Honeywell MK XXII, MK VI, MK VII, MK V, MK VIII User Manual

4.6 (13)

EGPWS LINE MAINTENANCE MANUAL

MK V

MK VI

MK VII

MK VIII

MK XXII

Enhanced Ground Proximity Warning Systems

Line Maintenance Manual

Document No: 060-4199-180, Rev G

Release date: 29 Mar 2010

Honeywell International, Inc.

Redmond, Washington 98073-9701

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This document is an unpublished work.

Copyright 2005, 2010 Honeywell International, Inc.

All rights reserved.

This document and all information and expression contained herein are the property of Honeywell 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 signatures constitute approval. Actual Signatures are on file at Honeywell in Redmond, WA.

DRAWN

R. Halbert

23 FEB 00

 

 

 

CHECK

 

 

 

 

 

ENGR

R. Halbert

23 FEB 00

 

 

 

MFG

 

 

 

 

 

QA

 

 

 

 

 

APVD

G. Gilliland

23 FEB 00

 

 

 

APVD

 

 

 

 

 

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REVISIONS

SHT

REV

DESCRIPTION

All

 

Initial release.

 

 

Reason 01 Severity 10

 

 

 

All

A

Direct update:

 

 

Incorporate –008 changes

 

 

Reason 01 Severity 10

All

B

Direct update to incorporate EGPWC/GNSSU part numbers

 

 

and troubleshooting information. Revised Level 2

 

 

descriptions.

 

 

Reason 01 Severity 10

 

 

 

All

C

Direct update to incorporate Airbus and Boeing part number

 

 

changes, Revised Flight History Download Card P/Ns,

 

 

reformatted TOC and added the following RAAS-related

 

 

sections:

(1)Section 2.2.15

(2)“Application Software Version Invalid” and “RCD Failed” (MK V/VII) aural annunciations to Table 3-2.

(3)Sections 3.8.42 and 3.8.43

(4)Appendix C

 

 

Reason 01 Severity 10

All

D

1) Deleted “Revisions Status of Sheets Index” table on

 

 

Sheet 3.

2)Section 3.2 (Troubleshooting Guide): Added the statement “(this sentence does not apply to internal GPS engines)” after the existing sentence “If no faults are present, verify that position data from the GPS, IRS, or FMC is correct”.

3)Section 6.1.2 (Installation): Added step 6 to account for RAAS equipped EGPWC units.

4)Appendix C:

-Revised Table B1-1 to C1-1.

-Revised Table B1-2 to C1-2.

-Table C1-2: Added note that “Operators/Installers must refer to their Instructions for Continued Airworthiness (ICA) documentation to identify the approved RCD configurations specific to their aircraft type/model having RAAS installed”.

Reason 01 Severity 10

 

DATE

APPROVED

23 FEB 00

R. Halbert

23 FEB 00

G. Gilliland

 

 

07 AUG 01

R. Henderson

07

AUG 01

L. Matter

 

 

13 FEB 02

B. Breen

13

FEB 02

G. Gilliland

08 JAN 04

J. Castro

09 JAN 04

L. Matter

27 SEP 04

K. Christofferson

30 SEP 04

S. Wright

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REVISIONS

SHT

REV

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All

E

Section 3.3.2 – added RAAS maintenance message to short

 

 

Level 1 Self-Test sequence and two notes, one to ensure

 

 

RAAS messages only occur if RAAS is activated and one to

 

 

explain the GPS NOT NAVIGATING enunciation.

 

 

Section 3.5 - added note to ensure RAAS message only

 

 

occurs if RAAS is activated.

 

 

Section 6.1.2 – modified step 6 to add Level 3 Self-Test.

 

 

Reason 01 Severity 10

All

F

Updated per ECO-65820

 

 

Updated document to include MK XXII helicopter EGPWS

 

 

and to include software -230-230 changes for RAAS and

 

 

newly introduced optional functions for Stabilized Approach

 

 

Monitor, Long Landing Monitor, Altimeter Monitor, and

 

 

Takeoff Flap Configuration Monitor.

 

 

EFF PT: 10

All

G

Updated per ECO-87380

 

 

Updated document to include software -232-232 changes

 

 

for newly introduced function (Low Airspeed Monitor).

 

 

EFF PT: 14A DISP: USE

 

 

 

DATE

APPROVED

01 FEB 05

S. Wright

03 FEB 05

K. Christofferson

23 JUN 09

J. Mulkins

 

See AeroPDM

 

for additional

 

approvals

29 MAR 10

J. Mulkins

 

See AeroPDM

 

for additional

 

approvals

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TABLE OF CONTENTS

1

INTRODUCTION.....................................................................................................................................................

8

1.1

SCOPE......................................................................................................................................................................

8

1.2

APPLICABILITY ...........................................................................................................................................................

8

1.3

REFERENCE DOCUMENTS ..........................................................................................................................................

9

2 DESCRIPTION AND OPERATION ......................................................................................................................

10

2.1 GENERAL SYSTEM DESCRIPTION..............................................................................................................................

10

2.1.1

Enhanced Ground Proximity Warning Computer (EGPWC).....................................................................

11

2.2 OPERATION.............................................................................................................................................................

11

2.2.1

Mode 1 – Excessive Descent Rate ...........................................................................................................

11

2.2.2

Mode 2A/2B - Terrain Closure Rate..........................................................................................................

11

2.2.3

Mode 3 - Descent After Takeoff ................................................................................................................

11

2.2.4

Mode 4A/4B/4C - Unsafe Terrain Clearance ............................................................................................

11

2.2.5

Mode 5 - Descent Below Glideslope .........................................................................................................

12

2.2.6

Mode 6 - Advisory Callouts (optional) .......................................................................................................

12

2.2.7

Mode 7 - Windshear Detection (Optional for MK V/VII only).....................................................................

14

2.2.8

Envelope Modulation (not available in MK VI/VIII -001)............................................................................

14

2.2.9

Terrain Clearance Floor and Runway Field Clearance Floor ...................................................................

14

2.2.10

Terrain Alerting and Display (optional)......................................................................................................

15

2.2.11

Peaks Display Mode (optional)..................................................................................................................

16

2.2.12

Geometric Altitude (GPS Required) ..........................................................................................................

16

2.2.13

Weather Radar AutoTilt (MK V and MK VII only) ......................................................................................

16

2.2.14

System Display and Annunciation.............................................................................................................

17

2.2.15

Runway Awareness and Advisory System (option for MK V and MK VII only).........................................

17

2.2.16

Stabilized Approach Monitor (option for MK V and MK VII only) ..............................................................

17

2.2.17

Altimeter Monitor (option for MK V and MK VII only) ................................................................................

17

2.2.18

Takeoff Flap Configuration Monitor (option for MK V and MK VII only) ....................................................

18

2.2.19

Long Landing Monitor (option for MK V and MK VII only).........................................................................

18

2.2.20

Low Airspeed Monitor (MK V Boeing 737NG only)...................................................................................

18

2.2.21

Lamp Format .............................................................................................................................................

19

2.3 SYSTEM MAINTENANCE............................................................................................................................................

20

2.3.1

Maintenance Philosophy ...........................................................................................................................

20

2.3.2

System Operation During an Inop Condition.............................................................................................

20

2.3.3

BIT Description ..........................................................................................................................................

20

2.3.4

EGPWC Front Panel .................................................................................................................................

21

2.3.5

Self-Test Functions....................................................................................................................................

22

3

FAULT ISOLATION (TROUBLESHOOTING) .....................................................................................................

23

3.1

GENERAL ................................................................................................................................................................

23

3.2

TROUBLESHOOTING GUIDE ......................................................................................................................................

23

3.3

LEVEL 1 SELF-TEST - GO/NO GO TEST ....................................................................................................................

24

3.3.1

Self-Test Preamble....................................................................................................................................

24

3.3.2 Short Level 1 Self-Test..............................................................................................................................

