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1 APPLICATION DASH NO. NEXT ASSY USED ON PRODUCTION - Release - 06 Mar :56:53 MST - Printed on 06 Mar 2013 TITLE SHEET INDEX SHEET NO. TITLE SHEET 1 REVISION STATUS OF SHEETS INDEX 2 REVISIONS 3 DOCUMENT 9 This document is an unpublished work. Copyright Honeywell International Inc. All rights reserved. This document and all information and expression contained herein are the property of Honeywell International Inc., and is provided to the recipient in confidence on a need to know basis. Your use of this document is strictly limited to a legitimate business purpose requiring the information contained therein. Your use of this document constitutes acceptance of these terms. Typed signatures constitute approval. Actual signatures on file at Honeywell in Redmond WA. DRAWN CHECK ENGR MFG QA CONTRACT NO Marc Calhoun Marc Calhoun PRECIOUS METAL INDICATOR CODE: Honeywell International Inc. NA Redmond, Washington Product Specification for the Enhanced Ground Proximity Warning System (EGPWS) SIZE CAGE CODE DWG NO. REV. APVD Lyle Kendall A AC APVD SCALE: NONE SHEET 1 OF 198 HIF-2121/R DOC

2 REVISION STATUS OF SHEETS INDEX ADDED SHEETS ADDED SHEETS SHEET NUMBER REV LTR SHEET NUMBER REV LTR SHEET NUMBER REV LTR SHEET NUMBER REV LTR SHEET NUMBER REV LTR SHEET NUMBER REV LTR All AC HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 2

3 REVISIONS SH REV DESCRIPTION DATE APPROVED All A Details of each sections updates are listed in the Revision History at the beginning of each section. Changes made after the date of the previous revision were made as part of this revision. 1/7/98 1/7/98 C. Bambini L. Kendall Reason: 01 Severity: 10 All B Details of each sections updates are listed in the Revision History at the beginning of each section. Changes made after the date of the previous revision were made as part of this revision. Reason: 01 Severity: 10 All C Details of each sections updates are listed in the Revision History at the beginning of each section. Changes made after the date of the previous revision were made as part of this revision. Reason: 01 Severity: 10 All D Details of each sections updates are listed in the Revision History at the beginning of each section. Changes made after the date of the previous revision were made as part of this revision. Reason: 01 Severity: 10 All E Details of each sections updates are listed in the Revision History at the beginning of each section. Changes made after the date of the previous revision were made as part of this revision. Reason: 01 Severity: 10 All F Details of each sections updates are listed in the Revision History at the beginning of each section. Changes made after the date of the previous revision were made as part of this revision. Reason: 01 Severity: 10 ALL G Details of each sections updates are listed in the Revision History at the beginning of each section. Changes made after the date of the previous revision were made as part of this revision. Reason: 01 Severity: 10 ALL H Details of each sections updates are listed in the Revision History at the beginning of each section. Changes made after the date of the previous revision were made as part of this revision. Reason: 01 Severity: 10 ALL J Details of each sections updates are listed in the Revision History at the beginning of each section. Changes made after the date of the previous revision were made as part of this revision. Reason: 01 Severity: 10 ALL K Details of each sections updates are listed in the Revision History at the beginning of each section. Changes made after the date of the previous revision were made as part of this revision. Reason: 01 Severity: 10 5/19/98 5/19/98 5/19/98 10/09/98 10/09/98 29-MAR MAR-99 8-NOV-99 8-NOV-99 6-JUN-00 6-JUN Aug Aug DEC DEC MAR MAR APR APR-02 M. Calhoun L. Kendall J Mitchell J. Kistler L. Kendall N Paterson A Loos J Kistler A Loos J Egilsrud J Kistler K. Allen G. Ostrom M. Calhoun G. Ostrom G. Ostrom B. Breen G. Ostrom B. Breen HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 3

