Honeywell MK XXII, MK VI, MK VII, MK V, MK VIII User Manual
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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EGPWS LINE MAINTENANCE MANUAL
This document is an unpublished work.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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A
REVISIONS
SHT REV DESCRIPTION DATE
All Initial release.
23 FEB 00
PPROVED
R. Halbert
Reason 01 Severity 10
All A Direct update:
Incorporate –008 changes
Reason 01 Severity 10
All
All C Direct update to incorporate Airbus and Boeing part number
B Direct update to incorporate EGPWC/GNSSU part numbers
and troubleshooting information. Revised Level 2
descriptions.
Reason 01 Severity 10
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
23 FEB 00
07 AUG 01
07 AUG 01
13 FEB 02
13 FEB 02
08 JAN 04
09 JAN 04
G. Gilliland
R. Henderson
L. Matter
B. Breen
G. Gilliland
J. Castro
L. Matter
All D 1) Deleted “Revisions Status of Sheets Index” table on
Sheet 3.
2) Section 3.2 (Troubleshooting Guide)
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)
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
:
: Added step 6 to account for
: Added the
27 SEP 04
30 SEP 04
K. Christofferson
S. Wright
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A
REVISIONS
SHT REV DESCRIPTION DATE
PPROVED
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
01 FEB 05
03 FEB 05
23 JUN 09
29 MAR 10
S. Wright
K. Christofferson
J. Mulkins
See AeroPDM
for additional
approvals
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 GENERAL........................................................................................................................................................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
965-0976-020-XXX-XXX
965-0976-040-XXX-XXX
965-0976-060-XXX-XXX
965-1676-XXX (Airbus P/N)
965-1690-XXX (Boeing P/N)
115 VAC, -40° to +70°
115 VAC, Internal 8 channel
GPS, -40° to +70°
28 VDC, -55° to +70°
115 VAC, Integral GNSSU,
-40° to +70°
115 VAC, -40° to +70°
115 VAC, -40° to +70°
965-1076-001-XXX-XXX
965-1076-020-XXX-XXX
965-1076-030-XXX-XXX
965-1076-040-XXX-XXX
965-1076-060-XXX-XXX
115 VAC, -40° to +70°
115 VAC, Internal 8 channel
GPS, -40° to +70°
28 VDC, Internal 8 channel
GPS, 55° to +70°
28 VDC, -55° to +70°
115 VAC, Integral GNSSU,
-40° to +70°
MK VI EGPWC PART NUMBERS MK VIII EGPWC PART NUMBERS MK XXII EGPWC PART NUMBERS
965-1176-XXX
965-1186-XXX
28 VDC, -55° to +70°
28 VDC, Internal 8 channel
GPS, -55° to +70°
965-1206-XXX
965-1216-XXX
28 VDC, -55° to +70°
28 VDC, Internal 8 channel
GPS, -55° to +70°
965-1590-XXX
965-1595-XXX
28 VDC, Internal 8 channel
GPS, -55° to +70°
28 VDC, Improved CPU,
Internal 8 channel GPS,
-55° to +70°
965-1180-XXX
965-1190-XXX
28 VDC, Improved CPU,
-55° to +70°
28 VDC, Improved CPU,
Internal 8 channel GPS,
-55° to +70°
965-1210-XXX
965-1220-XXX
TABLE 1-1 EGPWC Part Numbers
28 VDC, Improved CPU,
-55° to +70°
28 VDC, Improved CPU,
Internal 8 channel GPS,
-55° to +70°
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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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.
provides an overall system block diagram.
Figure 2-1
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
“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
HEIGHT”
At descent below minimums (DH altitude) setting plus
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
MODEL
V VI VII VIII XXII
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“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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#
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CALLOUT DESCRIPTION
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
MODEL
V VI VII VIII XXII
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“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
# # # #
• • • • •
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“FIVE” At descent below 5 feet
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# 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.
2.2.15 RUNWAY 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.
2.2.18 TAKEOFF 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).
“SINK RATE, SINK RATE”
“PULL UP”
“TERRAIN, TERRAIN”
“OBSTACLE, OBSTACLE”
“CAUTION TERRAIN”
“CAUTION OBSTACLE”
“TOO LOW TERAIN”
“TOO LOW GEAR”
“TOO LOW FLAPS”
“DON’T SINK”
“
GLIDESLOPE”
Modes 1-4, TA
All caution and
warning alerts
Mode 5 only
(RED)
PULL
UP
Push toTest
(AMBER)
BELOW
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).
(RED)
All Modes, TA
All warning alerts
All Modes, TA
All caution alerts
Note: Actual legends may vary.
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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PULL
UP
Push to Test
(AMBER)
GPWS
Glideslope
Push to Cancel
PULL UP”
“
“SINK RATE, SINK RATE”
“TERRAIN, TERRAIN”
“OBSTACLE, OBSTACLE”
“CAUTION TERRAIN”
“CAUTION OBSTACLE”
“TOO LOW TERAIN”
“TOO LOW GEAR”
“TOO LOW FLAPS”
“DON’T SINK”
“GLIDESLOPE”
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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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EGPWS LINE MAINTENANCE MANUAL
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
and Section 3.4.2.
3.4.1
*Useful Tip #1 – The red Computer Fail LED illuminated does not guarantee
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
does not illuminate during this bench test, the aircraft wiring is causing the Computer Fail condition.
the EGPWS is failed. It is possible for
. If the red Computer Fail LED
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
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©
utility (see Appendix A).
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