25

3.3.3 Long Level 1 Self-Test...............................................................................................................................

26

3.4

LEVEL 2 SELF-TEST - CURRENT FAULTS...................................................................................................................

26

3.4.1

Current Faults - Internal ............................................................................................................................

27

3.4.2

Current Faults - External ...........................................................................................................................

27

3.5

LEVEL 3 SELF-TEST - SYSTEM CONFIGURATION........................................................................................................

33

3.6

LEVEL 4 SELF-TEST - FAULT HISTORY ......................................................................................................................

36

3.7

LEVEL 5 SELF-TEST - ALERT HISTORY......................................................................................................................

37

3.8

LEVEL 6 SELF-TEST - DISCRETE INPUT TEST ............................................................................................................

37

3.8.1

ARINC 552 / ALT 55 Radio Altitude Validity Flag Discretes .....................................................................

 

38

3.8.2

GND Landing Gear Discrete .....................................................................................................................

 

38

 

 

 

 

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3.8.3

+28V Landing Gear Discrete .....................................................................................................................

 

38

 

3.8.4

GND Landing Flap Discrete or Flap Override ...........................................................................................

 

39

 

3.8.5

+28V Landing Flap or Flap Override Discrete ...........................................................................................

 

39

 

3.8.6

Flap Position Discretes ..............................................................................................................................

 

40

 

3.8.7

Self - Test Discrete ......................................................................................................................................

 

40

 

3.8.8

Steep Approach Discretes .........................................................................................................................

 

40

 

3.8.9

GND ILS Tuned Discrete ...........................................................................................................................

 

41

 

3.8.10

+28V ILS Tuned Discrete ..........................................................................................................................

 

41

 

3.8.11

Glideslope Validity Discretes .....................................................................................................................

 

41

 

3.8.12

GND Glideslope Inhibit Discrete ................................................................................................................

 

42

 

3.8.13

+28 V Glideslope Inhibit Discrete ..............................................................................................................

 

42

 

3.8.14

GND Glideslope Cancel Discrete ..............................................................................................................

 

42

 

3.8.15

Decision Height Discrete ...........................................................................................................................

 

42

 

3.8.16

Mode 6 Volume Control Discrete ..............................................................................................................

 

43

 

3.8.17

Callouts Enable Discrete (MK V and MK VII only) ....................................................................................

 

43

 

3.8.18

GND Audio Suppress(Inhibit)/All Modes Inhibit Discrete ..........................................................................

 

43

 

3.8.19

+28 V Audio Suppress(Inhibit)/All Modes Inhibit Discrete .........................................................................

 

43

 

3.8.20

AOA Validity Discretes (MK V and MK VII only) .......................................................................................

 

44

 

3.8.21

Display Select Discretes ............................................................................................................................

 

44

 

3.8.22

Terrain Awareness & TCF Inhibit ..............................................................................................................

 

44

 

3.8.23

Simulator Reposition (MK V and MK VII only) ..........................................................................................

 

44

 

3.8.24

Weather Radar On/Off ...............................................................................................................................

 

45

 

3.8.25

Localizer Validity Discretes (MK V and MK VII only) .................................................................................

 

45

 

3.8.26

Attitude Validity Discretes ..........................................................................................................................

 

45

 

3.8.27

Airspeed Validity Discrete .........................................................................................................................

 

45

 

3.8.28

Barometric Altitude Rate Validity Discretes ...............................................................................................

 

46

 

3.8.29

Acceleration Self - Test In Progress Discrete .............................................................................................

 

46

 

3.8.30

Longitudinal Acceleration Validity Discrete ...............................................................................................

 

46

 

3.8.31

.......................................................................................................................................................................

 

 

46

 

3.8.32 .......................................................................................................

Normal Acceleration Validity Discrete

 

46

 

3.8.33 ...........................................................................................................

Magnetic Heading Validity Discrete

 

47

 

3.8.34 .......................................................................................................................

AOA Vane Heater Discrete

 

47

 

3.8.35 ............................................................................

PLI Deselect Switch Discretes (MK V and MK VII only)

 

47

 

3.8.36 ..................................................................................................................

Autopilot Disconnect Discretes

 

47

 

3.8.37 .............................................................................................................................

Tactical Select Discrete

 

48

 

3.8.38 ................................................................................................................................

Altitude Alert Discrete

 

48

 

3.8.39 ........................................................................................

Corrected Barometric Altitude Validity Discrete

 

48

 

3.8.40 ...........................................................................................................

Momentary Flap Override Discrete

 

48

 

3.8.41 ......................................................................................................................

Weight On Wheels Discrete

 

49

 

3.8.42 ...............................................................................................................................

GPWS Inhibit Discrete

 

49

 

3.8.43 ....................................................................................

RAAS EnABLE Discrete (MK V and MK VII Only)

 

49

 

3.8.44 ........................................................................................

RAAS Inhibit Discrete (MK V and MK VII Only)

 

49

 

3.8.45 ...................................................

Stabilized Approach Monitor Enable Discrete (MK V and MK VII Only)

 

50

 

3.8.46 .....................................................

Stabilized Approach Monitor Inhibit Discrete (MK V and MK VII Only)

 

50

 

3.8.47 ..................................................................

Low Airspeed Monitor Inhibit Discrete (MK V – 737NG Only)

 

50

4

MAINTENANCE ..............................................................................................................................PRACTICES

 

51

4.1 GENERAL ................................................................................................................................................................

 

 

51

4.2 DATABASE .................................................................................................................................................UPDATE

 

 

51

 

4.2.1 ....................................................................................................................

Database Update Frequency

 

51

 

4.2.2 ..................................................................................................................................

Loading a Database

 

51

4.3 FLIGHT ..............................................................................................................................HISTORY DOWNLOADING

 

52

 

4.3.1 ...............................................................................

Obtaining an EGPWS Flight History Download Card

 

52

 

4.3.2 .................................................................................................................................

Download Procedure

 

52

 

4.3.3 ............................................................................................................

Transcription of the PCMCIA Card

 

53

4.4 PROGRAMMING ........................................................THE CONFIGURATION MODULE (MK VI, MK VIII, MK XXII ONLY)

 

54

 

4.4.1 ...................................................

Configuration Module Reprogramming (MK VI, MK VIII, MK XXII only)

 

55

5

SERVICING ..........................................................................................................................................................

 

 

57

 

 

 

 

 

 

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5.1

GENERAL ................................................................................................................................................................

57

6

REMOVAL/INSTALLATION.................................................................................................................................

57

6.1

EGPWC.................................................................................................................................................................

57

6.1.1

Removal .....................................................................................................................................................

57

6.1.2

Installation .................................................................................................................................................

57

6.2

CONFIGURATION MODULE (MK VI, MK VIII, AND MK XXII ONLY) ...............................................................................

57

6.2.1

Removal .....................................................................................................................................................

57

6.2.2

Installation .................................................................................................................................................

57

6.3

DISPLAY SWITCHING RELAYS (IF INSTALLED).............................................................................................................

58

6.3.1

Removal .....................................................................................................................................................

58

6.3.2

Installation .................................................................................................................................................

58

7

ADJUSTMENT/TEST ...........................................................................................................................................

58

7.1

ADJUSTMENT ..........................................................................................................................................................

58

7.2

TEST

.......................................................................................................................................................................

58

7.2.1 ..............................................................................................................................

EGPWS Ground Tests

58

8

INSPECTION/CHECK ..........................................................................................................................................

59

8.1

GENERAL ................................................................................................................................................................

59

9

CLEANING/PAINTING .........................................................................................................................................

59

9.1

GENERAL ................................................................................................................................................................

59

10

REPAIRS ..............................................................................................................................................................

59

10.1 ........................................................................................................................................................