4 REVISIONS SH REV DESCRIPTION DATE APPROVED All L Details of each sections updates are listed in the Revision History at the beginning of each section. Changes made after the date of the previous revision were made as part of this revision. 18-JUN JUN-02 N Paterson J Kistler Reason: 01 Severity: 10 All M Release 218 update. Details of each sections updates are listed in the Revision History at the beginning of each section. Changes made after the date of the previous revision were made as part of this revision. Reason: 01 Severity: 10 All N MK VII Mercury update. Details of each sections updates are listed in the Revision History at the beginning of each section. Changes made after the date of the previous revision were made as part of this revision. Reason: 01 Severity: 10 All P Release 224 update. Details of each sections updates are listed in the Revision History at the beginning of each section. Changes made after the date of the previous revision were made as part of this revision. Reason: 01 Severity: 10 All R MK VII update for Environmental Qualification information. Details of each sections updates are listed in the Revision History at the beginning of each section. Changes made after the date of the previous revision were made as part of this revision. Reason: 01 Severity: 10 All T Release 226 update. Details of each sections updates are listed in the Revision History at the beginning of each section. Changes made after the date of the previous revision were made as part of this revision. All U Update to Environmental Qualification information pertaining to Explosion Proofness. Details of each sections updates are listed in the Revision History at the beginning of each section. Changes made after the date of the previous revision were made as part of this revision. Reason: 01 Severity: 10 All V Update per ECO Release 230 update. Details of each sections updates are listed in the Revision History at the beginning of each section. Changes made after the date of the previous revision were made as part of this revision. EFF PT: 10 All W Update per ECO Release 232 update. Details of each sections updates are listed in the Revision History at the beginning of each section. Changes made after the date of the previous revision were made as part of this revision. EFF PT: 14A 23-Oct Oct SEP SEP APR APR JUN JUN AUG AUG FEB FEB MAY MAY-10 M Henderson J Kistler G. Ostrom B. Breen E. Wilmot A. Lowe E. Wilmot J. Kistler E. Wilmot A. Lowe E. Wilmot A. Lowe M Calhoun See AeroPDM for additional approvals W. Goo See AeroPDM for additional approvals HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 4

5 REVISIONS SH REV DESCRIPTION DATE APPROVED All Y Update per ECO Release 056 update. Details of each sections updates are listed in the Revision History at the beginning of each section. Changes made after the date of the previous revision were made as part of this revision. EFF PT: 14A 26-JUL-11 A.N. Hans See AeroPDM for additional approvals All AA Update per ECO Details of each sections updates are listed in the Revision History at the beginning of each section. Changes made after the date of the previous revision were made as part of this revision. EFF PT: 14A All AB Update per ECO Details of each sections updates are listed in the Revision History at the beginning of each section. Changes made after the date of the previous revision were made as part of this revision. EFF PT: 14A All AC Update per ECO Added sections , , , and EFF PT: 14A 16-DEC DEC MAR-13 L. Ngo See AeroPDM for additional approvals J. Ehlers See AeroPDM for additional approvals G. Ostrom See AeroPDM for additional approvals HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 5

6 Contents 1 INTRODUCTION PART NUMBER PURPOSE SYSTEM OVERVIEW Ground Proximity Warning Terrain and Obstacle Awareness Mode 7 - Windshear Alerting Maintenance/Test Interfaces System Elements System Limitations Installation Procedures and Limitations TSO Deviations Non-TSO Functions DOCUMENT OVERVIEW REFERENCE DOCUMENTS INTRODUCTION HONEYWELL DOCUMENTS AND DRAWINGS INDUSTRY AND GOVERNMENT DOCUMENTS BOEING DOCUMENTS AND DRAWINGS AIRBUS DOCUMENTS AND DRAWINGS CAIMS DOCUMENTS TERRAIN DATA REFERENCES COMPUTER DESIGN CRITERIA INTRODUCTION FUNCTIONAL PARTITIONING ENVIRONMENTAL RTCA/DO-160C Environmental, xxx-xxx, xxx-xxx, xxx-xxx, and xxx-xxx RTCA/DO-160C Environmental, xxx-xxx, xxx-xxx, xxx-xxx RTCA/DO-160D Environmental, xxx-xxx RTCA/DO-160D Environmental, xx RTCA/DO-160E Environmental, xxx-xxx RELIABILITY/MAINTAINABILITY Scheduled Maintenance Reliability PERFORMANCE POWER EGPWC Power Requirements System Response to Power Interrupts MECHANICAL Packaging Connectors Mounting Cooling Weight SOFTWARE DESIGN REQUIREMENTS EXTERNAL INTERFACE FUNCTIONAL INPUTS RADIO ALTITUDE INPUT PROCESSING Supported Altimeter Types HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 6

