by connection of the SmartCable to the MK XXII EGPWS front panel test connector and insertion of the PCMCIA card. LEDs are provided on the SmartCable for PCMCIA interface operation. The PCMCIA / SmartCable is not intended as an on-line/in-flight storage medium and must be removed after completion of the upload/download operation.

Electrical Characteristics Refer to the Motorola SPI specification Data definition Refer to the Motorola SPI specification Maximum Recommended Cable Length 2 meters Pin Assignment (Signal Mnemonic):

Clock Master Data Out Master Data In SmartCable Select SmartCable +5VDC SmartCable +5VDC Return PCMCIA Card Present SmartCable Ground

J3-7 J3-9 J3-8 J3-10 J3-6 J3-1 J3-2 J3-12, -13, -14

(SPICLK) (SPIMOSI) (SPIMISO) (SPISEL_SC#) (SC_PWR) (GND) (CARD_PRES#) (GND)

NOTE: SmartCable +5VDC Return is common with RS-232 Maintenance Port common.

4.2.15.3 GSE PRESENT DISCRETE INPUT

A discrete input for test and Ground Support Equipment is provided. Grounding this pin indicates to the EGPWS that test or Ground Support Equipment is connected to the computer.

Active Threshold Voltage (Logic True) < 0.8 VDC Inactive Threshold Voltage (Logic False) > 2.0 VDC Input Impedance > 20 K Maximum Fault Current < 500 A Pin Assignment (Signal Mnemonic): J3-11 (GSE_PRES#)

4.2.15.4 FRONT PANEL STATUS INDICATORS

The MK XXII EGPWC front panel provides three LEDs for indicating system and LRU status. A yellow LED labeled “EXTERNAL FAULT” is activated when a signal fault external to the MK XXII EGPWC is detected. A green LED labeled “COMPUTER OK” is activated when the MK XXII EGPWC itself is okay. A red LED labeled “COMPUTER FAIL” is activated when the MK XXII EGPWS has detected an internal computer fault.

Refer to Product Specification 965-1595-601 for a detailed discussion of status indications, recommended maintenance actions, Self-Test activation and response.



5.0 AIRCRAFT APPLICATION DATA

This section describes the MK XXII EGPWS interfaces for aircraft applications. Section 5.1 is a listing of the selection categories defining the various aircraft sensor interfaces and EGPWS functional options. Section 5.2 describes how the Category ID’s are selected and programmed for the interface to aircraft sensors and EGPWS functional options. Section 5.3 and its sub-sections define the specific aircraft interfaces available for the MK XXII EGPWS.

5.1 CONFIGURATION TYPES

The selection of the basic interfaces to the MK XXII EGPWS can be found in the following categories:

Category 1 Aircraft / Mode Type Select Category 2 Air Data Input Select Category 3 Position Input Select Category 4 Altitude Callouts Category 5 Audio Menu Select Category 6 Terrain Display Select Category 7 Options 1 Select Category 8 Radio Altitude Input Select Category 9 Navigation Input Select Category 10 Attitude Input Select Category 11 Heading Input Select Category 12 Windshear Input Select Category 13 I / O Discretes Select Category 14 Audio Output Level Category 15 Autorotation Threshold Category 16 Torque Input Select Category 17 Options 2 Select Category 18 Options 3 Select Category 19 Options 4 Select

5.2 CONFIGURATION SELECTION

Each category provides information relative to aircraft interfaces or EGPWS functional options required or used for EGPWS operation. Each category must be defined for the specific aircraft application according to the available aircraft sensors or equipment and the intended EGPWS function. The choices provided are available in each category identified by an “ID” number. The ID number is selected for each category and is used to load the selected configuration in a configuration module installed in the aircraft wiring (physically part of one of the EGPWC mating connectors). For example, selecting Category 2, ID 1 defines the Air Data Input as ARINC 429 per Table 5.3.2-1 in Category 2. With this ID programmed into the configuration module the EGPWC will look for and use the interface defined for this ID. Table 3 can be used to record the selected ID for each category for later reference when programming the configuration module. This programming is accomplished using a programming software tool available from Honeywell or generating a data text string and transferring this data (in either case) via the EGPWC RS-232C to the configuration module (see Section 4.2.18). Once programmed, the configuration is available and read by any installed EGPWC on power up.

LIMITATIONS: The described use of the configuration module provides for maximum flexibility in selection of input sensors and output behavior. Every attempt has been made to avoid conflicts arising between categories and to reflect the known configurations of aircraft. However in the case of input sensors it should not be construed that all combinations are valid configurations. There may be configurations not supported by the EGPWS software configuration building process (which will cause the EGPWS to fail in an obvious manner). In general you cannot have redundancy through the mixing of analog and digital sources; however redundant digital signals on different buses are permissible. As it is not practical to verify all possible sensor combinations, verification of particular sensor combinations is part of the installation certification process. If you intend to implement a sensor configuration not currently identified in Section 5.3, please contact Honeywell or an authorized dealer/installer.



Table 3 Category ID Selection procedure

Step (Category)

Signal Selection

Instruction Ident No.

1

Selects:

a) Aircraft / Mode Type

Using Table 5.3.1, and any sub-tables contained within, locate the Aircraft / Mode Type.

Record the Ident (ID No.) on the space available on Ident column of this table.

ID #

2

Selects:

a) Air Data Source

Using Table 5.3.2, and any sub-tables contained within, locate the desired Air Data signal type.


ID #

3

Selects:

a) Position Source

Using Table 5.3.3, and any sub-tables contained within, locate the desired Position signal type.


ID #

4

Selects:

a) Altitude Callouts Menu

Using Table 5.3.4 and any sub-tables contained within, locate the desired Altitude Call-Out Menu.


ID #

5 Selects:

a) Audio Menu

Using Table 5.3.5 and any sub-tables contained within, locate the desired Audio Menu type.


ID #

6

Selects:

a) Display Config.

Using Table 5.3.6 and any sub-tables contained within, locate the desired Display indicator type / range bus type.


ID #

7

Selects:

a) TA&D Alternate Pop Up

b) Peaks Mode Enable

c) Obstacle Awareness Enable

d) Bank Angle Enable

e) Weight on Wheels Reversal

f) GPS Altitude Reference

Using Table 5.3.7 and any sub-tables contained within, select the desired True or False condition for TA&D Alternate Pop Up, Peaks Mode Enable, Obstacle Awareness Enable, Bank Angle Enable, WOW Reversal Select, and GPS Altitude Reference type.


ID #

8

Selects:

a) Radio Altitude Source

Using Table 5.3.8, and any sub-tables contained within, locate the desired Radio Altitude and Decision Height signal type.


ID #

9

Selects:

a) Glideslope and/or Localizer Source

Using Table 5.3.9, and any sub-tables contained within, locate the desired Navigation signal type.


ID #



Step (Category)

Signal Selection


10

Selects:

a) Attitude Source

Using Table 5.3.10, and any sub-tables contained within, locate the desired Attitude signal type.


ID #

11

Selects:

a) Magnetic Heading Source

Using Table 5.3.11, and any sub-tables contained within, locate the desired Magnetic Heading signal type.


ID #

12 Selects: Using Table 5.3.12, Windshear is not

available for helicopter applications. Please select ID 0.


ID #

13

Selects:

a) Input Discrete Functions

b) Output Discrete Functions

c) Lamp Format

Using Table 5.3.13, and any sub-tables contained within, locate the desired I / O Discrete type and Lamp Format.


ID #

14

Selects:

a) Audio Output Level

Using Table 5.3.14, and any sub-tables contained within, locate the desired Volume type.


ID #

15 Selects:

a) Autorotation Threshold

Using Table 5.3.15, locate the desired Autorotation Threshold. This Category is used on helicopters only.


ID #

16 Selects:

a) Torque Source

Using Table 5.3.16, and any sub-tables contained within, locate the desired Torque signal type


ID #

17

Selects:

a) Helo Normal Pop-Up Range

b) Helo Low Altitude Pop-Up Range

c) Auto Rotation Callouts

d) Mode 6B always ON enable

e) Normal Terrain Airspeed select

f) Low Altitude Airspeed Select

g) Low Altitude No VFOM Select

Using Table 5.3.17 select the desired Auto Rotation callout menu. In addition, if the selected display supports auto-range then use this category to select the desired Terrain Display Range to be used for auto-ranging during Normal operation and the range to be used during Low-Altitude operation. Select the Mode 6B Always On option (Normally used for Offshore Operation). Select Normal Terrain (Not Tactical select) function use of Airspeed in Lieu of Ground speed for SAR/EMS Operation. Select Low Altitude (Tactical select) function use of Airspeed in Lieu of Ground speed for SAR/EMS Operation. Select Low Altitude No VFOM for No VFOM Bias.


ID #

0



Step (Category)

Signal Selection


18

Selects:

a) Audio Inhibit Time (Minutes)

b) Inhibit All except Minimums type Callout and 100 ft Callout

c) Inhibit All except Minimums type Callout

d) Inhibit includes Too Low Gear

e) Inhibit Altitude Callouts below 50 ft over runway

f) Lower MDA/DH select logic

Using Table 5.3.18 select the desired inhibit time for the Timed Audio Inhibit. Select additional Inhibit options where all audio except the selected Minimums Type Callout and 100 Ft Callout are inhibited, or all audio except the selected Minimums Type Callout is inhibited and/or where the Too Low Gear alert is added to the inhibited message list. Select inhibiting of Altitude Callouts at 50 feet and below when over a runway. Select using the Lower of two MDA/DH Inputs as the Callout Altitude.


ID #

19

Selects:

a) Low Altitude option

b) Mode 2 Terrain inhibit

Using Table 5.3.19 select the desired Low Altitude Option to Inhibit/Enable Mode 1 ‘PULLUP’ and ‘SINKRATE’, Mode 4 ‘TOO LOW GEAR’, Mode 4 ‘TOO LOW TERRAIN’, Forward Looking Terrain Alerting – Look down and enable Peaks Water Priority. In addition, select Mode 2 Inhibit option to inhibit/Enable Mode 2 alerts when Terrain Inhibit switch is activated.


ID #



5.3 CONFIGURATION SELECTION TABLES

Configuration selection is defined by category (or group of functions or inputs). The Category number identifies the subsection where the details are defined. For example Air Data, Category 2, is defined in Section 5.3.2, and Position Input Source, Category 3, is defined in Section 5.3.3.

5.3.1 CATEGORY 1, AIRCRAFT / MODE TYPE SELECT

Category 1 defines the Aircraft Type. The Aircraft Type determines the Warning/Alert Modes Type, Operational Speed Type, Fixed/Retractable Gear Type and Tail Strike Type.

Warning/Alert Modes Type The MK XXII uses helicopter optimized GPWS modes, which are defined in the MK XXII Product Specification 965-1595-601. Mode 1 is inhibited continuously on the S-92 aircraft. The only Mode that varies for the Helicopter types listed below is Mode 4 where the difference is shown in Table 6.2.4.1-1 of the MK XXII Product Specification.

Operational Speed Type Slow speed helicopters are those whose operational speed range is 90 knots and above, and whose approach speed profile is approximately 60 knots. Fast speed helicopters are those whose operational speed range is 100 knots and above, and whose approach speed profile is approximately 70 knots.

Fixed/Retractable Gear Type Category 1 Aircraft Type and Category 5 Audio Menu Select have unique ID’s for Fixed Gear and Retractable Gear aircraft. For Fixed Gear aircraft an ‘inair’ condition will be indicated when the aircraft is greater than 10 feet AGL for more than 1 second. For Retractable Gear aircraft an ‘inair’ condition will be indicated when Weight on Wheels indicates airborne or the aircraft is greater than 10 feet AGL for more than 1 second. A Gear stuck fault will be indicated when the Weight on Wheels indicates “loaded” but gear is up or Weight on Wheels indicates “unloaded” but gear is down and the aircraft is less than 10 feet AGL and pitch is less than a flat pitch threshold.

Tail Strike Type The Tail Strike function provides an aural advisory of impending tail strike. The warning is computed from Radar Altitude and Pitch Angle. Warning boundary parameters are designed to accommodate most airframe geometry’s however some aircraft have unique warning boundaries and some have characteristics that do not require a Tail Strike advisory (like no tail rotar). Tail Strike Type 0 turns off the Tail Strike warning. Tail Strike Types 1 through 4 have additional slope/offset boundaries that make the Tail Strike advisory more or less sensitive. See in the MK XXII Product Specification 965-1595-601 for further details of the Tail Strike advisory.

10 20 30 400

10

20

30

40

50 50

35

11

TAIL STRIKE BOUNDARY

TYPE 2BoundaryLow Tail

PITCH

RA

DIO

ALT

ITU

DE

TYPE 1

Boundary

High Tail

30

TYPE 4BoundaryAW 139

TYPE 3Boundary

S-92



The following table provides ID values for each of the basic helicopter type descriptions. For purposes of selecting an ID, use the “Description” provided in Table 5.3.1 appropriate to the desired variables as given above.

TABLE 5.3.1 AIRCRAFT / MODE TYPE SELECT

ID Aircraft /

Mode Type 1

DESCRIPTION Effectivity

128 128

SLOW

Cruise >90 kts

App 60-90 kts Hover <60 kts

S-76, AS-332, Agusta 109 Retractable Gear, Tail Strike Type 1

-020

129 129 EC-155B, AS-365, HH-65, Bell 430, Agusta 109

Retractable Gear, Tail Strike Type 2 -020

130 130 Bell 407, Bell 412, Bell 212

Fixed Gear, Tail Strike Type 1 -020

131 131 EC-135, Bell 430, Bell 427, AS-355, AS-350


132 132


133 133 MD-900, MD-902


134 134 S-92 3


135 135

FAST

Cruise >100 kts

App 70-100 kts Hover <70 kts

S-92 3 Retractable Gear, Tail Strike Type 3

-024

136 136 S-76, AS-332, Agusta 109


137 137 EC-155B, AS-365, HH-65, Bell 430, Agusta 109


138 138 Bell 407


139 139 EC-135, Bell 430, Bell 427, AS-355, AS-350


140 140


141 141 MD-900, MD-902 2


142 142 SLOW

Retractable Gear, Tail Strike Type 3

-026

143 143


144 144

FAST

Retractable Gear, Tail Strike Type 3

-026

145 145


146 146 EC-225, EC-725

Retractable Gear, Tail Strike Type 1, Gear Down Fault Inhibited -028

147 147 Agusta-Westland AW-139

Offshore operation, Retractable Gear, Tail Strike Type 4 -030

Note 1: The only attitude types in Category 10 that may be used with these aircraft types are those with both pitch

and roll (analog attitude types) or pitch, roll, pitch rate and roll rate (digital attitude types). Note 2: MD-900, MD-902 use Mode 4 type 13, Fixed Gear (Slow). Note 3: For S-92 aircraft Mode 1 was turned off and Mode 6 and Tail Strike type were changed in –022 software

version. Bank Angle type was changed in -024 software version.



5.3.2 CATEGORY 2, AIR DATA INPUT SELECT

The following table provides identification of the Air Data source type. The entry in the Air Data Type corresponds to a table that provides detailed information on the configuration. For example, the details for Air Data Type #2 are found in Table 5.3.2.In this category, only the following signals are defined:

Uncorrected Barometric Altitude in analog and/or RS-422 or ARINC 429 format, and associated validity. Temperature (Outside Air or Static Air) in analog or ARINC 429 format. Corrected Barometric Altitude in ARINC 429 format. Barometric Rate in ARINC 429 format. Computed Airspeed in ARINC 429 format. TABLE 5.3.2 AIR DATA INPUT SELECT

ID Air Data Type Description Effectivity (Table 5.3.2-x)

0 0 Kollsman CIC 04077 Analog – altitude and 500 OAT (Note 3) -020 1 1 ARINC 429 Digital without Corrected Altitude label 204 -020 2 2 ARINC 575 Digital (i.e., Collins ADC-80, 81, 82) -020 3 3 Collins ADS-65 Analog - altitude and 500 OAT (Note 3) -020 4 4 Kollsman CIC 02702 Analog - altitude and 500 OAT (Note 2, 3) -020 5 5 ARINC 429 Digital with Corrected Altitude label 204 -020 6 6 ARINC 429 Digital without Baro Rate label 212 -020

10 10 ARINC 429 Digital with 500 OAT (i.e. Shadin 2000) -020 11 11 Honeywell AZ-241 or AZ-800 with additional OAT

Analog – altitude and 500 OAT (Note 2, 3) -020

12 12 Honeywell AZ-241 OR AZ-800 Analog – altitude and internal constant for OAT (Note 2,3)

-020

14 14 ARINC 429 Digital without Corrected Altitude label 204 High Speed bus

-024

253 253 ARINC 429 Digital (via dual IOC buses). (Note 1) -020 254 254 ARINC 429 Digital (via dual IOC buses). (Note 1) -020

Note 1: IDs 253 and 254 may only be used in conjunction with other IOC bus selections for categories 6, 8, 9, 10, 11, 12, 13 and 16 that use the same ARINC 429 receiver channels and bus speeds.

Note 2: The AZ-800 provides an OAT signal with reference provided by the ADC. This is not compatible with the EGPWS interface. The AZ-241 provides no OAT interface. The customer may either add an additional OAT probe (ID 11) or use the internal constant (ID 12). ID 11 is to be recommended in operations in temperature extremes.

Note 3: ID 0, 3, 4, 11, and 12 may not be used with Radio Altitude type 6 (APN-209).



TABLE 5.3.2-0: AIR DATA INPUT SELECT #0 SIGNAL CONNECTION SUMMARY DATA

Uncorrected Barometric Altitude

(+) = J1-62 (-) = J1-43

Format: DC with Validity Flag Input Type: Basic Fault Designation: BAROMETRIC ALTITUDE FAULT Validity: Barometric Alt Valid (+28V)

Outside Air Temp Total Air Temperature Probe element Excitation: Temp Input (probe element): Ground

5 V = J1-25 (+) = J1-63 (-) = J1-44 GND = J1-53

Format: DC Input Type: Basic Fault Designation: STATIC AIR TEMPERATURE FAULT

OA

T P

RO

BE

ELE

ME

NT

25J1

(5 V Ref)

63

44

Temp In

4.42 K Ohms

53

Voa

t

Chassis Gnd

-+

Note: Nominal 500 Temperature Probe only. Resistance @ 0C: 500 0.6

Connection example: Kollsman CIC Temperature Sensor, P/N 05257 (2 wire). Connect positive lead to both J1-25 and J1-63. Connect negative lead to both J1-44 and J1-53 (Chassis Ground).

Other probes may have three contacts.

Computed Airspeed No Connection Substitute Ground Speed for Airspeed (airspeed is not available with this air data input)

PIN FUNCTION CONNECTION PIN TYPE CHANNEL

DESIGNATION REFERENCE

Polarity/Configuration

Barometric Altitude Validity Discrete (+28V)

J1-9 Input 28V_DISC_08 >+17V = Valid < +4.4V = Invalid

Configuration Data Type Summary Data

Derive Baro Altitude Rate Analog Baro Altitude Rate is derived using Uncorrected Barometric Altitude. Baro Rate is not available with this air data source.

TABLE 5.3.2-1: AIR DATA INPUT SELECT #1 CHANNEL 429RX_2

CONNECT TO: ADC #1 Format: ARINC 429 (Low Speed)

Fault Designation: AIR DATA BUS Bus Type: Basic

A = J2-39 B = J2-38

Data Uncorrected. Baro. Alt Computed Airspeed Barometric Rate Static Air Temperature

Label 203 206 212 213

Sig. Bits 17 14 11 11

Range ±131,072 FT ±1024 KTS ±32768 FPM 512 Degrees

Signal Type Basic Basic Basic Basic

Resolution 1.0 0.0625 16.0 0.25

Rate (ms) 31.3-62.5 62.5-125 31.3-62.5 250-500




A = J2-39 B = J2-38


Label 203 206 212 213

Sig. Bits 17 13 11 10

Range ±131,072 FT ±1024 KTS ±20480 FPM ±512 Degrees


Resolution 1.0 0.125 10.0 0.5

Rate (ms) 31.3-62.5 62.5-125 31.3-62.5 250-500





(+) = J1-62 (-) = J1-43



5 V = J1-25 (+) = J1-63 (-) = J1-44 GND = J1-53


OA

T P

RO

BE

ELE

ME

NT

25J1

(5 V Ref)

63

44

Temp In

4.42 K Ohms

53

Voa

t

Chassis Gnd

-+
















(+) = J1-62 (-) = J1-43



5 V = J1-25 (+) = J1-63 (-) = J1-44 GND = J1-53


OA

T P

RO

BE

ELE

ME

NT

25J1

(5 V Ref)

63

44

Temp In

4.42 K Ohms

53

Voa

t

Chassis Gnd

-+












TABLE 5.3.2-5: AIR DATA INPUT SELECT #5

CHANNEL 429RX_2



A = J2-39 B = J2-38

Data Uncorrected. Baro. Alt Corrected Baro. Alt Computed Airspeed Barometric Rate Static Air Temperature

Label 203 204 206 212 213

Sig. Bits 17 17 14 11 11

Range ±131,072 FT ±131,072 FT ±1024 KTS ±32678 FPM ±512 Degrees

Signal Type Basic Basic Basic Basic Basic

Resolution 1.0 1.0 0.0625 16.0 0.25

Rate (ms) 31.3-62.5 31.3-62.5 62.5-125 31.3-62.5 250-500




A = J2-39 B = J2-38

Data Uncorrected. Baro. Alt Computed Airspeed Static Air Temperature

Label 203 206 213

Sig. Bits 17 14 11

Range ±131,072 FT ±1024 KTS ±512 Degrees

Signal Type Basic Basic Basic

Resolution 1.0 0.0625 0.25

Rate (ms) 31.3-62.5 62.5-125 250-500


Derive Baro Altitude Rate Digital Baro Altitude Rate is derived using Uncorrected Barometric Altitude. Baro Rate is not available with this air data source.






A = J2-39 B = J2-38

Data Uncorrected. Baro. Alt Corrected Baro. Alt Computed Airspeed Barometric Rate

Label 203 204 206 212

Sig. Bits 17 17 14 11

Range ±131,072 FT ±131,072 FT ±1024 KTS ±32678 FPM


Resolution 1.0 1.0 0.0625 16.0

Rate (ms) 31.3-62.5 31.3-62.5 62.5-125 31.3-62.5


5 V = J1-25 (+) = J1-63 (-) = J1-44 GND = J1-53


OA

T P

RO

BE

ELE

ME

NT

25J1

(5 V Ref)

63

44

Temp In

4.42 K Ohms

53

Voa

t

Chassis Gnd

-+








(+) = J1-62 (-) = J1-43



5 V = J1-25 (+) = J1-63 (-) = J1-44 GND = J1-53


OA

T P

RO

BE

ELE

ME

NT

25J1

(5 V Ref)

63

44

Temp In

4.42 K Ohms

53

Voa

t

Chassis Gnd

-+












TABLE 5.3.2-12: AIR DATA INPUT SELECT #12

SIGNAL CONNECTION SUMMARY DATA


(+) = J1-62 (-) = J1-43


Outside Air Temp No Connection Format: Internal Constant 250C and Valid. Input Type: Basic Fault Designation: Static Air Temperature.

Computed Airspeed No Connection Substitute Ground Speed for Airspeed (airspeed is not available with this air data input).







Derive Baro Altitude Rate Analog Baro Altitude Rate is derived using Uncorrected Barometric Altitude. Although the AZ-800 provides Baro rate, the EGPWS does not have an analog connection available.




CONNECT TO: ADC #1 Format: ARINC 429 (High Speed)


A = J2-39 B = J2-38


Label 203 206 212 213

Sig. Bits 17 14 11 11

Range ±131,072 FT ±1024 KTS ±32768 FPM 512 Degrees


Resolution 1.0 0.0625 16.0 0.25

Rate (ms) 31.3-62.5 62.5-125 31.3-62.5 250-500

TABLE 5.3.2-253 AIR DATA INPUT SELECT #253 (EH-101)

CHANNEL 429RX_2

CONNECT TO: IOC #1 Format: ARINC 429 (High Speed)

Fault Designation: IOC BUS 1 Bus Type: Basic

Data Label Sig. Bits Range Signal Type Resolution Rate (ms) See Note

A = J2-39 Uncorrected. Baro. Alt 203 17 ±131,072 FT Basic 1.0 31.3-62.5 B = J2-38 Computed Airspeed 206 14 ±1024 KTS Basic 0.0625 62.5-125 Barometric Rate 212 11 ±32768 FPM Basic 16.0 31.3-62.5 Static Air Temperature 213 11 ±512 Degrees Basic 0.25 250-500

CHANNEL 429RX_5



Data Label Sig. Bits Range Signal Type Resolution Rate (ms) See Note

A = J2-21 Uncorrected. Baro. Alt 203 17 ±131,072 FT Basic 1.0 31.3-62.5 B = J2-04 Computed Airspeed 206 14 ±1024 KTS Basic 0.0625 62.5-125 Barometric Rate 212 11 ±32768 FPM Basic 16.0 31.3-62.5 Static Air Temperature 213 11 ±512 Degrees Basic 0.25 250-500

Note: Rates shown are the typical ARINC 429 update rates, actual rates may vary. For example in the EH-101 application the update rate for all labels is 80ms. TABLE 5.3.2-254: AIR DATA INPUT SELECT #254 (S-92, AW-139)

CHANNEL 429RX_1



A = J2-37 B = J2-36


Label 203 204 206 212 213

Sig. Bits 17 17 14 11 11



Resolution 1.0 1.0 0.0625 16.0 0.25

Rate (ms) 31.3-62.5 31.3-62.5 62.5-125 31.3-62.5 250-500

CHANNEL 429RX_3



A = J2-41 B = J2-40


Label 203 204 206 212 213

Sig. Bits 17 17 14 11 11



Resolution 1.0 1.0 0.0625 16.0 0.25

Rate (ms) 31.3-62.5 31.3-62.5 62.5-125 31.3-62.5 250-500



5.3.3 CATEGORY 3, POSITION INPUT SELECT

The following table provides identification of the Position source signal. Each entry in the Position Input Type column has a corresponding table that provides detailed information on the configuration. For example, the details for Position Input Type #0 are found in Table 5.3.3-0.

In this category, only the following Position signals are defined:

Altitude Date Ground Speed Horizontal Figure of Merit (HFOM) Horizontal. Integrity Limit Latitude Position (course/fine) Longitude Position (course/fine)

Sensor Status True Track Angle Universal Time Correlation Vertical Figure of Merit (VFOM) North/South Velocity East/West Velocity Vertical Velocity

TABLE 5.3.3: POSITION INPUT SELECT

ID Position Input

Type Description Effectivity

(Table 5.3.3-x) 0 0 GPS, ARINC 429 low speed, ARINC 743A format -020

1 1 GPS, ARINC 429 low speed, ARINC 743 format -020

2 2 GPS, Internal -020

3 3 GPS, RS-232 GPS-PXPRESS format -020

4 4 GPS, ARINC 429 high speed, ARINC 743A format -020

5 5 GPS, ARINC 429 high speed, ARINC 743 format -020

10 10 GPS, ARINC 429 low speed, ARINC 743A format: No N/S-E/W velocities (Note 2 and 3)

-020

11 11 GPS, ARINC 429 low speed, ARINC 743 format: No N/S-E/W velocities (Note 2 and 3)

-020

12 12 GPS, ARINC 429 high speed, ARINC 743A format: No N/S-E/W velocities (Note 2 and 3)

-020

13 13 GPS, ARINC 429 high speed, ARINC 743 format: No N/S-E/W velocities (Note 2 and 3)

-020

14 14 GPS, ARINC 429 low speed, ARINC 743A format: Honeywell HT-1000 (label 366 & 367, no Sensor Status)

-024

252 252 Dual GPS, ARINC 429 low speed, ARINC 743A format (Note 3)

-026

253 253 Dual IOC GPS, ARINC 429 high speed, ARINC 743A format: No N/S-E/W velocities

-020

255 255 Dual GPS, ARINC 429 high speed, ARINC 743A format (Note 3)

-020

Note 1: The GPS Altitude Reference in Category 7, Options 1 Select, must be properly applied for the appropriate GPS Position type. At the time of release of this document, all GPS sources except the Universal GPS1000 based systems are of MSL type. The Universal GPS1000 based GPS sources are of WGS-84 type. If the internal GPS source (ID=2) is defined, the GPS altitude reference in Category 7 must be MSL.

Note 2: ID 10, 11, 12, 13, and 253 may only be used when pitch and roll attitude inputs are configured for use in Category 10 Attitude Input Select.

Note 3: ID 10, 11, 12, 13 and 255 are valid for helicopter application but are not preferred sources because they do not provide Vertical Velocity.



TABLE 5.3.3-0: POSITION INPUT TYPE 0 (LOW SPEED ARINC 743A GPS) CHANNEL 429RX_4

CONNECT TO: GPS (ARINC 743A-2) Format: ARINC 429 (Low Speed)

Fault Designation: GPS BUS Bus Type: Basic

A = J2-25 B = J2-8

Data Latitude - Normal

Longitude - Normal GPS Hor. Int. Limit

Altitude VFOM HFOM

VDOP*** HDOP***

Ground Speed True Track Angle

North/South Velocity East/West Velocity Vertical Velocity

Sensor Status **UTC **Date

Label 110 111 130 076 136 247 102 101 112 103 166 174 165 273 125 260

Sig. Bits 20 20 17 20 18 18 15 15 15 15 15 15 15 19 19 19

Range ±180 Degrees ±180 Degrees

16 nm ±131,072 FT

32768 ft 16 nm

1024 meters 1024 meters ±4096 Knots ±180 Degrees ±4096 Knots ±4096 Knots ±32768 fpm Discrete Wd Discrete Wd Discrete Wd

Signal Type Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic

Resolution 0.000171661377 0.000171661377

0.00012207 0.125 0.125

0.000061035 0.03125 0.03125 0.125

0.005493164063 0.125 0.125

1 n/a

0.1 min 1 day

*Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000

*Slowest acceptable update rate in milliseconds. **This label is not required. Data used if present. ***HDOP(101) and VDOP(102) labels added in -030.

TABLE 5.3.3-1: POSITION INPUT TYPE 1 (LOW SPEED ARINC 743 GPS)

CHANNEL 429RX_4

CONNECT TO: GPS (ARINC 743) Format: ARINC 429 (Low Speed)


A = J2-25 B = J2-8



Altitude VDOP*** HDOP***


North/South Velocity East/West Velocity

Vertical Velocity Sensor Status

**UTC **Date

Label 110 111 130 076 102 101 112 103 166 174 165 273 125 260

Sig. Bits 20 20 17 20 15 15 15 15 15 15 15 19 19 19


16 nm ±131,072 FT 1024 meters 1024 meters ±4096 Knots ±180 Degrees ±4096 Knots ±4096 Knots ±32768 fpm Discrete Wd Discrete Wd Discrete Wd

Signal Type Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic

Resolution 0.000171661377 0.000171661377

0.00012207 0.125

0.03125 0.03125 0.125

0.005493164063 0.125 0.125

1 n/a

0.1 min 1 day

*Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000

*Slowest acceptable update rate in milliseconds. **This label is not required. Data used if present. ***HFOM and VFOM internally computed by EGPWS from HDOP and VDOP. HDOP(101) and VDOP(102) labels added in -030.

TABLE 5.3.3-2: POSITION INPUT TYPE 2 (INTERNAL GPS)

CHANNEL Internal GPS Fault Designation: INTERNAL GPS Bus Type: Basic

Data Latitude

Longitude HP Error Altitude VP Error


East Velocity North Velocity

Vertical Velocity GPS State

Integrity State Error Status

ID/byte 15/1-4 15/5-8 15/9-12 16/1-4 16/5-8 17/1-4 17/5-8 18/1-4 18/5-8 18/9-12

1C/0 1C/1

1C/6-7

Sig. Bits 32 32 32 32 32 32 32 32 32 32 8 8 8


meters meters meters

meters/sec 360 Degrees meters/sec meters/sec meters/sec

Discrete Wd Discrete Wd Discrete Wd

Signal Type Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic Basic

Resolution real single-precision real single-precision real single-precision real single-precision real single-precision real single-precision real single-precisionreal single-precision real single-precision real single-precision

n/a n/a n/a

Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000

Note: "MSL" reference must be selected when an internal GPS is utilized. Refer to Table 5.3.7



TABLE 5.3.3-3: POSITION INPUT TYPE 3 (RS-232 GPS, PXPRESS FORMAT) CHANNEL GPS_RXA

CONNECT TO: GPS (Pxpress format) Format: RS-232 (9600 baud)


J2-28 (cm) J2-29 (Rx)

Data Latitude

Longitude HP Error Altitude VP Error


East Velocity North Velocity

Vertical Velocity GPS State

Integrity State Error Status

ID/byte 15/1-4 15/5-8 15/9-12 16/1-4 16/5-8 17/1-4 17/5-8 18/1-4 18/5-8 18/9-12

1C/0 1C/1

1C/6-7

Sig. Bits 32 32 32 32 32 32 32 32 32 32 8 8 8


meters meters meters

meters/sec 360 Degrees meters/sec meters/sec meters/sec

Discrete Wd Discrete Wd Discrete Wd


Resolution real single-precision real single-precision real single-precision real single-precision real single-precision real single-precision real single-precision real single-precision real single-precision real single-precision

n/a n/a n/a

*Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000

* Slowest acceptable update rate in milliseconds.

TABLE 5.3.3-4: POSITION INPUT TYPE 4 (HIGH SPEED ARINC 743A GPS) CHANNEL 429RX_4

CONNECT TO: GPS (ARINC 743A-2) Format: ARINC 429 (High Speed)


A = J2-25 B = J2-8



Altitude VFOM HFOM

VDOP*** HDOP***




Label 110 111 130 076 136 247 102 101 112 103 166 174 165 273 125 260

Sig. Bits 20 20 17 20 18 18 15 15 15 15 15 15 15 19 19 19


16 nm ±131,072 FT

32768 ft 16 nm



Resolution 0.000171661377 0.000171661377

0.00012207 0.125 0.125

0.000061035 0.03125 0.03125 0.125

0.005493164063 0.125 0.125

1 n/a

0.1 min 1 day

*Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000


TABLE 5.3.3-5: POSITION INPUT TYPE 5 (HIGH SPEED ARINC 743 GPS) CHANNEL 429RX_4

CONNECT TO: GPS (ARINC 743) Format: ARINC 429 (High Speed)


A = J2-25 B = J2-8



Altitude VFOM HFOM

VDOP*** HDOP***


North/South Velocity East/West Velocity

Vertical Velocity Sensor Status

**UTC **Date

Label 110 111 130 076 136 247 102 101 112 103 166 174 165 273 125 260

Sig. Bits 20 20 17 20 18 18 15 15 15 15 15 15 15 19 19 19


16 nm ±131,072 FT

32768 ft 16 nm



Resolution 0.000171661377 0.000171661377

0.00012207 0.125 0.125

0.000061035 0.03125 0.03125 0.125

0.005493164063 0.125 0.125

1 n/a

0.1 min 1 day

*Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000




TABLE 5.3.3-10: POSITION INPUT TYPE 10 (LOW SPEED ARINC 743A GPS, NO N/S-E/W VELOCITIES) CHANNEL 429RX_4



A = J2-25 B = J2-8



Altitude VFOM HFOM

VDOP*** HDOP***



Label 110 111 130 076 136 247 102 101 112 103 273 125 260

Sig. Bits 20 20 17 20 18 18 15 15 15 15 19 19 19


16 nm ±131,072 FT

32768 ft 16 nm

1024 meters 1024 meters ±4096 Knots ±180 Degrees Discrete Wd Discrete Wd Discrete Wd


Resolution 0.000171661377 0.000171661377

0.00012207 0.125 0.125

0.000061035 0.03125 0.03125 0.125

0.005493164063 n/a

0.1 min 1 day

*Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000


TABLE 5.3.3-11: POSITION INPUT TYPE 11 (LOW SPEED ARINC 743 GPS, NO N/S-E/W VELOCITIES)

CHANNEL 429RX_4

CONNECT TO: GPS (ARINC 743) Format: ARINC 429 (Low Speed)


A = J2-25 B = J2-8



Altitude VFOM HFOM

VDOP*** HDOP***



Label 110 111 130 076 136 247 102 101 112 103 273 125 260

Sig. Bits 20 20 17 20 15 15 15 15 15 15 19 19 19


16 nm ±131,072 FT 1024 meters 1024 meters 1024 meters 1024 meters ±4096 Knots ±180 Degrees Discrete Wd Discrete Wd Discrete Wd


Resolution 0.000171661377 0.000171661377

0.00012207 0.125

0.03125 0.03125 0.03125 0.03125 0.125

0.005493164063 n/a

0.1 min 1 day

*Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000


TABLE 5.3.3-12: POSITION INPUT TYPE 12 (HIGH SPEED ARINC 743A GPS, NO N/S-E/W VELOCITIES)

CHANNEL 429RX_4

CONNECT TO: GPS (ARINC 743A-2) Format: ARINC 429 (High Speed)


A = J2-25 B = J2-8



Altitude VFOM HFOM

VDOP*** HDOP***



Label 110 111 130 076 136 247 102 101 112 103 273 125 260

Sig. Bits 20 20 17 20 18 18 15 15 15 15 19 19 19


16 nm ±131,072 FT

32768 ft 16 nm



Resolution 0.000171661377 0.000171661377

0.00012207 0.125 0.125

0.000061035 0.03125 0.03125 0.125

0.005493164063 n/a

0.1 min 1 day

*Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000

*Slowest acceptable update rate in milliseconds. **This label is not required. Data used if present ***HDOP(101) and VDOP(102) labels added in -030.