G ENERAL

59

11

APPENDIX ...................................................................................................................................A: WINVIEWS

60

12

APPENDIX ............................................................................B: TROUBLESHOOTING DO’S AND DO NOT’S

61

13

APPENDIX .................................................C: RAAS MAINTENANCE MESSAGES (AURAL & DISPLAYED)

62

14

APPENDIX .......................................D: STABILIZED APPROACH MONITOR MAINTENANCE MESSAGES

64

15

APPENDIX ..............................................................E: ALTIMETER MONITOR MAINTENANCE MESSAGES

65

16

APPENDIX ........................F: TAKEOFF FLAP CONFIGURATION MONITOR MAINTENANCE MESSAGES

66

17

APPENDIX ......................................................G: LONG LANDING MONITOR MAINTENANCE MESSAGES

67

18

APPENDIX ......................................................H: LOW AIRSPEED MONITOR MAINTENANCE MESSAGES

68

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EGPWS LINE MAINTENANCE MANUAL

1 INTRODUCTION

1.1 SCOPE

This document provides information about the Enhanced Ground Proximity Warning System (EGPWS) with respect to Line Maintenance Operations. This includes Description and Operation, Troubleshooting, Removal and Installation, Adjustment and Test, and other related information. It is intended that the information in this document be combined with detailed aircraft installation documentation for operator specific line maintenance procedures.

1.2 APPLICABILITY

This manual is applicable to the MK V, MK VI, MK VII, MK VIII, and MK XXII EGPWS with the following part numbers and general description:

MK V EGPWC PART NUMBERS

MK VII EGPWC PART NUMBERS

 

 

 

 

965-0976-003-XXX-XXX

115 VAC, -40° to +70°

965-1076-001-XXX-XXX

115 VAC, -40° to +70°

 

 

 

 

965-0976-020-XXX-XXX

115 VAC, Internal 8 channel

965-1076-020-XXX-XXX

115 VAC, Internal 8 channel

GPS, -40° to +70°

GPS, -40° to +70°

 

 

 

 

 

 

965-0976-040-XXX-XXX

28 VDC, -55° to +70°

965-1076-030-XXX-XXX

28 VDC, Internal 8 channel

GPS, 55° to +70°

 

 

 

 

 

 

 

965-0976-060-XXX-XXX

115 VAC, Integral GNSSU,

965-1076-040-XXX-XXX

28 VDC, -55° to +70°

-40° to +70°

 

 

 

 

 

 

 

965-1676-XXX (Airbus P/N)

115 VAC, -40° to +70°

965-1076-060-XXX-XXX

115 VAC, Integral GNSSU,

-40° to +70°

 

 

 

 

 

 

 

965-1690-XXX (Boeing P/N)

115 VAC, -40° to +70°

 

 

 

 

 

 

MK VI EGPWC PART NUMBERS

MK VIII EGPWC PART NUMBERS

MK XXII EGPWC PART NUMBERS

 

 

 

 

 

 

 

 

965-1176-XXX

28

VDC, -55° to +70°

965-1206-XXX

28

VDC, -55° to +70°

965-1590-XXX

28 VDC, Internal 8 channel

GPS, -55° to +70°

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

28

VDC, Internal 8 channel

 

28

VDC, Internal 8 channel

 

28 VDC, Improved CPU,

965-1186-XXX

965-1216-XXX

965-1595-XXX

Internal 8 channel GPS,

 

GPS, -55° to +70°

 

GPS, -55° to +70°

 

-55° to +70°

 

 

 

 

 

 

 

965-1180-XXX

28

VDC, Improved CPU,

965-1210-XXX

28

VDC, Improved CPU,

 

 

 

-55° to +70°

 

-55° to +70°

 

 

 

 

 

 

 

 

 

28 VDC, Improved CPU,

 

28 VDC, Improved CPU,

 

 

965-1190-XXX

Internal 8 channel GPS,

965-1220-XXX

Internal 8 channel GPS,

 

 

 

-55° to +70°

 

-55° to +70°

 

 

 

 

 

TABLE 1-1 EGPWC Part Numbers

 

 

NOTE: X’s represent variable values defining a specific application and configuration software version (i.e., -230-230 for MK V/VII or -011 for MK VI/VIII/XXII original model or -026 for MK VI/VIII/XXII with improved CPU).

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MK V & MK VII EGPWC (left) and MK VI, MK VIII, MK XXII EGPWC (right)

Figure 1-1 - Enhanced Ground Proximity Warning Computers

1.3 REFERENCE DOCUMENTS

The following documents are identified as additional EGPWS references:

MK V and MK VII:

965-0976-603 .........Product Specification for the EGPWS (MK V and MK VII)

060-4404-000………Product Description for Runway Awareness and Advisory System (RAAS) prior to -230-230 060-4564-000………Product Description, Flight Safety Functions of the EGPWS

993-0976-401 .........

Interface Control Document for the Mark V EGPWS

993-1076-401 .........

Interface Control Document for the Mark VII EGPWS

060-4199-125 .........

Installation Design Guide for the MK V EGPWS

060-4199-225 .........

Installation Design Guide for the MK VII EGPWS

060-4241-000 .........

MK V and MK VII EGPWS Pilot Guide

060-4267-000 .........

EGPWS Terrain Database Airport Coverage List (MK V and MK VII)

060-4353-000 .........

EGPWS Terrain Database Obstacle Coverage Chart

MK VI, MK VIII, MK XXII:

965-1176-601 .........

Product Specification for the MK VI and MK VIII EGPWS (original model)

965-1180-601 .........

Product Specification for the MK VI and MK VIII EGPWS (with improved CPU)

965-1590-601 .........

Product Specification for the MK XXII EGPWS (original model)

965-1595-601 .........

Product Specification for the MK XXII EGPWS (with improved CPU)

993-1176-401 .........

Interface Control Document for the Mark VI/VIII/XXII EGPWS (original model)

993-1180-401 .........

Interface Control Document for the Mark VI/VIII/XXII EGPWS (with improved CPU)

060-4314-125 .........

Installation Design Guide for the MK VI/VIII EGPWS (original model)

060-4314-150………Installation Design Guide for the MK VI/VIII EGPWS (with improved CPU)

060-4314-225 .........

Installation Design Guide for the MK XXII EGPWS (original model)

060-4314-250………Installation Design Guide for the MK XXII EGPWS (with improved CPU)

060-4314-000 .........

MK VI and MK VIII EGPWS Pilot Guide

060-4314-200 .........

MK XXII EGPWS Pilot Guide

060-4326-000 .........

EGPWS Terrain Database Airport Coverage List (MK VI and MK VIII)

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Honeywell MK XXII, MK VI, MK VII, MK V, MK VIII User Manual

EGPWS LINE MAINTENANCE MANUAL

2 DESCRIPTION AND OPERATION

2.1 GENERAL SYSTEM DESCRIPTION

The purpose for the Enhanced Ground Proximity Warning System (EGPWS) is to help prevent accidents caused by Controlled Flight Into Terrain (CFIT), obstacles, or severe windshear. The Enhanced Ground Proximity Warning Computer (EGPWC) accepts a variety of aircraft sensors and system inputs and applies alerting algorithms to provide the flight crew with aural messages and visual annunciations when the boundaries of alerting envelopes are exceeded. A graphic depiction of terrain and obstacles within the range selected on an EFIS or Weather Radar display may be configured for enhanced situational awareness with respect to terrain and obstacles. Figure 2-1 provides an overall system block diagram.

Figure 2-1: Enhanced Ground Proximity Warning System

The EGPWS is comprised of the following:

Aircraft sensors and systems providing input signals

The Enhanced Ground Proximity Warning Computer (EGPWC)

Flight deck audio systems (speaker and interphone)

Alert lamps and/or EFIS or EICAS displays (for alert and system status messages)

EFIS Navigation Display (ND), Multi-Function Display (MFD), or Weather Radar Indicator for display of terrain

Switching relay(s) when required for switching display inputs from weather display to terrain display

GPS antenna for direct connection to EGPWC with internal GPS sensors

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2.1.1 ENHANCED GROUND PROXIMITY WARNING COMPUTER (EGPWC)

All EGPWS functions are processed by a single Line Replaceable Unit (LRU) called the Enhanced Ground Proximity Warning Computer (EGPWC).