7 5.1.2 Excessive Rate Detection Radio Altitude Voting Radio Altitude Reasonableness Stuck Radio Altimeter Check GPS DATA MONITORING GPS Altitude Monitoring GPS Position Monitoring DEAD RECKONING SYSTEM FUNCTIONS MODE CONTROL Air/Ground Mode GPWS Takeoff/Approach Mode Windshear Takeoff/Approach Mode Mode 2 Takeoff Simulator Reposition Terrain Awareness Alerting Guard PROGRAM PINS MKV EGPWS Feature Selection MKVII EGPWS Feature Selection GPWS FUNCTIONS Mode 1 -- Excessive Descent Rate Mode 2 -- Excessive Terrain Closure Rate Mode 3 -- Descent After Takeoff Mode 4 -- Unsafe Terrain Clearance Mode 5 -- Descent Below Glideslope TERRAIN CLEARANCE FLOOR TCF System Requirements ADVISORY ALERTS Minimums/Approaching Minimums Type Callouts Altitude Callouts Smart Altitude Callouts Excessive Bank Angle Callout (Honeywell Algorithm) Bank Angle Option 1 (Basic Boeing Algorithm) Bank Angle Option 2 (Alternate Boeing Algorithm) Speed Brake Alert (KC-135) Low Airspeed Monitor (737NG) WINDSHEAR DETECTION ALERTS Honeywell Windshear Detection Boeing Windshear Detection EXTERNAL TRIGGERED ALERTS Windshear Annunciation Engine Fail/V1 Annunciation Boeing Speed Brake Annunciation TERRAIN AWARENESS FUNCTIONS EGPWS Input Processing and Signal Selection Local Terrain Processing Terrain Threat Detection Terrain/Obstacle Displays and Alerts Terrain Database Obstacle Database Internal Magnetic Variation Database Geometric Altitude WGS-84 Correction Horizontal Position Source Selection ENVELOPE MODULATION SYSTEM OUTPUTS HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 7

8 6.9.1 Serial Output Audio Output Discrete Outputs Display Output and Control Reserved Pitch Limit Indicator Outputs Mercury AT GNSS MAINTENANCE FUNCTIONS Maintenance Philosophy System Status LRU Flight History Recording Front Panel PCMCIA Interface Self-Test Maintenance Systems Support ATP BIT Tests RS-232 Test Interface Data Loading Interface Configuration Management and Version Identification Present Status Output Format Flight History Output Formats PXpress Internal GPS Status Format Mercury Internal GPS Status Format AUTOTILT EGPWS/GNSSU INTERNAL MERCURY GPS General Capabilities Functional Requirements System Interface Performance Requirements Growth Provisions Compatible Navigation Systems APPENDICES APPENDIX A: DEFINITIONS HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 8