TABLE 5.3.3-13: POSITION INPUT TYPE 13 (HIGH SPEED ARINC 743 GPS, NO N/S-E/W VELOCITIES) CHANNEL 429RX_4

CONNECT TO: GPS (ARINC 743) Format: ARINC 429 (High Speed)


A = J2-25 B = J2-8



Altitude VFOM HFOM

VDOP*** HDOP***



Label 110 111 130 076 136 247 102 101 112 103 273 125 260

Sig. Bits 20 20 17 20 15 15 15 15 15 15 19 19 19


16 nm ±131,072 FT 1024 meters 1024 meters 1024 meters 1024 meters ±4096 Knots ±180 Degrees Discrete Wd Discrete Wd Discrete Wd


Resolution 0.000171661377 0.000171661377

0.00012207 0.125

0.03125 0.03125 0.03125 0.03125 0.125

0.005493164063 n/a

0.1 min 1 day

*Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000


TABLE 5.3.3-14: POSITION INPUT TYPE 14 (LOW SPEED ARINC 743A, HT-1000 GPS) CHANNEL 429RX_4



A = J2-25 B = J2-8



Altitude VFOM HFOM



**UTC **Date

Label 110 111 130 076 136 247 112 103 166 174 165 125 260

Sig. Bits 20 20 17 20 18 18 15 15 15 15 15 19 19


16 nm ±131,072 FT

32768 ft 16 nm

±4096 Knots ±180 Degrees ±4096 Knots ±4096 Knots ±32768 fpm Discrete Wd Discrete Wd


Resolution 0.000171661377 0.000171661377

0.00012207 0.125 0.125

0.000061035 0.125

0.005493164063 0.125 0.125

1 0.1 min 1 day

*Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000

*Slowest acceptable update rate in milliseconds. **This label is not required. Data used if present.



TABLE 5.3.3-252: POSITION INPUT TYPE 252 (DUAL LOW SPEED ARINC 743A GPS) CHANNEL 429RX_4

CONNECT TO: GPS #1 (ARINC 743A-2) Format: ARINC 429 (Low Speed)

Fault Designation: GPS BUS 1 Bus Type: Basic

A = J2-25 B = J2-8



Altitude VFOM HFOM

VDOP*** HDOP***



Label 110 111 130 076 136 247 102 101 112 103 273 125 260

Sig. Bits 20 20 17 20 18 18 15 15 15 15 19 19 19


16 nm ±131,072 FT

32768 ft 16 nm



Resolution 0.000171661377 0.000171661377

0.00012207 0.125 0.125

0.000061035 0.03125 0.03125 0.125

0.005493164063 n/a

0.1 min 1 day

*Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000

CHANNEL 429RX_7

CONNECT TO: GPS #2 (ARINC 743A-2) Format: ARINC 429 (Low Speed)


A = J2-23 B = J2-6



Altitude VFOM HFOM

VDOP*** HDOP***



Label 110 111 130 076 136 247 102 101 112 103 273 125 260

Sig. Bits 20 20 17 20 18 18 15 15 15 15 19 19 19


16 nm ±131,072 FT

32768 ft 16 nm



Resolution 0.000171661377 0.000171661377

0.00012207 0.125 0.125

0.000061035 0.03125 0.03125 0.125

0.005493164063 n/a

0.1 min 1 day

*Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000

*Slowest acceptable update rate in milliseconds. **This label is not required. Data used if present. ***HDOP(101) and VDOP(102) labels added in -030. Note: This configuration may not be selected if an AHRS configuration is required for Attitude and Heading information

(refer to Category 10 type 1 and Category 11 type 1), due to the conflict with Channel 429RX-7.



TABLE 5.3.3-253: POSITION INPUT TYPE 253 (DUAL IOC HIGH SPEED ARINC 743A GPS) CHANNEL 429RX_1

CONNECT TO: IOC #1 (ARINC 743A-2) Format: ARINC 429 (High Speed)


A = J2-37 B = J2-36


Longitude - Normal Latitude - Fine

Longitude - Fine Vertical Velocity

GPS Hor. Int. Limit Altitude VFOM HFOM

VDOP*** HDOP***



Label 110 111 120 121 165 130 076 136 247 102 101 112 103 273 125 260

Sig. Bits 20 20 11 11 15 17 20 18 18 15 15 15 15 19 19 19


±0.000172 ±0.000172

±32768 fpm 16 nm

±131,072 FT 32768 ft 16 nm



Resolution 0.000171661377 0.000171661377 0.000000083819 0.000000083819

1 0.00012207

0.125 0.125

0.000061035 0.03125 0.03125 0.125

0.005493164063 n/a

0.1 min 1 day

*Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000

CHANNEL 429RX_3

CONNECT TO: IOC #2 (ARINC 743A-2) Format: ARINC 429 (High Speed)


A = J2-41 B = J2-40


Longitude - Normal Latitude - Fine

Longitude - Fine Vertical Velocity

GPS Hor. Int. Limit Altitude VFOM HFOM

VDOP*** HDOP***



Label 110 111 120 121 165 130 076 136 247 102 101 112 103 273 125 260

Sig. Bits 20 20 11 11 15 17 20 18 18 15 15 15 15 19 19 19


±0.000172 ±0.000172

±32768 fpm 16 nm

±131,072 FT 32768 ft 16 nm



Resolution 0.000171661377 0.000171661377 0.000000083819 0.000000083819

1 0.00012207

0.125 0.125

0.000061035 0.03125 0.03125 0.125

0.005493164063 n/a

0.1 min 1 day

*Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000

*Slowest acceptable update rate in milliseconds. **This label is not required. Data used if present. ***HDOP(101) and VDOP(102) labels added in -030. Note: This Position Input Type is designed to be used with Category 6 Terrain Display Select Types that also source

their data from dual IOC buses and other compatible IOC tables in Categories 8, 9, 10, 11, and 16. See Tables 5.3.6-231, -234, -235, -236, -249, and -251.



Table 5.3.3-255: Position Input Type 255 (Dual High Speed ARINC 743A GPS) CHANNEL 429RX_4

CONNECT TO: GPS #1 (ARINC 743A-2) Format: ARINC 429 (High Speed)


A = J2-25 B = J2-8



Altitude VFOM HFOM

VDOP*** HDOP***



Label 110 111 130 076 136 247 102 101 112 103 273 125 260

Sig. Bits 20 20 17 20 18 18 15 15 15 15 19 19 19


16 nm ±131,072 FT

32768 ft 16 nm



Resolution 0.000171661377 0.000171661377

0.00012207 0.125 0.125

0.000061035 0.03125 0.03125 0.125

0.005493164063 n/a

0.1 min 1 day

*Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000

CHANNEL 429RX_7

CONNECT TO: GPS #2 (ARINC 743A-2) Format: ARINC 429 (High Speed)


A = J2-23 B = J2-6



Altitude VFOM HFOM

VDOP*** HDOP***



Label 110 111 130 076 136 247 102 101 112 103 273 125 260

Sig. Bits 20 20 17 20 18 18 15 15 15 15 19 19 19


16 nm ±131,072 FT

32768 ft 16 nm



Resolution 0.000171661377 0.000171661377

0.00012207 0.125 0.125

0.000061035 0.03125 0.03125 0.125

0.005493164063 n/a

0.1 min 1 day

*Rate (ms) 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000 1000

*Slowest acceptable update rate in milliseconds. **This label is not required. Data used if present. ***HDOP(101) and VDOP(102) labels added in -030. Note: This configuration may not be selected if an AHRS configuration is required for Attitude and Heading information

(refer to Category 10 type 1 and Category 11 type 1), due to the conflict with Channel 429RX-7.



5.3.4 CATEGORY 4, ALTITUDE CALLOUTS

The following table provides identification of the Altitude Callouts Menu. Each entry in the ID column corresponds to a particular menu selection.

The Altitude Callouts menu consists of standard callout options. The Auto-rotation mode reversion (helicopter) callout options, previously selected in this Category are now selected via category 17. Selecting Auto-rotation Option 0 in Category 17 will result in the callouts listed being enunciated whether the aircraft is in auto-rotation or not. Selecting a non-zero auto-rotation option in Category 17 will result in the identified standard callouts if the aircraft is not in auto-rotation and the selected auto-rotation callouts if the aircraft is in auto-rotation.

Smart Callout activation (“Smart 500”) is reflected by a “500” callout being spoken at the end of the selected callout menu sequence in the Long Level 1 Self-Test. In addition, the Callout menu ID number and the “Smart Callout Selected” configuration message, will both be given during level 3 Self-Test and in the RS232 Present Status display.

FOR PART NUMBERS -022: Altitude callout ID 16 thru ID 40 were added in an attempt to satisfy the European AVAD callout requirement. Those are replaced in part number -024 with an improved callout function. See table at end of section. FOR PART NUMBER -024: Unique altitude callouts ID 17 thru ID 46 are similar to the other callout except that the callout between 100 feet and 160 feet does not latch and only has a 20 foot hysteresis to re-enable the callout. These callouts are intended for over water operation only and meet the AVAD requirements. FOR PART NUMBER -026 AND ON: Unique altitude callouts ID 17 thru ID 46 and ID 63 thru ID 68 are similar to the other callout except that the callout between 100 feet and 160 feet does not latch and only has a 20 foot hysteresis to re-enable the callout. These callouts are intended for over water operation only and meet the AVAD requirements.

TABLE 5.3.4: ALTITUDE CALLOUTS

ID MENU Effectivity 0 MINIMUMS-MINIMUMS, Smart 500 1, 200, 100, 50, 40, 30, 20 ,10 -020 1 MINIMUMS-MINIMUMS, Smart 500 1, 200 -020 2 MINIMUMS-MINIMUMS, Smart 500 1, 100, 50, 40, 30, 20, 10 -020 3 MINIMUMS-MINIMUMS, Smart 500 1 -020 4 MINIMUMS-MINIMUMS, 200, 100, 50, 40, 30, 20, 10 -020 5 MINIMUMS-MINIMUMS, 200 -020 6 MINIMUMS-MINIMUMS, 100, 50, 40, 30, 20, 10 -020 7 (no callouts) -020 8 MINIMUMS-MINIMUMS -020

14 MINIMUMS-MINIMUMS, 100 -020 15 MINIMUMS-MINIMUMS, 200, 100 -020 16 MINIMUMS-MINIMUMS, 200, 50, 40, 30, 20, 10 -024 17 MINIMUMS-MINIMUMS, 200, 100A -024 18 MINIMUMS-MINIMUMS, 200, 110A -024 19 MINIMUMS-MINIMUMS, 200, 120A -024 20 MINIMUMS-MINIMUMS, 200, 130A -024 21 MINIMUMS-MINIMUMS, 200, 140A -024 22 MINIMUMS-MINIMUMS, 200, 150A -024 23 MINIMUMS-MINIMUMS, 200, 160A -024 24 MINIMUMS-MINIMUMS, 100A, 50, 40, 30, 20, 10 -024 25 MINIMUMS-MINIMUMS, 110A, 50, 40, 30, 20, 10 -024 26 MINIMUMS-MINIMUMS, 120A, 50, 40, 30, 20, 10 -024 27 MINIMUMS-MINIMUMS, 130A, 50, 40, 30, 20, 10 -024 28 MINIMUMS-MINIMUMS, 140A, 50, 40, 30, 20, 10 -024 29 MINIMUMS-MINIMUMS, 150A, 50, 40, 30, 20, 10 -024



ID MENU Effectivity 30 MINIMUMS-MINIMUMS, 160A, 50, 40, 30, 20, 10 -024 31 MINIMUMS-MINIMUMS, 100A -024 32 MINIMUMS-MINIMUMS, 110A -024 33 MINIMUMS-MINIMUMS, 120A -024 34 MINIMUMS-MINIMUMS, 130A -024 35 MINIMUMS-MINIMUMS, 140A -024 36 MINIMUMS-MINIMUMS, 150A -024 37 MINIMUMS-MINIMUMS, 160A -024 38 MINIMUMS-MINIMUMS, 200, 100A, 80, 60, 40, 20 -024 39 MINIMUMS-MINIMUMS, 200, 100A, 50 -024 40 MINIMUMS-MINIMUMS, 200, 100A, 50, 40, 30, 20, 10 -024 41 MINIMUMS-MINIMUMS, 200, 110A, 50, 40, 30, 20, 10 -024 42 MINIMUMS-MINIMUMS, 200, 120A, 50, 40, 30, 20, 10 -024 43 MINIMUMS-MINIMUMS, 200, 130A, 50, 40, 30, 20, 10 -024 44 MINIMUMS-MINIMUMS, 200, 140A, 50, 40, 30, 20, 10 -024 45 MINIMUMS-MINIMUMS, 200, 150A, 50, 40, 30, 20, 10 -024 46 MINIMUMS-MINIMUMS, 200, 160A, 50, 40, 30, 20, 10 -024 47 CHECK HEIGHT2, Smart 500 1, 200, 100, 50, 40, 30, 20, 10 -026 48 CHECK HEIGHT2, Smart 500 1, 200 -026 49 CHECK HEIGHT2, Smart 500 1, 100, 50, 40, 30, 20, 10 -026 50 CHECK HEIGHT2, Smart 500 1 -026 51 CHECK HEIGHT2, 200, 100, 50, 40, 30, 20, 10 -026 52 CHECK HEIGHT2, 200 -026 53 CHECK HEIGHT2, 100, 50, 40, 30, 20, 10 -026 54 CHECK HEIGHT2 -026 55 CHECK HEIGHT2, 500, 200, 100, 50, 40, 30, 20, 10 -026 56 CHECK HEIGHT2, 500, 200 -026 57 CHECK HEIGHT2, 500, 100, 50, 40, 30, 20, 10 -026 58 CHECK HEIGHT2, 500 -026 59 CHECK HEIGHT2, 1000, 500, 400, 300, 200, 100, 50, 40, 30, 20, 10 -026 60 CHECK HEIGHT2, 100 -026 61 CHECK HEIGHT2, 200, 100 -026 62 CHECK HEIGHT2, 200, 50, 40, 30, 20, 10 -026 63 CHECK HEIGHT2, 200, 100A -026 64 CHECK HEIGHT2, 100A, 50, 40, 30, 20, 10 -026 65 CHECK HEIGHT2, 100A -026 66 CHECK HEIGHT2, 200, 100A, 80, 60, 40, 20 -026 67 CHECK HEIGHT2, 200, 100A, 50 -026 68 CHECK HEIGHT2, 200, 100A, 50, 40, 30, 20, 10 -026

Note: Selecting an Altitude Callout ID without a minimums callout can be accomplished by leaving the Decision

Height input discrete open or connected to +28VDC. 1 The Smart 500 Callout function will not be given if in autorotation. 2 The Check Height callout in menus 47-68 can only be used in conjunction with Category 5 Audio Menu selects

129, 251 and 252. A Unique altitude callouts ID 17 thru ID 46 and ID 63 thru ID 68 are similar to the other callout except that the

callout between 100 feet and 160 feet does not latch and only has a 20 foot hysteresis to re-enable the callout. These callouts are intended for over water operation only and meet the European AVAD requirements.



5.3.5 CATEGORY 5, AUDIO MENU SELECT

The following table provides identification of the Voice Menu type. Each entry in the Voice Menu column has a corresponding table that provides detailed information on the configuration. For example, the details for Voice Menu # 128 are found in Table 5.3.5-128.

TABLE 5.3.5: AUDIO MENU TYPE

ID Audio Menu Type Description Effectivity (Table 5.3.5.-x)

128 128 Basic Helicopter Menu -020 129 129 Basic Helicopter Menu with Check Height -026

251 251 S-76 Helicopter Menu with Check Height -026 252 252 S-92 Helicopter Menu with Check Height -026 253 253 S-92 Helicopter Menu with Single Altitude -026 254 254 S-76 Helicopter Menu -024 255 255 S-92 Helicopter Menu -020

TABLE 5.3.5-128: AUDIO MENU TYPE 128 (BASIC HELICOPTER) ALERT/WARNING CONDITION AUDIO MENU NOTES

MODE 1 PULL UP PULL UP 1 MODE 2 PULL UP PREFACE TERRAIN TERRAIN 1, 2 MODE 2 PULL UP PULL UP 1 TERRAIN AWARENESS PREFACE WARNING! TERRAIN 1, 2 TERRAIN AWARENESS WARNING WARNING! TERRAIN 1, 3 OBSTACLE AWARENESS PREFACE WARNING! OBSTACLE 1, 2 OBSTACLE AWARENESS WARNING WARNING! OBSTACLE 1, 3 MODE 2 TERRAIN TERRAIN MODE 6 MINIMUMS SELECTED CALLOUTS (See 5.3.4) MODE 6 ALTITUDE ALTITUDE ALTITUDE (See 5.3.4) TERRAIN AWARENESS CAUTION CAUTION TERRAIN (PAUSE) CAUTION TERRAIN 4 OBSTACLE AWARENESS CAUTION CAUTION OBSTACLE (PAUSE) CAUTION OBSTACLE 4 MODE 4 TOO LOW TERRAIN TOO LOW TERRAIN TCF TOO LOW TERRAIN TOO LOW TERRAIN MODE 6 ALTITUDE CALLOUTS SELECTED CALLOUTS (See 5.3.4) MODE 4 TOO LOW GEAR TOO LOW GEAR MODE 1 SINKRATE SINKRATE Note: The basic warning is “SINKRATE (PAUSE) SINKRATE”.

However, if the Mode 1 Pullup curve is violated only a single “Sinkrate” may occur prior to the pull up voice.

5

MODE 3 DON’T SINK DON’T SINK (PAUSE) DON’T SINK MODE 5 GLIDESLOPE GLIDESLOPE MODE 6 BANK ANGLE BANK ANGLE (PAUSE) BANK ANGLE,

BANK ANGLE BANK ANGLE (Honeywell algorithm at low altitudes)

MODE 6 TAIL STRIKE TAIL TOO LOW TA&D INVALID ALERT BE ALERT TERRAIN INOP

Note 1: These are the only voices that can interrupt. Note 2: The preface voices will always be given prior to the warning voice. Note 3: Voice message is continuous. Note 4: Voice message will repeat every 10 seconds. Note 5: Long Self-Test will only issue a single ‘Sinkrate”.



TABLE 5.3.5-129: AUDIO MENU TYPE 129 (BASIC HELICOPTER WITH CHECK HEIGHT) ALERT/WARNING CONDITION AUDIO MENU NOTES

MODE 1 PULL UP PULL UP 1 MODE 2 PULL UP PREFACE TERRAIN TERRAIN 1, 2 MODE 2 PULL UP PULL UP 1 TERRAIN AWARENESS PREFACE WARNING! TERRAIN 1, 2 TERRAIN AWARENESS WARNING WARNING! TERRAIN 1, 3 OBSTACLE AWARENESS PREFACE WARNING! OBSTACLE 1, 2 OBSTACLE AWARENESS WARNING WARNING! OBSTACLE 1, 3 MODE 2 TERRAIN TERRAIN MODE 6 MINIMUMS SELECTED CALLOUTS (See 5.3.4) MODE 6 ALTITUDE CHECK HEIGHT (PAUSE) CHECK HEIGHT (See 5.3.4) TERRAIN AWARENESS CAUTION CAUTION TERRAIN (PAUSE) CAUTION TERRAIN 4 OBSTACLE AWARENESS CAUTION CAUTION OBSTACLE (PAUSE) CAUTION OBSTACLE 4 MODE 4 TOO LOW TERRAIN TOO LOW TERRAIN TCF TOO LOW TERRAIN TOO LOW TERRAIN MODE 6 ALTITUDE CALLOUTS SELECTED CALLOUTS (See 5.3.4) MODE 4 TOO LOW GEAR TOO LOW GEAR MODE 1 SINKRATE SINKRATE Note: The basic warning is “SINKRATE (PAUSE) SINKRATE”.


5



MODE 6 TAIL STRIKE TAIL TOO LOW TA&D INVALID ALERT BE ALERT TERRAIN INOP

Note 1: These are the only voices that can interrupt. Note 2: The preface voices will always be given prior to the warning voice. Note 3: Voice message is continuous. Note 4: Voice message will repeat every 10 seconds. Note 5: Long Self-Test will only issue a single ‘Sinkrate”.



TABLE 5.3.5-251: AUDIO MENU TYPE 251 (S-76 HELICOPTER FACTORY INSTALLATIONS ONLY)ALERT/WARNING CONDITION AUDIO MENU NOTES

LOW ROTOR DISCRETE LOW ROTOR 1, 3 FIRE ENGINE 1 DISCRETE FIRE ENGINE 1 (PAUSE) FIRE ENGINE 1 1 FIRE ENGINE 2 DISCRETE FIRE ENGINE 2 (PAUSE) FIRE ENGINE 2 1 ENGINE 1 FAILURE DISCRETE ENGINE 1 FAILURE (PAUSE) ENGINE 1 FAILURE 1 ENGINE 2 FAILURE DISCRETE ENGINE 2 FAILURE (PAUSE) ENGINE 2 FAILURE 1 MODE 1 PULL UP PULL UP 1 MODE 2 PULL UP PREFACE TERRAIN TERRAIN 1, 2 MODE 2 PULL UP PULL UP 1 TERRAIN AWARENESS PREFACE WARNING! TERRAIN 1, 2 TERRAIN AWARENESS WARNING WARNING! TERRAIN 1, 3 OBSTACLE AWARENESS PREFACE WARNING! OBSTACLE 1, 2 OBSTACLE AWARENESS WARNING WARNING! OBSTACLE 1, 3 MODE 2 TERRAIN TERRAIN MODE 6 MINIMUMS SELECTED CALLOUTS (See 5.3.4) 1 MODE 6 ALTITUDE CHECK HEIGHT (PAUSE) CHECK HEIGHT (See 5.3.4) TERRAIN AWARENESS CAUTION CAUTION TERRAIN (PAUSE) CAUTION TERRAIN 4 OBSTACLE AWARENESS CAUTION CAUTION OBSTACLE (PAUSE) CAUTION OBSTACLE 4 MODE 4 TOO LOW TERRAIN TOO LOW TERRAIN TCF TOO LOW TERRAIN TOO LOW TERRAIN MODE 6 ALTITUDE CALLOUTS SELECTED CALLOUTS (See 5.3.4) MODE 4 TOO LOW GEAR TOO LOW GEAR MODE 1 SINKRATE SINKRATE Note: The basic warning is “SINKRATE (PAUSE) SINKRATE”.


5



DE-COUPLE DISCRETE DECOUPLE MODE 6 TAIL STRIKE TAIL TOO LOW TA&D INVALID ALERT BE ALERT TERRAIN INOP

Note 1: These are the only voices that can interrupt. Note 2: The preface voices will always be given prior to the warning voice. Note 3: Voice message is continuous. Note 4: Voice message will repeat every 10 seconds. Note 5: Long Self-Test will only issue a single 'Sinkrate".



TABLE 5.3.5-252: AUDIO MENU TYPE 252 (S-92 HELICOPTER WITH CHECK HEIGHT)ALERT/WARNING CONDITION AUDIO MENU NOTES

LOW ROTOR DISCRETE LOW ROTOR 1, 3 FIRE ENGINE 1 DISCRETE FIRE ENGINE 1 (PAUSE) FIRE ENGINE 1 1 FIRE ENGINE 2 DISCRETE FIRE ENGINE 2 (PAUSE) FIRE ENGINE 2 1 ENGINE 1 FAILURE DISCRETE ENGINE 1 FAILURE (PAUSE) ENGINE 1 FAILURE 1 ENGINE 2 FAILURE DISCRETE ENGINE 2 FAILURE (PAUSE) ENGINE 2 FAILURE 1 GEAR BOX OIL OUT DISCRETE GEAR BOX OIL OUT (PAUSE) GEAR BOX OIL OUT 1 GEAR BOX PRESSURE DISCRETE GEAR BOX PRESSURE (PAUSE) GEAR BOX PRESSURE 1

SWASH PLATE TEMPERATURE DISCRETE SWASH PLATE TEMPERATURE (PAUSE) SWASH PLATE TEMPERATURE

1

FIRE APU DISCRETE FIRE APU (PAUSE) FIRE APU 1 MODE 1 PULL UP PULL UP 1 MODE 2 PULL UP PREFACE TERRAIN TERRAIN 1, 2 MODE 2 PULL UP PULL UP 1 TERRAIN AWARENESS PREFACE WARNING! TERRAIN 1, 2 TERRAIN AWARENESS WARNING WARNING! TERRAIN 1, 3 OBSTACLE AWARENESS PREFACE WARNING! OBSTACLE 1, 2 OBSTACLE AWARENESS WARNING WARNING! OBSTACLE 1, 3 MODE 4 TOO LOW TERRAIN TOO LOW TERRAIN TCF TOO LOW TERRAIN TOO LOW TERRAIN MODE 4 TOO LOW GEAR TOO LOW GEAR SMOKE IN BAGGAGE DISCRETE SMOKE IN BAGGAGE (PAUSE) SMOKE IN BAGGAGE 1 SMOKE IN CABIN DISCRETE SMOKE IN CABIN (PAUSE) SMOKE IN CABIN 1 MODE 2 TERRAIN TERRAIN TERRAIN AWARENESS CAUTION CAUTION TERRAIN (PAUSE) CAUTION TERRAIN 4 OBSTACLE AWARENESS CAUTION CAUTION OBSTACLE (PAUSE) CAUTION OBSTACLE 4 MODE 1 SINKRATE SINKRATE Note: The basic warning is “SINKRATE (PAUSE) SINKRATE”.


5

MODE 3 DON’T SINK DON’T SINK (PAUSE) DON’T SINK HOVER ALTITUDE DISCRETE HOVER ALTITUDE 1, 3 AIRSPEED DISCRETE AIRSPEED 1, 3 MODE 6 MINIMUMS SELECTED CALLOUTS (See 5.3.4) 1 MODE 6 ALTITUDE CHECK HEIGHT (PAUSE) CHECK HEIGHT (See 5.3.4) MODE 6 ALTITUDE CALLOUTS SELECTED CALLOUTS (See 5.3.4) MODE 5 GLIDESLOPE GLIDESLOPE CHECK POWER DISCRETE CHECK POWER 1 DE-COUPLE DISCRETE DECOUPLE MODE 6 TAIL STRIKE TAIL TOO LOW MODE 6 BANK ANGLE BANK ANGLE (PAUSE) BANK ANGLE,


CHECK ALTITUDE DISCRETE CHECK ALTITUDE LEVEL OFF DISCRETE LEVEL OFF TA&D INVALID ALERT BE ALERT TERRAIN INOP




TABLE 5.3.5-253: AUDIO MENU TYPE 253 (S-92 HELICOPTER WITH SINGLE ALTITUDE)ALERT/WARNING CONDITION AUDIO MENU NOTES



1



5

MODE 3 DON’T SINK DON’T SINK (PAUSE) DON’T SINK HOVER ALTITUDE DISCRETE HOVER ALTITUDE 1, 3 AIRSPEED DISCRETE AIRSPEED 1, 3 MODE 6 MINIMUMS SELECTED CALLOUTS (See 5.3.4) 1 MODE 6 ALTITUDE ALTITUDE (triggered by DH setting) MODE 6 ALTITUDE CALLOUTS SELECTED CALLOUTS (See 5.3.4) MODE 5 GLIDESLOPE GLIDESLOPE CHECK POWER DISCRETE CHECK POWER 1 DE-COUPLE DISCRETE DECOUPLE MODE 6 TAIL STRIKE TAIL TOO LOW MODE 6 BANK ANGLE BANK ANGLE (PAUSE) BANK ANGLE,






TABLE 5.3.5-254: AUDIO MENU TYPE 254 (S-76 HELICOPTER FACTORY INSTALLATIONS ONLY)ALERT/WARNING CONDITION AUDIO MENU NOTES

LOW ROTOR DISCRETE LOW ROTOR 1, 3 FIRE ENGINE 1 DISCRETE FIRE ENGINE 1 (PAUSE) FIRE ENGINE 1 1 FIRE ENGINE 2 DISCRETE FIRE ENGINE 2 (PAUSE) FIRE ENGINE 2 1 ENGINE 1 FAILURE DISCRETE ENGINE 1 FAILURE (PAUSE) ENGINE 1 FAILURE 1 ENGINE 2 FAILURE DISCRETE ENGINE 2 FAILURE (PAUSE) ENGINE 2 FAILURE 1 MODE 1 PULL UP PULL UP 1 MODE 2 PULL UP PREFACE TERRAIN TERRAIN 1, 2 MODE 2 PULL UP PULL UP 1 TERRAIN AWARENESS PREFACE WARNING! TERRAIN 1, 2 TERRAIN AWARENESS WARNING WARNING! TERRAIN 1, 3 OBSTACLE AWARENESS PREFACE WARNING! OBSTACLE 1, 2 OBSTACLE AWARENESS WARNING WARNING! OBSTACLE 1, 3 MODE 2 TERRAIN TERRAIN MODE 6 MINIMUMS SELECTED CALLOUTS (See 5.3.4) 1 MODE 6 ALTITUDE ALTITUDE ALTITUDE (triggered by DH setting) TERRAIN AWARENESS CAUTION CAUTION TERRAIN (PAUSE) CAUTION TERRAIN 4 OBSTACLE AWARENESS CAUTION CAUTION OBSTACLE (PAUSE) CAUTION OBSTACLE 4 MODE 4 TOO LOW TERRAIN TOO LOW TERRAIN TCF TOO LOW TERRAIN TOO LOW TERRAIN MODE 6 ALTITUDE CALLOUTS SELECTED CALLOUTS (See 5.3.4) MODE 4 TOO LOW GEAR TOO LOW GEAR MODE 1 SINKRATE SINKRATE Note: The basic warning is “SINKRATE (PAUSE) SINKRATE”.


5



DE-COUPLE DISCRETE DECOUPLE MODE 6 TAIL STRIKE TAIL TOO LOW TA&D INVALID ALERT BE ALERT TERRAIN INOP




TABLE 5.3.5-255: AUDIO MENU TYPE 255 (S-92 HELICOPTER)ALERT/WARNING CONDITION AUDIO MENU NOTES



1



5

MODE 3 DON’T SINK DON’T SINK (PAUSE) DON’T SINK HOVER ALTITUDE DISCRETE HOVER ALTITUDE 1, 3 AIRSPEED DISCRETE AIRSPEED 1, 3 MODE 6 MINIMUMS SELECTED CALLOUTS (See 5.3.4) 1 MODE 6 ALTITUDE ALTITUDE ALTITUDE (See 5.3.4) MODE 6 ALTITUDE CALLOUTS SELECTED CALLOUTS (See 5.3.4) MODE 5 GLIDESLOPE GLIDESLOPE CHECK POWER DISCRETE CHECK POWER 1 DE-COUPLE DISCRETE DECOUPLE MODE 6 TAIL STRIKE TAIL TOO LOW MODE 6 BANK ANGLE BANK ANGLE (PAUSE) BANK ANGLE,






5.3.6 CATEGORY 6, TERRAIN DISPLAY SELECT

The following table (5.3.6) has an identification number (ID) associated with each Terrain Display configuration. Each of the ID rows has a group number for the Display Configuration, the Input Control. The TA&D Pop Up Disable function is defined by a Boolean. The ID groups will completely identify a particular Terrain Display Interface.

ID Table 5.3.6-x

Application Notes Effectivity

0 KC Picture Bus (KCPB) with Terrain Awareness Corrected Altitude GSL (Note 1) -020

1 No Display, TA&D and TCF Enabled -020

2 No Display, TA&D and TCF Disabled -020

3 Collins ProLine II (4x4) (Note 3) -020

4 Honeywell/Bendix PPI-4A/4B (Note 2) -020

5 Collins ProLine II (5x6) (Note 3) -020

6 Collins ProLine II (5x4,5x5) (Note 3) -020

9 Honeywell/Bendix EFIS 40/50 (Non-Integrated) -020

10 Honeywell/Bendix EFIS 40/50 (Integrated) (Note 7) -020

12 Collins WXI-701/711, without Auto Range -020

13 Honeywell Primus 880/660/440 (Integrated) WXPD w/ SCI range -020

14 Honeywell/Bendix PPI-4A/4B without Auto Range (Note 2) -020

15 Honeywell Primus 880/660/440 (Integrated) WXPD w/ SCI range and aircraft symbol on overlay -020

16 Honeywell/Bendix,IN182A, IN812A (RDR 2000, RDS 81/82) -020

17 Honeywell/Bendix, IN842A, IN862A (RDR 2100, RDS 84/86) -020

18 KC Picture Bus (KCPB) w/o presentation of Terrain Awareness Corrected Altitude (Note 1 and Note 5) -020

19 KC Picture Bus (KCPB) with Digital Discrete Word and Terrain Awareness Corrected Altitude GSL (Note 1) -020

20 KC Picture Bus (KCPB) with Digital Discrete Word, w/o presentation of Terrain Awareness Corrected Altitude (Note 1 and Note 5)

-020

228 Collins 8x10 -028

229 Honeywell/Bendix,IN182A, IN812A (RDR 2000 with Binary Peaks) -024

230 KC Picture Bus (KCPB) with Digital Discrete Word (Note 1 and Note 6) -020

231 Collins FDS-255 (Integrated with binary Peaks) -020

232 Collins FDS-255 (Non-integrated) -020

233 KC Picture Bus (KCPB) (Note 1) -020

234 Collins 8x10 for S-92 helicopters -020

235 Collins ProLine 4 (Non-Integrated) -020

236 Collins ProLine 4 (Integrated) -020

242 KC Picture Bus (KCPB) (Note 1 and Note 6) -020

246 Honeywell/Bendix EFIS 10 (Non-Integrated) -020

249 Honeywell Primus Epic & Epic CDS/R with overlay Peaks Elevations -021

250 Honeywell EDZ-705 (5x5), EDZ-756 (5x6) (Integrated) with DC-811 range push button control -020

251 Honeywell Primus Epic & Epic CDS/R with binary Peaks Elevations -020

255 Honeywell SPZ8000 (Integrated) w/ SCI range (Note 5) -020

Note 1: For a description of the KCPB features implemented in a particular software release, see Appendix B: KCPB Phased Implementation in the EGPWS Interface Methodology document 060-4303-000.

Note 2: This configuration is applicable to RDR-4B with a mod that makes it capable of displaying blue.

Note 3: Refer to Rockwell Collins Service Information Letter, EFIS 84/85/86 SIL 2-99 Dated March 16/99 or later revision, for information describing the requirements to interface an EGPWS to the Collins Pro Line II system equipped with EFIS 84/85/86 Displays and WXR-350/840/700 or TWR-850 Weather Radar systems.

Note 4: For helicopters applications (MK XXII) Peaks Enable is always true regardless of the selection from Category 7 Table 5.3.7.

Note 5: With this configuration the EGPWC shall not overlay Terrain Awareness Corrected Altitude.

Note 6: This is the only display configuration applicable to helicopters using Category 16, Torque Input Select Type ID 6. This display type is the only one available that uses RX429-8 for range control. Torque Input Select Type 6 inputs torque data as RS-422 on RX429/422-1.

Note 7: ID 10 must have Category 7, Peaks Mode Enabled, selected.



In this category the following signals are configured by the ID number:

Signal Name Signal Type Defined By Terrain Display Bus: KCPB or ARINC Display Configuration Group Range Bus: ARINC 429 or RS-422 Display Input Control Group TA&D Alternate Pop Up Boolean Defined directly in Table

In cases where the signals are on the same ARINC 429 bus with other signals (IOC, EFIS), you may: In other categories select the same bus type with the same interface connection and the same Fault Designation

name and Channel as this category. In this case a single physical bus with a single connection satisfies more than one category, or;

In other categories select a different bus Fault Designation name and Channel connection and wire the connections to the same source (if loading permits). Note: In this case a single bus failure will result in multiple bus names being faulted in the EGPWS self test. In this case a single physical bus with multiple connections satisfies more than one category.