The MK V and MK VII EGPWC are digitally controlled computers housed in a 2 MCU ARINC 600-6 form factor chassis intended for Air Transport type aircraft. Installation configuration is defined by program pin strapping in the aircraft.

The MK VI and MK VIII EGPWC are digitally controlled computers housed in a non-ARINC form factor chassis intended for Business and General Aviation and Regional Turboprop type aircraft. These models have fewer interface and functional options. The installation configuration is defined in a programmed Configuration Module installed in the aircraft.

The MK XXII EGPWC is a digitally controlled computer housed in a non-ARINC form factor chassis intended for various rotorcraft. Similar to the MK VI and MK VIII EGPWC, this model has fewer interface and functional options. The installation configuration is defined in a programmed Configuration Module installed in the helicopter.

The EGPWC receives information in AC, DC, discrete, and synchro analog formats, and RS-232, RS-422, ARINC 429 or ARINC 575 digital formats. Discrete signals can be either ground or +28V discretes. The EGPWC provides discrete, audio and ARINC 429 outputs for alerts and system status, and video (ARINC 453/708) for terrain display. The EGPWC is rack mounted and does not require any forced air cooling when operated within the normal operating temperature range given in the Table 1-1.

2.2 OPERATION

2.2.1 MODE 1 – EXCESSIVE DESCENT RATE

Mode 1 provides audio and visual alerts for excessive descent rates into terrain. When the EGPWS caution alert envelope is penetrated, the message “SINKRATE” is enunciated and EGPWS alert lights illuminate. Continuing the excessive descent rate into the EGPWS warning alert envelope results in a “PULL-UP” enunciation and EGPWS alert lights illuminated. Mode 1 is desensitized to eliminate unwanted (nuisance) alerts when the EGPWS determines that the aircraft is above a Glideslope beam. In some fixed-wing applications, Mode 1 is also desensitized when Steep Approach or Flap Override is active. In helicopter applications, Mode 1 is disabled when autorotation is detected.

2.2.2 MODE 2A/2B - TERRAIN CLOSURE RATE

Mode 2 provides audio and visual alerts for dangerously high terrain closure rates. Two sub-modes, referred to as Mode 2A and 2B, are defined. Mode 2A is active when flaps are not in the landing position and the aircraft is not on an ILS approach within ± 2 dots of glideslope center. Mode 2B is active when the flaps are in the landing position or while on an ILS approach within ± 2 dots of glideslope deviation. When the caution alert envelope is penetrated, the message “TERRAIN, TERRAIN” is enunciated and EGPWS alert lights illuminate. Continuing the high terrain closure rate into the warning alert envelope results in a “PULL-UP” enunciation and EGPWS alert lights illuminated.

2.2.3 MODE 3 - DESCENT AFTER TAKEOFF

Mode 3 provides audio and visual alerts for excessive altitude loss after takeoff, or after a go-around from below 245 feet above ground level (AGL), when flaps and gear are not in the landing configuration. Penetrating the Mode 3 alert envelope causes the voice message “DON’T SINK, DON’T SINK” and illumination of EGPWS alert lights.

2.2.4 MODE 4A/4B/4C - UNSAFE TERRAIN CLEARANCE

Mode 4 provides audio and visual alerts for unsafe terrain clearance with respect to phase of flight, height above ground, and speed. Three sub-modes, referred to as Mode 4A, 4B, and 4C, are defined. Mode 4A is active during cruise and approach with landing gear up. Mode 4B is active during cruise and approach with landing gear down and flaps up. Mode 4C is active during takeoff when either gear or flaps are not in the landing configuration. The aural enunciations for Mode 4A are “TOO LOW TERRAIN” or “TOO LOW GEAR” depending on airspeed. Mode 4B

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provides “TOO LOW TERRAIN” or “TOO LOW FLAPS” depending on airspeed. Mode 4C provides “TOO LOW TERRAIN”. EGPWS alert lights are illuminated during these alerts.

2.2.5 MODE 5 - DESCENT BELOW GLIDESLOPE

Mode 5 provides audio and visual alerts for excessive glideslope deviation when the aircraft descends below the glideslope beam on front-course ILS approaches. Two levels of alerting are provided. If the aircraft is below 1000 feet AGL and gets to or exceeds 1.3 dots glideslope deviation (fly-up), a ‘soft’ (reduced volume) “GLIDESLOPE” is enunciated. Exceeding 2 dots below 300 feet AGL provides a hard (full volume) “GLIDESLOPE” enunciation. EGPWS alert lights are illuminated during these alerts.

2.2.6 MODE 6 - ADVISORY CALLOUTS (OPTIONAL)

The EGPWC can be programmed to enunciate Mode 6 Advisory Callouts based on menu selectable options. Mode 6 includes Altitude Awareness, Minimums/Approaching Minimums, and Bank Angle type callouts as defined for each EGPWS model (refer to an applicable Interface Control Document or Installation Design Guide). The menu selected Advisory Callouts are defined and enabled in the installation configuration. If Altitude Callouts are not enabled, only (DH based) “MINIMUMS” callouts will be provided. The MK XXII offers a tail strike advisory for helicopters.

Only aural callouts are provided for Mode 6. EGPWS alert lights are NOT illuminated for Mode 6 callouts. The following table identifies all of the Mode 6 Callouts that are available and the applicability to each model.

TABLE 2-1: MODE 6 CALLOUTS

 

CALLOUT

 

DESCRIPTION

 

 

 

 

MODEL

 

 

 

 

 

V

VI

VII

VIII

XXII

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

“DECISION HEIGHT“

 

At descent below minimums setting (DH)

 

 

#

#

#

 

 

 

 

 

 

 

 

 

 

 

 

“CHECK HEIGHT”

 

At descent below minimums setting (DH)

 

 

#

#

#

#

 

 

 

 

 

 

 

 

 

 

 

“ALTITUDE-ALTITUDE”

 

At descent below minimums setting (DH) with gear up

 

#

#

#

#

 

 

 

 

 

 

 

 

 

 

 

 

“MINIMUMS”

 

At descent below minimums setting (DH)

 

 

#

#

#

 

 

 

 

 

 

 

 

 

 

 

 

“MINIMUM”

 

At descent below minimums setting (DH)

 

 

#

#

#

 

 

 

 

 

 

 

 

 

 

 

“MINIMUMS-MINIMUMS”

At descent below minimums setting (DH)

 

 

 

 

 

 

 

 

 

 

 

 

 

 

“DECIDE”

 

At descent below minimums setting (DH)

 

 

#

#

#

 

 

 

 

 

 

 

 

 

 

“APPROACHING DECISION

At descent below minimums (DH altitude) setting plus

 

#

#

#

 

HEIGHT”

 

100 feet

 

 

 

 

 

 

 

 

“APPROACHING MINIMUMS”

At descent below minimums setting (DH altitude) plus

 

#

#

#

 

 

 

80 feet

 

 

 

 

 

 

 

 

“PLUS HUNDRED”

 

At descent below minimums setting (DH altitude) plus

 

#

#

#

 

 

 

100 feet

 

 

 

 

 

 

 

 

“FIFTY ABOVE”

 

At descent below minimums setting (DH altitude) plus

 

#

#

#

 

 

 

50 feet

 

 

 

 

 

 

 

 

“RADIO ALTIMETER”

 

At descent below 2500 feet

 

 

#

#

#

 

 

 

 

 

 

 

 

 

 

 

“TWENTY FIVE HUNDRED”

At descent below 2500 feet

 

 

#

#

#

 

 

 

 

 

 

 

 

 

 

 

 

“ONE THOUSAND”

 

At descent below 1000 feet

 

 

#

 

 

 

 

 

 

 

 

 

 

 

 

“FIVE HUNDRED”

 

At descent below 500 feet

 

 