9 1 Introduction Product Specification Revision History Effectivity Date - Modified By Description of the Updates App. Cfg. 10/8/97 - A. Loos SCR 2206: Add Section KC-135 Speed Brake Description /27/97 - MJC : Corrected Mode 3 enable conditions to indicate that either Gear All All or Flaps not in Landing configuration enable the mode. 11/07/97 N Paterson SCR 2205: Added KC-135 Bank Angle curve to figure /21/97 G Ostrom Updated 3 DC ratio input type to 3 wire DC ratio in table found in section /26/97 - C. Bambini Fixed typos and formatting /5/98 - C. Bambini SCR 2507: Revised section Revised figures and Section , changed number of ground and +28V activated discretes from 24 and 22 respectively to Section , add mounting tray and connector part numbers for MK7 EGPWS. 4/3/98 N Paterson SCR 2538 Added KC-135 Mode 4 warning boundaries to Figures and /12/98 G. Ostrom Section , updated MK VII EGPWC Mounting Tray information This update includes changes from ADCN A-01. 5/15/98 C. Bambini SCR 2537: Section , revised obstacle activation description /18/98 G. Ostrom Section 1.0, added x part number. Section corrected section pointer. Revised figure Revised section /19/98 G. Ostrom Section , modified steep approach bias description /20/98 MJC SCR 2203: Revised front connector interface in figure /09/98 C. Simsic Section 1.0, added MK VII with GPS-PXPRESS card part number and differences. 29/OCT/98 MJC SCR 3223: Added 2 new program pins to table in Also revised to deleted comment that windshear is enabled via program pin as it is a basic feature. 27-MAR-99 - NSP SCR 3636: Added MK V with internal GPS Part Numbers SEP-99 GAB SCR 3844: Added descriptions of Modes 2A/B and 4A/B reductions based on the status of terrain awareness and TCF functions. 07-OCT-99 MJC SCR 4334: Added x-reference in section for TCF changes made in the 210. Added AlliedSignal p/n's for connector contacts in Added note on Smart Callout operation in the OCT-99 - JDK SCR 4334: Added note to Section to indicate that 208(Mod 1) will fix the Smart Callout function. 22-OCT-99 - JDK SCR 4334: Updated tray part numbers in section OCT-99 - JDK SCR 4334: Updated tray part numbers in section NOV-99 A Loos SCR 4334: Add 1.2.7, Installation Procedures and Limitations NOV-99 - JDK SCR 4334: General document clean up MAY-00 J. Egilsrud SCR 4942: General document clean up JUN-00 Susie Wright General document cleanup to delete proprietary notice in footer AUG-01 S. Gagnon SCR 6334: Section 1.0 Added part number, also lower connector J MAR-02 G. Ostrom SCR 6741: Section 1.0 Added x and x part numbers. Section Added x. Section 1.2 added two new block diagrams for internal GPS. 13-JUN-02 N Paterson Added Boeing Part Number HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 9

10 Effectivity Date - Modified By Description of the Updates App. Cfg. 09-Oct-03 A Loos SCR Section 1.0 add note that RAAS RCD Part Number is not part of the 16 digit EGPWS Part Number. Add RAAS option to text and figures were applicable. New and revise text in and describing Mode 2 changes for Revise to indicate that TCF is revised in 218. Add RAAS option to Figures and 2. Add RAAS to SEP-05 G. Ostrom SCR 8373: Revised table section to note -06x Mercury LRU - - differences. 23-APR-09 M. Calhoun Updated for release APR-09 M. Calhoun Added section with TSO deviation information MAY-09 M. Calhoun Incorporated review comments and updated TSO deviation information in section MAR-10 M. Calhoun SCR 9696: Updated for /-055 release to add part numbers to section 1.0, and to add Low Airspeed Monitor to sections 1.2 and MAY-10 W. Goo SCR 9731: Added section Revised heading in sections and JUL-11 A.N. Hans Added Boeing Mode 4B Corner airspeed in section & figure Added -056 Part number to table Section DEC-11 L. Ngo SCR 9872: Updated reference to the software release from -228 to the - correct -226 in section JAN-13 J. Ehlers SCR 9851: Updated to add support of LPV approaches in Mode MAR-13 G Ostrom Added sections , , , and Part Number This document is the Product Specification for the Enhanced Ground Proximity Warning System (EGPWS), Honeywell part numbers: x-xxx-xxx : MKV EGPWC x-xxx-xxx : MKV EGPWC x-xxx-xxx : MKV EGPWC (28VDC) x-xxx-xxx : MKV EGPWC x-xxx-xxx : MKVII EGPWC x-xxx-xxx : MKVII EGPWC x-xxx-xxx: MKVII EGPWC x-xxx-xxx : MKVII EGPWC (28VDC) x-xxx-xxx : MKVII EGPWC x Boeing MKV EGPWS Differences, where they exist, between the different part numbers, are highlighted within this document. The series part number MKV EGPWCs are intended for current generation aircraft types that provide ARINC 429 interfaces. However, these part numbers can accommodate up to four DC analog inputs. The x series part number MKV EGPWCs include an internal GPS-PXPRESS card. The x series part number MKV EGPWCs are 28 VDC powered. The x series part number MKV EGPWCs include an internal Mercury AT GNSS card. The series part number MKVII EGPWCs are intended for mainly older generation aircraft types that provide a multitude of analog signal interfaces. However, these part numbers can accommodate a limited number of ARINC 429 inputs. The x and x series part number MKVII EGPWCs include an internal GPS-PXPRESS card. The x series part number MKVII EGPWCs are 28 VDC powered. HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 10