Table 5.3.6-0 KC Picture Bus with Terrain Awareness Corrected Altitude DISPLAY CONFIGURATION GROUP 0

Function Value Display Type KC Picture Bus (KCPB) Sweep Type Curtain (Vertical or Horizontal scan) Auto Pop Up Pop Up On Caution or Warning

Category 7, Options Select Group #1, TA&D Alternate Pop Up: Always False Peaks Mode (Elevations via overlay)

Peaks On Category 7, Options Select Group #1 Peaks Enable: Always True

Manual select None (Terrain selection is controlled by display system) Manual deselect None (Terrain deselection is controlled by display system) Auto Range Controlled by display response (if selected a 10 nm range will be used) Moving Marker None Overlay Page Controlled by display Display bus type KCPB CHANNEL 453TX_1

CONNECT TO: DISPLAY BUS #1 Format: KCPB

A = J1-58 B = J1-59

Terrain Display data

CHANNEL 453TX_2


A = J1-56 B = J1-57


DISPLAY INPUT CONTROL GROUP 0

CHANNEL 429_422RX_1

CONNECT TO: KCPB-IND # 1 Format: ARINC 429 (Low Speed)

Fault Designation: KCPB BUS 1 Bus Type: Basic

Data

Range4

Label 271

Sig. Bits 11

Range 0.5-1023.5NM

Signal Type Basic

Resolution 0.5

Rate (ms) 250

A = J2-37 Query/Continuous Response 011 Discrete N/A Basic N/A 1000 B = J2-36 DSU Status Data (DSU only) 350 Discrete N/A Basic N/A 1000 Key Press/Display Mode

4 012 Discrete N/A Basic N/A 250

CHANNEL 429RX_3

CONNECT TO: KCPB-IND # 2 Format: ARINC 429 (Low Speed)


Data

Range 4

Label 271

Sig. Bits 11

Range 0.5-1023.5NM

Signal Type Basic

Resolution 0.5

Rate (ms) 250



OUTPUT 429 BUS GROUP 0 Channel Pins Comments

429TX_1 (Low Speed) A = J2-43 B = J2-42

Transmits (Section 6) Label sets: 6.1.1.x, 6.1.2.x, 6.1.3.x, and 6.1.4.x

Integration notes: 1. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input

channels. This prevents the EGPWS from reporting an external bus fault on the second channel. 2. This Display Group is configured by the Display using response labels on its ARINC 429 data bus. 3. This display will cause the GPWS, TERRAIN, and TERRAIN INOP lamps to turn on only at the beginning of the

EGPWS Self-Test (standard operation is for the INOP lamps to be on for the entire Self-Test). 4. Label 012 is optional. The current fault and fault history message “RANGE” for label 271 (Range) is not shown if

Range Keys are requested on label 012 (Key Press/Display Mode). 5. Some KCPB compatible displays require the EGPWS ARINC 429 Output Bus be connected to the KCPB display.



Table 5.3.6-1 No Display – TAD and TCF Enabled OUTPUT 429 BUS GROUP 0

Channel Pins Comments

429TX_1 (Low Speed) A = J2-43 B = J2-42


Table 5.3.6-2 TA&D / TCF Disabled OUTPUT 429 BUS GROUP 0

Channel Pins Comments

429TX_1 (Low Speed) A = J2-43 B = J2-42




Table 5.3.6-3 Collins ProLine II (4x4) DISPLAY CONFIGURATION GROUP 6

Function Value Display Type Collins Pro-Line II (4x4) Display Sweep Type Standard with +/-60 degree limit Auto Pop Up Pop Up On Caution or Warning



Manual select Anytime Manual deselect Anytime Auto Range No Moving Marker No Overlay Page Yes; Peaks Elevations located on the upper left side of Terrain image. Display bus type Standard ARINC 453 CHANNEL 453TX_1

CONNECT TO: DISPLAY BUS #1 Format: ARINC 708/708A

A = J1-58 B = J1-59


CHANNEL 453TX_2


A = J1-56 B = J1-57



CHANNEL 429_422RX_1

CONNECT TO: WX-IND #1 (range) Format: ARINC 429 (Low Speed)

Fault Designation: DISPLAY BUS 1 Bus Type: Basic

A = J2-37 B = J2-36

Data Range (Display Word 2)

Label 271

Sig. Bits Discrete

Range 5-320NM

Signal Type Basic

Resolution N/A

Rate (ms) 100

CHANNEL 429RX_3



A = J2-41 B = J2-40


Label 271

Sig. Bits Discrete

Range 5-320NM

Signal Type Basic

Resolution N/A

Rate (ms) 100

CONN PIN # REFERENCE NAME PIN FUNCTION Polarity/Configuration

J1-32 GND_DISC_12 Display Select Discrete #1 Type 1 (Momentary) Gnd = Display Select Toggle <not> Gnd = Normal



429TX_1 (Low Speed) A = J2-43 B = J2-42


Integration note: 1 When interfacing to a single display controller configuration the bus must be connected to both EGPWS input

channels. This prevents the EGPWS from reporting an external bus fault on the second channel.



Table 5.3.6-4 Honeywell/Bendix PPI-4A/4B DISPLAY CONFIGURATION GROUP 1

Function Value Display Type Bendix PPI-4A/4B (MAP-MODE) Sweep Type Standard

Auto Pop Up3 Pop Up On Caution or Warning Category 7, Options Select Group #1, TA&D Alternate Pop Up: Always False

Peaks Mode2 (Elevations via overlay)


Manual select Anytime Manual deselect Anytime Auto Range Yes 10NM Moving Marker No Overlay Page Peaks numbers located in the lower right corner. Display bus type Standard ARINC 453 CHANNEL 453TX_1


A = J1-58 B = J1-59


CHANNEL 453TX_2


A = J1-56 B = J1-57



CHANNEL 429_422RX_1



A = J2-37 B = J2-36


Label 271

Sig. Bits Discrete

Range 5-320NM

Signal Type Basic

Resolution N/A

Rate (ms) 100

CHANNEL 429RX_3



A = J2-41 B = J2-40


Label 271

Sig. Bits Discrete

Range 5-320NM

Signal Type Basic

Resolution N/A

Rate (ms) 100





429TX_1 (Low Speed) A = J2-43 B = J2-42



channels. This prevents the EGPWS from reporting an external bus fault on the second channel. 2 Honeywell/Bendix PPI 4B (mod 24 or later) with blue water capability required for Peaks display, PN 2041222-

0434, -4434, -5451, -5454, -6429. 3 Popup occurs on all display modes via the PWS Caution bit in the ARINC 453 word. All PPI except (-6429) are

popup capable.



Table 5.3.6-5 Collins ProLine II (5x6) DISPLAY CONFIGURATION GROUP 2

Function Value Display Type Collins ProLine II (5x6) Sweep Type Standard with +/-60 degree limit Auto Pop Up Pop Up On Caution or Warning



Manual select Anytime Manual deselect Anytime Auto Range No Moving Marker No Overlay Page Peaks Elevations located on upper left side of Terrain image. Display bus type Standard ARINC 453 CHANNEL 453TX_1


A = J1-58 B = J1-59


CHANNEL 453TX_2


A = J1-56 B = J1-57



CHANNEL 429_422RX_1



A = J2-37 B = J2-36


Label 271

Sig. Bits Discrete

Range 5-320NM

Signal Type Basic

Resolution N/A

Rate (ms) 100

CHANNEL 429RX_3



A = J2-41 B = J2-40


Label 271

Sig. Bits Discrete

Range 5-320NM

Signal Type Basic

Resolution N/A

Rate (ms) 100





429TX_1 (Low Speed) A = J2-43 B = J2-42






Table 5.3.6-6 Collins ProLine II (5x4,5x5) DISPLAY CONFIGURATION GROUP 3

Function Value Display Type Collins ProLine II (5x4, 5x5) Sweep Type Standard with +/-60 degree limit Auto Pop Up Pop Up On Caution or Warning



Manual select Anytime Manual deselect Anytime Auto Range No Moving Marker No Overlay Page Peaks Elevations located on upper left side of Terrain image Display bus type Standard ARINC 453 CHANNEL 453TX_1


A = J1-58 B = J1-59

Terrain Display data to switching relay/Symbol Generator

CHANNEL 453TX_2


A = J1-56 B = J1-57



CHANNEL 429_422RX_1



A = J2-37 B = J2-36


Label 271

Sig. Bits Discrete

Range 5-320NM

Signal Type Basic

Resolution N/A

Rate (ms) 100

CHANNEL 429RX_3



A = J2-41 B = J2-40


Label 271

Sig. Bits Discrete

Range 5-320NM

Signal Type Basic

Resolution N/A

Rate (ms) 100





429TX_1 (Low Speed) A = J2-43 B = J2-42


Integration note: 1. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input




Table 5.3.6-9 Honeywell/Bendix EFIS 40/50 (Non-Integrated) DISPLAY CONFIGURATION GROUP 7

Function Value Display Type Honeywell/Bendix EFIS 40/50 Non-Integrated Sweep Type Sweep range +/- 60 degrees Auto Pop Up Pop Up On Caution or Warning



Manual select Anytime WXR is on and display is in proper Mode Manual deselect Anytime Auto Range No Moving Marker No Overlay Page Peaks Elevations at upper right corner of display. Display bus type Standard ARINC 453 CHANNEL 453TX_1


A = J1-58 B = J1-59


CHANNEL 453TX_2


A = J1-56 B = J1-57



CHANNEL 429_422RX_1



A = J2-37 B = J2-36

Data Mode (Display Word 1) Range (Display Word 2)

Discrete Word (VP) 2

Label270 271 273

Sig. BitsDiscrete Discrete Discrete

Range Mode, Tilt, Gain5-320NM VP Mode, Bit 11


Resolution N/A N/A N/A

Rate 100 ms 100 ms 100 ms

CHANNEL 429RX_3



A = J2-41 B = J2-40



Label270 271 273










429TX_1 (Low Speed) A = J2-43 B = J2-42



channels. This prevents the EGPWS from reporting an external bus fault on the second channel. 2. Not compatible with Radar indicators without VP mode.



Table 5.3.6-10 Honeywell/Bendix EFIS 40/50 (Integrated) DISPLAY CONFIGURATION GROUP 8

Function Value Display Type Honeywell/Bendix EFIS 40/50 Integrated Sweep Type Sweep range +/- 90 degrees

Auto Pop Up Pop Up On Caution or Warning Category 7, Options Select Group #1, TA&D Alternate Pop Up: Always False

Peaks Mode Peaks Always Enabled

The EFIS display supplies the Peak Elevations as stroked characters. The EFIS can be configured to place the Elevations on the bottom left or right side of the display.

Manual select Anytime Manual deselect Anytime Auto Range 2 None (Terrain selection is controlled by display system) Moving Marker No Overlay Page No, the display supplies a “TERR” mode annunciation. Display bus type Standard ARINC 453 CHANNEL 453TX_1

CONNECT TO: TERRAIN DISPLAY BUS #1 Format: ARINC 708/708A

A = J1-58 B = J1-59


CHANNEL 453TX_2


A = J1-56 B = J1-57



CHANNEL 429_422RX_1



A = J2-37 B = J2-36



Label270 271 273






CHANNEL 429RX_3



A = J2-41 B = J2-40



Label270 271 273










429TX_1 (Low Speed) A = J2-43 B = J2-42


Integration notes: 1. Peaks Elevations are transmitted digitally to the display via Label 025 on the ARINC 453 bus; they are then displayed as stroked characters on

the bottom left or right of the display (depending on EFIS strapping). 2. To Pop Up for a Terrain Caution or Warning it is necessary for the EFIS to receive two discrete signals from the EGPWS (one to indicate that

Terrain is selected and one to indicate that selection was due to an alert). The EFIS needs to distinguish between manual selection and alert conditions so it will know when it should auto-range. Both EFIS and EGPWS start to auto-range on a Caution or Warning to minimize any latency problem displaying status during an alert.

3. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel.

4. Not compatible with Radar indicators without VP mode.

5. This display will cause the GPWS and TERRAIN INOP lamps to turn on only at the beginning of the EGPWS Self-Test (standard operation is for the INOP lamps to be on for the entire Self-Test).



Table 5.3.6-12 Collins WXI-701/711 PPI, without Auto Range DISPLAY CONFIGURATION GROUP 10

Function Value Display Type Collins WXI-701/711 PPI Sweep Type Fan Auto Pop Up Pop Up On Caution or Warning



Manual select Anytime Manual deselect Anytime Auto Range No Moving Marker No Overlay Page Peaks located at the bottom left of display. Display bus type Standard ARINC 453 CHANNEL 453TX_1


A = J1-58 B = J1-59


CHANNEL 453TX_2


A = J1-56 B = J1-57



CHANNEL 429_422RX_1



A = J2-37 B = J2-36


Label 271

Sig. Bits Discrete

Range 5-320NM

Signal Type Basic

Resolution N/A

Rate (ms) 100

CHANNEL 429RX_3



A = J2-41 B = J2-40


Label 271

Sig. Bits Discrete

Range 5-320NM

Signal Type Basic

Resolution N/A

Rate (ms) 100





429TX_1 (Low Speed) A = J2-43 B = J2-42


Integration note: 1. Left/Right shift keys on the display are not to be used when displaying terrain. 2. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input




Table 5.3.6-13 Honeywell P880/660/440 (Integrated WXPD w/ SCI range) DISPLAY CONFIGURATION GROUP 11

Function Value Display Type Honeywell P880/660/440 radar displays Integrated Sweep Type Honeywell Auto Pop Up Pop Up On Caution or Warning



Manual select Anytime Manual deselect Anytime Auto Range No Moving Marker Yes (across bottom of display) Overlay Page Peaks located at the bottom left of display. Display bus type Honeywell picture bus CHANNEL 453TX_1

CONNECT TO: TERRAIN DISPLAY BUS #1 Format: WXPD

A = J1-58 B = J1-59

Terrain Display data to switching relay/Symbol Generator #1

CHANNEL 453TX_2

CONNECT TO: Not supported for this display type


CHANNEL 429_422RX_1

CONNECT TO: SCI Bus 1 Format: RS-422 (12K baud)


A = J2-36 B = J2-37

Data Range (Mode/Range Word)

Label 80

Sig. Bits 4 Discrete

Range 2000NM

Signal Type Basic

Resolution N/A

Rate (ms) 100




429TX_1 (Low Speed) A = J2-43 B = J2-42


Integration note: 1. The Radar Indicator part number must end in –X1X. 2. The RS-422 receive channel J2-36 / J2-37 is swapped High and Low from ARINC 429 receive channels.



Table 5.3.6-14 Honeywell/Bendix PPI-4A/4B without Auto Range DISPLAY CONFIGURATION GROUP 12

Function Value Display Type Bendix PPI-4A/4B (MAP-MODE) Sweep Type Standard

Auto Pop Up Pop Up On Caution or Warning Category 7, Options Select Group #1, TA&D Alternate Pop Up: Always False

Peaks Mode (Elevations via overlay)


Manual select Anytime Manual deselect Anytime Auto Range No Moving Marker No Overlay Page Peaks numbers located in the lower right corner. Display bus type Standard ARINC 453 CHANNEL 453TX_1

CONNECT TO: TERRAIN DISPLAY BUS #1 Format: ARINC 453

A = J1-58 B = J1-59


CHANNEL 453TX_2

CONNECT TO: TERRAIN DISPLAY BUS #2 Format: ARINC 453

A = J1-56 B = J1-57



CHANNEL 429_422RX_1



A = J2-37 B = J2-36


Label 271

Sig. Bits Discrete

Range 5-320NM

Signal Type Basic

Resolution N/A

Rate (ms) 100

CHANNEL 429RX_3



A = J2-41 B = J2-40


Label 271

Sig. Bits Discrete

Range 5-320NM

Signal Type Basic

Resolution N/A

Rate (ms) 100





429TX_1 (Low Speed) A = J2-43 B = J2-42



channels. This prevents the EGPWS from reporting an external bus fault on the second channel. 2. Honeywell/Bendix PPI 4B (mod 24 or later) with blue water capability required for Peaks display, PN 2041222-

0434, -4434, -5451, -5454, -6429.



Table 5.3.6-15 Honeywell P880/660/440 Integrated DISPLAY CONFIGURATION GROUP 13

Function Value Display Type Honeywell Integrated P880/660/440 radar displays with A/C symbol Sweep Type Honeywell Auto Pop Up Pop Up On Caution or Warning



Manual select Anytime Manual deselect Anytime Auto Range No Moving Marker Yes (across bottom of display) Overlay Page Peaks numbers located in the lower left of display. Display bus type Honeywell picture bus CHANNEL 453TX_1


A = J1-58 B = J1-59


TERRAIN DISPLAY BUS #2 453TX_2

CONNECT TO: Not supported for this display type


CHANNEL 429_422RX_1

CONNECT TO: SCI Bus 1 Format: RS-422 (12K baud)


A = J2-36 B = J2-37


Label 80


Range 2000NM

Signal Type Basic

Resolution N/A

Rate (ms) 100




429TX_1 (Low Speed) A = J2-43 B = J2-42


Integration Notes: 1. This display type overlays an inverted T aircraft symbol 2. The Radar Indicator part number must end in –X1X. 3. The channel 429_422RX polarity is reversed from ARINC 429 receive applications.



Table 5.3.6-16 Honeywell/Bendix IN182A/IN812A Radar display (RDR 2000) DISPLAY CONFIGURATION GROUP 15

Function Value Display Type Bendix IN182A/IN812A Radar Display (RDR-2000 radar system) Sweep Type Sweep range +/- 50 degrees Auto Pop Up Pop Up On Caution or Warning



Manual select Anytime WXR is on and display is in proper Mode Manual deselect Anytime Auto Range No Moving Marker No Overlay Page Peaks Elevation located on upper right side of Terrain image. Display bus type Standard ARINC 453 CHANNEL 453TX_1

CONNECT TO: TERRAIN DISPLAY BUS #1Format: ARINC 708/708A

A = J1-58 B = J1-59


CHANNEL 453TX_2


A = J1-56 B = J1-57



CHANNEL 429_422RX_1

CONNECT TO: WX-IND #1 (range) 1 Format: ARINC 429 (Low Speed)


A = J2-37 B = J2-36

Data Mode (Display Word 1) Range (Display Word 2) Discrete Word (VP) 2

Label270 271 273






CHANNEL 429RX_3



A = J2-41 B = J2-40


Label270 271 273










429TX_1 (Low Speed) A = J2-43 B = J2-42


Integration Notes: 1 When interfacing to a single display controller configuration the bus must be connected to both EGPWS input

channels. This prevents the EGPWS from reporting an external bus fault on the second channel. 2 Not compatible with Radar indicators without VP mode, part numbers RDS-81 IN-812A 066-3114-00, IN-812A 066-

3114-01; RDS-82 IN-182A 066-3084-00, IN-182A 066-3084-01, IN-182A 066-3084-02, IN-182A 066-3084-03.



Table 5.3.6-17 Honeywell/Bendix IN842A/IN862A Radar display (RDR 2100) DISPLAY CONFIGURATION GROUP 16

Function Value Display Type Bendix IN842A/IN862A Radar Display (RDR-2100 radar system) Sweep Type Sweep range +/- 60 degrees Auto Pop Up Pop Up On Caution or Warning



Manual select Anytime WXR is on and display is in proper Mode Manual deselect Anytime Auto Range No Moving Marker No Overlay Page Peaks Elevation located on upper right side of Terrain image. Display bus type Standard ARINC 453 CHANNEL 453TX_1


A = J1-58 B = J1-59


CHANNEL 453TX_2


A = J1-56 B = J1-57



CHANNEL 429_422RX_1



A = J2-37 B = J2-36


Label270 271 273






CHANNEL 429RX_3



A = J2-41 B = J2-40


Label270 271 273










429TX_1 (Low Speed) A = J2-43 B = J2-42



channels. This prevents the EGPWS from reporting an external bus fault on the second channel. 2 Not compatible with Radar indicators without VP mode, part numbers RDS-84 IN-842A 066-3085-00, IN-842A

066-3085-01, RDS-86 IN-862A 066-3086-00, IN-862A 066-3086-01, RDR 2100 IN-862A 066-3086-00, IN-862A 066-3086-01.



Table 5.3.6-18 KC Picture Bus w/o presentation of Terrain Awareness Corrected Altitude DISPLAY CONFIGURATION GROUP 17




Manual select None (Display Control Selection) Manual deselect None (Display Control Selection) Auto Range Controlled by display response (if selected a 10 nm range will be used) Moving Marker None Overlay Page Controlled by display Display bus type KCPB CHANNEL 453TX_1

CONNECT TO: TERRAIN DISPLAY BUS #1 Format: KCPB

A = J1-58 B = J1-59


CHANNEL 453TX_2


A = J1-56 B = J1-57



CHANNEL 429_422RX_1

CONNECT TO: KCPB-IND #1 (range) 1 Format: ARINC 429 (Low Speed)


A = J2-37 B = J2-36

Data

Range5

Query/Continuous Response DSU Status Data (DSU only)

Key Press/Display Mode5

Label 271 011 350 012

Sig. Bits 11 Discrete Discrete Discrete

Range 0.5-1023.5NM N/A N/A N/A


Resolution 0.5 N/A N/A N/A

Rate (ms) 250 1000 1000 250

CHANNEL 429RX_3



A = J2-41 B = J2-40

Data

Range5



Label 271 011 350 012





Rate (ms) 250 1000 1000 250


429TX_1 (Low Speed) A = J2-43 B = J2-42


Integration Notes: 1. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input

channels. This prevents the EGPWS from reporting an external bus fault on the second channel. 2. This Display Group is configured by the Display using response labels on its ARINC 429 data bus. 3. Some KCPB compatible displays require the EGPWS ARINC 429 Output Bus be connected to the KCPB display. 4. This display will cause the GPWS and TERRAIN INOP lamps to turn on only at the beginning of the EGPWS Self-

Test (standard operation is for the INOP lamps to be on for the entire Self-Test). 5. Label 012 is optional. The current fault and fault history message “RANGE” for label 271 (Range) is not shown

if Range Keys are requested on label 012 (Key Press/Display Mode).



Table 5.3.6-19 KC Picture Bus with Digital Discrete Word and Terrain Awareness Corrected Alt. DISPLAY CONFIGURATION GROUP 0






A = J1-58 B = J1-59


CHANNEL 453TX_2


A = J1-56 B = J1-57



CHANNEL 429_422RX_1



A = J2-37 B = J2-36

Data

Range5



Discrete Word

Label 271 011 350 012 017

Sig. Bits 11 Discrete Discrete Discrete Discrete

Range 0.5-1023.5NM N/A N/A N/A N/A


Resolution 0.5 N/A N/A N/A N/A

Rate (ms) 250 1000 1000 250 200

CHANNEL 429RX_3



A = J2-41 B = J2-40

Data

Range5



Discrete Word

Label 271 011 350 012 017





Rate (ms) 250 1000 1000 250 200


429TX_1 (Low Speed) A = J2-43 B = J2-42








Table 5.3.6-20 KC Picture Bus with Digital Discrete Word w/o Terrain Awareness Corrected Alt. DISPLAY CONFIGURATION GROUP 17






A = J1-58 B = J1-59


CHANNEL 453TX_2


A = J1-56 B = J1-57


DISPLAY INPUT CONTROL GROUP 4 CHANNEL 429_422RX_1



A = J2-37 B = J2-36

Data

Range5



Discrete Word

Label 271 011 350 012 017





Rate (ms) 250 1000 1000 250 200

CHANNEL 429RX_3



A = J2-41 B = J2-40

Data

Range5



Discrete Word

Label 271 011 350 012 017





Rate (ms) 250 1000 1000 250 200


429TX_1 (Low Speed) A = J2-43 B = J2-42








Table 5.3.6-228 Collins 8x10 DISPLAY CONFIGURATION GROUP 240

Function Value Display Type Collins Sweep Type Fan Auto Pop Up Category 7, Options Select Group #1 not used for this display The display system will monitor EGPWS ARINC label 274, bit 28 (left) and bit 29

(right), on the transition from 0 to 1 the display will automatically Pop-Up to the Terrain display mode. The display is always deselected manually. The display can be configured to not Pop-Up.

Peaks Mode Category 7, Options Select Group #1 not used Peaks always enabled Binary Peaks Elevations Yes - Data passed by ARINC 429, Labels 011 and 012 Manual select None (Terrain selection is controlled by display system) Manual deselect None (Terrain deselection is controlled by display system) Auto Range Yes (The display will monitor EGPWS label 274, bit 28 (left) and bit 29 (right) on the

‘0’ to ‘1’ bit transition the affected display will change its range to 5 NM if EGPWS label 300, bit 26 = 0 or 2 NM if bit 26 = 1.

Moving Marker No Overlay Page For Terrain Database version display only Display bus type Standard ARINC 708/453 label 055 CHANNEL 453TX_1


A = J1-58 B = J1-59

Terrain Display data to switching relay/MFD #1

CHANNEL 453TX_2


A = J1-56 B = J1-57

Terrain Display data to switching relay/MFD #2


CONNECT TO: Display #1 Bus2

Format: ARINC429 (High Speed) Fault Designation: DISPLAY BUS 1 Bus Type: Basic

A = J2-37 B = J2-36

Data Range (Display Word 2 type 2) MFD Discrete Word 1

Label 271 301

Sig. Bits N/A Discrete

Range 0.25-320NM Mode, Format

Signal Type Basic Basic

Resolution N/A N/A

Rate (ms) 100 100

CHANNEL 429RX_3

CONNECT TO: Display #2 Bus2

Format: ARINC429 (High Speed) Fault Designation: DISPLAY BUS 2 BUS TYPE: BASIC

A = J2-41 B = J2-40


Label 271 301




Resolution N/A N/A

Rate (ms) 100 100


429TX_1 (Low Speed) A = J2-43 B = J2-42

Transmits (Section 6) Label sets: 6.1.1.x, 6.1.2.x, 6.1.3.x, 6.1.4.x, 6.1.5.x, and 6.1.6.x

429TX_2 (Low Speed) A = J2-26 B = J2-9


Integration Notes: 1. This display requires the ARINC 429 data from the EGPWS. Output 429 Bus Group 1 supports the Collins Fault

Summary Words (Labels 350, 351, 355). The displays will Pop-up in response to EGPWS label 274, bit 28 (left side) and bit 29 (right side).

2. When interfacing to a single display controller configuration, the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel.



Table 5.3.6-229 Honeywell/Bendix IN182A/IN812A Radar display (RDR 2000) with Binary Peaks DISPLAY CONFIGURATION GROUP 235

Function Value Display Type Bendix IN182A/IN812A Radar Display (RDR-2000 radar system) Sweep Type Sweep range +/- 50 degrees Auto Pop Up Pop Up On Caution or Warning when the display is in the proper mode.

Category 7, Options Select Group #1, TA&D Alternate Pop Up: Always False Peaks Mode


Binary Peaks Elevations Yes; Data passed by ARINC 429 labels 011 and 012 (Terrain Mode and Peaks Elevation digits are located at the top left corner of display)

Manual select Anytime WXR is on and display is in proper Mode Manual deselect Anytime Auto Range No Moving Marker No Overlay Page Yes; TERR located on upper right side of Terrain image. Display bus type Standard ARINC 453 CHANNEL 453TX_1


A = J1-58 B = J1-59


CHANNEL 453TX_2


A = J1-56 B = J1-57



CHANNEL 429_422RX_1



A = J2-37 B = J2-36

Data Mode (Display Word 1) Range (Display Word 2 type 2)

Discrete Word (VP)2

Label270 271 273


Range Mode, Tilt, Gain 0.25-320NM VP Mode, Bit 11




CHANNEL 429RX_3



A = J2-41 B = J2-40

Data Mode (Display Word 1) Range (Display Word 2 type 2)


Label270 271 273


Range Mode, Tilt, Gain 0.25-320NM VP Mode, Bit 11








429TX_1 (Low Speed) A = J2-43 B = J2-42

Transmits (Section 6) Label sets: 6.1.1.x, 6.1.2.x, 6.1.3.x, 6.1.4.x, and 6.1.6.x



2 Not compatible with Radar indicators without VP mode, part numbers RDS-81 IN-812A 066-3114-00, IN-812A 066-3114-01; RDS-82 IN-182A 066-3084-00, IN-182A 066-3084-01, IN-182A 066-3084-02, IN-182A 066-3084-03.



Table 5.3.6-230 KC Picture Bus with Digital Discrete Word, Receive Channel 8 DISPLAY CONFIGURATION GROUP 0






A = J1-58 B = J1-59


CHANNEL 453TX_2


A = J1-56 B = J1-57


DISPLAY INPUT CONTROL GROUP 241 CHANNEL 429RX_8

6



A = J2-24 B = J2-07

Data

Range5



Discrete Word

Label 271 011 350 012 017





Rate (ms) 250 1000 1000 250 200

CHANNEL 429RX_3



A = J2-41 B = J2-40

Data

Range5



Discrete Word

Label 271 011 350 012 017





Rate (ms) 250 1000 1000 250 200


429TX_1 (Low Speed) A = J2-43 B = J2-42


Integration Notes: 1. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This

prevents the EGPWS from reporting an external bus fault on the second channel. 2. This Display Group is configured by the Display using response labels on its ARINC 429 data bus. 3. Some KCPB compatible displays require the EGPWS ARINC 429 Output Bus be connected to the KCPB display. 4. This display will cause the GPWS and TERRAIN INOP lamps to turn on only at the beginning of the EGPWS Self-Test

(standard operation is for the INOP lamps to be on for the entire Self-Test). 5. Label 012 is optional. The current fault and fault history message “RANGE” for label 271 (Range) is not shown if Range

Keys are requested on label 012 (Key Press/Display Mode). 6. This Display type and type 242 are the only display configurations applicable to helicopters using Category 16, Torque Input

Select Type ID 6. These display types are the only ones available that uses RX429-8 for range control. Torque Input Select Type 6 inputs torque data as RS-422 on RX429/422-1.



Table 5.3.6-231 Collins FDS-255 (Integrated with binary Peaks Elevations) DISPLAY CONFIGURATION GROUP 236

Function Value Display Type Collins FDS-255 with binary Peaks Elevations Sweep Type Fan Auto Pop Up 2 Pop Up On Caution or Warning

Category 7, Options Select Group #1, TA&D Alternate Pop Up: Always False Peaks Mode Peaks On

Category 7, Options Select Group #1 Peaks Enable: Always True Binary Peaks Elevations Yes - Data passed by ARINC 429, Labels 011 and 012 (Terrain Mode and Peaks

Elevation digits are located at the top left corner of display) Manual select None (Terrain selection is controlled by display system) Manual deselect None (Terrain deselection is controlled by display system) Auto Range 2 Yes to 5 NM normal or 2 NM Low Altitude mode (controlled by display, see

integration note 2.) Moving Marker No Overlay Page No Display bus type Standard ARINC 708 with divide by 20 range discrete bit CHANNEL TX453-1


A = J1-58 B = J1-59


CHANNEL TX453-2


A = J1-56 B = J1-57



CONNECT TO: IOC #1 Bus 1

Format: ARINC429 (High Speed) Fault Designation: IOC BUS 1 Bus Type: Basic

A = J2-37 B = J2-36

Data Range (Display Word 2 type 2)

Label 271

Sig. Bits N/A

Range 0.25-320NM

Signal Type Basic

Resolution N/A

Rate (ms) 100

CHANNEL 429RX_3

CONNECT TO: IOC #2 Bus 1

Format: ARINC429 (High Speed) Fault Designation: IOC BUS 2 BUS TYPE: BASIC

A = J2-41 B = J2-40

Data Range (Display Word 2 type 2)

Label 271

Sig. Bits N/A

Range 0.25-320NM

Signal Type Basic

Resolution N/A

Rate (ms) 100


429TX_1 (Low Speed) A = J2-43 B = J2-42

Transmits (Section 6) Label sets: 6.1.1.x, 6.1.2.x, 6.1.3.x, 6.1.4.x, 6.1.5.x and 6.1.6.x

429TX_2 (Low Speed) A = J2-26 B = J2-9


Integration Notes:


2. Pop-Up and Auto-range: The FDS-255 will monitor EGPWS 429 label 051 for Pop-Up bits, (bit 11 left channel and bit 12 right channel). When the Pop-Up bit for the affected channel transitions from a ‘0’ to a ‘1’ the corresponding display will : a) If Terrain is not selected then the display will automatically select Terrain mode and the Display Format shell be commanded to ARC. b) The FDS-255 shell monitor EGPWS 429 label 300, bit 26. If bit 26 is not set (‘0’) then the FDS-will command the range to the EGPWS be changed to 5 NM, or if bit 26 is set (‘1’) a range of 2 NM (all ranges are full scale). c) The display range or mode are reselectable by the operator immediately after the display has began sweeping the Terrain data. d) The ‘1’ to ‘0’ transition of EGPWS 429 label 051, bits 11 or 12 will be ignored by the display (unless there is a failure condition the deselection of Terrain mode is always done manually).



3. Status and Failure Monitoring The FDS-255 shell further monitor EGPWS labels, and display Terrain mode annunciations as shown below:

Priority ARINC Label FDS-255 Annunciation Description

High 1

274, bits 31/30 = 1/0 “TERR TEST” (white)

During EGPWS Self-Test a Terrain test pattern will be displayed (display will follow Pop-Up logic as described above)

2 274, bit 14 “GPWS INOP” (yellow) EGPWS classic modes INOP

3 274, bit 24 “TERR INOP” (yellow) The FDS-255 will clear the Terrain display

4 274, bit 27 “TERR N/A” (yellow) The FDS-255 will clear the Terrain display

5 050, bit 17 “TERR INHB” (white) The FDS-255 will continue to display Terrain when selected, Pop-Up will not be commanded by the EGPWS (Helicopter specific)

6 Low

- “TERR” (white) Terrain selected by FDS-255 (manually or via Pop-Up)



Table 5.3.6-232 Collins FDS-255 (Non-Integrated ) DISPLAY CONFIGURATION GROUP 237

Function Value Display Type Collins FDS-255 with selection controlled by the EGPWS Sweep Type Fan Auto Pop Up Pop Up On Caution or Warning



Manual select Anytime Manual deselect Anytime Auto Range No Moving Marker No Overlay Page Yes; Peaks numbers are located at the lower left of the display. Display bus type Standard CHANNEL TX453-1


A = J1-58 B = J1-59


CHANNEL TX453-2


A = J1-56 B = J1-57





A = J2-37 B = J2-36


Label 271

Sig. Bits Discrete

Range 5-320NM

Signal Type Basic

Resolution N/A

Rate (ms) 100

CHANNEL 429RX_3



A = J2-41 B = J2-40


Label 271

Sig. Bits Discrete

Range 5-320NM

Signal Type Basic

Resolution N/A

Rate (ms) 100





429TX_1 (Low Speed) A = J2-43 B = J2-42


Interface Notes: 1. At the time of this writing this interface has not been verified with an actual Helicopter FDS-255 display. It is

highly recommended that you discuss the suitability of this interface for your application with a Honeywell EGPWS representative prior to installation.

2. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the EGPWS from reporting an external bus fault on the second channel.

3. The FDS-255 will show the “WX” annunciations when Terrain is displayed.



Table 5.3.6-233 KC Picture Bus with Terrain Awareness Corrected Altitude DISPLAY CONFIGURATION GROUP 0




Manual select None (Display Control Selection) Manual deselect None (Display Control Selection) Auto Range Controlled by display response (if selected a 10 nm range will be used) Moving Marker None Overlay Page Controlled by display Display bus type KCPB CHANNEL 453TX_1


A = J1-58 B = J1-59


CHANNEL 453TX_2


A = J1-56 B = J1-57





Data

Range5

Label 271

Sig. Bits 11

Range 0.5-1023.5NM

Signal Type Basic

Resolution 0.5

Rate (ms) 250



CHANNEL 429RX_3



Data

Range5

Label 271

Sig. Bits 11

Range 0.5-1023.5NM

Signal Type Basic

Resolution 0.5

Rate (ms) 250




429TX_1 (Low Speed) A = J2-43 B = J2-42


429TX_2 (Low Speed) A = J2-26 B = J2-9


Interface Notes: 1. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input






Table 5.3.6-234 Collins 8x10 (S-92) DISPLAY CONFIGURATION GROUP 240

Function Value Display Type Collins Sweep Type Fan Auto Pop Up Category 7, Options Select Group #1 not used for this display The display system will monitor EGPWS ARINC label 274, bit 28 (left) and bit 29

(right), on the transition from 0 to 1 the display will automatically Pop-Up to the Terrain display mode. The display is always deselected manually. The display can be configured to not Pop-Up.