#

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

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CALLOUT

DESCRIPTION

 

 

MODEL

 

V

VI

VII

VIII

XXII

 

 

 

 

 

 

 

 

 

500 TONE

Provides 2 second 960 Hz tone at descent below 500

#

#

#

 

feet

 

 

 

 

 

SMART “FIVE HUNDRED”

At descent below 500 feet (only) during non-precision

 

approach

 

 

 

 

 

“FIVE HUNDRED”

Above field callout within 5 nm of a runway in the

#

#

#

 

database

 

 

 

 

 

 

 

 

 

 

 

 

 

“FIVE HUNDRED ABOVE”

Above field callout within 5 nm of a runway in the

#

#

#

 

database

 

 

 

 

 

 

 

 

 

 

 

 

 

“FOUR HUNDRED”

At descent below 400 feet

#

 

 

 

 

 

 

 

“THREE HUNDRED”

At descent below 300 feet

#

 

 

 

 

 

 

 

“TWO HUNDRED”

At descent below 200 feet

 

 

 

 

 

 

 

“ONE HUNDRED SIXTY”

At descent below 160 feet

#

#

#

#

 

 

 

 

 

 

 

“ONE HUNDRED FIFTY”

At descent below 150 feet

#

#

#

#

 

 

 

 

 

 

 

“ONE HUNDRED FORTY”

At descent below 140 feet

#

#

#

#

 

 

 

 

 

 

 

“ONE HUNDRED THIRTY”

At descent below 130 feet

#

#

#

#

 

 

 

 

 

 

 

“ONE HUNDRED TWENTY”

At descent below 120 feet

#

#

#

#

 

 

 

 

 

 

 

“ONE HUNDRED TEN”

At descent below 110 feet

#

#

#

#

 

 

 

 

 

 

 

“ONE HUNDRED”

At descent below 100 feet

 

 

 

 

 

 

 

100 TONE

Provides 2 second 700 Hz tone at descent below 100

#

#

#

 

feet

 

 

 

 

 

“EIGHTY”

At descent below 80 feet

#

#

 

 

 

 

 

 

 

“SIXTY”

At descent below 60 feet

#

#

 

 

 

 

 

 

 

“FIFTY”

At descent below 50 feet

 

 

 

 

 

 

 

“FOURTY”

At descent below 40 feet

 

 

 

 

 

 

 

“THIRTY FIVE”

At descent below 35 feet

#

#

#

 

 

 

 

 

 

 

35 TONE

Provides 1 second 1400 Hz tone at descent below 35

#

#

#

 

feet

 

 

 

 

 

“THIRTY”

At descent below 30 feet

 

 

 

 

 

 

 

“TWENTY”

At descent below 20 feet

 

 

 

 

 

 

 

20 TONE

Provides 1/2 second 2800 Hz tone at descent below

#

#

#

 

20 feet

 

 

 

 

 

 

“FIFTEEN”

At descent below 15 feet

#

#

#

 

 

 

 

 

 

 

“TEN“

At descent below 10 feet

 

 

 

 

 

 

 

“FIVE”

At descent below 5 feet

#

#

#

 

 

 

 

 

 

 

 

 

 

 

 

 

 

# Not currently identified in any menu option for the model indicated.

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2.2.6.1 EXCESSIVE BANK ANGLE CALLOUT

The Bank Angle Callout feature provides callout enunciation for excessive bank angles based on altitude and bank angle limits defined by aircraft type. It is intended to enhance situational awareness during intentional or unintentional maneuvering, and for protection against wing or engine strikes when close to the runway.

When the bank angle limit is reached, the aural callout “BANK ANGLE, BANK ANGLE” is given. Follow-on aural messages are only provided when the aircraft roll angle increases an additional 20% from the previous callout. Bank Angle Callouts are enabled by the installation configuration.

2.2.6.2 TAIL STRIKE CALLOUT

A tail strike alert function is provided by the MK XXII for applicable rotary wing aircraft based upon Radio Altitude, Pitch Attitude, Pitch Rate and Barometric Altitude Rate. The voice message “Tail Too Low “ is provided continuously while within the alert boundary. Unique alert boundaries are provided for applicable aircraft types.

2.2.7 MODE 7 - WINDSHEAR DETECTION (OPTIONAL FOR MK V/VII ONLY)

Mode 7 provides the flight crew with visual and aural alerts for windshear of sufficient magnitude to be potentially hazardous to the aircraft. The system is capable of detecting severe decreasing performance shears (i.e. increasing tailwind/decreasing headwind and/or downdraft) which present an immediate danger to the aircraft. The system is also capable of detecting severe increasing performance shears (increasing headwind/decreasing tailwind and/or up draft). While these shears may not present an immediate danger to the aircraft, these shears can indicate that the atmospheric instability is such that an encounter with a severe decreasing performance shear is likely.

A detected increasing performance shear will result in an aural “CAUTION WINDSHEAR” enunciation and cockpit light annunciation when enabled. A detected decreasing performance shear will result in an aural siren followed by “WINDSHEAR, WINDSHEAR, WINDSHEAR” with a corresponding cockpit warning light annunciation.

2.2.8 ENVELOPE MODULATION (NOT AVAILABLE IN MK VI/VIII -001)

Envelope Modulation provides improved alert protection and expanded alerting margins at identified key locations throughout the world. Due to terrain features at or near certain specific airports, normal operations have resulted in nuisance or missed alerts at these locations in the past. With the introduction of accurate position information and a terrain and airport database, it is now possible to identify these areas and adjust the normal alerting process to compensate for the condition.

Modes 4, 5, and 6 are expanded at certain locations to provide alerting protection consistent with normal approaches. Modes 1, 2, and 4 are desensitized at other locations to prevent nuisance alerts that result from unusual terrain or approach procedures. In all cases, very specific information is used to correlate the aircraft position and phase of flight prior to modulating the envelopes. This function is automatic and transparent to crew operation.

2.2.9 TERRAIN CLEARANCE FLOOR AND RUNWAY FIELD CLEARANCE FLOOR

The Terrain Clearance Floor (TCF) alerting function adds an additional element of protection to the standard Ground Proximity Warning System for fixed-wing aircraft. It creates an increasing terrain clearance envelope around the airport runway to provide CFIT protection against situations where Mode 4 provides limited or no protection. TCF alerts are based on current aircraft location, destination runway center point position, and Radio Altitude (altitude AGL). TCF is active during takeoff, cruise, and final approach. TCF complements the existing Mode 4 protection by providing an alert based on insufficient terrain clearance even when in landing configuration.

The TCF function is enhanced in all fixed-wing models (beginning with release –210-210 for the MK V/VII) with the addition of a Runway Field Clearance Floor (RFCF) alerting function. RFCF is based on current aircraft location, destination runway center point position, and Geometric Altitude or altitude Above Sea Level (ASL) relative to the destination runway. RFCF provides short landing protection for runways that are significantly higher than the surrounding terrain.

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When an aircraft penetrates either the TCF or the RFCF alert envelope, the aural message “TOO LOW TERRAIN” will occur. This aural message will occur once when initial envelope penetration occurs, and one time thereafter for each 20% degradation in either Altitude (AGL) or Altitude (ASL) depending on which envelope was violated (TCF or RFCF respectively). EGPWS cockpit alert annunciations remain illuminated until the alert envelope is exited. The TCF and RFCF functions are not available in the MK XXII.

2.2.9.1 RUNWAY DATABASE

The EGPWS Runway Database consists of data records for all airport runways offered for the coverage provided by the Terrain Database. For the MK V and MK VII, all hard surface runways in the world 3500 feet or greater in length are supported. For the MK VI, all runways 2000 feet or greater in length within the database region installed are supported. The MK VIII has the ability to select >2000 foot or >3500 foot runway lengths. For the MK XXII, only runways 2000 feet or greater with a published approach procedure are included. The database provides the means of accessing the records of runways closest to the current aircraft position.