11 The x series part number MKVII EGPWCs include an internal Mercury AT GNSS card. The x series part number MK V EGPWCs include an upgraded 486DX5 microprocessor and increased clock speed exclusively for Boeing. The Boeing part number is only a 10 digit number and does not have a 16 digit part number sequence as described below. This part number is required for Boeing unique VSD and IRNAV functions. In order to minimize complexity, the EGPWC utilizes a 16 digit part number. This 16-digit part number will identify the configuration of the EGPWC, which affects form, fit, or function as seen by the pilot. In order to support manufacturing the EGPWC 16-digit part number is mapped to a 10-digit part number for production purposes via a 960-XXXX drawing. The 16 digit part number is defined as follows: 965-XXXX-XXX-YYY-ZZZ (example or ) Hardware (including boot code) = 965-XXXX-XXX Application software = -YYY Configuration software = -ZZZ Terrain database - version not identified in 16 digit part number. Envelope Modulation database - version not identified in 16 digit part number. Reloadable Customer Definitions database (RCD) - version not identified in 16 digit part number. Modifications - All modifications will be identified via mod dots. No mod dots will be skipped. The digits identifying the application software and configuration software will match the respective version numbers of the application software and configuration software. The subcomponents making up each of the items listed above are identified via the 960-XXXX system drawing and the 965-XXXX top assembly drawing. See section for details on configuration management. The following table shows the S/W version equivalency between the xx and the x part numbers: Aside from VSD and IAN/GLS support, the is functionally equivalent to the: No equivalent release Purpose The Product Specification describes all of the basic system functions and design criteria for the Enhanced Ground Proximity Warning System (EGPWS). This document does not fully describe the following non-tso functions hosted in the EGPWS. These are described in the Product Description document referenced in section 2: Runway Awareness and Advisory System (RAAS) Stabilized Approach Monitor Altimeter Monitor Takeoff Flap Configuration Monitor Long Landing Monitor This document serves two major purposes. First, it describes the system functions for EGPWS customers. Secondly, it provides a system description for regulatory authorities. 1.2 System Overview The purpose of the Enhanced Ground Proximity Warning System is to help prevent accidents caused by Controlled Flight HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 11

12 into Terrain (CFIT) or severe windshear. The RAAS and Long Landing Alert options provide calls that increase crew situational awareness during operation on and around airports. The Stabilized Approach Monitor function is a tool that helps reduce the risk of Runway Excursions, long landings, and hard landings, by encouraging stabilized approaches. The Altimeter Monitor function detects and provides an aural and visual advisory for Altitude setting errors typically due to confusion or miscommunication, and/or failure to set the altimeter when passing through the transition altitude. The Takeoff Flap Configuration Monitor provides advance notice (upon runway alignment) of an improper flap configuration. The system achieves these objectives by accepting a variety of aircraft parameters as inputs, applying alerting algorithms, and providing the flight crew with aural alert messages and visual annunciations and displays in the event that the boundaries of any alerting envelope are exceeded. Figure 1.2-1, 1.2-2, and provide an overall system block diagram. GPWS ALGORITHMS AURAL CALLOUTS AUDIO ALERT MESSAGES FLIGHT DECK SPEAKERS AND INTERPHONE AIRCRAFT SENSORS AND SYSTEMS AIRCRAFT PARAMETERS I N P U T P R O C E S S I N G TERRAIN AWARENESS & OBSTACLE ALERTING AND DISPLAY ALGORITHMS TERRAIN CLEARANCE FLOOR ALGORITHMS WINDSHEAR DETECTION AND ALERTING ALGORITHMS RAAS, Approach Monitor, Altimeter Monitor, Long Landing, & Takeoff Flap Algorithms (OPTIONAL) O U T P U T P R O C E S S I N G VISUAL ALERT MESSAGES TERRAIN DISPLAY DATA ALERT LAMPS AND EFIS DISPLAY EFIS NAV. DISPLAY OR Wx RADAR INDICATOR EGPWC FIGURE 1.2-1: ENHANCED GROUND PROXIMITY WARNING SYSTEM AIRCRAFT SENSORS AND SYSTEMS MHz L1 Antenna/LNA AIRCRAFT PARAMETERS I N P U T P R O C E S S I N G GPWS ALGORITHMS AURAL CALLOUTS TERRAIN AWARENESS & OBSTACLE ALERTING AND DISPLAY ALGORITHMS TERRAIN CLEARANCE FLOOR ALGORITHMS WINDSHEAR DETECTION AND ALERTING ALGORITHMS RAAS, Approach Monitor, Altimeter Monitor, Long Landing, & Takeoff Flap Algorithms (OPTIONAL) O U T P U T P R O C E S S I N G AUDIO ALERT MESSAGES VISUAL ALERT MESSAGES TERRAIN DISPLAY DATA FLIGHT DECK SPEAKERS AND INTERPHONE ALERT LAMPS AND EFIS DISPLAY EFIS NAV. DISPLAY OR Wx RADAR INDICATOR PXPRESS GPS SENSOR EGPWC FIGURE 1.2-2: ENHANCED GROUND PROXIMITY WARNING SYSTEM WITH INTERNAL PXPRESS GPS SENSOR HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 12