Peaks Mode Category 7, Options Select Group #1 not used Peaks always enabled Binary Peaks Elevations Yes - Data passed by ARINC 429, Labels 011 and 012 Manual select None (Terrain selection is controlled by display system) Manual deselect None (Terrain deselection is controlled by display system) Auto Range Yes (The display will monitor EGPWS label 274, bit 28 (left) and bit 29 (right) on the

‘0’ to ‘1’ bit transition the affected display will change its range to 5 NM if EGPWS label 300, bit 26 = 0 or 2 NM if bit 26 = 1.

Moving Marker No Overlay Page For Terrain Database version display only Display bus type Standard ARINC 708/453 label 055 CHANNEL 453TX_1


A = J1-58 B = J1-59


CHANNEL 453TX_2


A = J1-56 B = J1-57



CONNECT TO: IOC #1 Bus2


A = J2-37 B = J2-36


Label 271 301


Range 0.25-320NMMode,Format


Resolution N/A N/A

Rate (ms) 100 100

CHANNEL 429RX_3



A = J2-41 B = J2-40


Label 271 301




Resolution N/A N/A

Rate (ms) 100 100


429TX_1 (Low Speed) A = J2-43 B = J2-42


429TX_2 (Low Speed) A = J2-26 B = J2-9


Integration Notes: 1. This display requires the ARINC 429 data from the EGPWS. Output 429 Bus Group 1 supports the Collins Fault





Table 5.3.6-235 Collins ProLine IV (Non-Integrated) DISPLAY CONFIGURATION GROUP 2

Function Value Display Type Collins ProLine IV (5x6) Sweep Type Standard with +/-60 degree limit Auto Pop Up Pop Up On Caution or Warning

Category 7, Options Select Group #1, TA&D Alternate Pop Up: Always False


Peaks On

Category 7, Options Select Group #1 Peaks Enable: Always True

Manual select Anytime Manual deselect Anytime Auto Range No Moving Marker No Overlay Page Peaks Elevations located on upper left side of Terrain image. Display bus type Standard ARINC 453 CHANNEL 453TX_1


A = J1-58 B = J1-59


CHANNEL 453TX_2


A = J1-56 B = J1-57





A = J2-37 B = J2-36


Label 155

Sig. Bits Discrete

Range 5-640NM

Signal Type Basic

Resolution N/A

Rate (ms) 50

CHANNEL 429RX_3




Label 155

Sig. Bits Discrete

Range 5-640NM

Signal Type Basic

Resolution N/A

Rate (ms) 50




429TX_1 (Low Speed) A = J2-43 B = J2-42


Integration Notes: 1 When interfacing to a single display controller configuration, the bus must be connected to both EGPWS input




Table 5.3.6-236 Collins ProLine IV (Integrated) DISPLAY CONFIGURATION GROUP 241

Function Value Display Type Collins ProLine IV (5x6) Sweep Type Standard with +/-60 degree limit Auto Pop Up Pop Up On Caution or Warning – Popup controlled by display system



Peaks On


Pop Down Never Automatically pop down Manual select None (Terrain selection is controlled by display system) Manual deselect None (Terrain deselection is controlled by display system) Auto Range Yes (controlled by display system) Moving Marker No Overlay Page Peaks Elevations located on upper left side of Terrain image. Peaks does not support

blue water. Display Priority Standard Display bus type ARINC compatible format – Collins ProLine 4 (label 077) Terrain Mode Annunciation Standard CHANNEL 453TX_1


A = J1-58 B = J1-59


CHANNEL 453TX_2


A = J1-56 B = J1-57





A = J2-37 B = J2-36


Label 155

Sig. Bits Discrete

Range 5-640NM

Signal Type Basic

Resolution N/A

Rate (ms) 50

CHANNEL 429RX_3



A = J2-41 B = J2-40


Label 155

Sig. Bits Discrete

Range 5-640NM

Signal Type Basic

Resolution N/A

Rate (ms) 50


429TX_1 (Low Speed) A = J2-43 B = J2-42


429TX_2 (Low Speed) A = J2-26 B = J2-9


Integration Notes: 1 When interfacing to a single display controller configuration, the bus must be connected to both EGPWS input

channels. This prevents the EGPWS from reporting an external bus fault on the second channel. 2 This display requires the ARINC 429 data from the EGPWS. Output 429 Bus Group 1 supports the Collins Fault


3 This display will cause the GPWS and TERRAIN INOP lamps to turn on only at the beginning of the EGPWS Self-Test (standard operation is for the INOP lamps to be on for the entire Self-Test).



Table 5.3.6-242 KC Picture Bus without Digital Discrete Word, Receive Channel 8 DISPLAY CONFIGURATION GROUP 0




Peaks On


Manual select None (Display Controls Selection) Manual deselect None (Display Controls Selection) Auto Range Controlled by display response (if selected a 10 nm range will be used) Moving Marker None Overlay Page Controlled by display Display bus type KCPB CHANNEL 453TX_1


A = J1-58 B = J1-59


CHANNEL 453TX_2


A = J1-56 B = J1-57



CHANNEL 429RX_8

4

CONNECT TO: KCPB-IND #1 (range)

1

Format: ARINC 429 (Low Speed)


A = J2-24 B = J2-07

Data

Range3



Label 271 011 350 012





Rate (ms) 250 1000 1000 250

CHANNEL 429RX_3

CONNECT TO: KCPB-IND #2 (range)

1



A = J2-41 B = J2-40

Data

Range3



Label 271 011 350 012





Rate (ms) 250 1000 1000 250


429TX_1 (Low Speed) A = J2-43 B = J2-42


429TX_2 A = J2-26 B = J2-9

No Connection (No Data Output)


channels. This prevents the EGPWS from reporting an external bus fault on the second channel. 2. This Display Group is configured by the Display using response labels on its ARINC 429 data bus. 3. Label 012 is optional. The current fault and fault history message “RANGE” for label 271 (Range) is not shown if

Range Keys are requested on label 012 (Key Press/Display Mode). 4. This Display type and type 230 are the only display configurations applicable to helicopters using Category 16,

Torque Input Select Type ID 6. These display types are the only ones available that uses RX429-8 for range control. Torque Input Select Type 6 inputs torque data as RS-422 on RX429/422-1.



Table 5.3.6-246 Honeywell /Bendix EFIS 10 (Non-Integrated) DISPLAY CONFIGURATION GROUP 246

Function Value Display Type Bendix EFIS 10 display with EFIS 86 radar system Sweep Type Normal, Sweep range +/- 90 degrees Auto Pop Up Pop Up On Caution or Warning



Peaks On


Manual select Anytime 1 Manual deselect Anytime 1 Auto Range No Moving Marker No Overlay Page Yes; Peaks numbers are located at the lower left of the display. Display bus type Standard ARINC 708/453 CHANNEL 453TX_1


A = J1-58 B = J1-59


CHANNEL 453TX_2


A = J1-56 B = J1-57



CONNECT TO: WX-IND #1 (range)

2



A = J2-37 B = J2-36


Label270 271

Sig. Bits Discrete Discrete

Range Mode, Tilt, Gain 5-320NM


Resolution N/A N/A

Rate 100 ms 100 ms

CHANNEL 429RX_3

CONNECT TO: WX-IND #2 (range)

2



A = J2-41 B = J2-40


Label270 271


Range Mode, Tilt, Gain 5-320NM


Resolution N/A N/A

Rate 100 ms 100 ms





429TX_1 (Low Speed) A = J2-43 B = J2-42


429TX_2 A = J2-26 B = J2-9


Integration note: 1. Either weather or a weather test pattern must be displayed before Terrain can be viewed. The white weather

annunciation “WX” will still be present when terrain is displayed. 2. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input




Table 5.3.6.-249 Honeywell Primus Epic & Epic CDS/R, with overlay Peaks Elevations (Integrated) DISPLAY CONFIGURATION GROUP 249

Function Value Display Type Honeywell Integrated Primus Epic CDS/R (Control Display System/Retrofit), with

overlay peaks elevations Sweep Type Honeywell Auto Pop Up Pop Up On Caution or Warning from neither, based upon Honeywell display configuration.


Peaks On


Manual select None (Terrain selection is controlled by display system) Manual deselect None (Terrain deselection is controlled by display system) Auto Range Yes, 10 NM Moving Marker No Overlay Page Yes, for Peaks Elevations only (located lower right side of display) Display bus type Honeywell picture bus CHANNEL TX453-1

CONNECT TO: TERRAIN DISPLAY BUS #1/#2 Format: WXPD

A = J1-58 B = J1-59

Honeywell left/right interleaved picture bus to MFD and PFD


CONNECT TO: IOC Bus #1 Format: ARINC 429 (High Speed)


A = J2-37 B = J2-36

Data FWC & GP Discrete word

Label 171

Sig. Bits 15-18 25-28

Range Format 1, Type 1 2000NM Discrete

Signal Type Basic

Resolution N/A

Rate (ms) 100

CHANNEL 429RX_3



A = J2-41 B = J2-40


Label 171

Sig. Bits 15-18 25-28


Signal Type Basic

Resolution N/A

Rate (ms) 100


429TX_1 (Low Speed) A = J2-43 B = J2-42


Integration notes: 1. The EGPWS ARINC 429 Output Bus must be connected to the display.

2. Display channels 1 and 2 are multiplexed on ARINC 453 Bus 1. 3. The ‘IOC BUS’ fault will be present only if both MG inputs have failed. 4. The Honeywell EFIS SG & MG provide terrain display relay control.

5. This display will cause the GPWS and TERRAIN INOP lamps to turn on only at the beginning of the EGPWS Self-Test (standard operation is for the INOP lamps to be on for the entire Self-Test).

6. This display uses the following ARINC 429 labels from the EGPWS for annunciation’s: Label 050 If bits 11-14 left range output from EGPWS does not match left MFD range (via label 171), then display white “RANGE

MISMATCH” on left PFD and MFD. If bits 15-18 right range output from EGPWS does not match right MFD range (via label 171), then display white “RANGE MISMATCH” on right PFD and MFD.

Label 051 If Bit 17 = 1 then Epic CDS/R will place “TERRAIN OFF” message on PFD and MFD. Labels 052-055 EGPWS ASCII characters are not used. Green TERRAIN on PFD and MFD by EFIS. Label 274 If Bit 13 or 22 =1 then display red “PULL UP” on left and right PFD.

If Bit 12 or 23 =1 then display amber “GND PROX” on left and right PFD. If Bit 14 = 1 then display white “GPWS FAIL” message on PFD. If Bit 24 = 1 then display amber “TERRAIN FAIL” message on PFD and MFD (Terrain cleared by Epic). If Bit 27 = 1 then display amber “TERRAIN NA” message on PFD and MFD (Terrain cleared by Epic). If Bit 28 = 1 and display configured for pop on Pilots side, then Pop Up Terrain on left MFD. If Bit 29 = 1 and display configured for pop on CoPilots side, then Pop Up Terrain on right MFD. If Bit 14 and Bit 24 = 1 then display amber “EGPWS SYS FAIL” on PFD in lieu of “GPWS FAIL” message on the PFD. If bits 30 and 31 = 01 (functional test) then display white “TERRAIN TEST” on PFD and MFD.



Table 5.3.1.6-250 Honeywell EDZ705 (5x5), EDZ756 (5x6) with DC-811 range push button control DISPLAY CONFIGURATION GROUP 250

Function Value Display Type Honeywell (SPZ8000 new style - every fourth display line is blanked) Sweep Type Honeywell

Auto Pop Up Pop Up On Caution or Warning



Peaks On

Category 7, Options Select Group #1 Peaks Enable: Always True Manual select None (Terrain selection is controlled by display system) Manual deselect None (Terrain deselection is controlled by display system) Auto Range Yes (10NM) Moving Marker Yes (Honeywell type) Overlay Page Yes for Peaks Elevations only (located middle right of display). Display bus type Honeywell picture bus CHANNEL 453TX_1


A = J1-58 B = J1-59

Terrain Display data to switching relay/Symbol Generator #1 and MFD left channel

CHANNEL 453TX_2


A = J1-56 B = J1-57

Terrain Display data to switching relay/Symbol Generator #2 and MFD right channel


CHANNEL 429_422RX_12

CONNECT TO: DC-811 #11

Format: RS-422 (7.8125K baud) Fault Designation: DISPLAY BUS 1 Bus Type: Basic

A = J2-36 B = J2-37

Data Range (Up/Down)

Label N/A

Sig. Bits

Range

Signal Type Basic

Resolution N/A

Rate (ms) 100

CHANNEL 422RX_2

CONNECT TO: DC-811 #21

Format: RS-422 (7.8125K baud) Fault Designation: DISPLAY BUS 2 Bus Type: Basic

A = J2-10 B = J2-11

Data Range (Up/Down)

Label N/A

Sig. Bits

Range

Signal Type Basic

Resolution N/A

Rate (ms) 100


429TX_1 (Low Speed) A = J2-43 B = J2-42


Integration Notes: 1. When interfacing to a single display controller configuration the bus must be connected to both EGPWS input channels. This prevents the

EGPWS from reporting an external bus fault on the second channel. 2. The channel 429_422RX polarity is reversed from ARINC 429 receive applications.

3. The EGPWS ARINC 429 Output Bus must be connected to the display. 4. This display uses the following ARINC 429 labels from the EGPWS for annunciation’s:

The Terrain display will annunciate: “TERR" in green or cyan (depending on the program) when the Terrain is selected and valid. “TERR” in amber if Terrain is selected and any of the following conditions are TRUE:

The EGPWS ARINC 429 output bus is missing or labels 050 and 051 are absent or unreadable for 2 seconds. EGPWS ARINC label 051 bit 13 = 0 (“Terrain Display Valid” bit FALSE) EGPWS ARINC label 050 bit 17 = 1 (“Terrain Inhibit” bit TRUE)

Note - Per customer request for EDZ705 and EDZ756, the display does not blank when Terrain is Inhibited, nor is an amber TERR presented. This change is part of the EFIS system

EGPWS ARINC labels are valid, but range in label 050 disagrees with range via SCI bus label 80 (Label 050 bit 11-14 contain left display range and bits 15-18 the right).

The display will be blanked when the amber “TERR” is present. The Terrain display will Pop Up to Terrain mode as follows:

If all the conditions indicated by for the amber “TERR” above are FALSE. If the display is in normal MFD mode (not HSI backup, or SG backup) AND if Label 051 bit 11 transitions from 0 to 1 (rising edge),

AND Checklist is not selected on the MFD, AND TCAS Auto Pop Up is not occurring. The display will change to Map mode. The display will energize the Terrain selection relays. The display will annunciate “TERR”. The display will change to the range indicated by the EGPWS ARINC 429 Label 050.



Table 5.3.6.-251 Honeywell Primus Epic & Epic CDS/R, with binary Peaks Elevations (Integrated) DISPLAY CONFIGURATION GROUP 251

Function Value Display Type Honeywell Integrated Primus Epic CDS/R (Control Display System/Retrofit), with

binary peaks elevations Sweep Type Honeywell Auto Pop Up Pop Up On Caution or Warning from neither, based upon Honeywell display configuration.

Category 7, Options Select Group #1, TA&D Alternate Pop Up: Always False Peaks Mode Peaks On


Binary Peaks Elevations Yes - Data passed by ARINC 429, Labels 011 and 012 Manual select None (Terrain selection is controlled by display system) Manual deselect None (Terrain deselection is controlled by display system) Auto Range Yes, the autorange will be 5 NM standard, or 2 NM when low altitude mode is

indicated by EGPWS ARINC label 300, bit 26 being set to ‘1’. Moving Marker No Overlay Page No Display Priority Standard Display bus type Honeywell picture bus CHANNEL TX453-1

CONNECT TO: TERRAIN DISPLAY BUS #1/#2 Format: WXPD

A = J1-58 B = J1-59

Honeywell left/right interleaved picture bus to MFD and PFD




A = J2-37 B = J2-36


Label 171

Sig. Bits 15-18 25-28


Signal Type Basic

Resolution N/A

Rate (ms) 100

CHANNEL 429RX_3



A = J2-41 B = J2-40


Label 171

Sig. Bits 15-18 25-28


Signal Type Basic

Resolution N/A

Rate (ms) 100


429TX_1 (Low Speed) A = J2-43 B = J2-42


429TX_2 (Low Speed) A = J2-26 B = J2-9


Integration notes: 1. The EGPWS ARINC 429 Output Bus must be connected to the display. 2. Display channels 1 and 2 are multiplexed on ARINC 453 Bus 1. 3. The ‘IOC BUS’ fault will be present only if both MG inputs have failed. 4. The Honeywell EFIS SG & MG provide terrain display relay control. 5. This display will cause the GPWS and TERRAIN INOP lamps to turn on only at the beginning of the EGPWS Self-

Test (standard operation is for the INOP lamps to be on for the entire Self-Test). 6. This display uses the following ARINC 429 labels from the EGPWS for annunciation’s:

Label 011/012 Upper/Lower Peaks Elevations – “xxx/xxx” on PFD and MFD. Label 050 If bits 11-14 left range output from EGPWS does not match left MFD range (via label 171), then

display white “RANGE MISMATCH” on left PFD and MFD. If bits 15-18 right range output from EGPWS does not match right MFD range (via label 171), then display white “RANGE MISMATCH” on right PFD and MFD.

Label 051 If Bit 17 = 1 then the Epic CDS/R will place “WARNINGS INHIBITED” centered within the Terrain window.

Labels 052-055 EGPWS ASCII characters are not used. Green TERRAIN on PFD and MFD by Epic.



Label 274 If Bit 13 or 22 =1 then display red “PULL UP” on left and right PFD. If Bit 12 or 23 =1 then display amber “GND PROX” on left and right PFD. If Bit 14 = 1 then display white “GPWS FAIL” message on PFD. If Bit 24 = 1 then display amber “TERRAIN FAIL” message on PFD and MFD (Terrain cleared by Epic). If Bit 27 = 1 then display amber “TERRAIN NA” message on PFD and MFD (Terrain cleared by Epic).. If Bit 28 = 1 and display configured for pop on Pilots side, then Pop Up Terrain on left MFD. If Bit 29 = 1 and display configured for pop on CoPilots side, then Pop Up Terrain on right MFD. If Bit 14 and Bit 24 = 1 then display amber “EGPWS SYS FAIL” on PFD in lieu of “GPWS FAIL” message on the PFD. If bits 30 and 31 = 01 (functional test) then display white “TERRAIN TEST” on PFD and MFD.



Table 5.3.6-255 Honeywell SPZ8000 (w/ SCI range) DISPLAY CONFIGURATION GROUP 255

Function Value Display Type Honeywell (5x6) (SPZ8000) older style; does not blank every fourth weather radar

display line. This interface supports SG-810 and SG-811 SPZ8000 systems only. Sweep Type Honeywell Auto Pop Up Pop Up On Caution or Warning



Peaks On


Manual select None (Terrain selection is controlled by display system) Manual deselect None (Terrain deselection is controlled by display system) Auto Range Yes (10 NM) Moving Marker Yes (Honeywell type) Overlay Page Yes, Peaks Elevations (located lower right of display) Display bus type Honeywell picture bus CHANNEL 453TX_1


A = J1-58 B = J1-59


CHANNEL 453TX_2


A = J1-56 B = J1-57

Terrain Display data to switching relay/Symbol Generator #2 (NOTE: Range setting always follows Display Bus #1).


CONNECT TO: SCI Bus #1 Format: RS-422 (12K baud)


A = J2-36 B = J2-37


Label 80


Range 2000NM

Signal Type Basic

Resolution N/A

Rate (ms) 100


429TX_1 (Low Speed) A = J2-43 B = J2-42


429TX_2 A = J2-26 B = J2-9


Integration Notes: 1. The EGPWS ARINC 429 Output Bus must be connected to the SPZ8000 display. 2. The channel 429_422RX polarity is reversed from ARINC 429 receive applications. 3. This display type may also be used for an integrated P880/660/440 display, but requires Auto Pop Up to be disabled and

relay selection to be controlled directly from an alternate action switch (for new installations of P880/660/440 use ID 13).



5.3.7 CATEGORY 7, OPTIONS 1 SELECT

The following table provides identification of the Options 1 Select. Each entry in the ID column corresponds to a particular combination of TA&D Alternate Pop Up, Obstacle Awareness Enabled, Peaks Mode Enabled, Bank Angle Enable, Steep Approach Enabled, Flap / WOW Reversal and GPS Altitude Reference selection. Refer to section 7.5 for configuration messages that will be present for each option selected.

Note: For Helicopter applications Peaks Mode Enable is always True and Steep Approach & TA&D Alternate Pop Up are always False. The Option Select Group #1 table has been minimized to reflect only the remaining valid ID’s.

TABLE 5.3.7: OPTIONS SELECT GROUP #1

ID Steep Approach Enabled1

TA&D Alternate Pop Up

Peaks Mode

Enabled2

Obstacle Awareness

Enabled

Bank Angle

Enable3

Flap / WOW

Reversal

GPS Altitude

Reference4

Effectivity

16 False False True False False False WGS-84 -020 17 False False True False False False MSL -020 18 False False True False False True WGS-84 -020 19 False False True False False True MSL -020 20 False False True False True False WGS-84 -020 21 False False True False True False MSL -020 22 False False True False True True WGS-84 -020 23 False False True False True True MSL -020 24 False False True True False False WGS-84 -020 25 False False True True False False MSL -020 26 False False True True False True WGS-84 -020 27 False False True True False True MSL -020 28 False False True True True False WGS-84 -020 29 False False True True True False MSL -020 30 False False True True True True WGS-84 -020 31 False False True True True True MSL -020

1 TRUE enables steep approach selection via Steep Approach Select Discrete (see Section 5.3.13 and 6.6.29). This option must be FALSE for helicopter applications. 2 Enables PEAKS mode display if display supports (see display configuration group Section 5.3.6). This mode is always true for helicopters regardless of the option selection provided for in this category. 3 This option must be FALSE if Roll Angle is configured to No Connection. Refer to Table 5.3.10. 4 "MSL" reference must be selected when an internal GPS is utilized. Refer to Table 5.3.3-2



5.3.8 CATEGORY 8, RADIO ALTITUDE INPUT SELECT

The following table provides identification of the Radio Altitude type. The entry in the Radio Altitude Type corresponds to a table that provides detailed information on the configuration. For example, the details for Radio Altitude Type #1 are found in Table 5.3.8-1. ARINC 552, ALT 55 and digital ARINC 429 compatible Radio Altimeters are supported.

CAUTION: ALT 50 and 55 radio altimeters use an average altitude tracking technique that does not track the nearest terrain. This can produce errors up to 200 to 300 feet in high bank turns and mountainous terrain. This characteristic may degrade EGPWS performance for Modes 1 thru 6.

In this category, only the following signals are defined:

Radio Altitude source selection, input scaling, and associated validities. Decision Height (DH) Minimum Decision Altitude (MDA) TABLE 5.3.8: RADIO ALTITUDE INPUT SELECT

ID Radio Altitude

Type (Table 5.3.8-x)

Description

Effectivity

0 0 Analog Radio Altitude (ARINC 552) -020 1 1 Analog Radio Altitude (ALT 55) -020 2 2 Digital Radio Altitude (ARINC 429) (Note 2) -020 3 3 Analog Radio Altitude (RT-200/300) -020 4 4 Analog Radio Altitude (KRA 405) -020 5 5 Analog Radio Altitude (ALT 50) -020 6 6 Analog Radio Altitude (APN 209) (Note 4) -022

251 251 Digital Radio Altitude with DH/MDA (170) via dual IOC buses (ARINC 429) (Note 1)

-020

252 252 Digital Radio Altitude with DH (370) via dual IOC buses (ARINC 429) (Note 1)

-020

253 253 Digital Radio Altitude with DH Discrete via dual IOC buses (ARINC 429) (Note 1)

-020

254 254 Digital Radio Altitude with DH (370) and MDA (170)

via dual IOC buses (ARINC 429) (Notes 1,3) -020

255 255 Digital Radio Altitude (ARINC 429) via dual IOC buses (ARINC 429) (Notes 1)

-020

Note 1: IDs 251-255 may only be used in conjunction with other IOC bus selections for categories 2, 6,

9, 10, 11, 12, 13 and 16 that use the same ARINC 429 receiver channels and bus speeds. Note 2: Digital Radio Altimeters cannot be used on two engine Helicopters with Digital Torque. Note 3: ID 254 must be used in conjunction with Category 9, ID 254, since this provides Label 163

which determines from bits 19-21 whether MDA or DH is displayed. Note 4: ID 6 (APN 209) may not be used with analog Air Data types 0, 3, 4, 11 and 12. ID 6 is not

compatible with TSO C151 requirements (0 to 1500 ft range).



TABLE 5.3.8-0: RADIO ALTITUDE INPUT SELECT TYPE 0 (ARINC 552) SIGNAL CONNECTION SUMMARY DATA

Radio Altimeter #1 (+) = J1-64 (-) = J1-45

Format: ARINC 552 with Validity Flag Input Type: Basic Fault Designation: RADIO ALTIMETER FAULT Validity: Radio Altitude Valid Discrete #1 (+28V)

PIN FUNCTION CONNECTION PIN TYPE CHANNEL DESIGNATION REFERENCE


Radio Altitude Validity Discrete #1 (+28V)

J1-29 Input 28V_DISC_07 >+17V = Valid <+4.4V = Invalid

DH Discrete (Gnd) J1-33 Input GND_DISC_11 Gnd = Below DH <not> Gnd = Above DH

CONFIGURATION DATA Description Value Out of Track Maximum Pseudo altitude is only allowed to operate within

these limits. 2800

Out of Track Minimum -20

Pseudo Altitude Type Selects parameters for pseudo altitude engage logic Roll Engage 30° / DisEngage 25° Pitch Engage 45° / DisEngage 43° Engage Time Limit (Max) 120sec

Field Enable Type Selects pseudo altitude field elevation False

TABLE 5.3.8-1: RADIO ALTITUDE INPUT SELECT TYPE 1 (ALT 55)



Format: Alt 55 with Validity Flag Input Type: Basic Fault Designation: RADIO ALTIMETER FAULT Validity: Radio Altitude Valid Discrete #1 (+28V)







these limits. 2800




TABLE 5.3.8-2: RADIO ALTITUDE INPUT SELECT TYPE 2 (ARINC 429)

CHANNEL 429RX_5

CONNECT TO: LRRA #1 (Left) Format: ARINC 429 (Low Speed)

Fault Designation: RADIO ALTIMETER BUS Bus Type: Basic

A = J2-21 B = J2-4

Data Radio Altitude

Label 164

Sig. Bits 16

Range ±8192 FT

Signal Type Basic

Resolution 0.125

Rate (ms) 25-50





these limits. 2800






TABLE 5.3.8-3: RADIO ALTITUDE INPUT SELECT TYPE 3 (RT-200/300) SIGNAL CONNECTION SUMMARY DATA


Format: DC with Validity Flag (RT-200/300) Input Type: Basic Fault Designation: RADIO ALTIMETER FAULT Validity: Radio Altitude Valid Discrete #1 (+28V)







these limits. 2800




TABLE 5.3.8-4: RADIO ALTITUDE INPUT SELECT TYPE 4 (KRA 405)










these limits. 2800




TABLE 5.3.8-5: RADIO ALTITUDE INPUT SELECT TYPE 5 (ALT 50)










these limits. 2100






TABLE 5.3.8-6: RADIO ALTITUDE INPUT SELECT TYPE 6 (APN 209 - H60 BLACKHAWK) SIGNAL CONNECTION SUMMARY DATA

Radio Altimeter #1 (+) = J1-64 (-) = J1-45 Note 1

Format: APN 209 (-7mVDC/FT, 1500 FT, 0V=0FT, Out-of-Trk= <-11VDC, PTT= 1000 FT) Input Type: Basic Fault Designation: RADIO ALTIMETER FAULT Validity: Radio Altitude Valid



Radio Altitude Validity (+) = J1-62 (-) = J1-43

Input ALT_H ALT_L

>+3.5V = Valid <+1.0V = Invalid



these limits. 1570




Note 1: APN 209 connections as follows: Remote Analog Alt Signal ………. RT 1115A pin J2-2 to MK XXII (+) J1-64 * Signal Gnd ………………………. RT 1115A pin J2-11 to MK XXII (-) J1-45 Reliability Signal ……..……….… RT 1115A pin J1-12 to MK XXII (+) J1-62 Signal Gnd ………………………. RT 1115A pin J1-4 to MK XXII (-) J1-43 Low Altitude Warning Out ……… RT 1115A pin J1-1 to MK XXII J1-33 *The EGPWS analog card will reverse negative voltage and scale the input to positive altitude reading.

TABLE 5.3.8-251: RADIO ALTITUDE INPUT SELECT TYPE 251 (DUAL IOC BUSES WITH DH/MDA) CHANNEL 429RX_1



A = J2-37 B = J2-36

Data Radio Altitude

Label 164

Sig. Bits 16

Range ±8192 ft

Signal Type Basic

Resolution 0.125

Rate (ms) 25-50

Decision Height/MDA 170 DH 12 MDA 14

0-4096 ft 0-16384 ft

Basic 1.0 1000

CHANNEL 429RX_3



A = J2-41 B = J2-40

Data Radio Altitude

Label 164

Sig. Bits 16

Range ±8192 ft

Signal Type Basic

Resolution 0.125

Rate (ms) 25-50

Decision Height/MDA 170 DH 12 MDA 14

0-4096 ft 0-16384 ft

Basic 1.0 1000


these limits. 2800






TABLE 5.3.8-252: RADIO ALTITUDE INPUT SELECT TYPE 252 (DUAL IOC BUSES WITH DH) CHANNEL 429RX_2



A = J2-39 B = J2-38

Data Radio Altitude Decision Height (format 1)

Label 164 370

Sig. Bits 16 16

Range ±8192 FT ±8192 FT


Resolution 0.125 0.125

Rate (ms) 25-50 100-200

CHANNEL 429RX_5



A = J2-21 B = J2-04


Label 164 370

Sig. Bits 16 16

Range ±8192 FT ±8192 FT



Rate (ms) 25-50 100-200


these limits. 2800




Format 1 = 0/0 SDI

TABLE 5.3.8-253: RADIO ALTITUDE INPUT SELECT TYPE 253 (DUAL IOC BUSES WITH DH DISCRETE)

CHANNEL 429RX_1



A = J2-37 B = J2-36

Data Radio Altitude

Label 164

Sig. Bits 16

Range ±8192 FT

Signal Type Basic

Resolution 0.125

Rate (ms) 25-50

CHANNEL 429RX_3



A = J2-41 B = J2-40

Data Radio Altitude

Label 164

Sig. Bits 16

Range ±8192 FT

Signal Type Basic

Resolution 0.125

Rate (ms) 25-50





these limits. 2800






TABLE 5.3.8-254: RADIO ALTITUDE INPUT SELECT TYPE 254 (DUAL IOC BUSES WITH DH & MDA) CHANNEL 429RX_1



A = J2-37 B = J2-36

Data Radio Altitude Decision Height (format 3) MDA (format 3)

Label 164 370 170

Sig. Bits 16 16 16

Range ±8192 FT ±8192 FT ±65536 FT


Resolution 0.125 0.125 1

Rate (ms) 25-50 100-200 200

CHANNEL 429RX_3



A = J2-41 B = J2-40

Data Radio Altitude Decision Height (format 3) MDA (format 3)

Label 164 370 170

Sig. Bits 16 16 16

Range ±8192 FT ±8192 FT ±65536 FT


Resolution 0.125 0.125 1

Rate (ms) 25-50 100-200 200


these limits. 2800




Format 3 = no SDI

TABLE 5.3.8-255: RADIO ALTITUDE INPUT SELECT TYPE 255 (DUAL IOC BUSES WITH DH)

CHANNEL 429RX_1



A = J2-37 B = J2-36


Label 164 370

Sig. Bits 16 16

Range ±8192 FT ±8192 FT



Rate (ms) 25-50 100-200

CHANNEL 429RX_3



A = J2-41 B = J2-40


Label 164 370

Sig. Bits 16 16

Range ±8192 FT ±8192 FT



Rate (ms) 25-50 100-200


these limits. 2800




Format 1 = 0/0 SDI



5.3.9 CATEGORY 9, NAVIGATION INPUT SELECT

The following table provides identification of the Navigation type. The entry in the Navigation Type corresponds to a table that provides detailed information on the configuration. For example, the details for Navigation Type #1 are found in Table 5.3.9-1. In this category, only the following signals are defined:

Glideslope source selection Localizer source selection. (optional for digital only) PFD Mode Select Word ILS Select Source Configuration Data Selected Course Vertical & Lateral deviation (added -030 software) In cases where the signals are on an ARINC 429 bus with other signals, you may: In other categories select the same but with the same Fault Designation name and Channel connection as the

category. In this case a single physical bus with a single connection satisfies more than one category, or; In other categories select a different bus Fault Designation name and Channel connection and wire the

connections to the same source (if loading permits). Note: In this case a single bus failure will result in multiple bus names being faulted in the EGPWS self-test. In this case a single physical bus with multiple connections satisfies more than one category.

Note: Numerous (but not all) Envelope Modulation cases require a localizer input. Therefore a NAV ID that supplies both Glideslope and Localizer should be selected in this category if possible. However, due to hardware limitations, use of localizer for installations that can only provide low level validity is not supported. In these cases only ID #1 can be selected. Envelope Modulation will still function for these glideslope only installations, but not for those envelope modulation areas that require a localizer crosscheck.



TABLE 5.3.9: NAVIGATION INPUT SELECT

ID Navigation

Inputs Select (Table 5.3.9-x)

Description Effectivity

0 0 Analog Glideslope (ARINC 547) with +28V Validity Flag

-020

1 1 Analog Glideslope (ARINC 547) with Low Level Validity

-020

2 2 Digital Glideslope (ARINC 429) -020

3 3 Digital Glideslope and Localizer (ARINC 429) -020

4 4 Digital KN40 Glideslope and Localizer (ARINC 429) -020

5 5 Analog Glideslope/Localizer (ARINC 547) with +28V Validity Flags

-020

6 6 Digital Glideslope, Localizer, Vertical Deviation, Lateral Deviation, and Mode Control (ARINC 429)

-030

248 248 Digital Glideslope and Localizer, Vertical and Lateral Deviation via dual IOC buses (ARINC 429) (Note 1)

-030

249 249 Digital Glideslope and Localizer w/SDI, Selected Course

via dual IOC buses (ARINC 429) (Note 1) -026

250 250 Digital Glideslope, Localizer, Selected Course, PFD Mode via dual IOC buses (ARINC 429) (Note 2)

-020

251 251 Digital Glideslope, Localizer, Selected Course via dual IOC buses (ARINC 429) (Note 1)

-020

252 252 Digital Glideslope and Localizer via dual IOC buses (ARINC 429) (Note 1)

-020


-020

254 254 Digital Glideslope, Localizer, PFD Mode via dual IOC buses (ARINC 429) (Note 2)

-020


-020

Note 1: IDs 248, 249, 251, 252, 253, and 255 may only be used in conjunction with other IOC bus selections for categories 2,6,8,10,11, 12, 13 and 16 that use the same ARINC 429 receiver channels and bus speeds.

Note 2: IDs 250 and 254 may only be used in conjunction with other IOC bus selections for categories 2,6,8,10,11, 12, 13 and 16 that use the same ARINC 429 receiver channels and bus speeds. The use of either the left or right source is based on the displayed source provided on label 163.