2.2.10 TERRAIN ALERTING AND DISPLAY (OPTIONAL)

The Terrain Alerting and Display (TAD) function monitors aircraft position with respect to local database-cataloged terrain to provide rapid audio and visual alerts when a terrain threat is detected. Terrain threats are recognized and annunciated when terrain violates specific computed envelope boundaries forward of the aircraft path. The terrain database also includes obstacles (when and where available) providing similar annunciations when cataloged obstacles violate the same envelope boundaries.

Terrain Alerting outputs (lights and audio) behaves in the same manner as the standard GPWS mode alerts. Either caution or warning alerts will initiate a specific audio alert phrase. The caution aural is “CAUTION TERRAIN” or “CAUTION OBSTACLE” and the warning aural is “TERRAIN, TERRAIN, PULL UP” or “OBSTACLE, OBSTACLE, PULL UP” (minor variations exist).

Complementing the terrain threat alerts, the EGPWS also maintains a synthetic image of local terrain forward of the aircraft for display on EFIS Navigation Displays (ND’s), Multi-Functional Displays (MFD’s), or Weather Radar Indicators. The EGPWS may be configured to automatically de-select the Weather Display and pop-up a display of the terrain threats when they occur. The logic used for these configurable controls also provides an external input for predictive windshear alerts that can override a Terrain Display and revert to the weather display with the corresponding windshear data.

The EGPWS provides up to two optional external displays outputs, each with independent range-scaling control in the same fashion as weather radar with more than one indicator. Changes of range scaling to one display do not affect the other display. Each of these two independent outputs may be used to drive more than one display.

2.2.10.1 TERRAIN AND OBSTACLE DATABASE

The EGPWS Terrain Database is the earth’s surface divided into grid sets and cells referenced to the geographic (latitude/longitude) coordinate system of the World Geodetic System 1984 (WGS-84). Elements of the grid sets include the highest terrain altitude (above MSL) in each cells respective area. Grid sets vary in resolution depending on geographic location. Because the overwhelming majority of “Controlled Flight Into Terrain (CFIT)” accidents occur near an airport, and the fact that aircraft operate in closer proximity to terrain near an airport, higher resolution grids are used around airports. Lower resolution grids are used outside of airport areas where aircraft altitude enroute makes CFIT accidents unlikely and for which detailed terrain features are not important to the flight crew.

Digital Elevation Models (DEM’s) are available for most of the airports around the world today. In cases where data is not currently available, DEM’s are generated from available topographic maps, sectional charts, and airline approach plates. The process of acquiring, generating, assembling, and updating the database is governed by strict configuration controls to insure the highest level of data integrity for generation of the EGPWS Terrain Database.

The EGPWS Terrain Database is organized in a flexible and expandable manner. Using digital compression techniques, the complete database is stored in non-volatile memory within the LRU. Updates and additions are easily accomplished via a PCMCIA card interface.

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The Obstacle Database (in MK V and MK VII -204-204 and later, and MK VI, MK VIII and MK XXII) is a separate file included within the terrain database. Both files are loaded into the EGPWS in the terrain database PCMCIA card. The obstacle database is accessed by the EGPWC application software only if obstacle alerting is enabled by installation configuration. The obstacle data is processed by the EGPWS in the same fashion as terrain, and is presented on the display as terrain (uses same coloring scheme).

MK V, MK VII, and MK VIII EGPWS utilize a worldwide Terrain Database. The MK VI EGPWS utilizes a regional Terrain Database consisting of one of the following regions:

the Americas Region (designated “N”) for all of North, Central, and South America,

the Atlantic Region (designated “A”) covering Greenland, Europe, Africa, and Asia,

the Pacific Region (designated “P”) covering Europe, East Africa, Asia, Australia, the Pacific Ocean (to 120W longitude including most of the US west coast).

The MK XXII utilizes 11 regional databases. For either worldwide or regional Terrain Databases, the Obstacle Database currently covers cataloged obstacles (see Section 1.3) that are 100 feet high or higher. The MK XXII database of obstacles is unique in the inclusion of oil rigs.

2.2.11 PEAKS DISPLAY MODE (OPTIONAL)

As an enhancement to the “standard” EGPWS terrain display, the Peaks Mode (when enabled by the installation configuration) allows terrain below the aircraft to be viewed on the EGPWS terrain display during all phases of flight (for MK V and MK VII -206-206 and later, and MK VI, MK VIII, and MK XXII). At altitudes safely above terrain for the chosen display range, the terrain is displayed independent of aircraft altitude emphasizing the highest and lowest displayed elevations to provide enhanced situational awareness. This can be particularly valuable to the flight crew in case of an unplanned descent or off-route deviation and for previewing terrain prior to or during descent.

The EGPWS terrain display uses colors and shading patterns corresponding to the vertical displacement between terrain elevation and the current altitude of the aircraft. With the “standard” display, terrain more than 2000 feet below the aircraft is not displayed typically leaving the terrain display blank during the enroute portion of flight. The Peaks Mode Display adds additional density patterns and level thresholds based on terrain elevations relative to the range and distribution of terrain in the display area. The Peaks Mode is thus a “merged” display applicable to all phases of flight.

Within the Peaks Mode display, two elevation numbers indicate the highest and lowest terrain currently being displayed. The elevation numbers indicate terrain in hundreds of feet Above Sea Level (ASL). The terrain elevation numbers are displayed with the “highest” terrain number on top, and the “lowest” terrain number beneath it. The “highest” terrain number is shown in the same color as the highest terrain color pattern on the display, and the “lowest” terrain number is shown in the color of the lowest terrain color pattern shown on the display. A single elevation number is displayed when there is no appreciable difference in terrain elevations such as when flying over water (displayed blue on some display systems) or flat terrain. The elevation numbers on the display are also an indication that the terrain display is selected.

2.2.12 GEOMETRIC ALTITUDE (GPS REQUIRED)

Geometric Altitude (for MK V and MK VII -206-206 and later, and MK VI, MK VIII, and MK XXII) is a computed pseudo-Corrected Barometric Altitude (computed altitude “Above Sea Level” - ASL). This is designed to ensure optimal operation of the EGPWS enhanced functions through all phases of flight and atmospheric conditions. Geometric Altitude uses GPS Altitude, an improved pressure altitude calculation, Radio Altitude, and Terrain and Runway elevation data to reduce or eliminate errors potentially induced into Corrected Barometric Altitude by temperature extremes, non-standard altitude conditions, and altimeter miss-sets. Geometric Altitude also allows continuous EGPWS operations in QFE environments without custom inputs or special operational procedures.

2.2.13 WEATHER RADAR AUTOTILT (MK V AND MK VII ONLY)

MK V and MK VII EGPWS (-210-210 and later) provide an automatic Weather Radar tilt angle capability. The AutoTilt function uses aircraft altitude above the terrain and the terrain database to generate an optimum tilt angle for the Weather Radar. The Auto-Tilt angle results in minimum ground clutter on the display while maintaining the optimum weather detection capability. With manual tilt control, there can be over-scan where weather cells and terrain are

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below the antenna beam scan resulting in a blank display. Alternately, under-scan, where the antennas scan is hitting the ground below the weather cells, results in ground clutter display. The calculated tilt angle is transmitted on the ARINC 429-output bus (labels 061, 062, 063, 064, and 065) for any compatible Weather Radar system. See the appropriate Part Number ICD for complete Label definitions.

2.2.14 SYSTEM DISPLAY AND ANNUNCIATION

In addition to the aural (voice) alerts provided over the cockpit speaker and interphone system, the EGPWS drives cockpit annunciators and/or Electronic Flight Instrument Systems (EFIS) with system status and alert annunciations. For some EFIS displays, the EGPWS is designed to interface and display the EGPWS terrain video as well as alert annunciations directly onto the EFIS without the use of external relays or annunciators. This is referred to as an “integrated” EFIS display. For other displays (some EFIS and all Radar Indicators), the terrain video is relay switched into the display system externally taking the place of weather radar video. In this case, external switching and annunciation is required. This is referred to as a “Bolt-On” display. The interface and display characteristics are defined for each display system and programmed into the EGPWC as part of the configuration software.