TABLE 5.3.9-0: NAVIGATION INPUTS SELECT 0 SIGNAL CONNECTION SUMMARY DATA

Glideslope Deviation (+) = J1-65 (-) = J1-46

Format: ARINC 547 with Validity Flag & ILS Select Input Type: Basic Fault Designation: GLIDESLOPE FAULT Validity: Glideslope Validity Discrete #1 (+28V)



Glideslope Validity Discrete #1

J1-11 Input 28V_DISC_06 >+17V = Valid < +4.4V = Not Valid

+28V ILS Tuned Discrete #1

J1-39 Input 28V_DISC_01 >+17V = ILS Tuned < +4.4V = ILS Not Tuned

GND ILS Tuned Discrete #1

J1-20 Input GND_DISC_01 Gnd = ILS Tuned <not> Gnd = ILS Not Tuned

Configuration Data Type ILS Source Select Type None

TABLE 5.3.9-1: NAVIGATION INPUTS SELECT 1



Format: ARINC 547 with Low Level Validity & ILS Select Input Type: Basic Fault Designation: GLIDESLOPE FAULT Validity: Low Level Glideslope Deviation Validity

Low Level Glideslope Deviation Validity

(+) = J1-30 (-) = J1-10

Format: DC Input Type: Basic Fault Designation: GLIDESLOPE LOW LEVEL VALIDITY FAULT > 0.145V = Valid (typical active range is 0.16V to 0.84V) <= 0.145V = Invalid









CHANNEL 429RX_6

CONNECT TO: ILS #1 Format: ARINC 429 (Low Speed)

Fault Designation: ILS BUS Bus Type: Basic

A = J2-22 B = J2-5

Data Glideslope

Label 174

Sig. Bits 12

Range ±0.8 DDM

Signal Type Basic

Resolution 0.0001953125

Rate (ms) 33.3-66.6



CHANNEL 429RX_6



A = J2-22 B = J2-5

Data Glideslope Localizer

Label 174 173

Sig. Bits 12 12

Range ±0.8 DDM ±0.4 DDM


Resolution 0.0001953125 0.00009765625

Rate (ms) 33.3-66.6 33.3-66.6




TABLE 5.3.9-4: NAVIGATION INPUTS SELECT 4 CHANNEL 429RX_6



A = J2-22 B = J2-5

Data Glideslope Localizer ILS Select (VOR/ILS Freq)

Label 174 173 034

Sig. Bits 12 12 Discrete

Range ±0.8 DDM ±0.4 DDM n/a


Resolution 0.0001953125 0.00009765625 Bit 14 = ILS

Rate (ms) 33.3-66.6 33.3-66.6 167-333

Configuration Data Type KN40 Nav Source True ILS Source Select Type None




Format: ARINC 547 with Validity Super Flag & ILS Select Input Type: Basic Fault Designation: GLIDESLOPE FAULT Validity: Glideslope Validity Discrete #1 (+28V)

Localizer Deviation (+) = J1-30 (-) = J1-10

Format: ARINC 547 with Validity Flag & ILS Select Input Type: Basic Fault Designation: LOCALIZER FAULT Validity: Localizer Validity Discrete #1 (+28V)


Polarity/Configuration Reference

Localizer Validity Discrete #1


Glideslope Validity Discrete #1







TABLE 5.3.9-6: NAVIGATION INPUTS SELECT 6 (EPIC/APEX)

CHANNEL 429RX_6



Data Label Sig. Bits Range Signal Type Resolution Rate (ms) A = J2-22 Glideslope 174 12 ±0.8 DDM Basic 0.0001953125 33.3-100 B = J2-5 Localizer

Vertical Deviation Lateral Deviation* Mode 5 Control

173 117 116 163

12 12 12 Discrete

±0.4 DDM ±0.8 DDM ±0.4 DDM Discrete

Basic Basic Basic Basic

0.00009765625 0.0001953125 0.00009765625 n/a

33.3-100 33.3-100 33.3-100 33.3-100


* Fault message is “Horizontal Deviation”

Note: The installer should insure that the labels 116 and 117 will only transmit data in DDM form because this selection does not use a PFD Mode Select Word to define valid modes.



TABLE 5.3.9-248: NAVIGATION INPUTS SELECT 248 (EPIC) CHANNEL 429RX_1





173 117 116 163

12 12 12 Discrete



0.00009765625 0.0001953125 0.00009765625 n/a

33.3-100 33.3-100 33.3-100 33.3-100

Selected Course 100 11 ±180 degrees Basic 0.087890625 33.3-100

CHANNEL 429RX_3





173 117 116 163

12 12 12 Discrete



0.00009765625 0.0001953125 0.00009765625 n/a

33.3-100 33.3-100 33.3-100 33.3-100

Selected Course 100 11 ±180 degrees Basic 0.087890625 33.3-100


* Fault message is “Horizontal Deviation”



CHANNEL 429RX_2



Data Label Sig. Bits Range Signal Type Resolution Rate (ms) A = J2-39 Glideslope with SDI 174 12 ±0.8 DDM Basic 0.0001953125 33.3-100 B = J2-38 Localizer with SDI 173 12 ±0.4 DDM Basic 0.00009765625 33.3-100 Selected Course 100 11 ±180 degrees Basic 0.087890625 33.3-100

CHANNEL 429RX_5



Data Label Sig. Bits Range Signal Type Resolution Rate (ms) A = J2-21 Glideslope with SDI 174 12 ±0.8 DDM Basic 0.0001953125 33.3-100 B = J2-04 Localizer with SDI 173 12 ±0.4 DDM Basic 0.00009765625 33.3-100 Selected Course 100 11 ±180 degrees Basic 0.087890625 33.3-100

Configuration Data Type ILS Source Select Type None SDI Bits 9 & 10 00 = Not used 10 = ILS #1 01 = ILS #2 11 = MLS






A = J2-37 B = J2-36

Data Glideslope Localizer PFD Mode Select Word Selected Course

Label 174 173 163 100

Sig. Bits 12 12 Discrete 11

Range ±0.8 DDM ±0.4 DDM Type 4 ±180 degrees


Resolution 0.0001953125 0.00009765625 n/a 0.087890625

Rate (ms) 33.3-66.6 33.3-66.6 250 200

CHANNEL 429RX_3



A = J2-41 B = J2-40

Data Glideslope Localizer PFD Mode Select Word Selected Course

Label 174 173 163 100

Sig. Bits 12 12 Discrete 11

Range ±0.8 DDM ±0.4 DDM Type 4 ±180 degrees


Resolution 0.0001953125 0.00009765625 n/a 0.087890625

Rate (ms) 33.3-66.6 33.3-66.6 250 200

Configuration Data Type ILS Source Select Type PFD


CHANNEL 429RX_1



Data Label Sig. Bits Range Signal Type Resolution Rate (ms) A = J2-37 Glideslope 174 12 ±0.8 DDM Basic 0.0001953125 33.3-100 B = J2-36 Localizer 173 12 ±0.4 DDM Basic 0.00009765625 33.3-100 Selected Course 100 11 ±180 degrees Basic 0.087890625 33.3-100

CHANNEL 429RX_3



Data Label Sig. Bits Range Signal Type Resolution Rate (ms) A = J2-41 Glideslope 174 12 ±0.8 DDM Basic 0.0001953125 33.3-100 B = J2-40 Localizer 173 12 ±0.4 DDM Basic 0.00009765625 33.3-100 Selected Course 100 11 ±180 degrees Basic 0.087890625 33.3-100



CHANNEL 429RX_2



Data Label Sig. Bits Range Signal Type Resolution Rate (ms) A = J2-39 Glideslope 174 12 ±0.8 DDM Basic 0.0001953125 33.3-66.6 B = J2-38 Localizer 173 12 ±0.4 DDM Basic 0.00009765625 33.3-66.6

CHANNEL 429RX_5



Data Label Sig. Bits Range Signal Type Resolution Rate (ms) A = J2-21 Glideslope 174 12 ±0.8 DDM Basic 0.0001953125 33.3-66.6 B = J2-04 Localizer 173 12 ±0.4 DDM Basic 0.00009765625 33.3-66.6





CONNECT TO: IOC #1 (High Speed)


A = J2-37 B = J2-36


Label 174 173

Sig. Bits 12 12



Resolution 0.0001953125 0.00009765625

Rate (ms) 33.3-66.6 33.3-66.6

CHANNEL 429RX_3



A = J2-41 B = J2-40


Label 174 173

Sig. Bits 12 12



Resolution 0.0001953125 0.00009765625

Rate (ms) 33.3-66.6 33.3-66.6



CHANNEL 429RX_1



A = J2-37 B = J2-36

Data Glideslope Localizer PFD Mode Select Word

Label 174 173 163


Range ±0.8 DDM ±0.4 DDM Type 4


Resolution 0.0001953125 0.00009765625 n/a

Rate (ms) 33.3-66.6 33.3-66.6 250

CHANNEL 429RX_3



A = J2-41 B = J2-40

Data Glideslope Localizer PFD Mode Select Word

Label 174 173 163


Range ±0.8 DDM ±0.4 DDM Type 4


Resolution 0.0001953125 0.00009765625 n/a

Rate (ms) 33.3-66.6 33.3-66.6 250

Configuration Data Type ILS Source Select Type PFD

TABLE 5.3.9-255: NAVIGATION INPUTS SELECT 255 (PROLINE 4/21)

CHANNEL 429RX_1



A = J2-37 B = J2-36


Label 117 116

Sig. Bits 12 12



Resolution 0.0001953125 0.00009765625

Rate (ms) 33.3-66.6 33.3-66.6

CHANNEL 429RX_3



A = J2-41 B = J2-40


Label 117 116

Sig. Bits 12 12



Resolution 0.0001953125 0.00009765625

Rate (ms) 33.3-66.6 33.3-66.6





5.3.10 CATEGORY 10, ATTITUDE INPUT SELECT

The following table provides identification of the Roll Attitude Angle type. The entry in the Attitude Input Select corresponds to a table that provides detailed information on the configuration. For example, the details for Attitude Input Select #1 are found in 5.3.10-1.


Roll Attitude Pitch Attitude Roll Rate Source Pitch Rate Source Inertial Vertical Speed Inertial Altitude TABLE 5.3.10: ATTITUDE INPUT SELECT

ID Attitude Input

Select (Table 5.3.10-x)


0 0 Analog Roll (3-Wire Synchro) without validity (Note 4) -020

2 2 Analog Pitch and Roll (3-Wire Synchro) -020

4 4 Analog Roll (3-Wire Synchro) with validity (Note 4) -020

6 6 Digital Pitch, Roll, Pitch Rate, Roll Rate, and IVS (High Speed ARINC 429) (Note 2 and 3)

-020

7 7 Analog Pitch and Roll (3-Wire Synchro) with Gnd validity

-022

128 128 Digital Pitch, Roll, Pitch Rate, and Roll Rate (High Speed ARINC 429) (Note 2)

-020

253 253 Digital Pitch, Roll, Pitch Rate and Roll Rate, Vertical Speed and Altitude (ARINC 429 via dual IOC buses) (Note 1)

-020

254 254 Digital Pitch, Roll, Pitch Rate and Roll Rate (ARINC 429 via dual IOC buses) (Note 1)

-020

Note 1: ID 253 and 254 may only be used in conjunction with other IOC bus selections for categories 2,6,8,9,11, 12, 13 and 16 that use the same ARINC 429 receiver channels and bus speeds.

Note 2: Category 10 and Category 11 use the same ARINC 429 receiver if a digital source is selected. It is acceptable for digital sources to be used for both categories if desired, however it must be noted that both categories must use high speed ARINC 429 ID's or both categories must use low speed ARINC 429 ID's.

Note 3: This ID may only be used with a Category 2 Barometric Altitude Rate sources that are digital. Analog sources are not compatible with this ID because of the presence of IVS.

Note 4: Not compatible with ‘Dead Reckoning’. Dead Reckoning requires both Pitch and Roll signals.

TABLE 5.3.10-0: ATTITUDE INPUT SELECT TYPE 0


Roll Attitude (X) = J1-1 (Y) = J1-21 (Z) = J1-2

Format: 3 Wire Synchro Input Type: Basic Fault Designation: ROLL FAULT Validity: None Reference: None



TABLE 5.3.10-2: ATTITUDE INPUT SELECT TYPE 2 SIGNAL CONNECTION SUMMARY DATA


Format: 3 Wire Synchro with Validity Flag Input Type: Basic Fault Designation: ROLL FAULT Validity: Attitude Validity Discrete #1 Reference: None

Pitch Attitude (X) = J1-5 (Y) = J1-7 (Z) = J1-6

Format: 3 Wire Synchro with Validity Flag Input Type: Basic Fault Designation: PITCH FAULT Validity: Attitude Validity Discrete #1 Reference: None



Attitude Validity Discrete #1











CHANNEL 429RX_7

CONNECT TO: AHRS/IRS/INS/EGI Format: ARINC 429 (High Speed)

Fault Designation: AHRS BUS Bus Type: Basic

Data Roll Angle

Label 325

Sig. Bits 14

Range ±180 degrees

Signal Type Basic


Rate (ms) 10-20

A = J2-23 Pitch Angle 324 14 ±180 degrees Basic 0.010986328125 10-20 B = J2-6 Body Roll Rate 327 13 ±128 deg/sec Basic 0.01562500 10-20 Body Pitch Rate 326 13 ±128 deg/sec Basic 0.01562500 10-20 Inertial Vertical Speed 365 15 ±32,768 FPM Basic 1.0 20-40

Note: This ID may only be used with a Category 2 Barometric Altitude Rate sources that are digital. Analog sources are not compatible with this ID because of the presence of IVS.





Pitch Attitude (X) = J1-5 (Y) = J1-7 (Z) = J1-6

Format: 3 Wire Synchro with Validity Flag Input Type: Basic Fault Designation: PITCH FAULT Validity: Attitude Validity Discrete #1 Reference: None




J1-67 Input GND_DISC_14 GND = Valid <not>GND = Invalid



TABLE 5.3.10-128: ATTITUDE INPUT SELECT TYPE 128 CHANNEL 429RX_7

CONNECT TO: AHRS Format: ARINC 429 (High Speed)


A = J2-23 B = J2-6

Data Roll Angle Pitch Angle Body Roll Rate Body Pitch Rate

Label 325 324 327 326

Sig. Bits 14 14 13 13

Range ±180 degrees ±180 degrees ±128 deg/sec ±128 deg/sec


Resolution 0.010986328125 0.010986328125 0.01562500 0.01562500

Rate (ms) 10-20 10-20 10-20 10-20


CHANNEL 429RX_1



Data Roll Angle

Label 325

Sig. Bits 14

Range ±180 degrees

Signal Type Basic


Rate (ms) 10-20

A = J2-37 Pitch Angle 324 14 ±180 degrees Basic 0.010986328125 10-20 B = J2-36 Body Roll Rate 327 13 ±128 deg/sec Basic 0.01562500 10-20 Body Pitch Rate 326 13 ±128 deg/sec Basic 0.01562500 10-20 Inertial Vertical Speed 365 15 ±32,768 FPM Basic 1.0 20-40 Altitude 361 20 131,072 Ft Basic 0.125 20-40

CHANNEL 429RX_3



Data Roll Angle

Label 325

Sig. Bits 14

Range ±180 degrees

Signal Type Basic


Rate (ms) 10-20

A = J2-41 Pitch Angle 324 14 ±180 degrees Basic 0.010986328125 10-20 B = J2-40 Body Roll Rate 327 13 ±128 deg/sec Basic 0.01562500 10-20 Body Pitch Rate 326 13 ±128 deg/sec Basic 0.01562500 10-20 Inertial Vertical Speed 365 15 ±32,768 FPM Basic 1.0 20-40 Altitude 361 20 131,072 Ft Basic 0.125 20-40

Note: This ID may only be used with a Category 2 Barometric Altitude Rate sources that are digital. Analog sources are not compatible with this ID because of the presence of IVS. TABLE 5.3.10-254: ATTITUDE INPUT SELECT TYPE 254

CHANNEL 429RX_1



A = J2-37 B = J2-36


Label 325 324 327 326

Sig. Bits 14 14 13 13



Resolution 0.010986328125 0.010986328125 0.01562500 0.01562500

Rate (ms) 10-20 10-20 10-20 10-20

CHANNEL 429RX_3



A = J2-41 B = J2-40


Label 325 324 327 326

Sig. Bits 14 14 13 13



Resolution 0.010986328125 0.010986328125 0.01562500 0.01562500

Rate (ms) 10-20 10-20 10-20 10-20



5.3.11 CATEGORY 11, HEADING INPUT SELECT

The following table provides identification of the Heading type. The entry in the Heading Input Select corresponds to a table that provides detailed information on the configuration. For example, the details for Magnetic Heading Input Select #1 are found in 5.3.11-1.


Magnetic Heading True Heading TABLE 5.3.11: HEADING INPUT SELECT

ID Heading Input

Select (Table 5.3.11-x)


0 0 Analog Magnetic Heading (3-Wire Synchro with reference and validity discrete)

-020

2 2 High Speed ARINC 429 (Note 2) -020

3 3 High Speed ARINC 429 (Note 2) -020

254 254 Digital True Heading (High Speed) (ARINC 429 via dual IOC buses) (Note 1 and 2)

-020

255 255 Digital Magnetic Heading (High Speed) (ARINC 429 via dual IOC buses) (Note 1)

-020

Note 1: ID 254 and 255 may only be used in conjunction with other IOC bus selections for categories 2, 6, 8, 9, 10, 12, 13 and 16 that use the same ARINC 429 receiver channels and bus speeds.

Note 2: Category 10 and Category 11 use the same ARINC 429 receiver if a digital source is selected. It is acceptable for digital sources to be used for both categories if desired. However, note that both categories must use high speed ARINC 429 ID's or both categories must use low speed ARINC 429 ID's.

TABLE 5.3.11-0: HEADING INPUT SELECT 0


Magnetic Heading

(X) = J1-22 (Y) = J1-23 (Z) = J1-3 Reference (H) = J1-4 (C) = J1-24

Format: 5 Wire Synchro with Validity Flag Input Type: Basic Fault Designation: MAGNETIC HEADING FAULT Validity: Magnetic Heading Validity Discrete (+28V) Reference: Nominal 26 VAC



Magnetic Heading Validity Discrete



CHANNEL 429RX_7

CONNECT TO: AHRS Format: ARINC 429 (High Speed)


A = J2-23 B = J2-6

Data Magnetic Heading

Label 320

Sig. Bits 15

Range ±180 degrees

Signal Type Basic

Resolution 0.0054931640625

Rate (ms) 10-50



TABLE 5.3.11-3: HEADING INPUT SELECT 3 CHANNEL 429RX_7

CONNECT TO: AHRS/IRS/INS/EGI Format: ARINC 429 (High Speed)


A = J2-23 B = J2-6

Data Magnetic Heading True Heading

Label 320 314

Sig. Bits 15 15

Range ±180 degrees ±180 degrees


Resolution 0.0054931640625 0.0054931640625

Rate (ms) 10-50 25-50


CHANNEL 429RX_1



A = J2-37 B = J2-36

Data True Heading

Label 314

Sig. Bits 15

Range ±180 degrees

Signal Type Basic

Resolution 0.0054931640625

Rate (ms) 25-50

CHANNEL 429RX_3



A = J2-41 B = J2-40

Data True Heading

Label 314

Sig. Bits 15

Range ±180 degrees

Signal Type Basic

Resolution 0.0054931640625

Rate (ms) 25-50


CHANNEL 429RX_1



A = J2-37 B = J2-36


Label 320

Sig. Bits 15

Range ±180 degrees

Signal Type Basic

Resolution 0.0054931640625

Rate (ms) 25-50

CHANNEL 429RX_3



A = J2-41 B = J2-40


Label 320

Sig. Bits 15

Range ±180 degrees

Signal Type Basic

Resolution 0.0054931640625

Rate (ms) 25-50

5.3.12 CATEGORY 12, WINDSHEAR INPUT SELECT

The Windshear warning is not applicable to Helicopters.

The following table provides the definition of Windshear Input Select ID 0, which is used for helicopter installations.

TABLE 5.3.12: WINDSHEAR INPUT SELECT

ID Description Windshear INOP Disable Windshear Disable Effectivity

0 No Windshear TRUE TRUE -020



5.3.13 CATEGORY 13, INPUT / OUTPUT DISCRETE TYPE SELECT

The following table provides identification of the Input/Output Discrete Type. Each entry in the Input/Output Discrete Type column has a corresponding table that provides detailed information on the configuration. For example, the details for Input/Output Discrete Type #128 are found in Table 5.3.13-128.

TABLE 5.3.13: INPUT/OUTPUT DISCRETE TYPE SELECT

ID Input/Output Discrete Type

(Table 5.3.13-x)

Description Helicopter Input / Output discrete definitions Effectivity

128 128 (Lamp Format 1, TCAS Inhibit) -020

129 129 (Lamp Format 2, TCAS Inhibit) -020

130 130 (Lamp Format 2, Audio On) -024

131 131 S-92 (Lamp Format 2, TCAS Inhibit) (Note 1) -020

132 132 EH-101 (Lamp Format 2, TCAS Inhibit) (Note 1) -020

133 133 S-92 (Lamp Format 2, Audio On) (Note 1) -024

134 134 EH-101 (Lamp Format 2, Audio On) (Note 1) -024

135 135 S-762 (Lamp Format 2, Audio On, no Eng Out) -024

136 136 S-762 (Lamp Format 2, Audio On, Eng Out) -024

137 137 (Lamp Format 2, Audio On, Audio Priority) -026

138 138 (Lamp Format 2, Audio On, Audio Priority, Digital Discretes) -026

139 139 EH-101 (Lamp Format 2, Audio On, Audio Priority, Digital Discretes) (Note 1)

-026

Note 1: ID 131, 132, 133, 134, 138 and 139 may only be used in conjunction with other IOC bus

selections for categories 6, 8, 9, 10, 11, 12, 13 and 16 that use the same ARINC 429 receiver channels and bus speeds.

2 S-76 factory installations only.



TABLE 5.3.13-128: INPUT/OUTPUT DISCRETE TYPE 128

CONN PIN #

CHANNEL DESIGNATION REFERENCE

PIN

TYPE

PIN FUNCTION


J1-38 28V_DISC_02 Input +28V Glideslope Inhibit Discrete >+17V = Inhibit <+4.4V = Not Inhibit

J1-19 GND_DISC_02 Input GND Glideslope Inhibit Discrete Gnd = Inhibit <not> Gnd = Not Inhibit

J1-37 28V_DISC_03 Input +28V WOW Discrete >+17V = WOW <+4.4V = Not WOW

J1-18 GND_DISC_03 Input GND WOW Discrete Gnd = WOW <not> Gnd = Not WOW

J1-36 28V_DISC_04 Input +28V Audio Inhibit Discrete >+17V = Inhibit <+4.4V = Not Inhibit

J1-17 GND_DISC_04 Input Timed Audio Inhibit Discrete (Note 1, 3) Gnd = Audio Inhibit Toggle <not> Gnd = Normal

J1-35 28V_DISC_05 Input +28V Landing Gear Discrete >+17V = Gear Down <+4.4V = Gear Up

J1-16 GND_DISC_05 Input GND Landing Gear Discrete Gnd = Gear Down <not> Gnd = Gear Up

J1-15 GND_DISC_06 Input Glideslope Cancel Discrete (Note 1) Gnd = Cancel Toggle <not> Gnd = Normal

J1-14 GND_DISC_07 Input Low Altitude Mode Select (Tactical) (Note 1) Gnd = Low Altitude Mode Select<not> Gnd = Normal

J1-13 GND_DISC_08 Input Mode 6 Low Volume Discrete Gnd = Low Volume <not> Gnd = Normal

J1-12 GND_DISC_09 Input Terrain Awareness Inhibit Discrete (Note 2) Gnd = Inhibit <not> Gnd = Not Inhibit

J1-34 GND_DISC_10 Input Self-Test Discrete (Note 1) Gnd = Self-Test Toggle <not> Gnd = Normal

J1-72 MON_OUT_1 Output GPWS INOP Discrete

J1-55 MON_OUT_2 Output TAD INOP Discrete Terrain Not Available

J1-78 DISC_OUT_1 Output GPWS Warning Discrete Terrain Awareness Caution or Warning Obstacle Awareness Caution or Warning

Lamp Format= Type 1

J1-77 DISC_OUT_2 Output GPWS Alert Discrete (Glideslope Only) Lamp Format= Type 1

J1-76 DISC_OUT_3 Output Glideslope Cancel Discrete

J1-73 DISC_OUT_4 Output Low Altitude Mode Discrete (Tactical)

J1-69 DISC_OUT_5 Output TCAS Inhibit discrete

J1-54 DISC_OUT_6 Output Terrain Display Select #1 Discrete

J1-51 DISC_OUT_8 Output Terrain Awareness Caution or Warning Obstacle Awareness Caution or Warning

Gnd = Terrain Pop Up


J1-52 DISC_OUT_7 Output Timed Audio Inhibit Gnd = Audio Inhibit Note 1: Provided by Momentary cockpit switch (non-latching). Note 2: Provided by Alternate cockpit switch (Latching) with guard if inhibiting. Note 3: See section 3.3.18.2 for further selectable options and details.




CONN PIN #


PIN

TYPE

PIN FUNCTION







J1-17 GND_DISC_04 Input Timed Audio Inhibit Discrete (Note 1, 3, 4) Gnd = Audio Inhibit Toggle <not> Gnd = Normal



J1-15 GND_DISC_06 Input Glideslope Cancel Discrete (Note 1, 3) Gnd = Cancel Toggle <not> Gnd = Normal

J1-14 GND_DISC_07 Input Low Altitude Mode Select (Tactical) (Note 1, 3) Gnd = Low Altitude Mode Select<not> Gnd = Normal


J1-12 GND_DISC_09 Input Terrain Awareness Inhibit Discrete (Note 2, 3) Gnd = Inhibit <not> Gnd = Not Inhibit

J1-34 GND_DISC_10 Input Self-Test Discrete (Note 1, 3) Gnd = Self-Test Toggle <not> Gnd = Normal



J1-78 DISC_OUT_1 Output GPWS Warning Discrete Terrain Awareness Warning Obstacle Awareness Warning

Lamp Format= Type 2

J1-77 DISC_OUT_2 Output GPWS Alert Discrete Terrain Awareness Caution Obstacle Awareness Caution

Lamp Format= Type 2








J1-52 DISC_OUT_7 Output Timed Audio Inhibit Gnd = Audio Inhibit Note 1: Provided by Momentary cockpit switch (non-latching). Note 2: Provided by Alternate cockpit switch (Latching) with guard if inhibiting Note 3: Function is provided as an OR operation of the physical discrete (defined in this category) and the 429 Discrete Word bit if configured by

display type in Category 6. However, the installation should not use both sources at the same time. Note 4: See section 3.3.18.2 for further selectable options and details.




CONN PIN #


PIN

TYPE

PIN FUNCTION


















Lamp Format= Type 2


Lamp Format= Type 2



J1-69 DISC_OUT_5 Output Audio On discrete










CONN PIN #


PIN

TYPE

PIN FUNCTION














J1-67 GND_DISC_14 Input DCU Reversion discrete Gnd = Use DCU Bus 1 <not> Gnd = Use DCU Bus 2




Lamp Format= Type 2


Lamp Format= Type 2








J1-52 DISC_OUT_7 Output Timed Audio Inhibit Gnd = Audio Inhibit Note 1: Provided by Momentary cockpit switch (non-latching). Note 2: Provided by Alternate cockpit switch (Latching) with guard if inhibiting Note 3: Function is provided as an OR operation of the physical discrete (defined in this category) and the 429 Discrete Word bit, label 303 (MFD

Command word). However, the installation should not use both sources at the same time. Note 4: The Terrain Awareness Inhibit Discrete is provided in the MFD Command word. Note 5: See section 3.3.18.2 for further selectable options and details.

Input/Output Discrete Type 131 CONTINUED NEXT PAGE



CHANNEL 429RX_1

CONNECT TO: IOC #1 Bus Format: ARINC 429 (High Speed)


A = J2-37 B = J2-36

Data MFD Command Word (Format 1)

Label 303

Sig. Bits Discrete

Range N/A

Signal Type Basic

Resolution N/A

Rate (ms) 100

CHANNEL 429RX_3



A = J2-41 B = J2-40


Label 303

Sig. Bits Discrete

Range N/A

Signal Type Basic

Resolution N/A

Rate (ms) 100

CHANNEL 429RX_2

CONNECT TO: DCU #1 Bus Format: ARINC 429 (Low Speed)

Fault Designation: DCU BUS 1 Bus Type: Basic

A = J2-39 B = J2-38

Data Aural Warning Set Word Aural Warning Reset Word

Label 270 271


Range N/A N/A


Resolution N/A N/A

Rate (ms) 100 100

CHANNEL 429RX_5



A = J2-21 B = J2-04


Label 270 271


Range N/A N/A


Resolution N/A N/A

Rate (ms) 100 100

Label 303 MFD Command Word Bits 11 – 14 Self Test Command Codes

BITS Command 11 12 13 14 0 0 0 0 No Test Command 0 0 1 0 Short Level 1 Test Command 0 1 0 0 Long Level 1 Test Command 0 1 1 0 Level 2 Test Command 1 0 0 0 Level 3 Test Command 1 0 1 0 Level 4 Test Command 1 1 0 0 Level 5 Test Command 1 1 1 0 Level 6 Test Command 0 0 0 1 Self Test Cancel Command 0 0 1 1 Skip Command

Bits 15 – 29 (Format 1) BIT Command 15 Glideslope Cancel (momentary) 16 Timed Audio Inhibit (momentary) 17 Terrain Awareness & TCF Inhibit (momentary) 18 Low Altitude (momentary) 19 Weight On Wheels 20 Landing Gear Position (0 = Gear down) 21 Backcourse 22 ICS Audio On 23 EH-101 Master/Slave Control (not used by EGPWS)

24 - 29 Not Used

Bits 15 – 29 (Format 2) BIT Command 15 Glideslope Cancel (momentary) 16 Timed Audio Inhibit (momentary) 17 Terrain Awareness & TCF Inhibit (toggle) 18 Low Altitude (momentary) 19 Weight On Wheels 20 Landing Gear Position (0 = Gear down) 21 Backcourse 22 ICS Audio On 23 EH-101 Master/Slave Control (not used by EGPWS)

24 - 29 Not Used

Label 270 Aural Warning Set Word Bit Assignments Bits 9 – 10 Page selection

BIT PAGE 1 2 3 4 9 0 0 1 1 10 0 1 0 1



Label 270 Aural Warning Set Word Bit Assignments (continued) Page 1: Bits 11 – 29 Page 2: Bits 11 – 29

BIT Command BIT Command 11 Low Rotor Set 11 110 Ft. Set (not used by EGPWS) 12 Fire Engine 1 Set 12 120 Ft. Set (not used by EGPWS) 13 Fire Engine 2 Set 13 130 Ft. Set (not used by EGPWS) 14 Engine 1 Failure Set 14 140 Ft. Set (not used by EGPWS) 15 Engine 2 Failure Set 15 150 Ft. Set (not used by EGPWS) 16 Landing Gear Up Set (not used by EGPWS) 16 160 Ft. Set (not used by EGPWS) 17 Fire APU Set 17 Check Power Set 18 Airspeed Set 18 Smoke in Cabin Set 19 Smoke In Baggage Set 19 Spare 20 Minimums Set (not used by EGPWS) 20 Spare 21 Altitude Set (not used by EGPWS) 21 Spare 22 100 Ft. Set (not used by EGPWS) 22 Spare 23 Coupled Hover Altitude Set 23 Spare 24 Swash Plate Temperature Set 24 Spare 25 Level Off Set 25 Spare 26 Decouple Set 26 Spare 27 Hover Altitude Set 27 Spare 28 Gear Box Pressure Set 28 Spare 29 Aural Alert Invalid 29 Reserved

Label 270 Page 3 and 4 are undefined. Label 271 Aural Warning Set Word Bit Assignments Bits 9 – 10 Page selection

BIT PAGE 1 2 3 4 9 0 0 1 1 10 0 1 0 1

Page 1: Bits 11 – 29 Page 2: Bits 11 – 29 BIT Command BIT Command 11 Low Rotor Reset 11 110 Ft. Reset (not used by EGPWS) 12 Fire Engine 1 Reset 12 120 Ft. Reset (not used by EGPWS) 13 Fire Engine 2 Reset 13 130 Ft. Reset (not used by EGPWS) 14 Engine 1 Failure Reset 14 140 Ft. Reset (not used by EGPWS) 15 Engine 2 Failure Reset 15 150 Ft. Reset (not used by EGPWS) 16 Landing Gear Up Reset (not used by EGPWS) 16 160 Ft. Reset (not used by EGPWS) 17 Fire APU Reset 17 Check Power Reset 18 Airspeed Reset 18 Smoke in Cabin Reset 19 Smoke In Baggage Reset 19 Spare 20 Minimums Reset (not used by EGPWS) 20 Spare 21 Altitude Reset (not used by EGPWS) 21 Spare 22 100 Ft. Reset (not used by EGPWS) 22 Spare 23 Coupled Hover Altitude Reset 23 Spare 24 Swash Plate Temperature Reset 24 Spare 25 Level Off Reset 25 Spare 26 Decouple Reset 26 Spare 27 Hover Altitude Reset 27 Spare 28 Gear Box Pressure Reset 28 Spare 29 Reserved (IBIT Initiate) 29 Audio Hush

Label 271 Page 3 and 4 are undefined.




CONN PIN #

CHANNEL DESIGNATION REFERENCE PIN TYPE PIN FUNCTION Polarity/Configuration

















Lamp Format= Type 2


Lamp Format= Type 2








J1-52 DISC_OUT_7 Output Timed Audio Inhibit Gnd = Audio Inhibit

CHANNEL 429RX_2



A = J2-39 B = J2-38


Label 303

Sig. Bits Discrete

Range N/A

Signal Type Basic

Resolution N/A

Rate (ms) 100

CHANNEL 429RX_5



A = J2-21 B = J2-04


Label 303

Sig. Bits Discrete

Range N/A

Signal Type Basic

Resolution N/A

Rate (ms) 100

Note 1: Provided by Momentary cockpit switch (non-latching). Note 2: Provided by Alternate cockpit switch (Latching) with guard if inhibiting Note 3: Function is provided as an OR operation of the physical discrete (defined in this category) and the 429 Discrete Word bit, label 303 (MFD

Command word). However, the installation should not use both sources at the same time. Note 4: See Table 5.3.13-131for MFD Command Word definition. Note 5: See section 3.3.18.2 for further selectable options and details.




CONN PIN #














J1-67 GND_DISC_14 Input DCU Reversion discrete Gnd = Use DCU Bus 1 <not> Gnd = Use DCU Bus 2




Lamp Format= Type 2


Lamp Format= Type 2








J1-52 DISC_OUT_7 Output Timed Audio Inhibit Gnd = Audio Inhibit Note 1: Provided by Momentary cockpit switch (non-latching). Note 2: Provided by Alternate cockpit switch (Latching) with guard if inhibiting Note 3: Function is provided as an OR operation of the physical discrete (defined in this category) and the 429 Discrete Word bit, label 303 (MFD

Command word). However, the installation should not use both sources at the same time. Note 4: The Terrain Awareness Inhibit Discrete is provided in the MFD Command word. Note 5: See section 3.3.18.2 for further selectable options and details.




CHANNEL 429RX_1

CONNECT TO: IOC #1 Bus Format: ARINC429 (High Speed)


A = J2-37 B = J2-36


Label 303

Sig. Bits Discrete

Range N/A

Signal Type Basic

Resolution N/A

Rate (ms) 100

CHANNEL 429RX_3



A = J2-41 B = J2-40


Label 303

Sig. Bits Discrete

Range N/A

Signal Type Basic

Resolution N/A

Rate (ms) 100

CHANNEL 429RX_2



A = J2-39 B = J2-38


Label 270 271


Range N/A N/A


Resolution N/A N/A

Rate (ms) 100 100

CHANNEL 429RX_5

CONNECT TO: DCU #2 Bus Format: ARINC429 (Low Speed)


A = J2-21 B = J2-04


Label 270 271


Range N/A N/A


Resolution N/A N/A

Rate (ms) 100 100

Note 5: See Table 5.3.13-131for MFD Command Word, Aural Warning Set Word and Aural Warning Reset Word definition.




CONN PIN #


















Lamp Format= Type 2


Lamp Format= Type 2

J1-76 DISC_OUT_3 Output Glideslope Cancel Discrete J1-73 DISC_OUT_4 Output Low Altitude Mode Discrete (Tactical) J1-69 DISC_OUT_5 Output Audio On discrete J1-54 DISC_OUT_6 Output Terrain Display Select #1 Discrete



J1-49 DISC_OUT_9 Output Terrain Display Select #2 Discrete J1-52 DISC_OUT_7 Output Timed Audio Inhibit Gnd = Audio Inhibit

CHANNEL 429RX_2



A = J2-39 B = J2-38


Label 303

Sig. Bits Discrete

Range N/A

Signal Type Basic

Resolution N/A

Rate (ms) 100

CHANNEL 429RX_5



A = J2-21 B = J2-04


Label 303

Sig. Bits Discrete

Range N/A

Signal Type Basic

Resolution N/A

Rate (ms) 100

Note 1: Provided by Momentary cockpit switch (non-latching). Note 2: Provided by Alternate cockpit switch (Latching) with guard if inhibiting Note 3: Function is provided as an OR operation of the physical discrete (defined in this category) and the 429 Discrete Word bit, label 303 (MFD




TABLE 5.3.13-135: INPUT/OUTPUT DISCRETE TYPE 135 (S-76 FACTORY INSTALLATIONS ONLY)

CONN PIN #















J1-8 28V_DISC_09 Input +28V Low Rotor Discrete >+17V = Low Rotor <+4.4V = Normal

J1-48 28V_DISC_11 Input +28V Fire Engine #1 Discrete >+17V = Fire in Engine #1 <+4.4V = Normal


J2-31 GND_DISC_15 Input GND Decouple Discrete Gnd = Couple On <not> Gnd = Decoupled




Lamp Format= Type 2


Lamp Format= Type 2

J1-76 DISC_OUT_3 Output Glideslope Cancel Discrete J1-73 DISC_OUT_4 Output Low Altitude Mode Discrete (Tactical) J1-69 DISC_OUT_5 Output Audio On discrete J1-54 DISC_OUT_6 Output Terrain Display Select #1 Discrete



J1-49 DISC_OUT_9 Output Terrain Display Select #2 Discrete J1-52 DISC_OUT_7 Output Timed Audio Inhibit Gnd = Audio Inhibit

Note 1: Provided by Momentary cockpit switch (non-latching). Note 2: Provided by Alternate cockpit switch (Latching) with guard if inhibiting Note 3: Function is provided as an OR operation of the physical discrete (defined in this category) and the 429 Discrete Word bit if configured by




TABLE 5.3.13-136: INPUT/OUTPUT DISCRETE TYPE 136 (S-76 FACTORY INSTALLATIONS ONLY)

CONN PIN #















J1-8 28V_DISC_09 Input +28V Low Rotor Discrete >+17V = Low Rotor <+4.4V = Normal



J2-31 GND_DISC_15 Input GND Decouple Discrete Gnd = Couple On <not> Gnd = Decoupled




Lamp Format= Type 2


Lamp Format= Type 2













CHANNEL 429RX_8

CONNECT TO: ENG #1 Bus Format: ARINC 429 (Low Speed)

Fault Designation: ENGINE 1 BUS Bus Type: Basic

A = J2-24 B = J2-07

Data ECU Discrete Word

Label 353

Sig. Bits Discrete

Range N/A

Signal Type Basic

Resolution N/A

Rate (ms) 200

CHANNEL 429RX_5

CONNECT TO: ENG #2 Bus Format: ARINC 429 (Low Speed)


A = J2-21 B = J2-04

Data ECU Discrete Word

Label 353

Sig. Bits Discrete

Range N/A

Signal Type Basic

Resolution N/A

Rate (ms) 200

Label 353 ECU Discrete Word Bit 26 Assignment BIT 26 Definition

1 Engine Failure True 0 Engine Failure False




CONN PIN #


PIN

TYPE

PIN FUNCTION












J1-13 GND_DISC_08 Input Minimums/Check Height Silence Discrete (Note 1) Gnd = Low Volume <not> Gnd = Normal



J2-31 GND_DISC_15 Input ICS Audio On Discrete (Note 3) Gnd = Couple On <not> Gnd = Decoupled




Lamp Format= Type 2


Lamp Format= Type 2













CONN PIN #


PIN

TYPE

PIN FUNCTION











J1-14 GND_DISC_07 Input Low Altitude Mode Select (Tactical) (Note 1) Gnd = Low Altitude Mode Select<not> Gnd = Normal








Lamp Format= Type 2


Lamp Format= Type 2









Note 1: Provided by Momentary cockpit switch (non-latching) Note 2: Provided by Alternate cockpit switch (Latching) with guard if inhibiting Note 3: Function is provided as an OR operation of the physical discrete (defined in this category) and the 429 Discrete Word bit, label 303 (MFD





CHANNEL 429RX_1



A = J2-37 B = J2-36


Label 303

Sig. Bits Discrete

Range N/A

Signal Type Basic

Resolution N/A

Rate (ms) 100

CHANNEL 429RX_3



A = J2-41 B = J2-40


Label 303

Sig. Bits Discrete

Range N/A

Signal Type Basic

Resolution N/A

Rate (ms) 100




CONN PIN #


PIN

TYPE

PIN FUNCTION



















Lamp Format= Type 2


Lamp Format= Type 2









Note 1: Provided by Momentary cockpit switch (non-latching) Note 2: Provided by Alternate cockpit switch (Latching) with guard if inhibiting Note 3: Function is provided as an OR operation of the physical discrete (defined in this category) and the 429 Discrete Word bit, label 303 (MFD





CHANNEL 429RX_2



A = J2-39 B = J2-38


Label 303

Sig. Bits Discrete

Range N/A

Signal Type Basic

Resolution N/A

Rate (ms) 100

CHANNEL 429RX_5



A = J2-21 B = J2-04


Label 303

Sig. Bits Discrete

Range N/A

Signal Type Basic

Resolution N/A

Rate (ms) 100

5.3.14 CATEGORY 14, AUDIO OUTPUT LEVEL

The following table provides identification of the Audio Output Level Select. Each entry in the ID column corresponds to a particular nominal alert output level selection (Max, -6 dB, -12 dB, -18dB and –24dB). The nominal output is 4 W(rms) for the 8-ohm output and 100 mW(rms) for the 600-ohm output. The Audio Output Level can be additionally reduced by 6dB with the Mode 6 Low Volume discrete (see Category 13). The output power level will be the nominal maximum output (4W or 100mW) reduced by the volume selection from Table 5.3.14 and the Mode 6 Low Volume discrete.

TABLE 5.3.14: AUDIO OUTPUT LEVEL

ID Volume Select Effectivity

0 Nominal -020

1 -6 dB -020

2 -12 dB -020

3 -18 dB -020

4 -24 dB -020



5.3.15 CATEGORY 15, AUTOROTATION THRESHOLD

The following table provides identification of the Autorotation Threshold. Each entry in the ID column corresponds to an engine torque threshold for autorotation. Each helicopter type has a unique engine torque percentage during autorotation based on the aerodynamic qualities of the aircraft. This value is not typically published or well known, thus it has been included as a configuration item in Table 10.3.15. Since a typical Autorotation Threshold value is between 5% and 10%, the values have been chosen from 0% to 30% in increments of 0.5%.

TABLE 5.3.15: AUTOROTATION THRESHOLD

ID Autorotation

Threshold

% of Torque

Effectivity

0 N/A -020

1 0.5 % -020

2 1.0 % -020

3 1.5 % -020

4 2.0 % -020

5 2.5 % -020

6 3.0 % -020

7 3.5 % -020

8 4.0 % -020

9 4.5 % -020

10 5.0 % -020

11 5.5 % -020

12 6.0 % -020

13 6.5 % -020

14 7.0 % -020

15 7.5 % -020

16 8.0 % -020

17 8.5 % -020

18 9.0 % -020

19 9.5 % -020

20 10.0 % -020

21 10.5 % -020

22 11.0 % -020

23 11.5 % -020

24 12.0 % -020

25 12.5 % -020

26 13.0 % -020

27 13.5 % -020

28 14.0 % -020

29 14.5 % -020

30 15.0 % -020

31 15.5 % -020



ID Autorotation

Threshold

% of Torque

Effectivity

32 16.0 % -020

33 16.5 % -020

34 17.0 % -020

35 17.5 % -020

36 18.0 % -020

37 18.5 % -020

38 19.0 % -020

39 19.5 % -020

40 20.0 % -020

41 20.5 % -020

42 21.0 % -020

43 21.5 % -020

44 22.0 % -020

45 22.5 % -020

46 23.0 % -020

47 23.5 % -020

48 24.0 % -020

49 24.5 % -020

50 25.0 % -020

51 25.5 % -020

52 26.0 % -020

53 26.5 % -020

54 27.0 % -020

55 27.5 % -020

56 28.0 % -020

57 28.5 % -020

58 29.0 % -020

59 29.5 % -020

60 30.0 % -020



5.3.16 CATEGORY 16, TORQUE INPUT SELECT

The following table provides identification of Torque source type. Each entry in the ID column corresponds to an engine torque input configuration. The entry in the Torque Type corresponds to a table that provides detailed information on the configuration. For example, the details for Torque Type 2 are found in Table 5.3.16-2.

In cases where the signals are on an ARINC 429 bus with other signals, you may: In other categories select the same Fault Designation name and Channel connection as this category. In this

case a single physical bus with a single connection satisfies more than one category, or; In other categories select a different bus Fault Designation name and Channel connection and wire the

connections to the same source (if loading permits). Note: In this case a single bus failure will result in multiple bus names being faulted in the EGPWS self-test. In this case a single physical bus with multiple connections satisfies more than one category.

For single engine helicopter applications, the Torque Input needs to be treated as if there were two engines via aircraft wiring. Wire the single engine data into both HTAWS Torque Input(s), paralleling #1 and #2. TABLE 5.3.16 TORQUE TYPE SELECT

Torque Input Type


ID (Table

5.3.16-xx)

0 0 No Torque Input, Used Fixed 20% Torque -020

1 1 Digital, ARINC 429 S-76B/C+ -020

2 2 Analog, DC 0.032 VDC/% (Note 1) S-76C/A++ -020

3 3 Analog, DC 0.0278 VDC/% (Note 1) S-76A/A+ -020

4 4 Synchro Bell 212/412 -020

5 5 Digital, ARINC 429 BNR EC 155B AS 365N3 ARRIEL 2C engine

-020

6 6 Digital, RS-422 9600 baud (Note 5) MD900 PW206A engine

-021

7 7 Analog, DC 0.0429 VDC/% AS 322 -020

8 8 Analog, DC 0.015 + 0.0079836 VDC/% AS 365N1/N2 -020

9 9 Digital, ARINC 429 BCD AS 365N3 -020

10 10 Digital, ARINC 429 BNR Bell 427, 430 -020

11 11 Analog, DC 0.0219 VDC/% (Note 1) Bell 407 -020

12 12 Analog, DC 0.044 VDC/% Bell 212, 412 -020

13 Spare

14 14 Analog, DC 0.01025 + 0.004275 VDC/% AS 350 -020

15 15 Analog, DC 0.05 VDC/% HH-65 -020

16 16 Analog, DC 0.04 VDC/% -020



Torque Input Type


ID (Table

5.3.16-xx)

17 17 Digital, ARINC 429 (DC to 429 Torque Converter) -020

18 18 Digital, ARINC 429 (Note 2) S-92, AS-355 -020

19 19 Digital, ARINC 429 (Note 2) EH-101 -020

20 20 Digital, RS-422 9600 baud (Note 5) MD902 PW206E engine

-021

21 21 Digital, RS-422 9600 baud (Note 5) EC 135P1 PW206B V27

-021

22 22 Digital, RS-422 9600 baud (Note 5) EC 135P1 PW206B V28

-021

23 23 Analog, DC 0.0355 VDC/% H-60 Blackhawk -022

24 24 Digital, RS-422 9600 baud, Maintenance Port (8000 Hex Sync) (Note 4) (Note 5)

-021

25 25 Digital, RS-422 9600 baud, Maintenance Port (8FFF Hex Sync) (Note 5)

-021

26 26 Digital, RS-422 9600 baud (Note 5) A-109E PW206C V27

-021

27 27 Digital, RS-422 9600 baud (Note 5) A-109E PW206C V28

-021

28 28 Digital, RS-422 9600 baud, Maintenance Port (8000 Hex Sync) (Note 4) (Note 5)

-021

29 29 Digital, RS-422 9600 baud, Maintenance Port (8FFF Hex Sync) (Note 5)

-021

30 30 Digital, ARINC 429 Twin Engine Eurocopter EC 225/725, EC 135, EC 145, EC 155/A

-026

31 31 Analog, DC 0.1 VDC/% EC-145 -024

32 32 Digital, ARINC 429 Single Engine Eurocopter EC 120, EC 130, AS350B2 and B4

-026

33 33 Digital, ARINC 429 AS-355 -026

Note 1: This input requires that the raw signal is externally amplified by 30.23. No known amplifier currently exists; use ID 17 or ID 0 until a supplier is identified.

Note 2: ID 18 and 19 may only be used in conjunction with other IOC bus selections for categories 6, 8, 9, 10, 11, 12, 13 and 16 that use the same ARINC 429 receiver channels and bus speeds.

Note 3: The aircraft torque system is not compatible with the MK XXII DC Torque inputs. Use ID 0 for No Torque interface.

Note 4: ID 24 and 28 are not recommended for use as there is a risk that sync word definition (8000 Hex) may exist in data stream thus allowing the possibility of erroneous sync.

Note 5: ID 6, 20 - 22 and 24 - 29 are only compatible with Category 6, Terrain Display Select Type ID 242 that use RX429-8 for range control. This torque type inputs RS-422 torque data on RX429/422-1.



TABLE 5.3.16-0 TORQUE DATA SELECT 0 (GENERIC FIXED TORQUE 20%) SIGNAL CONNECTION SUMMARY DATAEngine Torque #1 No Connection Engine Torque #2 No Connection

TABLE 5.3.16-1 TORQUE DATA SELECT 1 (S-76B/C+) NOTE 1 CHANNEL RX429-8

CONNECT TO: Eng #1 Format: ARINC 429 (low speed)


A = J2-24 B = J2-07

Data Torque (Note 2)

Label 243

Sig. Bits 15

Range 799%

Signal Type Basic

Resolution 0.1

Rate (ms) 200

CHANNEL RX429-5



A = J2-21 B = J2-04


Label 243

Sig. Bits 15

Range 799%

Signal Type Basic

Resolution 0.1

Rate (ms) 200

Note 1: Digital Radar Altitude (type 2) cannot be used with this configuration both use ARINC 429 channel 5. Note 2: Label 243:

BITS Definition (BCD) 15 - 18 Tenths of Percent 19 - 22 Units of Percent 23 - 26 Tens of Percent 27 - 29 Hundreds of Percent

TABLE 5.3.16-2 TORQUE DATA SELECT 2 (S-76C/A++)


Engine Torque #1 (+) = J1-26 (–) = J1-27

Format: DC Input Type: Basic Fault Designation: ENGINE TORQUE 1

Engine Torque #2 (+) = J1-66 (–) = J1-47


Scale: Torque (%) = 31.23675%/VDC * Volts Signal Open Wire Threshold = -50% Signal reasonable Range = 0 to 120% TABLE 5.3.16-3 TORQUE DATA SELECT 3 (S-76A/A+)


Engine Torque #1 (+) = J1-26 (–) = J1-27


Engine Torque #2 (+) = J1-66 (–) = J1-47


Scale: Torque (%) = 35.91717929%/VDC * Volts Signal Open Wire Threshold = -50% Signal reasonable Range = 0 to 120% TABLE 5.3.16-4 TORQUE DATA SELECT 4 (BELL 212/412)


Engine Torque #1 (X) = J2-1 (Y) = J2-2 (Z) = J2-18

Format: 5 Wire Synchro Input Type: Basic Fault Designation: ENGINE TORQUE 1

Engine Torque #2 (X) = J2-19 (Y) = J2-20 (Z) = J2-3

Format: 5 Wire Synchro Input Type: Basic Fault Designation: ENGINE TORQUE 2

Synchro Reference (H) = J2-34 (C) = J2-35

Scale: >350° to <20° = 0% Torque ≥20° to 195° = 0.54285714 * Synchro Angle – 10.85 % Torque >195° to 350° = 95% Torque



TABLE 5.3.16-5 TORQUE DATA SELECT 5 (EC-155B AND AS-365N3) NOTE 1

Twin TURBOMECA Arriel 2C turbine engine CHANNEL RX429-8

CONNECT TO: Eng #1 Format: ARINC 429 (high speed)


A = J2-24 B = J2-07

Data Torque

Label 053

Sig. Bits 15

Range 0 to 180%

Signal Type Basic

Resolution 0. 0078125%

Rate (ms) 20

CHANNEL RX429-5



A = J2-21 B = J2-04

Data Torque

Label 053

Sig. Bits 15

Range 0 to 180%

Signal Type Basic

Resolution 0. 0078125%

Rate (ms) 20

Note 1: Digital Radar Altitude (type 2) cannot be used with this configuration both use ARINC 429 channel 5. Note 2: The actual number of significant bits is 16 but 15 bits will support the data range with MSB being bit 29. This is adjusted to make the

input processing work with the actual MSB.

TABLE 5.3.16-6 TORQUE DATA SELECT 6 (MD900) (PW206A ENGINE) NOTE 2 CHANNEL 429_422RX-1

CONNECT TO: Eng #1 Format: RS-422 (9600 baud)


A = J2-36 B = J2-37

Data Torque Torque Valid

Word 5 13

Sig. Bits 15 16

Range 256% N/A


Resolution 0.0078125 N/A

Rate (ms) 83 83

CHANNEL RX422-2



A = J2-10 B = J2-11


Word 5 13

Sig. Bits 15 16

Range 256% N/A



Rate (ms) 83 83

Note 1: Sync Word is 8000 (hex), Data Length is 000F (hex), Format 1. Note 2: This torque type is only compatible with Category 6, Terrain Display Select Types (KCPB) ID 230 & 242 that use RX429-8 for range

control. This torque type inputs RS-422 torque data on RX429/422-1.

TABLE 5.3.16-7 TORQUE DATA SELECT 7 (SUPER PUMA) SIGNAL CONNECTION SUMMARY DATA

Engine Torque #1 (+) = J1-26 (–) = J1-27


Engine Torque #2 (+) = J1-66 (–) = J1-47


Scale: Torque (%) = 23.31%/VDC * Volts Signal Open Wire Threshold = -50% Signal reasonable Range = -20% to 140% TABLE 5.3.16-8 TORQUE DATA SELECT 8 (AS365 DAUPHIN N1, N2) Twin TURBOMECA Arriel 1C2 turbine engines SIGNAL CONNECTION SUMMARY DATA

Engine Torque #1 (+) = J1-26 (–) = J1-27

Format: DC Input Type: Basic Fault Designation: ENGINE TORQUE 1 Validity: none

Engine Torque #2 (+) = J1-66 (–) = J1-47


Scale: Torque (%) = -1.879 + 125.256%/VDC * Volts Signal Open Wire Threshold = -50% Signal reasonable Range = -20% to 140%



TABLE 5.3.16-9 TORQUE DATA SELECT 9 (AS365 DAUPHIN N3) NOTE 1

Twin TURBOMECA Arriel 2C turbine engines CHANNEL RX429-8



A = J2-24 B = J2-07


Label 211

Sig. Bits 15

Range 799%

Signal Type Basic

Resolution 0.1

Rate (ms) 100

CHANNEL RX429-5



A = J2-21 B = J2-04


Label 211

Sig. Bits 15

Range 799%

Signal Type Basic

Resolution 0.1

Rate (ms) 100

Note 1: Digital Radar Altitude (type 2) cannot be used with this configuration. Note 2: Label 211:

BITS Definition (BCD) 15 - 18 Tenths of Percent 19 - 22 Units of Percent 23 - 26 Tens of Percent 27 - 29 Hundreds of Percent

TABLE 5.3.16-10 TORQUE DATA SELECT 10 (BELL 430 & 427) NOTE 1 CHANNEL RX429-8



A = J2-24 B = J2-07

Data Torque

Label 050

Sig. Bits 15

Range 0 to +126

Signal Type Basic

Resolution 0.1

Rate (ms) 100

CHANNEL RX429-5



A = J2-21 B = J2-04

Data Torque

Label 050

Sig. Bits 15

Range 0 to +126

Signal Type Basic

Resolution 0.1

Rate (ms) 100

Note 1: Digital Radar Altitude (type 2) cannot be used with this configuration. Label 050, Data bits 14 – 28 are 2’s Complement Binary.

TABLE 5.3.16-11 TORQUE DATA SELECT 11 (BELL 407) SIGNAL CONNECTION SUMMARY DATA

Engine Torque #1 (+) = J1-26 (–) = J1-27


Engine Torque #2 (+) = J1-66 (–) = J1-47


Scale: Torque (%) = + 45.6204%/VDC * Volts Signal Open Wire Threshold = -50% Signal reasonable Range = -20% to 140% TABLE 5.3.16-12 TORQUE DATA SELECT 12 (BELL 212/412) SIGNAL CONNECTION SUMMARY DATA

Engine Torque #1 (+) = J1-26 (–) = J1-27


Engine Torque #2 (+) = J1-66 (–) = J1-47


Scale: Torque (%) = + 22.70663%/VDC * Volts Signal Open Wire Threshold = -50% Signal reasonable Range = -20% to 140%



TABLE 5.3.16-14 TORQUE DATA SELECT 14 (AS-350D ASTAR) Single TURBOMECA Arriel 1D1 or 2B turbine engine


Engine Torque #1 (+) = J1-26 (–) = J1-27


Engine Torque #2 (+) = J1-66 (v) = J1-47


Note : Aircraft is single engine, connect torque signal to both EM22 inputs. Scale: Torque (%) = - 2.397 + 233.918%/VDC * Volts Signal Open Wire Threshold = -50% Signal reasonable Range = -20% to 140%

TABLE 5.3.16-15 TORQUE DATA SELECT 15 (COAST GUARD HH-65) SIGNAL CONNECTION SUMMARY DATA

Engine Torque #1 (+) = J1-26 (–) = J1-27


Engine Torque #2 (+) = J1-66 (–) = J1-47


Scale: Torque (%) = + 20.0%/VDC * Volts Signal Open Wire Threshold = -50% Signal reasonable Range = -20% to 140% TABLE 5.3.16-16 TORQUE DATA SELECT 16 (COMMON DC TORQUE) SIGNAL CONNECTION SUMMARY DATA

Engine Torque #1 (+) = J1-26 (–) = J1-27


Engine Torque #2 (+) = J1-66 (–) = J1-47


Scale: Torque (%) = + 25.0%/VDC * Volts Signal Open Wire Threshold = -50% Signal reasonable Range = -20% to 140% TABLE 5.3.16-17 TORQUE DATA SELECT 17 (GENERIC DC TO ARINC 429 TORQUE CONVERTER) CHANNEL RX429-8



A = J2-24 B = J2-07

Data Torque 1 Torque 2

Label 053 054

Sig. Bits 15 15

Range 0 to 180% 0 to 180%


Resolution 0. 0078125 0. 0078125

Rate (ms) 50 50

Note 1: The actual number of significant bits is 16 but 15 bits will support the data range. This is adjusted to make the input processing work with the actual MSB = to bit 29.

Label 053 and 054, Data bits 14 – 28 are 2’s Complement Binary.

TABLE 5.3.16-18 TORQUE DATA SELECT 1 (S-92) CHANNEL RX429-1

CONNECT TO: IOC #1 Format: ARINC 429 (high speed)


A = J2-37 B = J2-36

Data Torque

Label 336

Sig. Bits 12

Range 256%

Signal Type Basic

Resolution 0.0625

Rate (ms) 16.7

CHANNEL RX429-3



A = J2-41 B = J2-40

Data Torque

Label 336

Sig. Bits 12

Range 256%

Signal Type Basic

Resolution 0.0625

Rate (ms) 16.7

Label 336, Data bits 17 – 28 are 2’s Complement Binary. (Continued)



BITS Definition (SDI) 10 9 0 0 Invalid SDI 0 1 Engine #1 1 0 Engine #2 1 1 Invalid SDI

TABLE 5.3.16-19 TORQUE DATA SELECT 1 (EH-101) NOTE 1 CHANNEL RX429-2



A = J2-39 B = J2-38

Data Torque

Label 340

Sig. Bits 14

Range 256%

Signal Type Basic

Resolution 0.015625%

Rate (ms) 80

CHANNEL RX429-5



A = J2-21 B = J2-04

Data Torque

Label 340

Sig. Bits 14

Range 256%

Signal Type Basic

Resolution 0.015625%

Rate (ms) 80

Note 1: Digital Radar Altitude (type 2) cannot be used with this configuration. Label 340, Data bits 15 – 28 are 2’s Complement Binary.

BITS Definition (SDI) 10 9 0 0 Invalid SDI 0 1 Engine #1 1 0 Engine #2 1 1 Engine #3

TABLE 5.3.16-20 TORQUE DATA SELECT 20 (MD902) (PW206E ENGINE) NOTE 2 CHANNEL 429_422RX-1

CONNECT TO: Eng #1 Format: RS-422 – 9600 baud


A = J2-36 B = J2-37


Word 5 13

Sig. Bits 15 16

Range 256% N/A



Rate (ms) 83 83

CHANNEL RX422-2



A = J2-10 B = J2-11


Word 5 13

Sig. Bits 15 16

Range 256% N/A



Rate (ms) 83 83

Note 1: Sync Word is 8000 (hex), Data Length is 0013 (hex), Format 1. Note 2: This torque type is only compatible with Category 6, Terrain Display Select Type ID 242 that use RX429-8 for

range control. This torque type inputs RS-422 torque data on RX429/422-1.

TABLE 5.3.16-21 TORQUE DATA SELECT 21 (EC-135 P1) (PW206B ENGINE SW VERSION 27) NOTE 2 CHANNEL 429_422RX-1



A = J2-36 B = J2-37


Word 5 13

Sig. Bits 15 16

Range 256% N/A



Rate (ms) 83 83

CHANNEL RX422-2



= J2-10 B = J2-11


Word 5 13

Sig. Bits 15 16

Range 256% N/A



Rate (ms) 83 83

Note 1: Sync Word is 8000 (hex), Data Length is 0015 (hex), Format 1. Note 2: This torque type is only compatible with Category 6, Terrain Display Select Type ID 242 that use RX429-8 for

range control. This torque type inputs RS-422 torque data on RX429/422-1.



TABLE 5.3.16-22 TORQUE DATA SELECT 22 (EC-135 P1) (PW206B ENGINE SW VERSION 28) NOTE 2 CHANNEL 429_422RX-1



A = J2-36 B = J2-37


Word 5 13

Sig. Bits 15 16

Range 256% N/A



Rate (ms) 83 83

CHANNEL RX422-2



A = J2-10 B = J2-11


Word 5 13

Sig. Bits 15 16

Range 256% N/A



Rate (ms) 83 83

Note 1: Sync Word is 8FFF (hex), Data Length is 0019 (hex), Format 1. Note 2: This torque type is only compatible with Category 6, Terrain Display Select Type ID 242 that use RX429-8 for range


TABLE 5.3.16-23 TORQUE DATA SELECT 23 (H-60 BLACKHAWK) SIGNAL CONNECTION SUMMARY DATA

Engine Torque #1 (+) = J1-26 (–) = J1-27


Engine Torque #2 (+) = J1-66 (–) = J1-47


Scale: Torque (%) = + 28.13731%/VDC * Volts Signal Open Wire Threshold = -50% Signal reasonable Range = -20% to 140% TABLE 5.3.16-24 TORQUE DATA SELECT 24 (PW 206A/B/E MAINTENANCE PORT) (8000H SYNC) NOTE 2 CHANNEL 429_422RX-1



A = J2-36 B = J2-37


Word 7 11

Sig. Bits 15 16

Range 256% N/A



Rate (ms) 83 83

CHANNEL RX422-2



A = J2-10 B = J2-11


Word 7 11

Sig. Bits 15 16

Range 256% N/A



Rate (ms) 83 83

Note 1: Sync Word is 8000 (hex), Data Length is 0018 (hex) Format 2. Note 2: This torque type is only compatible with Category 6, Terrain Display Select Type ID 242 that use RX429-8 for range

control. This torque type inputs RS-422 torque data on RX429/422-1. TABLE 5.3.16-25 TORQUE DATA SELECT 25 (PW206A/B/E MAINTENANCE PORT) (8FFFH SYNC) NOTE 2 CHANNEL 429_422RX-1



A = J2-36 B = J2-37


Word 7 11

Sig. Bits 15 16

Range 256% N/A



Rate (ms) 83 83

CHANNEL RX422-2



A = J2-10 B = J2-11


Word 7 11

Sig. Bits 15 16

Range 256% N/A



Rate (ms) 83 83

Note 1: Sync Word is 8FFF (hex), Data Length is 0018 (hex) Format 2. Note 2: This torque type is only compatible with Category 6, Terrain Display Select Type ID 242 that use RX429-8 for range




TABLE 5.3.16-26 TORQUE DATA SELECT 26 (A109E) (PW206C ENGINE SW VERSION 27) NOTE 2 CHANNEL 429_422RX-1



A = J2-36 B = J2-37


Word 5 13

Sig. Bits 15 16

Range 256% N/A



Rate (ms) 83 83

CHANNEL RX422-2



A = J2-10 B = J2-11


Word 5 13

Sig. Bits 15 16

Range 256% N/A



Rate (ms) 83 83

Note 1: Sync Word is 8000 (hex), Data Length is 0015 (hex), Format 1. Note 2: This torque type is only compatible with Category 6, Terrain Display Select Type ID 242 that use RX429-8 for range

control. This torque type inputs RS-422 torque data on RX429/422-1. TABLE 5.3.16-27 TORQUE DATA SELECT 27 (A109E) (PW206C ENGINE SW VERSION 28) NOTE 2 CHANNEL 429_422RX-1



A = J2-36 B = J2-37


Word 5 13

Sig. Bits 15 16

Range 256% N/A



Rate (ms) 83 83

CHANNEL RX422-2



A = J2-10 B = J2-11


Word 5 13

Sig. Bits 15 16

Range 256% N/A



Rate (ms) 83 83

Note 1: Sync Word is 8FFF (hex), Data Length is 0019 (hex), Format 1. Note 2: This torque type is only compatible with Category 6, Terrain Display Select Type ID 242 that use RX429-8 for range


TABLE 5.3.16-28 TORQUE DATA SELECT 28 (PW 206C MAINTENANCE PORT) (8000H SYNC) NOTE 2 CHANNEL 429_422RX-1



A = J2-36 B = J2-37


Word 7 11

Sig. Bits 15 16

Range 256% N/A



Rate (ms) 83 83

CHANNEL RX422-2



A = J2-10 B = J2-11


Word 7 11

Sig. Bits 15 16

Range 256% N/A



Rate (ms) 83 83

Note 1: Sync Word is 8000 (hex), Data Length is 0018 (hex) Format 2. Note 2: This torque type is only compatible with Category 6, Terrain Display Select Type ID 242 that use RX429-8 for range


TABLE 5.3.16-29 TORQUE DATA SELECT 29 (PW206C MAINTENANCE PORT) (8FFFH SYNC) NOTE 2 CHANNEL 429_422RX-1



A = J2-36 B = J2-37


Word 7 11

Sig. Bits 15 16

Range 256% N/A



Rate (ms) 83 83

CHANNEL RX422-2



A = J2-10 B = J2-11


Word 7 11

Sig. Bits 15 16

Range 256% N/A



Rate (ms) 83 83

Note 1: Sync Word is 8FFF (hex), Data Length is 0018 (hex) Format 2. Note 2: This torque type is only compatible with Category 6, Terrain Display Select Type ID 242 that use RX429-8 for range




TABLE 5.3.16-30 TORQUE DATA SELECT 30 (TWIN ENGINE EUROCOPTER) CHANNEL RX429-8



A = J2-24 B = J2-07

Data Torque

Label 336

Sig. Bits 12

Range 256%

Signal Type Basic

Resolution 0.0625

Rate (ms) 100

Label 336, Data bits 17 – 28 are 2’s Complement Binary. BITS Definition (SDI)

10 9 0 0 Engine #1 0 1 Engine #2 1 0 Total Torque (not used by EGPWS) 1 1 Invalid SDI

TABLE 5.3.16-31 TORQUE DATA SELECT 31 (EC-145) SIGNAL CONNECTION SUMMARY DATA

Engine Torque #1 (+) = J1-26 (–) = J1-27


Engine Torque #2 (+) = J1-66 (–) = J1-47


Scale: Torque (%) = + 10.0%/VDC * Volts Signal Open Wire Threshold = -50% Signal reasonable Range = -20% to 140% TABLE 5.3.16-32 TORQUE DATA SELECT 32 (SINGLE ENGINE EUROCOPTER) CHANNEL RX429-8



A = J2-24 B = J2-07

Data Torque

Label 336

Sig. Bits 12

Range 256%

Signal Type Basic

Resolution 0.0625

Rate (ms) 100


10 9 0 0 Engine #1 only 0 1 Invalid SDI 1 0 Invalid SDI 1 1 Invalid SDI

TABLE 5.3.16-33 TORQUE DATA SELECT 33 (AS-355) CHANNEL RX429-8



A = J2-24 B = J2-07

Data Torque

Label 336

Sig. Bits 12

Range 256%

Signal Type Basic

Resolution 0.0625

Rate (ms) 100


10 9 0 0 Invalid SDI 0 1 Engine #1 1 0 Engine #2 1 1 Invalid SDI




The following table provides identification of the Options 2 Select. Each entry in the ID column corresponds to a particular combination of Auto-rotation callouts, Normal Helicopter TA&D Display Pop Up Range Selection and Low Altitude Helicopter TA&D Display Pop Up Range Selection. Refer to Section 6.5 for configuration messages that will be present for each option selected.

This category selects the Auto-rotation callouts via one of the following options:

Auto-rotation Callout Option Select 0: No Auto-rotation callouts selected (the callout menu selected via Category 4 will remain active in auto-rotation).

Auto-rotation Callout Option Select 1: Selects “200” and “100” for Auto-rotation. Auto-rotation Callout Option Select 2: Selects “200”, “100”, “80”, “60”, “40”, “20” and “10” for Auto-rotation.

If the display type selected via Category 6 supports Auto Pop-Up and Auto-Ranging then the Helo Normal Pop-Up Range Select chooses the Terrain Display Range to be forced during a non-Low Altitude Mode Pop-Up. The 2.5 NM range selection is recommended if the selected display type supports a 2.5 NM range.

If the display type selected via Category 6 supports Auto Pop-Up and Auto-Ranging then the Helo Low Altitude Pop-Up Range Select chooses the Terrain Display Range to be forced during a Low Altitude Mode Pop-Up. The 2.5NM range selection is recommended if the selected display type supports a 2.5 NM range.

When Mode 6B Always ON Enable is selected, Mode 6B logic (non-latching) is enabled all the time. This option is normally selected when the Check Height callout option is selected.

When Normal Terrain Airspeed Select is selected, the Terrain function will use Airspeed in Lieu of Ground speed in normal operations. Please be aware that if Airspeed is selected for Terrain function it can increase the likelihood of nuisance alerts when taking off or landing in strong headwinds.

When Low Altitude Airspeed Select is selected, the Terrain function will use Airspeed in Lieu of Ground speed in low altitude operations.

When Low Altitude No VFOM Select is selected, the VFOM biasing from the Low Altitude Terrain Floor height is removed allowing low level operation at 200 feet AGL.