Cockpit annunciations can vary somewhat aircraft to aircraft or operator to operator. In addition, several system options are defined by the installation configuration. One of these is EGPWS lamp format. Two formats are provided; Lamp Format 1 and Lamp Format 2. They are described and illustrated in the next page.

2.2.15RUNWAY AWARENESS AND ADVISORY SYSTEM (OPTION FOR MK V AND MK VII ONLY)

The Honeywell Runway Awareness and Advisory System (RAAS) offers significant safety enhancements for aircraft equipped with Honeywell’s MK V or MK VII Enhanced Ground Proximity Warning Systems (EGPWS). Honeywell’s Runway Awareness and Advisory System is a software enhancement hosted in the EGPWS Unit. RAAS uses GPS position data and the Honeywell EGPWS Database to provide aural advisories and alerts that supplement flight crew awareness of position during ground operations and on approach to landing. EGPWS protection and operation is unaltered by the addition of RAAS. RAAS installation is accomplished via a configuration database upload. The installation does require that the EGPWS has a source of GPS data, software -218-218 (or -002 or -051) or later, Terrain Database version 435 or later (454 or later if using software -230-230 or later), and the RAAS Configuration Database (RCD) or Reloadable Customer Definitions (RCD) is loaded. When enabled, RAAS operates automatically, without any action required from the flight crew. RAAS availability can be verified by performing an EGPWS self test. See Appendix C for RAAS Maintenance Messages.

2.2.16 STABILIZED APPROACH MONITOR (OPTION FOR MK V AND MK VII ONLY)

The Stabilized Approach Monitor function offers significant safety enhancements for aircraft equipped with Honeywell’s MK V or MK VII Enhanced Ground Proximity Warning Systems (EGPWS). Honeywell’s Stabilized Approach Monitor is a software enhancement hosted in the EGPWS Unit. Stabilized Approach Monitor uses GPS position data and the Honeywell EGPWS Database to provide aural advisories and alerts that supplement flight crew awareness of unstabilized approach to landing. EGPWS protection and operation is unaltered by the addition of Stabilized Approach Monitor. Stabilized Approach Monitor installation is accomplished via a configuration database upload. The installation does require that the EGPWS has a source of GPS data, software -230-230 or later, Terrain Database version 454 or later, and the Reloadable Customer Definitions (RCD) is loaded. When enabled, Stabilized Approach Monitor operates automatically, without any action required from the flight crew. Stabilized Approach Monitor availability can be verified by performing an EGPWS self test. See Appendix D for

Stabilized Approach Monitor Maintenance Messages.

2.2.17 ALTIMETER MONITOR (OPTION FOR MK V AND MK VII ONLY)

The Altimeter Monitor function offers significant safety enhancements for aircraft equipped with Honeywell’s MK V or MK VII Enhanced Ground Proximity Warning Systems (EGPWS). Honeywell’s Altimeter Monitor is a software enhancement hosted in the EGPWS Unit. Altimeter Monitor compares Corrected Altitude to the EGPWS blended Geometric Altitude solution to provide aural advisories that supplement flight crew awareness of incorrect altimeter setting or problems with the pressure altitude system. EGPWS protection and operation is unaltered by the addition of Altimeter Monitor. Altimeter Monitor installation is accomplished via a configuration database upload. The

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installation does require that the EGPWS has a source of GPS data, software -230-230 or later, Terrain Database version 454 or later, and the Reloadable Customer Definitions (RCD) is loaded. When enabled, Altimeter Monitor operates automatically, without any action required from the flight crew. Altimeter Monitor availability can be verified by performing an EGPWS self test. See Appendix E for Altimeter Monitor Maintenance Messages.

2.2.18TAKEOFF FLAP CONFIGURATION MONITOR (OPTION FOR MK V AND MK VII ONLY)

The Takeoff Flap Configuration Monitor function offers significant safety enhancements for aircraft equipped with Honeywell’s MK V or MK VII Enhanced Ground Proximity Warning Systems (EGPWS). Honeywell’s Takeoff Flap Configuration Monitor is a software enhancement hosted in the EGPWS Unit. Takeoff Flap Configuration Monitor uses GPS position data, Flap angle inputs, and the Honeywell EGPWS Database to provide aural alerts that supplement flight crew awareness of improper flap setting when the aircraft is aligned on a runway prior to takeoff. EGPWS protection and operation is unaltered by the addition of Takeoff Flap Configuration Monitor. Takeoff Flap Configuration Monitor installation is accomplished via a configuration database upload. The installation does require that the EGPWS has a source of GPS data, flap angle input, software -230-230 or later, Terrain Database version 454 or later, and the Reloadable Customer Definitions (RCD) is loaded. When enabled, Takeoff Flap Configuration Monitor operates automatically, without any action required from the flight crew. Takeoff Flap Configuration Monitor availability can be verified by performing an EGPWS self test. See Appendix F for Takeoff

Flap Configuration Monitor Maintenance Messages.

2.2.19 LONG LANDING MONITOR (OPTION FOR MK V AND MK VII ONLY)

The Long Landing Monitor function offers significant safety enhancements for aircraft equipped with Honeywell’s MK V or MK VII Enhanced Ground Proximity Warning Systems (EGPWS). Honeywell’s Long Landing Monitor is a software enhancement hosted in the EGPWS Unit. Long Landing Monitor uses GPS position data and the Honeywell EGPWS Database to provide aural alerts that supplement flight crew awareness of their position during a landing when the aircraft has not touched down in a nominal amount of time and/or distance. EGPWS protection and operation is unaltered by the addition of Long Landing Monitor. Long Landing Monitor installation is accomplished via a configuration database upload. The installation does require that the EGPWS has a source of GPS data, software -230-230 or later, Terrain Database version 454 or later, and the Reloadable Customer Definitions (RCD) is loaded. When enabled, Long Landing Monitor operates automatically, without any action required from the flight crew. Long Landing Monitor availability can be verified by performing an EGPWS self test.

See Appendix G for Long Landing Monitor Maintenance Messages.

2.2.20 LOW AIRSPEED MONITOR (MK V BOEING 737NG ONLY)

The Low Airspeed Monitor function offers significant safety enhancements for Boeing 737NG aircraft equipped with Honeywell’s MK V Enhanced Ground Proximity Warning Systems (EGPWS). Honeywell’s Low Airspeed Monitor is a software enhancement hosted in the EGPWS Unit. Low Airspeed Monitor uses Minimum Operating Speed and Stick Shaker Speed input from the Stall Management and Yaw Damper computers to provide an aural alert that supplements flight crew awareness that their airspeed had passes below 70% of the amber airspeed band. EGPWS protection and operation is unaltered by the addition of Low Airspeed Monitor. Low Airspeed Monitor installation is accomplished via an application software upload. The installation does require that the EGPWS has software -232-232 or later loaded. When installed, Low Airspeed Monitor operates automatically, without any action required from the flight crew. Low Airspeed Monitor availability can be verified by performing an EGPWS self test.

See Appendix H for Low Airspeed Monitor Maintenance Messages.

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2.2.21 LAMP FORMAT

The EGPWS contains two different caution/warning lamp illumination formats as described below. Lamp Format 1 provides EGPWS warning (red) and caution (amber) alert lamp drive logic such that:

Only a Mode 5 “Glideslope” alert will activate the caution lamp output (amber).

All other alerts (except “windshear” and Mode 6 callouts) will activate the warning lamp output (red).