TABLE 5.3.17: OPTIONS 2 SELECT

ID

Helo Normal Pop-Up

Range Select (in NM)

Helo Low Altitude Pop-Up Range Select

(in NM)

Auto-rotation Callout Option

Select

Mode 6B Always

ON Enable

Normal Terrain

Airspeed Select

(Note 1)

Low Altitude Airspeed

Select (Note 1)

Low Altitude

No VFOM Select

Effectivity

0 5 2.5 1 False False False False -020 1 5 2.5 2 False False False False -020 2 5 2.5 0 False False False False -020 3 5 5 1 False False False False -020 4 5 5 2 False False False False -020 5 5 5 0 False False False False -020 6 10 10 1 False False False False -020 7 10 10 2 False False False False -020 8 10 10 0 False False False False -020 9 2.5 2.5 1 False False False False -026

10 2.5 2.5 2 False False False False -026 11 2.5 2.5 0 False False False False -026 12 5 2.5 1 True False False False -026 13 5 2.5 2 True False False False -026



ID

Helo Normal Pop-Up



(in NM)


Select

Mode 6B Always

ON Enable

Normal Terrain

Airspeed Select

(Note 1)


Select (Note 1)

Low Altitude

No VFOM Select

Effectivity

14 5 2.5 0 True False False False -026 15 5 5 1 True False False False -026 16 5 5 2 True False False False -026 17 5 5 0 True False False False -026 18 10 10 1 True False False False -026 19 10 10 2 True False False False -026 20 10 10 0 True False False False -026 21 2.5 2.5 1 True False False False -026 22 2.5 2.5 2 True False False False -026 23 2.5 2.5 0 True False False False -026 24 5 2.5 1 False True False False -026 25 5 2.5 2 False True False False -026 26 5 2.5 0 False True False False -026 27 5 5 1 False True False False -026 28 5 5 2 False True False False -026 29 5 5 0 False True False False -026 30 10 10 1 False True False False -026 31 10 10 2 False True False False -026 32 10 10 0 False True False False -026 33 2.5 2.5 1 False True False False -026 34 2.5 2.5 2 False True False False -026 35 2.5 2.5 0 False True False False -026 36 5 2.5 1 True True False False -026 37 5 2.5 2 True True False False -026 38 5 2.5 0 True True False False -026 39 5 5 1 True True False False -026 40 5 5 2 True True False False -026 41 5 5 0 True True False False -026 42 10 10 1 True True False False -026 43 10 10 2 True True False False -026 44 10 10 0 True True False False -026 45 2.5 2.5 1 True True False False -026 46 2.5 2.5 2 True True False False -026 47 2.5 2.5 0 True True False False -026 48 5 2.5 1 False False True False -026 49 5 2.5 2 False False True False -026 50 5 2.5 0 False False True False -026 51 5 5 1 False False True False -026 52 5 5 2 False False True False -026 53 5 5 0 False False True False -026 54 10 10 1 False False True False -026 55 10 10 2 False False True False -026 56 10 10 0 False False True False -026 57 2.5 2.5 1 False False True False -026 58 2.5 2.5 2 False False True False -026 59 2.5 2.5 0 False False True False -026 60 5 2.5 1 True False True False -026 61 5 2.5 2 True False True False -026



ID

Helo Normal Pop-Up



(in NM)


Select

Mode 6B Always

ON Enable

Normal Terrain

Airspeed Select

(Note 1)


Select (Note 1)

Low Altitude

No VFOM Select

Effectivity

62 5 2.5 0 True False True False -026 63 5 5 1 True False True False -026 64 5 5 2 True False True False -026 65 5 5 0 True False True False -026 66 10 10 1 True False True False -026 67 10 10 2 True False True False -026 68 10 10 0 True False True False -026 69 2.5 2.5 1 True False True False -026 70 2.5 2.5 2 True False True False -026 71 2.5 2.5 0 True False True False -026 72 5 2.5 1 False True True False -026 73 5 2.5 2 False True True False -026 74 5 2.5 0 False True True False -026 75 5 5 1 False True True False -026 76 5 5 2 False True True False -026 77 5 5 0 False True True False -026 78 10 10 1 False True True False -026 79 10 10 2 False True True False -026 80 10 10 0 False True True False -026 81 2.5 2.5 1 False True True False -026 82 2.5 2.5 2 False True True False -026 83 2.5 2.5 0 False True True False -026 84 5 2.5 1 True True True False -026 85 5 2.5 2 True True True False -026 86 5 2.5 0 True True True False -026 87 5 5 1 True True True False -026 88 5 5 2 True True True False -026 89 5 5 0 True True True False -026 90 10 10 1 True True True False -026 91 10 10 2 True True True False -026 92 10 10 0 True True True False -026 93 2.5 2.5 1 True True True False -026 94 2.5 2.5 2 True True True False -026 95 2.5 2.5 0 True True True False -026 96 5 2.5 1 False False False True -026 97 5 2.5 2 False False False True -026 98 5 2.5 0 False False False True -026 99 5 5 1 False False False True -026

100 5 5 2 False False False True -026 101 5 5 0 False False False True -026 102 10 10 1 False False False True -026 103 10 10 2 False False False True -026 104 10 10 0 False False False True -026 105 2.5 2.5 1 False False False True -026 106 2.5 2.5 2 False False False True -026 107 2.5 2.5 0 False False False True -026 108 5 2.5 1 True False False True -026 109 5 2.5 2 True False False True -026



ID

Helo Normal Pop-Up



(in NM)


Select

Mode 6B Always

ON Enable

Normal Terrain

Airspeed Select

(Note 1)


Select (Note 1)

Low Altitude

No VFOM Select

Effectivity

110 5 2.5 0 True False False True -026 111 5 5 1 True False False True -026 112 5 5 2 True False False True -026 113 5 5 0 True False False True -026 114 10 10 1 True False False True -026 115 10 10 2 True False False True -026 116 10 10 0 True False False True -026 117 2.5 2.5 1 True False False True -026 118 2.5 2.5 2 True False False True -026 119 2.5 2.5 0 True False False True -026 120 5 2.5 1 False True False True -026 121 5 2.5 2 False True False True -026 122 5 2.5 0 False True False True -026 123 5 5 1 False True False True -026 124 5 5 2 False True False True -026 125 5 5 0 False True False True -026 126 10 10 1 False True False True -026 127 10 10 2 False True False True -026 128 10 10 0 False True False True -026 129 2.5 2.5 1 False True False True -026 130 2.5 2.5 2 False True False True -026 131 2.5 2.5 0 False True False True -026 132 5 2.5 1 True True False True -026 133 5 2.5 2 True True False True -026 134 5 2.5 0 True True False True -026 135 5 5 1 True True False True -026 136 5 5 2 True True False True -026 137 5 5 0 True True False True -026 138 10 10 1 True True False True -026 139 10 10 2 True True False True -026 140 10 10 0 True True False True -026 141 2.5 2.5 1 True True False True -026 142 2.5 2.5 2 True True False True -026 143 2.5 2.5 0 True True False True -026 144 5 2.5 1 False False True True -026 145 5 2.5 2 False False True True -026 146 5 2.5 0 False False True True -026 147 5 5 1 False False True True -026 148 5 5 2 False False True True -026 149 5 5 0 False False True True -026 150 10 10 1 False False True True -026 151 10 10 2 False False True True -026 152 10 10 0 False False True True -026 153 2.5 2.5 1 False False True True -026 154 2.5 2.5 2 False False True True -026 155 2.5 2.5 0 False False True True -026 156 5 2.5 1 True False True True -026 157 5 2.5 2 True False True True -026



ID

Helo Normal Pop-Up



(in NM)


Select

Mode 6B Always

ON Enable

Normal Terrain

Airspeed Select

(Note 1)


Select (Note 1)

Low Altitude

No VFOM Select

Effectivity

158 5 2.5 0 True False True True -026 159 5 5 1 True False True True -026 160 5 5 2 True False True True -026 161 5 5 0 True False True True -026 162 10 10 1 True False True True -026 163 10 10 2 True False True True -026 164 10 10 0 True False True True -026 165 2.5 2.5 1 True False True True -026 166 2.5 2.5 2 True False True True -026 167 2.5 2.5 0 True False True True -026 168 5 2.5 1 False True True True -026 169 5 2.5 2 False True True True -026 170 5 2.5 0 False True True True -026 171 5 5 1 False True True True -026 172 5 5 2 False True True True -026 173 5 5 0 False True True True -026 174 10 10 1 False True True True -026 175 10 10 2 False True True True -026 176 10 10 0 False True True True -026 177 2.5 2.5 1 False True True True -026 178 2.5 2.5 2 False True True True -026 179 2.5 2.5 0 False True True True -026 180 5 2.5 1 True True True True -026 181 5 2.5 2 True True True True -026 182 5 2.5 0 True True True True -026 183 5 5 1 True True True True -026 184 5 5 2 True True True True -026 185 5 5 0 True True True True -026 186 10 10 1 True True True True -026 187 10 10 2 True True True True -026 188 10 10 0 True True True True -026 189 2.5 2.5 1 True True True True -026 190 2.5 2.5 2 True True True True -026 191 2.5 2.5 0 True True True True -026

Note 1: Before selecting Airspeed Select Option see section 3.3.17.6 and 3.3.17.7 for further consideration.




The following table provides identification of the Options 3 Select.

When the Timed Audio Inhibit discrete is selected the inhibit time may be selected using Option 3. These configurations define the value of Audio Inhibit Time. When the table equals Toggle then Audio Inhibit Time shall equal zero. See Product Specification section 6.9.2 for a list of the basic audio inhibit exceptions.

The Inhibit All Except the configured Minimums Type Callout and the 100 Ft Callout Select and the Inhibit All Except the configured Minimums Type Callout Select are mutually exclusive options.

The Inhibit Includes Too Low Gear Select option is intended for those aircraft that perform SAR recovery operations with Gear Up and can be mixed with other audio inhibit options. The Inhibit Altitude Callouts 50 Ft and Below Over Runway Select when selected will inhibit configured Altitude Callouts from 50 feet and below when over a runway in the Runway Database in a Helicopter. Note: The Helicopter Runway Database only contains runways with a published approach procedure.

For aircraft with two valid digital sources of Minimum Decent Altitude (MDA) or Decision Height (DH) the source with the highest setting is selected for use in the minimum type callouts. When Lower MDA/DH Value Select is TRUE, the selection logic is reversed so that the source with the lower value is used for the callout altitude.


ID

Audio Inhibit Time

(Minutes)

Inhibit All except

Minimums Type Callout

and 100 Ft Callout Select

(Note 1)

Inhibit All except


Select (Note 1)

Inhibit Includes Too Low

Gear Select (Note 1)

Inhibit Altitude

Callouts 50 Ft and Below

Over Runway Select

Lower MDA/DH

Value Select Effectivity

0 5 False False False False False -026


2 7.5 False False False False False -026






8 Toggle False False False False False -026

9 5 True False False False False -026


11 7.5 True False False False False -026






17 Toggle True False False False False -026

18 5 False True False False False -026


20 7.5 False True False False False -026



ID

Audio Inhibit Time

(Minutes)

Inhibit All except



(Note 1)

Inhibit All except


Select (Note 1)



Inhibit Altitude


Over Runway Select

Lower MDA/DH







26 Toggle False True False False False -026

27 5 False False True False False -026


29 7.5 False False True False False -026






35 Toggle False False True False False -026

36 5 True False True False False -026


38 7.5 True False True False False -026






44 Toggle True False True False False -026

45 5 False True True False False -026


47 7.5 False True True False False -026






53 Toggle False True True False False -026

54 5 False False False True False -026



ID

Audio Inhibit Time

(Minutes)

Inhibit All except



(Note 1)

Inhibit All except


Select (Note 1)



Inhibit Altitude


Over Runway Select

Lower MDA/DH



56 7.5 False False False True False -026






62 Toggle False False False True False -026

63 5 True False False True False -026


65 7.5 True False False True False -026






71 Toggle True False False True False -026

72 5 False True False True False -026


74 7.5 False True False True False -026






80 Toggle False True False True False -026

81 5 False False True True False -026


83 7.5 False False True True False -026








ID

Audio Inhibit Time

(Minutes)

Inhibit All except



(Note 1)

Inhibit All except


Select (Note 1)



Inhibit Altitude


Over Runway Select

Lower MDA/DH


89 Toggle False False True True False -026

90 5 True False True True False -026

91 3 TRUE FALSE TRUE TRUE FALSE -026

92 7.5 True False True True False -026






98 Toggle True False True True False -026

99 5 False True True True False -026


101 7.5 False True True True False -026






107 Toggle False True True True False -026

108 5 False False False False True -026


110 7.5 False False False False True -026






116 Toggle False False False False True -026

117 5 True False False False True -026


119 7.5 True False False False True -026






ID

Audio Inhibit Time

(Minutes)

Inhibit All except



(Note 1)

Inhibit All except


Select (Note 1)



Inhibit Altitude


Over Runway Select

Lower MDA/DH




125 Toggle True False False False True -026

126 5 False True False False True -026


128 7.5 False True False False True -026






134 Toggle False True False False True -026

135 5 False False True False True -026


137 7.5 False False True False True -026






143 Toggle False False True False True -026

144 5 True False True False True -026


146 7.5 True False True False True -026






152 Toggle True False True False True -026

153 5 False True True False True -026


155 7.5 False True True False True -026




ID

Audio Inhibit Time

(Minutes)

Inhibit All except



(Note 1)

Inhibit All except


Select (Note 1)



Inhibit Altitude


Over Runway Select

Lower MDA/DH






161 Toggle False True True False True -026

162 5 False False False True True -026


164 7.5 False False False True True -026






170 Toggle False False False True True -026

171 5 True False False True True -026


173 7.5 True False False True True -026






179 Toggle True False False True True -026

180 5 False True False True True -026


182 7.5 False True False True True -026






188 Toggle False True False True True -026

189 5 False False True True True -026




ID

Audio Inhibit Time

(Minutes)

Inhibit All except



(Note 1)

Inhibit All except


Select (Note 1)



Inhibit Altitude


Over Runway Select

Lower MDA/DH


191 7.5 False False True True True -026






197 Toggle False False True True True -026

198 5 True False True True True -026


200 7.5 True False True True True -026






206 Toggle True False True True True -026

207 5 False True True True True -026


209 7.5 False True True True True -026






215 Toggle False True True True True -026

Note 1: Can only be used with Category 5 ID 128, 129, 251, 252, 253, 254 and 255, and Category 4 ID 17 thru 68




The following table provides identification of the Options 4 Select.

“Low Altitude Mode” is selected with the use of the Low Altitude Mode Select (Tactical) discrete. This discrete is sourced from an analog switch or digital ARINC 429 bits. Prior to the -030 release when “Low Altitude Mode” was activated GPWS classic modes and the forward looking terrain alert function were modified to allow flight in congested areas, low altitude routes or while performing special operations.

In release -030 and on, this option category allows tailoring of the MK XXII system response to the Low Altitude Mode Select (Tactical) discrete.

When Low Altitude Mode Select is true the HTAWS provides a “Reduced Protection Mode” allowing operations below the defined alert envelopes without issuing alerts. Low Altitude Mode Select affects the following modes regardless of the configuration option selected below (see table for further changes in operation):

GPWS Mode 2 inhibited. GPWS Mode 3 inactive above 100 feet AGL. Mode 6 provides the message “Altitude Altitude” or “Check Height” for each transitioning below the selected

decision height1. Forward Looking Terrain Alerting Threat Detection is biased to allow closer proximity to terrain.

1 For S-92 “Altitude Altitude” callout is always active. System Response to Low Altitude Mode Select (active)

Low Altitude Option

Suggested Operations Mode 1 Pullup & Sinkrate

Mode 4 Too Low

Gear

Mode 4 Too Low Terrain

FLTA Behavior

Peaks Water

Priority 02 Low level operations over land Inhibited Enabled Inhibited Low Alt - 1 SAR over water Inhibited Inhibited Inhibited SAR Enabled 2 Offshore transport Enabled Enabled Enabled Offshore Enabled

2 Low Alt Option ‘0’ configures the system to pre release -030 Low Altitude operation. If the category ID is not provided by the configuration module the default is ID ‘0’, option select ‘0’ Low level operations over land when Low Altitude Mode (Tactical) is selected.

Mode 1 ‘PULLUP’ and ‘SINKRATE’: When inhibited, Mode 1 alerts (aural and visual) are disabled.

Mode 4 ‘TOO LOW GEAR’: When inhibited, allows low level flight with gear up and no Mode 4 gear alerts. Applicable to rotorcraft with retractable gear. “Too Low Gear” alert is not provided for fixed gear aircraft.

Mode 4 ‘TOO LOW TERRAIN’: When inhibited, allows low level flight, at high speed, with gear up and no Mode 4 “Too Low Terrain” alerts.

FLTA (Forward Looking Terrain Alerting), Behavior:

Low Alt: When Low Altitude Mode Select (Tactical) discrete active, the Threat Detection envelopes are tailored to accommodate lower than normal flight with reduced protection.

SAR: When Low Altitude Mode Select (Tactical) discrete active, the Threat Detection envelopes are tailored to accommodate Search and Rescue operations.

Offshore: When Low Altitude Mode Select (Tactical) discrete active, the Threat Detection envelopes are tailored to accommodate Offshore transport operations over water.

Peaks Water Priority: The HTAWS provides a “peaks” display mode. The Peaks Mode adds additional density patterns and level thresholds based on absolute terrain elevations relative to the range and distribution of terrain in the display area. HTAWS paints sea level bodies of water (0 feet MSL) blue (cyan), provided the displays is capable of presenting the color. When a rotorcraft is low over the water, blue is replaced by yellow as the edge of the alert envelope reaches (look down) the surface of the water. This has been a distraction to pilots. When Peaks Water Priority is enabled the blue presentation will be provided over the water even at low altitudes.

Mode 2 Terrain Inhibit



Many HTAWS installations provide a Terrain Inhibit switch that allows the pilot to disable (or inhibit) Terrain Awareness Alerts. When this switch is active the Forward Looking Terrain Alerting function is inhibited however, the radio altimeter based, classic GPWS Mode 2 alerts are not. This can lead to pilot dissatisfaction. The following is a scenario to illustrate the potential for confusion: Pilot is flying VFR and is intentionally close to terrain; Forward Looking Terrain Alert activates providing “Caution! Terrain” aural and alert visual; pilot inhibits terrain by selecting the Terrain Inhibit switch; Forward Looking Terrain Alert ceases but due to close proximity to terrain the GPWS Mode 2 alert activates providing the “Terrain Terrain” aural and alert visual. In this scenario the pilot has made the decision and commanded the system to inhibit terrain alerts but the system continues to provide them albeit from a different mode. In the -030 release the Mode 2 Terrain Inhibit option allows the Terrain Inhibit switch to affect the Mode 2 function.

Mode 2 Terrain Inhibit = False; Terrain Inhibit does not affect Mode 2 (pre -030 release behavior).

Mode 2 Terrain Inhibit = True; Terrain Inhibit will also inhibit the Mode 2 alert function.

If the category ID is not provided by the configuration module the default is ID “0”, option select “False”.


ID Low

Altitude Option

Mode 2 Terrain Inhibit

Effectivity

0 0 False -030 1 1 False -030 2 2 False -030 3 0 True -030 4 1 True -030 5 2 True -030



6.0 OUTPUT DATA DEFINITION

6.1. ARINC 429 OUTPUT DATA

The MK XXII EGPWC provides one or two ARINC 429 low or high-speed output channels per section 5.3.6. The output consist of internal parameters that can be used for display selection or test purposes, and discrete outputs that can be used for test and recording. During LRU Self-Test the SSM of each output label is set to the Functional Test status code. The output types can be summarized as follows.

1) Internal data: Some internal data is output for test purposes only such as Radio Altitude, Computed Airspeed, Geometric Altitude, etc.

2) Alert status: Each type of Voice and Lamp activity is mapped to a specific label/BIT. This can be used to provide inputs to display systems and flight recorders.

3) Internal Mode status: Various internal EGPWC mode logic is transmitted for test purposes.

4) Terrain Display messages for TAD cockpit integration.

The ARINC 429 bus transmits both discrete and BNR labels. In the event of catastrophic computer failure, or 429 transmitter failure, outputs will not be transmitted. During Self-Test, the SSM will be set to functional test on all outputs (bits 31/30 = 1/0). During all other conditions of computer or input failures, the 429 outputs will continue to be transmitted as actual valid data. For valid status the standard discrete SSM format is used (00) except for data indicated as being in 2’s complement format where the standard BNR SSM format is used (11). The SDI bits (9/10) will always be set to “00”.

Note: Label 067 includes an indication of parameter inaccuracy that is not tied to the above discussion of SSM settings.

The following table identifies those outputs that are transmitted. Note that the outputs are segregated by functional groups. Refer to the subsections following the table for specific format information for each output. The subsections are in the same order as the table.



TABLE 6.1-1: ARINC 429 DITS OUTPUTS OPERATIONAL OUTPUTS

LABEL NAME DESCRIPTION NOTES DISCRETE OUTPUT WORDS

270 EGPWS ALERT DISCRETE #1 EGPWS ALERT INDICATION 1 271 EGPWC LOGIC DISCRETES INTERNAL LOGIC BOOLEANS 1 272 MODE 6 CALLOUTS DISCRETE #1 MODE 6 CALLOUT INDICATION #1 1 273 MODE 6 CALLOUTS DISCRETE #2 MODE 6 CALLOUT INDICATION #2 1 274 EGPWS ALERT DISCRETE #2 LAMP OUTPUT WORD 1 300 EGPWC ALERT DISCRETE #3 INOP INDICATIONS OF THE MK XXII EGPWC FUNCTIONS 1

INTERNAL DATA OUTPUTS

The internal data output labels are lowest priority.

135 GEOMETRIC ALTITUDE VFOM COMPUTED GEOMETRIC ALTITUDE VFOM 5 164 TERRAIN CLEARANCE RADIO ALTITUDE FILTERED BY MK XXII EGPWC 1 261 GEOMETRIC ALTITUDE COMPUTED GEOMETRIC ALTITUDE 5 067 COMPUTED TERRAIN CLEARANCE TERRAIN CLEARANCE COMPUTED BY EGPWS 5,6 310 LATITUDE PRESENT POSITION EGPWS SELECTED LATITUDE 5 311 LONGITUDE PRESENT POSITION EGPWS SELECTED LONGITUDE 5

TERRAIN DISPLAY OUTPUTS

050 DISPLAYED RANGE TERRAIN DISPLAY #1 AND #2 RANGE 2,4 051 TERRAIN DISPLAY STATUS WORD TERRAIN DISPLAY STATUS INFORMATION 2,4 052 MESSAGE WORD #1 COLOR OF DISPLAY MESSAGE 2,4 053 MESSAGE WORD #2 FIRST TWO CHARACTERS OF DISPLAY MESSAGE 2,4 054 MESSAGE WORD #3 SECOND TWO CHARACTERS OF DISPLAY MESSAGE 2,4 055 MESSAGE WORD #4 LAST TWO CHARACTERS OF DISPLAY MESSAGE 2,4

EQUIPMENT ID

377 EQUIPMENT IDENTIFICATION PROVIDES ARINC 429 DEFINED EQUIPMENT ID NO. (023) 3 FAULT SUMMARY WORDS

350 FAULT DIAGNOSTIC WORD #1 PROVIDES FAULT STATUS 5 351 FAULT DIAGNOSTIC WORD #2 PROVIDES FAULT STATUS 5 355 FAULT DIAGNOSTIC WORD #3 PROVIDES FAULT STATUS 5

PEAKS ELEVATION BINARY

011 PEAKS UPPER ELEVATION UPPER ELEVATION VALUE AND COLOR 6,8,9,10 012 PEAKS LOWER ELEVATION LOWER ELEVATION VALUE AND COLOR 6,8,9,10

NOTES: 1) Update rate 100 ms 10% 2) Update rate 200 ms 10% 3) Update rate 500 ms 10% 4) Transmitted only if Terrain Awareness function enabled 5) Update rate 1000 ms 10% 6) NCD and Failure Warning Indications Provided 7) 8) 9) Transmitted only if Peaks enabled 10) Update rate 500 ms 10% for each SDI

6.1.1 DISCRETE OUTPUT WORDS

The discrete output words transmit the status of all MK XXII EGPWC discrete and audio outputs. Label 274 is typically used to drive EFIS and/or EICAS displays. The other discrete labels are typically only used for flight recording and test purposes.



6.1.1.1 EGPWS ALERT DISCRETE #1 (270)

Data: Discrete Label: 270 Octal Significant Bits: (see table below) Sign Bit: N/A Transmit Interval: 100 msec 10% Bit No. ASSIGNED WARNING MESSAGE (1 = voice on) 11 SINKRATE (PAUSE) SINKRATE 12 PULL UP 13 TERRAIN OR TERRAIN-TERRAIN 14 DONT SINK (PAUSE) DONT SINK 15 TOO LOW GEAR 16 TOO LOW FLAPS (Not supported) 17 TOO LOW TERRAIN 18 GLIDESLOPE 19 MINIMUMS MINIMUMS 20 TERRAIN PULLUP (Not supported) 21 CAUTION TERRAIN 22 WARNING TERRAIN or WARNING OBSTACLE

Note: This bit is used for the alternate terrain and obstacle warning voice message the basic terrain warning message is mapped to bits 13 and 12 and obstacle warning voice mapped to bits 29 and 12.

* 23 Not supported by MK XXII * 24 Not supported by MK XXII * 25 ENGINE FAIL (Not supported) * 26 Not supported by MK XXII 27 CAUTION TERRAIN or TERRAIN AHEAD Note: This is the alternate Terrain Caution voice. 28 CAUTION OBSTACLE or OBSTACLE AHEAD 29 OBSTACLE OBSTACLE

NOTE (*): Bits will be set to zero when Not Supported

6.1.1.2 EGPWC LOGIC DISCRETES (271)

Data: Discrete Label: 271 Octal Significant Bits: (see table below) Sign Bit: N/A Transmit Interval: 100 msec 10% BIT No. DEFINITION * 11 Not supported by MK XXII * 12 Not supported by MK XXII 13 TERRAIN CLEARANCE FLOOR ALERT 14 ENVELOPE MOD IN PROGRESS 15 ENVELOPE MOD SNAPSHOT LATCH SET * 16 Not supported by MK XXII * 17 Not supported by MK XXII 18 TAKE-OFF MODE 19 MODE 1 SINKRATE 20 MODE 1 PULL UP 21 MODE 2 TERRAIN 22 MODE 2 PULL UP 23 MODE 3 VISUAL 24 MODE 4 VISUAL 25 MODE 5 VISUAL * 26 Not supported by MK XXII 27 TERRAIN AWARENESS CAUTION 28 TERRAIN AWARENESS WARNING * 29 Not supported by MK XXII




6.1.1.3 MODE 6 CALLOUTS DISCRETE #1 (272)

Data: Discrete Label: 272 Octal Significant Bits: (see table below) Sign Bit: N/A Transmit Interval: 100 msec 10% BIT NO ADVISORY MESSAGE (1 = voice on) 11 MINIMUMS * 12 (Not supported) 13 CHECK HEIGHT (pause) CHECK HEIGHT * 14 (Not supported) * 15 (Not supported) 16 TEN 17 TWENTY 18 THIRTY 19 FORTY 20 FIFTY 21 SIXTY 22 EIGHTY 23 ONE HUNDRED 24 TWO HUNDRED 25 THREE HUNDRED * 26 (Not supported) * 27 (Not supported) * 28 (Not supported) * 29 (Not supported)


6.1.1.4 MODE 6 CALLOUTS DISCRETE #2 (273)

Data: Discrete Label: 273 Octal Significant Bits: (see table below) Sign Bit: N/A Transmit Interval: 100 msec 10% BIT NO DEFINITION (1 = voice on) 11 FOUR HUNDRED 12 FIVE HUNDRED (NORMAL, SMART OR ABOVE FIELD) 13 ONE THOUSAND * 14 (Not supported) * 15 (Not supported) * 16 (Not supported) * 17 (Not supported) 18 BANK ANGLE (pause) BANK ANGLE * 19 (Not supported) * 20 (Not supported) * 21 (Not supported) * 22 (Not supported) 23 FIVE HUNDRED ABOVE (ABOVE FIELD) 24 TAIL TOO LOW 25 BE ALERT TERRAIN INOP 26 ALTITUDE ALTITUDE or ALTITUDE or CHECK HEIGHT * 27 (Not supported) * 28 (Not supported) 29 ONE HUNDRED TEN, ONE HUNDRED TWENTY, ONE HUNDRED THIRTY, ONE HUNDRED FORTY,

ONE HUNDRED FIFTY or ONE HUNDRED SIXTY.




6.1.1.5 EGPWS ALERT DISCRETE #2 (274)

Data: Discrete Label: 274 Octal Significant Bits: (see table below) Sign Bit: N/A Transmit Interval: 100 msec 10% Bit No. ASSOCIATED

DISCRETE PIN DEFINITION (1 = ON)

11 J1-76 (TYPICALLY GLIDESLOPE CANCEL) 12 J1-77 GPWS ALERT 13 J1-78 GPWS WARNING 14 ---- GPWS INOP * 15 ---- (Not supported) 16 J1-69 AUDIO ON * 17 ---- (Not supported) * 18 ---- (Not supported) 19 ---- CALLOUTS INOP 20 ---- TIMED AUDIO INHIBIT * 21 ---- ENGINE FAIL INOP (Not supported) 22 ---- TERRAIN AWARENESS WARNING or OBSTACLE AWARENESS WARNING 23 ---- TERRAIN AWARENESS CAUTION or OBSTACLE AWARENESS CAUTION 24 ---- TERRAIN AWARENESS INOP 25 FRONT PANEL LED EXTERNAL FAULT 26 FRONT PANEL LED COMPUTER FAIL 27 ---- TERRAIN AWARENESS NOT AVAILABLE 28 J1-54 TERRAIN DISPLAY DISCRETE #1 29 J1-49 TERRAIN DISPLAY DISCRETE #2


6.1.1.6 EGPWC ALERT DISCRETE #3 (300)

Data: Discrete Label: 300 Octal Significant Bits: (see table below) Sign Bit: N/A Transmit Interval: 100 msec 10% BIT No. DEFINITION 11 MODES 1-4 INOP 12 MODE 5 INOP 13 MODE 6 INOP 14 BANK ANGLE INOP * 15 (Not supported) 16 TERRAIN CLEARANCE FLOOR INOP or RUNWAY FIELD CLEARANCE FLOOR INOP 17 TERRAIN AWARENESS INOP 18 ENVELOPE MODULATION INOP 19 TOO LOW TERRAIN VISUAL ALERT 20 TOO LOW GEAR VISUAL ALERT 21 TCAS INHIBIT 22 SAR SELECT** 23 OFFSHORE SELECT** 24 TERRAIN AWARENESS & TCF INHIBIT 25 TAIL STRIKE INOP 26 TACTICAL SELECT * 27 (Not supported) 28 OBSTACLE AWARENESS CAUTION 29 OBSTACLE AWARENESS WARNING

NOTE (*): Bits will be set to zero when Not Supported NOTE (**): BIT 22 and BIT 23 defined in the -030 release are utilized by the Epic MCDU for indicating the status of the internal

latches.



6.1.2 INTERNAL DATA OUTPUTS

Internal data outputs are only used for test purposes.

6.1.2.1 GEOMETRIC ALTITUDE VFOM (135)

LABEL (Octal) 135 Units: Feet Max. Range: 32,768 Ft Approx. LSB: 0.125 Foot Data Bits: 11 to 28 = 18 + = N/A Sign Bit: 29 Pad Bits: N/A Transmit Interval (msec): 1000 10% Data Type: 2’s Compliment Binary SDI Bits: 9, 10

6.1.2.2 TERRAIN CLEARANCE (164)

LABEL (Octal) 164 Units: Feet Max. Range: 8,192 Feet Approx. LSB: 1.0 Foot Data Bits: 16 to 28 = 13 + = Above Ground Level (AGL) Sign Bit: 29 Pad Bits: 11 to 15 Transmit Interval (mSec): 100 10% Data Type: 2’s Compliment Binary SDI Bits: 9, 10

6.1.2.3 GEOMETRIC ALTITUDE (261)

LABEL (Octal) 261 Units: Feet Max. Range: 131,072 Ft Approx. LSB: 0.125 Foot Data Bits: 9 to 28 = 20 + = Above Sea Level (ASL) Sign Bit: 29 Pad Bits: N/A Transmit Interval (msec): 1000 10% Data Type: 2’s Compliment Binary SDI Bits: N/A

6.1.2.4 COMPUTED TERRAIN CLEARANCE (067)

LABEL (Octal) 067 Units: Feet Max. Range: 131,072 Ft Approx. LSB: 1.0 Foot Data Bits: 12 to 28 = 17 + = Above Ground Level (AGL) Sign Bit: 29 Pad Bits: N/A Transmit Interval (msec): 1000 10% Data Type: 2’s Compliment Binary SDI Bits: N/A

Bit Definitions 11 Set to 1 when Computed Terrain Clearance low accuracy is indicated 12 -28 Computed Terrain Clearance

6.1.2.5 LATITUDE – SELECTED EGPWS (310)

LABEL (Octal) 310 Units: Degrees Max. Range: 180 Degrees LSB: 0.00017166137695 Data Bits: 9 to 28 = 20 + = North Sign Bit: 29 Pad Bits: N/A Transmit Interval (mSec): 1000 10% Data Type: 2’s Compliment Binary SDI Bits: used for data

6.1.2.6 LONGITUDE – SELECTED EGPWS (311)

LABEL (Octal) 311 Units: Degrees Max. Range: 180 Degrees LSB: 0.00017166137695 Data Bits: 9 to 28 = 20 + = East Sign Bit: 29 Pad Bits: N/A Transmit Interval (mSec): 1000 10% Data Type: 2’s Compliment Binary SDI Bits: used for data



6.1.3 TERRAIN DISPLAY OUTPUTS

The following ARINC 429 outputs support the Terrain Display function.

6.1.3.1 DISPLAYED RANGE (050)

Data: Discrete Label (Octal): 050 Transmit Interval: 200 msec 10% BIT NO DEFINITION 11 – 14 TERRAIN DISPLAY RANGE #1 (0.5 to 2000 NM format) 15 – 18 TERRAIN DISPLAY RANGE #2 (0.5 to 2000 NM format) 19 - 29 UNDEFINED

NOTE: Bits contain left and right side Terrain Display Ranges (0.5 to 2000 NM, format as follows)

DISPLAY RANGE BIT ASSIGNMENTS

(Bits 14-11), & (Bits 18-15) DEFINITION (Bits 14-11), & (Bits 18-15) DEFINITION

0000 0.5 NM 1000 150 NM

0001 1.0 NM 1001 200 NM

0010 2.5 NM 1010 300 NM

0011 5.0 NM 1011 500 NM

0100 10 NM 1100 1000 NM

0101 25 NM 1101 2000 NM

0110 50 NM 1110 600 NM

0111 100 NM 1111 1200 NM

6.1.3.2 TERRAIN DISPLAY STATUS WORD (051)

Data: Discrete Label (Octal): 051 Transmit Interval: 200 msec 10%

BIT NO DEFINITION

11 POP UP BOOLEAN #1

12 POP UP BOOLEAN #2

13 TERRAIN DISPLAY VALID (cleared when TERRAIN AWARENESS NOT AVAILABLE or TERRAIN AWARENESS INOP are true)

14 SPARE

15 SPARE

16 Not Supported

17 TERRAIN AWARENESS & TCF INHIBIT

18 SPARE

19 SPARE

20 SPARE

21 SPARE

22 SPARE

23 SPARE

24 SPARE

25 SPARE

26 TERRAIN DISPLAY CAUTION

27 TERRAIN DISPLAY WARNING

28 Not Supported

29 SPARE



6.1.3.3 MESSAGE WORD #1 (052)

This label contains the color to be displayed on the 6-character terrain display window.

Data: Discrete Label (Octal): 052 Transmit Interval: 200 msec 10% BIT NO DEFINITION BIT Coding COLOR Code (Hex) 9 - 10 SDI (00)

11 Spare 12 Spare 13 Spare 14 Spare 15 Spare 16 Spare 17 Spare 18 Spare 19 Spare 20 Spare 21 Spare 22 Spare 23 Character Color LSB (7 bit Hex) BITS 0000001 = Red

0000010 = Amber 0000011 = Yellow 0000100 = Green 0000101 = Cyan 0000110 = Magenta 0000111= White

24 Character Color 25 Character Color 26 Character Color (not currently used) 27 Character Color (not currently used) 28 Character Color (not currently used) 29 Character Color (not currently used) MSB (7 bit Hex)

6.1.3.4 MESSAGE WORD #2 (053)

This label contains the first 2 characters to be displayed on the 6-character terrain display window.

Data: Discrete Label (Octal): 053 Transmit Interval: 200 msec 10% BIT NO DEFINITION BIT Coding TEXT Code (Hex) TEXT Code (Hex)

9,10 SDI (00) 11 Spare 20 = (space) 30 = 0 12 Spare 21 = ! 31 = 1 13 Spare 22 = “ 32 = 2 14 Spare 23 = # 33 = 3 15 Spare 24 = % 34 = 4 16 Character Code - Left Most of Set 1 of 6 LSB (7 bit Hex) 25 = $ 35 = 5 17 Character Code - Left Most of Set 1 of 6 26 = & 36 = 6 18 Character Code - Left Most of Set 1 of 6 27 = ‘ 37 = 7 19 Character Code - Left Most of Set 1 of 6 28 = ( 38 = 8 20 Character Code - Left Most of Set 1 of 6 29 = ) 39 = 9 21 Character Code - Left Most of Set 1 of 6 2A = * 3A = : 22 Character Code - Left Most of Set 1 of 6 MSB (7 bit Hex) 2B = + 3B = ; 23 Character Code - Next Most of Set 2 of 6 LSB (7 bit Hex) 2C = , 3C = < 24 Character Code - Next Most of Set 2 of 6 2D = - 3D = = 25 Character Code - Next Most of Set 2 of 6 2E = . 3E = > 26 Character Code - Next Most of Set 2 of 6 2F = / 3F = ? 27 Character Code - Next Most of Set 2 of 6 Continued at 28 Character Code - Next Most of Set 2 of 6 LABEL 054 Below 29 Character Code - Next Most of Set 2 of 6 MSB (7 bit Hex)



6.1.3.5 MESSAGE WORD #3 (054)

This label contains the second 2 characters to be displayed on the 6-character terrain display window.

Data: Discrete Label (Octal): 054 Transmit Interval: 200 msec 10% BIT NO DEFINITION BIT Coding TEXT Code (Hex) TEXT Code (Hex)

9,10 SDI (00) 11 Spare 40 = ° (Deg Sign) 50 = P 12 Spare 41 = A 51 = Q 13 Spare 42 = B 52 = R 14 Spare 43 = C 53 = S 15 Spare 44 = D 54 = T 16 Character Code - Left Most of Set 3 of 6 LSB (7 bit Hex) 45 = E 55 = U 17 Character Code - Left Most of Set 3 of 6 46 = F 56 = V 18 Character Code - Left Most of Set 3 of 6 47 = G 57 = W 19 Character Code - Left Most of Set 3 of 6 48 = H 58 = X 20 Character Code - Left Most of Set 3 of 6 49 = I 59 = Y 21 Character Code - Left Most of Set 3 of 6 4A = J 5A = Z 22 Character Code - Left Most of Set 3 of 6 MSB (7 bit Hex) 4B = K 5B = [ 23 Character Code - Next Most of Set 4 of 6 LSB (7 bit Hex) 4C = L 5C = \ 24 Character Code - Next Most of Set 4 of 6 4D = M- 5D = ] 25 Character Code - Next Most of Set 4 of 6 4E = N 5E = ^ 26 Character Code - Next Most of Set 4 of 6 4F = O 5F = _ (underscore) 27 Character Code - Next Most of Set 4 of 6 Continued at 28 Character Code - Next Most of Set 4 of 6 LABEL 055 Below 29 Character Code - Next Most of Set 4 of 6 MSB (7 bit Hex)

6.1.3.6 MESSAGE WORD #4 (055)

This label contains the last 2 characters to be displayed on the 6-character terrain display window.

Data: Discrete Label (Octal): 055 Transmit Interval: 200 msec 10% BIT NO DEFINITION BIT Coding

9,10 SDI (00) 11 Spare 12 Spare 13 Spare 14 Spare 15 Spare 16 Character Code - Left Most of Set 3 of 6 LSB (7 bit Hex) 17 Character Code - Left Most of Set 3 of 6 18 Character Code - Left Most of Set 3 of 6 19 Character Code - Left Most of Set 3 of 6 20 Character Code - Left Most of Set 3 of 6 21 Character Code - Left Most of Set 3 of 6 22 Character Code - Left Most of Set 3 of 6 MSB (7 bit Hex) 23 Character Code - Next Most of Set 4 of 6 LSB (7 bit Hex) 24 Character Code - Next Most of Set 4 of 6 25 Character Code - Next Most of Set 4 of 6 26 Character Code - Next Most of Set 4 of 6 27 Character Code - Next Most of Set 4 of 6 28 Character Code - Next Most of Set 4 of 6 29 Character Code - Next Most of Set 4 of 6 MSB (7 bit Hex)



6.1.4 EQUIPMENT IDENTIFICATION

This label provides the ARINC equipment identification for maintenance reporting.

6.1.4.1 EQUIPMENT IDENTIFICATION WORD

Data: Discrete Label (Octal): 377 Transmit Interval: 500 msec 10% BIT NO DEFINITION 11- 22 ID Code Equipment ID code = 023 Hex for EGPWC 23 - 29 Spare (set to zero)

6.1.5 FAULT SUMMARY WORDS (FOR PROLINE 4/21)

Provides fault diagnosis information.

6.1.5.1 FAULT DIAGNOSTIC WORD #1 (350)


BIT NO DEFINITION (1= Failed)

11 ARINC 429 INPUT #1 FAILED








19 SPARE

20 SPARE

21 SPARE

22 SPARE

23 SPARE

24 SPARE

25 SPARE

26 SPARE

27 SPARE

28 SPARE

29 SPARE






11 SPARE

12 SPARE

13 SPARE

14 SPARE

15 SPARE

16 SPARE

17 SPARE

18 SPARE

19 SUPPORT TASK FAILED

20 NVM FAULT

21 WATCHDOG TIMER FAULT

22 A/D FAIL FAULT

23 VOICE FAIL

24 DITS OUTPUT FAIL

25 TERRAIN DATABASE FAULT

26 FLASH FILE SYSTEM WRITE FAULT

27 DITS INPUT FAIL

28 VOICE DATABASE FAULT

29 SYSTEM OR MODE TASK FAULT




11 ENVELOPE MODULATION DATABASE FAULT

12 EXCESSIVE WATCHDOG TIMEOUTS FAILURE

13 AIRCRAFT DATABASE FAULT ‘OR’ CRC FAULT

14 IMAGE DISPLAY FAULT

15 INTERNAL GPS FAULT

16 CONFIGURATION MODULE FAILED

17 GLIDESLOPE CANCEL DISCRETE FAILED

18 AUDIO INHIBIT DISCRETE INPUT FAILED

19 SELF TEST DISCRETE INPUT FAILED

20 SPARE

21 GEAR INPUT FAILED

22 WEIGHT ON WHEELS FAILED

23 LOW ALTITUDE FAILED

24 TIMED AUDIO INHIBIT FAILED

25 SPARE

26 SPARE

27 SPARE

28 SPARE

29 SPARE



6.1.6 PEAK BINARY LABELS

The following ARINC 429 outputs are used to provide Peak Elevations and color information for integrated displays where the EFIS outputs stroke written Peaks Elevation information on the display. This label set consists of 2 labels containing upper and lower elevation, color, and display blanking data. Each label is transmitted with two different SDI values for the captain’s and first officer’s display values.

6.1.6.1 PEAKS UPPER ELEVATION (011)

Data: Discrete Label (Octal): 011 Transmit Interval: 500 msec 10% BIT NO DEFINITION

9 SDI 0 Not Used 1 1 Captain 0 F/O 1 Not Used 10 SDI 0 0 1 1 11 COLOR BIT 1 0 1 0 1 0 1 0 1 12 COLOR BIT 2 0 Black 0 Green 1 Yellow 1 Red 0 Magenta 0 Blue 1 Cyan 1 White 13 COLOR BIT 3 0 0 0 0 1 1 1 1 14 BLANK PEAKS ELEVATION DISPLAY 0 Normal Display 1 Blank Display 15 DASH PEAKS ELEVATION DISPLAY 0 Normal Display 1 Display Dashes 16 SPARE 17 SPARE 18 SPARE 19 SPARE 20 100 Ft

NOTE: Elevation bits are additive; e.g., bits 20 & 21 = 1 indicates 300 Ft.

21 200 Ft 22 400 Ft 23 800 Ft 24 1600 Ft Upper Peaks Elevation 25 3200 Ft 26 6400 Ft 27 12800 Ft 28 25600 Ft 29 SIGN 0 = 0 (Plus) 1 = - 51200 Ft 30 SSM 0 Failure 1 No Computed 0 Functional Test 1 Normal 31 SSM 0 Warning 0 Data 1 1 Operation 32 PARITY (Odd)

6.1.6.2 PEAKS LOWER ELEVATION (012)

Data: Discrete Label (Octal): 012 Transmit Interval: 500 msec 10% BIT NO DEFINITION

9 SDI 0 Not Used 1 Captain 0 F/O 1 Not Used 10 SDI 0 0 1 1 11 COLOR BIT 1 0 1 0 1 0 1 0 1 12 COLOR BIT 2 0 Black 0 Green 1 Yellow 1 Red 0 Magenta 0 Blue 1 Cyan 1 White 13 COLOR BIT 3 0 0 0 0 1 1 1 1 14 BLANK PEAKS ELEVATION DISPLAY 0 Normal Display 1 Blank Display 15 DASH PEAKS ELEVATION DISPLAY 0 Normal Display 1 Display Dashes 16 SPARE 17 SPARE 18 SPARE 19 SPARE 20 100 Ft

NOTE: Elevation bits are additive; e.g., bits 20 & 21 = 1 indicates 300 Ft.

21 200 Ft 22 400 Ft 23 800 Ft 24 1600 Ft Lower Peaks Elevation 25 3200 Ft 26 6400 Ft 27 12800 Ft 28 25600 Ft 29 SIGN 0 = 0 (Plus) 1 = - 51200 Ft 30 SSM 0 Failure 1 No Computed 0 Functional Test 1 Normal 31 SSM 0 Warning 0 Data 1 1 Operation 32 PARITY (Odd)



6.2 ARINC 708A OUTPUT

Two channels of ARINC 708A or KCPB (453) data is provided to drive terrain displays for installations that use the Terrain Awareness display function. Refer to document 060-4303-000, EGPWS Interface Methodology for further KCPB information. See Category 6 for more details on individual displays.

6.3 AUDIO OUTPUT

Mode computation outputs generally result in an audio voice alert unless inputs are invalid or one of the audio suppression discretes is active. The actual output message, or intended message during audio suppression, is sent to the alert lamp logic for proper output activation.

The audio outputs consist of an 8 ohm amplifier and a transformer isolated 600 ohm output. Additional automatic volume control lowers both outputs a fixed 6 dB below the nominal level on command. Refer to section 4.2.13 and Category 14 for information on volume levels.

Selectable sets of voice alert messages can be defined. Each set is selected by the Voice Menu option in Category 5.

6.4 DISCRETE OUTPUTS

Outputs from the various alert mode computations are first processed to determine which lamp outputs to produce. All of the lamp outputs are driven by solid state switches to ground. These outputs can also be used as discrete drivers for other devices. All monitor lamp outputs are normally a steady state switch to ground. Various formats of discrete outputs can be provided as defined in Category 13.

6.4.1 GROUND PROXIMITY ALERTS DISCRETE (LAMP) OUTPUTS

Two Lamp formats are defined as a function of the selected I/O Discrete Type of section 5.3.13. For Lamp Format type 1, only Mode 5 “Glideslope” message will activate the alert lamp output (amber). All other messages will activate the warning lamp output (red). Note that Mode 6 does not activate any lamp outputs, only voices.

With Lamp Format 2, only the messages containing the phrase “Pull Up” will activate the warning lamp output (red). All other messages will activate the alert lamp output (amber).

The Glideslope Cancel Input Discrete controls the output of the Mode 5 “Glideslope” message. If the Glideslope Cancel Input Discrete is activated then the caution lamp (amber) and the voice annunciation will be inhibited for the Mode 5 “Glideslope” message.

6.4.2 AUDIO ON DISCRETE

The Audio On discrete goes true whenever any voice message is being enunciated. It will stay true until the voice is completed. This output can be used to inhibit other audio systems (e.g., TCAS) during EGPWS audio or used to drive the audio key line input provided on some aircraft audio systems.

6.4.3 MONITOR DISCRETES (GPWS, TERRAIN INOP & TERRAIN NOT AVAILABLE)

The EGPWC produces two discrete monitor outputs. These discretes reflect the GPWS INOP and Terrain INOP / Terrain Not Available functions. These discretes activate with loss of EGPWC power. The status of these two discretes are also contained on an ARINC 429 output word.

Note: Some display systems provide one message area for both warning and associated INOP annunciation. There are conditions where GPW INOP and a GPWS warning can exist at the same time (e.g., Sinkrate warning can occur even if a Ground Airspeed input fault exists.) For these installations a configuration item INOP & Warning Annunciation in Same Window is provided which causes the INOP annunciation to extinguish whenever a valid warning annunciation is required. Various formats of monitor outputs can be provided as defined in Category 13.



6.4.4 TERRAIN DISPLAY SWITCHING DISCRETES (WXR/EGPWS DISPLAY SELECT)

The EGPWC produces two discrete outputs for controlling the terrain display(s). They can be used either to control picture bus switching relay(s) or connected directly to the symbol generator(s).

6.4.5 GLIDESLOPE CANCEL DISCRETE

The Glideslope Cancel discrete is active whenever Glideslope Cancel has been selected and is typically used to drive a lamp in the Glideslope Cancel switch.

6.4.6 TERRAIN / OBSTACLE AWARENESS ALERT DISCRETES

Terrain Awareness provides discrete alert outputs for Terrain / Obstacle Cautions and Warnings. These outputs can drive cockpit lamps or act as discrete inputs to other aircraft systems.

6.4.6.1 TERRAIN / OBSTACLE CAUTION

Terrain and Obstacle Cautions can be configured to activate any of the discrete outputs. Depending on configuration, the Caution discretes will typically activate either the GPWS Warn Lamp, the GPSW Alert Lamp, or will drive their own output lamps.

6.4.6.2 TERRAIN / OBSTACLE WARNING

Terrain and Obstacle Warnings can be configured to activate any of the discrete outputs. Depending on configuration, the Warning discretes will typically activate either the GPWS Warn Lamp or will drive their own output lamps.

6.4.6.3 TERRAIN POP UP (HELICOPTER)

Terrain and Obstacle Caution and Warning are combined (or’ed), on one discrete to make a Terrain Pop Up indication for an integrated display system. For helicopters this Pop Up discrete is forced false regardless of caution or warning conditions as long as Timed Audio Inhibit Discrete is active (see Category 13). The Pop Up discrete can be used by a display system to differentiate between a manual selection or one due to a Terrain/Obstacle Caution or Warning event.

6.4.7 LOW ALTITUDE MODE DISCRETE (TACTICAL)

The Low Altitude Mode Discrete is active whenever the Low Altitude Mode has been selected in helicopters only. Low Altitude Mode is known as ‘Tactical Mode’ in the EM5/7 and is used by military aircraft types.

6.4.8 TCAS INHIBIT DISCRETE

For some installations, a dedicated discrete output is provided to inhibit TCAS resolution advisories. This output is activated whenever the EGPWS is in a Warning or Alert state. It is not activated during Altitude Awareness callouts.

6.4.9 TIMED AUDIO INHIBIT DISCRETE

The Timed Audio Inhibit discrete is active whenever the Timed Audio latch is active (selected) in helicopters only.



6.5 SYSTEM CONFIGURATION STATUS

The EGPWC indicates the current hardware, software, databases, Category states and input discretes detected by the system. Each configuration item has a configuration message associated with it. This message is the message that will be read out during Present Status on the RS-232 interface or voice output during Self Test Level 3 to inform the user of the current configuration. TABLE 6.5-1: CONFIGURATION OPTIONS AND MESSAGES Selected Option/Condition Configuration Message Category 1 (WOW Reversal Select) FLAP WOW REVERSAL SELECTED Category 1 (Bank Angle Enable) BANK ANGLE SELECTED Category 4 (Smart Callout Selected) SMART CALLOUT SELECTED Category 6 (TA&D Disable) TERRAIN AWARENESS DISABLED

TERRAIN CLEARANCE FLOOR DISABLED Category 6 (TA&D Alternate Pop Up) ALTERNATE POP UP SELECTED Category 7 (Obstacle Awareness Enabled) OBSTACLE AWARENESS ENABLED Category 7 (Peaks Mode Enabled) PEAKS MODE ENABLED Category 7 (WGS84 Reference Selected) GPS ALTITUDE REFERENCE WGS 84 SELECTED Category 7 (MSL Reference Selected) GPS ALTITUDE REFERENCE MSL SELECTED Glideslope Inhibit input discrete activated GLIDESLOPE INHIBITED Mode 6 Volume Control Discrete Selected (CVT Item M6LwVolDsc)

MODE 6 LOW VOLUME SELECTED

GND Audio Suppress(Inhibit)/All Modes Inhibit Discrete Selected OR +28 V Audio Suppress(Inhibit)/All Modes Inhibit Discrete Selected

EXTERNAL EGPWS INHIBITED Note: Will only occur for present status as this condition inhibits self tests

Terrain Awareness & TCF Inhibit input discrete activated TERRAIN AWARENESS AND TCF DISABLED GPWS Inhibit input discrete activated GPWS INHIBITED

Note: Will only occur for present status as this condition inhibits self tests.

Category 17 non-Helo Type (only ID #0 selectable) None Category 17 Helo type and Autorotation Option X (Where X = Callout Option selected via Category 17)

AUTOROTATION CALLOUT OPTION X SELECTED5

Category 17 Helo type and Normal Pop Up Range 5 NORMAL POP UP RANGE 5 SELECTED5 Category 17 Helo type and Normal Pop Up Range 10 NORMAL POP UP RANGE 10 SELECTED5 Category 17 Helo type and Low Altitude Pop Up Range 2.5 LOW ALTITUDE POP UP RANGE 2.5 SELECTED5 Category 17 Helo type and Low Altitude Pop Up Range 5 LOW ALTITUDE POP UP RANGE 5 SELECTED5 Category 17 Helo type and Low Altitude Pop Up Range 10 LOW ALTITUDE POP UP RANGE 10 SELECTED5 Category 17 Mode 6B Always ON Enable MODE 6B ALWAYS ON SELECTED5,6 Category 17 Normal Terrain Airspeed Select NORMAL TERRAIN WITH AIRSPEED SELECTED5,6 Category 17 Low Altitude Airspeed Select LOW ALTITUDE WITH AIRSPEED SELECTED5,6 Category 17 SAR Select SAR LOW ALTITUDE SELECTED5,8 Category 18 Helo type and Audio Inhibit Time X Minutes (Where X = Audio Inhibit Time selected via Category 18

AUDIO INHIBIT TIME X 6,7

Category 18 Helo type and Inhibit All except Minimums Type Callout and 100 Ft Callout Select

INHIBIT ALL EXCEPT MINIMUMS TYPE CALLOUT AND 100 CALLOUT SELECTED 6,7

Category 18 Helo type and Inhibit All except Minimums Type Callout Select

INHIBIT ALL EXCEPT MINIMUMS TYPE CALLOUT SELECTED 6,7

Category 18 Helo type and Inhibit Includes Too Low Gear Select

INHIBIT TOO LOW GEAR SELECTED 6,7

Category 18 Helo type and Inhibit Altitude Callouts 50 Ft and Below Over Runway Select

INHIBIT RUNWAY CALLOUTS 50 AND BELOW SELECTED 6,7

Category 18 Helo type and Lower MDA/DH Value Select ALTERNATE DECISION HEIGHT SELECTED 6,7 Category 19 Helo type and Low Altitude Option X (Where X = Low Altitude Option selected via Category 19)

LOW ALTITUDE OPTION X SELECTED9

Category 19 Helo type and Mode 2 Terrain Inhibit MODE 2 TERRAIN INHIBIT SELECTED9



5 When category 17 is invalid, these messages will not be given. 6 Added in –026 7 When category 18 is invalid, these messages will not be given 8 Option added in -026 and renamed in -030 9 Added in -030

6.5.1 SYSTEM STATUS MESSAGES

System Status Messages provide additional information beyond Internal and External Current Faults in order to help isolate the reason for certain EGPWC INOP situations. These messages will be read out during Present Status on the RS-232 interface or voice output during Self-Test Level 2. The table below defines the System Status Messages.

TABLE 6.5.1-1: EGPWC SYSTEM STATUS MESSAGES

System Level Event Internal Indications System Status Message Bank Angle INOP BAINOP TRUE Bank Angle INOP Tail Strike INOP TSINOP TRUE Tail Too Low INOP Mode 1 INOP M1INOP TRUE Mode 1 INOP Mode 2 INOP M2INOP TRUE Mode 2 INOP Mode 3 INOP M3INOP TRUE Mode 3 INOP Mode 4 INOP M4INOP TRUE Mode 4 INOP Mode 5 INOP M5GPWINOP TRUE Mode 5 INOP Mode 6 INOP M6INOP TRUE Mode 6 INOP

TAD Deselected1 Latitude Invalid Terrain Awareness – No Valid Latitude

Longitude Invalid Terrain Awareness - No Valid Longitude True Heading Invalid Terrain Awareness - No Valid True Heading Corrected Altitude Invalid Terrain Awareness - No Valid Corrected Altitude Barometric Altitude Rate Invalid Terrain Awareness - No Valid Altitude Rate Roll Invalid Terrain Awareness - No Valid Roll Wx Mode 1 Invalid Terrain Awareness - Display Mode 1 Invalid Wx Mode 2 Invalid Terrain Awareness - Display Mode 2 Invalid Range 1 Invalid Terrain Awareness - Range 1 Invalid Range 2 Invalid Terrain Awareness - Range 2 Invalid Runway Distance invalid Terrain Awareness - No Valid Runway Obstacle Database Invalid Terrain Awareness: No Valid Obstacle

Terrain Awareness INOP2 TAINOP TRUE Terrain Awareness INOP

Terrain Not Available2 TAD Position Error AND TAINOP FALSE Terrain Awareness – Position Error

Outside Regional Database TRUE Terrain Awareness – Outside Regional Terrain Database

1 The following preconditions apply: a) The signal must not be faulted since if faulted, signal fault message will exist, b) TAD/TCF Inhibit Discrete is NOT selected, c) TAD Disable program pin is NOT selected, d) The signal condition must NOT be masked via the configuration database and both On-Ground and In-Air masks must be taken into account, e) The associated input signal must exist for the current aircraft configuration. 2 TAD INOP Preconditions: a) TAD/TCF Inhibit Discrete NOT selected, and b) TAD Disable configuration NOT selected.



7.0 CONNECTOR INTERFACE

7.1 PINOUT FOR FRONT CONNECTORS SORTED BY PIN NUMBER

TABLE 7.1: PIN ASSIGNMENT FOR FRONT CONNECTORS SORTED BY PIN NUMBER Connector

Pin Channel

Designation Reference

Signal Usage Summary*

J1-01 SYN_1X Roll Attitude Synchro (X leg) J1-02 SYN_1Z Roll Attitude Synchro (Z leg) J1-03 SYN_2Z Magnetic Heading Synchro (Z leg) J1-04 26REF_1H 26VAC Reference #1 (H) J1-05 SYN_3X Pitch Synchro (X leg) J1-06 SYN_3Z Pitch Synchro (Z leg) J1-07 SYN_3Y Pitch Synchro (Y leg) J1-08 28V_DISC_09 Autopilot Engaged Discrete (+28VDC) J1-09 28V_DISC_08 Barometric Altitude Validity Discrete (+28VDC) J1-10 GS_VAL_L Glideslope Deviation Low Level Validity (-) or Localizer Deviation - Low Level (+ left)J1-11 28V_DISC_06 Glideslope Validity Discrete (+28VDC) J1-12 GND_DISC_09 Terrain Awareness and TCF Inhibit Discrete (Ground) J1-13 GND_DISC_08 Mode 6 Low Volume Discrete (Ground) J1-14 GND_DISC_07 Flap Override Discrete (Ground) J1-15 GND_DISC_06 Glideslope Cancel Discrete (Ground) J1-16 GND_DISC_05 Landing Gear Discrete (Ground) J1-17 GND_DISC_04 Audio Inhibit Discrete (Ground) or Timed Audio Inhibit Discrete J1-18 GND_DISC_03 Landing Flaps Discrete (Ground) or Weight On Wheels (Ground) Discrete J1-19 GND_DISC_02 Glideslope Inhibit Discrete (Ground) J1-20 GND_DISC_01 ILS Tuned Discrete (Ground) J1-21 SYN_1Y Roll Attitude Synchro (Y leg) J1-22 SYN_2X Magnetic Heading Synchro (X leg) J1-23 SYN_2Y Magnetic Heading Synchro (Y leg) J1-24 26REF_1L 26VAC Reference #1 (L) J1-25 OAT_REF Air Temperature Reference (+5VDC) J1-26 TORQUE_1H Engine Torque #1 (+) J1-27 TORQUE_1L Engine Torque #1 (-) J1-28 28V_DISC_10 Magnetic Heading Validity Discrete (+28VDC) J1-29 28V_DISC_07 Radio Altitude Validity Discrete (+28VDC) J1-30 GS_VAL_H Glideslope Deviation Low Level Validity (+) or Localizer Deviation - Low Level (+ right) J1-31 GND_DISC_13 Display Selected Discrete #2 (Ground) J1-32 GND_DISC_12 Display Selected Discrete #1 (Ground) J1-33 GND_DISC_11 DH Discrete (Ground) J1-34 GND_DISC_10 Self Test Discrete (Ground) J1-35 28V_DISC_05 Landing Gear Discrete (+28VDC) J1-36 28V_DISC_04 Audio Inhibit Discrete (+28VDC) J1-37 28V_DISC_03 Landing Flaps Discrete (+28VDC) or Weight On Wheels (+28V) Discrete J1-38 28V_DISC_02 Glideslope Inhibit Discrete (+28VDC) J1-39 28V_DISC_01 ILS 1 Tuned Discrete (+28VDC) J1-40 PWR_H Power Input: 28 VDC (+) J1-41 PWR_L Power Input: 28 VDC (return) J1-42 GND Chassis Ground J1-43 ALT_L Barometric Altitude (-) J1-44 OAT_L Air Temperature (-) J1-45 RALT_L Radio Altitude: ARINC 552 or ALT 55 (-)



Connector Pin

Channel Designation Reference


J1-46 GSDEV_L Glideslope Deviation - Low Level (+ down) J1-47 TORQUE_2L Engine Torque #2 (-) J1-48 28V_DISC_11 Localizer Validity Discrete (+28VDC) J1-49 DISC_OUT_9 Terrain Select Relay Output #2 J1-50 MON_OUT_3 Spare Lamp Output (monitor) J1-51 DISC_OUT_8 Spare Lamp Output J1-52 DISC_OUT_7 Timed Audio Inhibit J1-53 GND Temperature Probe GND J1-54 DISC_OUT_6 Terrain Select Relay Output #1 J1-55 MON_OUT_2 TAD / TCF INOP Output (monitor) J1-56 453TX_2A Terrain Display Output Data #2 (A leg) J1-57 453TX_2B Terrain Display Output Data #2 (B leg) J1-58 453TX_1A Terrain Display Output Data #1 (A leg) J1-59 453TX_1B Terrain Display Output Data #1 (B leg) J1-60 PWR_H Power Input: 28 VDC (+) J1-61 PWR_L Power Input: 28 VDC (return) J1-62 ALT_H Barometric Altitude (+) J1-63 OAT_H Air Temperature (+) J1-64 RALT_H Radio Altitude: ARINC 552 or ALT 55 (+) J1-65 GSDEV_H Glideslope Deviation - Low Level (+ up) J1-66 TORQUE_2H Engine Torque #2 (+) J1-67 GND_DISC_14 GPWS Inhibit (GND) Discrete J1-68 28V_DISC_12 +28VDC Attitude Validity Discrete J1-69 DISC_OUT_5 Audio On (GND) Output or TCAS Inhibit Discrete (GND) Output J1-70 AUD_HL_H High Level Audio Output - 8 (+) J1-71 AUD_HL_L High Level Audio Output - 8 (-) J1-72 MON_OUT_1 GPWS INOP Output (monitor) J1-73 DISC_OUT_4 Spare Lamp Output J1-74 AUD_LL_L Low Level Audio Output – 600 (-) J1-75 AUD_LL_H Low Level Audio Output - 600 (+) J1-76 DISC_OUT_3 Glideslope Cancel Output J1-77 DISC_OUT_2 Glideslope Alert Output J1-78 DISC_OUT_1 GPWS Warning Output

J2-01 SYN_4X Configurable Synchro #1 (X leg) J2-02 SYN_4Y Configurable Synchro #1 (Y leg) J2-03 SYN_5Z Configurable Synchro #2 (Z leg) J2-04 429RX_5B Radio Altitude ARINC 429 Input (B leg) J2-05 429RX_6B ILS ARINC 429 Input (B leg) J2-06 429RX_7B Magnetic Heading/Roll ARINC 429 Input (B leg) J2-07 429RX_8B Spare ARINC 429 Input (B leg) J2-08 429RX_4B GPS ARINC 429 Input (B leg) J2-09 429TX_2B EGPWS ARINC 429 Output #2 (B leg) J2-10 422_232RX_2B Alt Display Range #2 or ADC RS-232 / 422 Input (B leg) J2-11 422_232RX_2A Alt Display Range #2 or ADC RS-232 / 422 Input (A leg) J2-12 GPS_RXB GPS RS-232 / 422 Input (B leg) J2-13 GPS_429_OUT_B Spare ARINC 429 output (B leg) J2-14 GND ADC RS-232 Common J2-15 28V_DISC_13 Spare Discrete Input J2-16 GND Configuration Module Power Return (Ground) J2-17 SC_PWR Configuration Module Power (+5VDC) J2-18 SYN_4Z Configurable Synchro #1 (Z leg) J2-19 SYN_5X Configurable Synchro #2 (X leg) J2-20 SYN_5Y Configurable Synchro #2 (Y leg) J2-21 429RX_5A Radio Altitude ARINC 429 Input (A leg)



Connector Pin

Channel Designation Reference


J2-22 429RX_6A ILS ARINC 429 Input (A leg) J2-23 429RX_7A Magnetic Heading/Roll ARINC 429 Input (A leg) J2-24 429RX_8A Spare ARINC 429 Input (A leg) J2-25 429RX_4A GPS ARINC 429 Input (A leg) J2-26 429TX_2A EGPWS ARINC 429 Output #2 (A leg) J2-27 422_232TX_2A ADC RS-232 / 422 Output (A leg) J2-28 GND GPS / ADC RS-232 / 422 Common J2-29 GPS_RXA GPS RS-232 / 422 Input (A leg) J2-30 GPS_429_OUT_A Spare ARINC 429 output (A leg) J2-31 GND_DISC_15 Spare Discrete Input J2-32 SPICLK Configuration Module Serial Clock J2-33 SPIMISO Configuration Module Serial Input J2-34 26REF_2H 26VAC Reference #2 (H) J2-35 26REF_2L 26VAC Reference #2 (L)

J2-36

429_422RX_1B Display Range #1 ARINC 429 (B leg) RS-422 Input (B leg)

J2-37

429_422RX_1A Display Range #1 ARINC 429 (A leg) RS-422 Input (A leg)

J2-38 429RX_2B Air Data ARINC 429 Input (B leg) J2-39 429RX_2A Air Data ARINC 429 Input (A leg) J2-40 429RX_3B Display Range #2 ARINC 429 Input (B leg) J2-41 429RX_3A Display Range #2 ARINC 429 Input (A leg) J2-42 429TX_1B EGPWS ARINC 429 Output #1 (B leg) J2-43 429TX_1A EGPWS ARINC 429 Output #1 (A leg) J2-44 422_232TX_2B ADC RS-232 / 422 Output (B leg) J2-45 GPS_TXA GPS RS-232 / 422 Output (A leg) J2-46 GPS_TXB GPS RS-232 / 422 Output (B leg) J2-47 J2-48 J2-49 SPISEL_CM# Configuration Module Serial Select J2-50 SPIMOSI Configuration Module Serial Output

J3-01 GND SmartCable Power Return (Ground) J3-02 CARD_PRES# PCMCIA Card Present J3-03 RS232RXD_MON EGPWS Monitor Port (RS232 Receive) J3-04 RS232TXD_MON EGPWS Monitor Port (RS232 Transmit) J3-05 Reserved J3-06 SC_PWR SmartCable Power (+5VDC) J3-07 SPICLK SmartCable Serial Clock J3-08 SPIMISO SmartCable Serial Input J3-09 SPIMOSI SmartCable Serial Output J3-10 SPISEL_SC# SmartCable Serial Select J3-11 GSE_PRES# GSE Present J3-12 GND Ground J3-13 GND Ground J3-14 GND Ground J3-15 Reserved

GPS ANT COAX GPS COAX connection



Figure 7.1-1: Front Panel Connector Orientation - J1, J2, J3, GPS ANT



Figure 7.1-2, Connector Pin References - J1, J2, J3



8.0 DEFINITIONS

The following acronyms are provided for use with this document:

Acronym Interpretation AAAS Alternate Audio Alert Select ADC Air Data Computer ADS Air Data System AGL Above Ground Level AHRS Attitude Heading Reference System AIC Analog Input Controller AIMS Airplane Information Management System AOA Angle of Attack ASA AlliedSignal Aerospace ASL Above Sea Level ATP Acceptance Test Procedure BCD Binary Coded Decimal BIST Built in Self Test BIT Built In Test BITE Built In Test Equipment BNR Binary BOSS Batch Oriented Simulation System C/O Callouts CAA Civil Aviation Authority CAIMS Central Aircraft Information/Maintenance System CFDS Centralized Fault Display System CFIT Controlled Flight Into Terrain CFM Cubic Feet per Minute CISRD CFDS Interface System Requirements Document CMC Central Maintenance Computer COTS Commercial Off the Shelf CP Control Panel CRS Course CW Clockwise DAA Digital/Analog Adapter DADC Digital Air Data Computer DAU Data Acquisition Unit DC Digital Command DDM Difference in Depth of Modulation DEVN Deviation DH Decision Height DITS Digital Information Transfer System DME Distance Measuring Equipment DO Discrete Output DSP Digital Signal Processor DSU Display Switching Unit DSWC Digital Stall Warning Computer EEPROM Electrically Erasable Programmable Read Only Memory EFCP EFIS Control Panel EFIS Electronic Flight Instrument System EGPWC Enhanced Ground Proximity Warning Computer EGPWD Enhanced Ground Proximity Warning Display EGPWS Enhanced Ground Proximity Warning System EICAS Engine Indication and Crew Alert System EMI Electromagnetic Interference ENB Enabled EPROM Erasable Programmable Read Only Memory F/T Functional Test



Acronym Interpretation F/W Fail/Warning F/W Fail/Warning FAA Federal Aviation Administration FCC Flight Control Computer FDR Flight Data Recorder FIAS Flight Inspection Aircraft System FMC Flight Management Computer FMS Flight Management System FPM Feet per Minute FSEU Flaps/Slats Electronic Unit FWC Fault Warning Computer G/S Glideslope GMT Greenwich Mean Time GPS Global Position System GPW Ground Proximity Warning GPWS Ground Proximity Warning System GT Greater Than H/W Hardware HDG Heading HDOP Horizontal Dilution of Position HSID Hardware/Software Interface Document I/O Input/Output IAC Integrated Avionics Computer ICD Interface Control Document ILS Instrument Landing System INOP Inoperative IOC Input/Output Concentrator IRS Inertial Reference System ISO International Standards Organization IVS Inertial Vertical Speed KT Knots KTS Knots LED Light Emitting Diode LRRA Low Range Radio Altimeter LRU Line Replaceable Unit LSB Least Significant Bit LT Less Than MCP Mode Control Panel MDA Minimum Barometric Altitude MFD Multi-Functional Display MKII Mark Two Warning Computer MKV Mark Five Warning Computer MKVI Mark Six Warning Computer MKVII Mark Seven Warning Computer MKVIII Mark Eight Warning Computer MKXXII Mark Twenty Two Warning Computer MLS Microwave Landing System MMU Memory Management Unit MSB Most Significant Bit N/A Not Applicable NCD No Computed Data ND Navigation Display NVM Non Volatile Memory OMS Onboard Maintenance System P/N Part Number PAR Parity PC Personal Computer



Acronym Interpretation PCMCIA Personal Computer Memory Card Industry Association PFD Primary Flight Display PMAT Portable Maintenance Access Terminal PP Program Pin PVM Processor/Voice/Memory PWS Predictive Windshear System QFE Corrected Baro Alt relative to field elevation QNH Corrected Baro Alt relative to sea level RA Radio Altitude RAM Random Access Memory RDOP Radar Display Output Processing ROM Read Only Memory RTCA Requirements and Technical Concepts for Aviation RTS Ready to Transmit Signal RWY Runway S/T Self Test S/W Software SDI Source/Destination Identifier SDRD Software Design Requirements Document SIG Significant SPC Stall Protection Computer SRD System Requirements Document SSM Sign Status Matrix ST Self Test SWC Stall Warning Computer TA&D Terrain Awareness & Display TACAN Tactical Air Navigation TAD Terrain Awareness Display TBD To Be Determined TCAS Traffic Collision Avoidance System TCF Terrain Clearance Floor TERPS United States’ Standards for Terminal Instrument Procedures TK Track TLB Translation Lookaside Buffer TSO Technical Standing Order TTL Tuned To Localizer UART Universal Asynchronous Receiver Transmitter USM Unsigned Magnitude UTC Universal Time Correlation UUT Unit Under Test VDC Volts, DC VDOP Vertical Dilution of Precision VHF Very High Frequency VLSI Very Large Scale Integrated Circuit VOR VHF Omni-directional Range W/S Windshear WC Warning Computer WX Weather

MK XXII - Honeywell MK XXII EGPWS Installation Manual CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO:...

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Transcript of MK XXII - Honeywell MK XXII EGPWS Installation Manual CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO:...