 

 

(RED)

“SINK RATE, SINK RATE”

 

 

“PULL UP”

 

 

PULL

“TERRAIN, TERRAIN”

Modes 1-4, TA

“OBSTACLE, OBSTACLE”

 

 

UP

“CAUTION TERRAIN”

All caution and

“CAUTION OBSTACLE”

“TOO LOW TERAIN”

warning alerts

Push toTest

“TOO LOW GEAR”

 

 

“TOO LOW FLAPS”

 

 

 

“DON’T SINK”

 

 

 

 

 

 

(AMBER)

 

Mode 5 only

BELOW

GLIDESLOPE”

 

 

GS

 

 

 

 

 

Push to Cancel

 

 

 

 

 

Lamp Format 2 provides EGPWS warning (red) and caution (amber) alert lamp drive logic such that:

Only the warning alerts containing the phrase “Pull Up” will activate the warning lamp output (red).

All other alerts (except “windshear” and Mode 6 callouts) will activate the caution lamp output (amber).

All Modes, TA

All warning alerts

All Modes, TA

All caution alerts

Note: Actual legends may vary.

(RED)

 

PULL

“ PULL UP”

UP

 

Push to Test

(AMBER)

“SINK RATE, SINK RATE”

“TERRAIN, TERRAIN”

 

“OBSTACLE, OBSTACLE”

GPWS

“CAUTION TERRAIN”

“CAUTION OBSTACLE”

“TOO LOW TERAIN”

Glideslope

“TOO LOW GEAR”

“TOO LOW FLAPS”

Push to Cancel

“DON’T SINK”

 

“GLIDESLOPE”

EGPWS caution or warning alerts lamp driver outputs are activated for all Mode 1-5 GPWS alerts and Terrain or Obstacle alerts when enabled. Windshear warning and caution alerts activate separate lamp outputs when enabled.

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2.3 SYSTEM MAINTENANCE

2.3.1 MAINTENANCE PHILOSOPHY

The EGPWS is an “on-condition” only maintenance system. No scheduled maintenance is required. This is accomplished by both continuous Built-In-Test (BIT) and event initiated test functions. Event initiated test refers to both power-up tests and manually activated Self-Tests. Results of these functions are indicated by system status indicators and messages so that the systems functionality can be assessed.

Detected faults are indicated to the flight crew during normal flight operations by system status annunciators or flight display (EFIS) messages in the cockpit (i.e., GPWS INOP or FAIL, W/S INOP or FAIL, TERR INOP or NOT AVAILABLE). On the ground, system status indications are expanded to direct fault isolation to the fault source whether internal or external to the EGPWC. Several levels of reporting are provided by the EGPWS Self-Test, and multiple means are provided to access the information. The intent is to provide information that will encourage the line mechanic to correct the real problem through clear fault messages and minimal effort.

2.3.2 SYSTEM OPERATION DURING AN INOP CONDITION

EGPWS continued airworthiness is predicated on system status indications. An indication of TERR INOP (only) or NOT AVAILABLE (only) is likely to indicate a loss of necessary GPS data for performing Terrain Alerting and Display functions, but has no effect on basic GPWS (Modes 1-7) functions. Additionally, a GPWS INOP (only) indicates a loss of basic GPWS functions, but this could be limited to say Mode 4 only because of a loss of necessary data required for that mode alone. In any case, the EGPWS will provide alerting based on the current capability of the EGPWC and its inputs.

For the MK VI and MK XXII, consideration should be given to any operation that will cross the boundaries of the regional database. Although this has no affect on the basic GPWS functions, the enhanced (TAD/TCF) functions will become inoperative once the aircraft leaves the database region. This is indicated by the TERR INOP or NOT AVAILABLE status indicator and the loss of terrain display when enabled and active.

2.3.3 BIT DESCRIPTION

The EGPWC contains an extensive BIT capability. The BIT functions provide high confidence that the Warning Computer and interface signal sources are operating properly, and that the EGPWS will perform its intended function. Detected failures are indicated via GPWS INOP, Windshear INOP, and Terrain INOP/NA annunciations and on the ARINC 429 bus output. Failures detected during flight are saved in the flight history and are enunciated during Level 4 of the cockpit Self-Test. BIT status is also available through the RS-232 port by use of a PC or terminal.

If the EGPWC detects an internal Warning Computer fault, it will turn on all the INOP lights. If the EGPWC detects an external input fault, it may or may not turn on the INOP light(s) depending on the input fault, the type of installation, and whether the aircraft is airborne or on the ground.

The EGPWC BIT performs three types of functions: Operation Monitoring, Operation Tests, and Restricted Tests.

Operation Monitoring consists of software checks that are performed as part of the normal Warning Computer processing. Operation Monitoring includes checks of data values and program flow control variables used for the warning computations to ensure they are within expected ranges. The statuses of various EGPWC hardware subsystems are continuously verified including core processor checks, voice generator circuitry checks, and ARINC 429 wrap-around tests. Operation Monitoring also includes extensive testing of the input signals to ensure the EGPWC is using proper data for its calculations.

Operation Tests run during normal operation without disrupting the EGPWC warning calculations or annunciations. Operations Tests include CPU instruction set tests, A/D tolerance tests, ROM check-sum verification tests, and nondestructive RAM tests. Operation Tests are scheduled by the operating system to be performed between the routines required for normal operation.

Restricted Tests destroy data or take an excessive amount of time to complete and cannot be run during normal system operation. These tests are usually run during system power up or during a cockpit initiated Self-Test.

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These tests primarily consist of more thorough hardware checks that would disrupt normal operation if continuously run.

2.3.4 EGPWC FRONT PANEL

To aid in troubleshooting the EGPWS, the front panel of the Warning Computer provides indicators and user interfaces as follows.

2.3.4.1 EGPWS STATUS LED’S

Three LED’s on the EGPWC front panel provide a high level indication of overall system status. These are:

a yellow “External Fault” LED

a green “Computer OK” LED

a red “Computer Fail” LED

The yellow “External Fault” LED indicates that a fault external to the EGPWC exists. The green “Computer OK” LED indicates that the EGPWC is operating correctly with no internal faults. The red “Computer Fail” LED indicates that the EGPWC has an internal fault. Further explanation of internal and external faults is given in Section 3.4.1 and Section 3.4.2.

*Useful Tip #1 – The red Computer Fail LED illuminated does not guarantee the EGPWS is failed. It is possible for invalid strapping/wiring (MK V/VII only) to cause the LED to illuminate. Before returning a MK V/VII for repair, bench test the unit with power/ground applied, making sure to ground the parity pin. If the red Computer Fail LED does not illuminate during this bench test, the aircraft wiring is causing the Computer Fail condition.

2.3.4.2 FRONT PANEL SELF-TEST INTERFACE (MK V AND MK VII ONLY)

The EGPWC front panel provides a Self-Test switch for activating Self-Test features described in Section 2.3.5. This switch functions the same as cockpit Self-Test switches.

2.3.4.3 AUDIO JACK (MK V AND MK VII ONLY)

The EGPWC front panel provides a headphone jack for use during Self-Test. The audio jack is a standard 600Ω monophonic audio output compatible with a standard 2-connector ¼" audio plug headphones.

2.3.4.4 FRONT PANEL PCMCIA INTERFACE

For the MK V and MK VII, a PCMCIA card slot is provided in the front panel. For the MK VI, MK VIII, and MK XXII the PCMCIA interface utilizes an external PCMCIA interface called a “SmartCable” connected to the front panel Test Connector.

The PCMCIA interface provides a data downloading capability (either loading a new database from a PCMCIA Card or downloading history data from the EGPWC to a Fault History Card).

2.3.4.5 FRONT PANEL TEST CONNECTOR

The EGPWC front panel Test Connector provides communications support capabilities intended for maintenance and test functions. For the MK V and MK VII, this includes RS-232 and 422 communications. For the MK VI, MK VIII, and MK XXII this includes RS-232, power, and signals used for PCMCIA (SmartCable) operation. These serve as access to EGPWS signal monitoring, flight history, initiating BITE tests, updating databases, and other functions. The interface is full duplex and is intended for human interaction using custom interface programs such as the Honeywell WinVIEWS© utility (see Appendix A).

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