13 AIRCRAFT SENSORS AND SYSTEMS MHz L1 Antenna/LNA AIRCRAFT PARAMETERS I N P U T P R O C E S S I N G GPWS ALGORITHMS AURAL CALLOUTS TERRAIN AWARENESS & OBSTACLE ALERTING AND DISPLAY ALGORITHMS TERRAIN CLEARANCE FLOOR ALGORITHMS WINDSHEAR DETECTION AND ALERTING ALGORITHMS RAAS, Approach Monitor, Altimeter Monitor, Long Landing, & Takeoff Flap Algorithms (OPTIONAL) MERCURY GPS SENSOR O U T P U T P R O C E S S I N G AUDIO ALERT MESSAGES VISUAL ALERT MESSAGES TERRAIN DISPLAY DATA FLIGHT DECK SPEAKERS AND INTERPHONE ALERT LAMPS AND EFIS DISPLAY EFIS NAV. DISPLAY OR Wx RADAR INDICATOR HS 429 (ARINC 743A GPS DATA) HS 429 (ARINC 743A GPS DATA) EGPWC FIGURE 1.2-3: ENHANCED GROUND PROXIMITY WARNING SYSTEM WITH INTERNAL MERCURY GPS SENSOR The system comprises the following groups of components: Aircraft sensors and other systems providing input signals The Enhanced Ground Proximity Warning Computer (EGPWC) Flight deck audio systems (speakers and interphone) Alert lamps and/or digital outputs to EFIS and EICAS displays (for alert and system status messages) EFIS navigation display (ND) 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 Sensor The system is designed to be fully compatible with normal operations of commercial aircraft: unwanted alerts will be very rare if the flight crew maintains situational awareness with respect to the terrain and if the crew follows correct avoidance procedures for any significant windshear activity. Several main alerting functional areas are integrated into the EGPWC, which is a single Line Replaceable Unit (LRU). Except for basic GPWS, each function is program pin or RCD selectable. The functional areas are: Basic Ground Proximity Warning Altitude awareness callouts Excessive bank angle alerting Windshear detection and alerting Terrain and Obstacle Awareness Alerting as well as optional display of this information, and Terrain Clearance Floor Runway Awareness and Advisory System Long Landing Monitor Altimeter Monitor Stabilized Approach Monitor Takeoff Flap Configuration Monitor Low Airspeed Monitor (737NG only) The basic Ground Proximity Warning (GPW) function is the backbone of the system, and the primary design objective has HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 13

14 been to maintain the integrity of this function independent of the other functions. For example, loss of the terrain awareness function will not affect the operation of the GPW functions (provided that the input signals necessary for GPW operation are still available). In addition to the main alerting functions, the computer also performs the following auxiliary functions: Input signal processing (including filtering and signal monitoring). Alert output processing (including alert prioritization, voice message synthesis, audio output and display and warning lamp drivers). Built-in test and monitoring including cockpit-activated self test. Interface with CMC/CFDS/CAIMS maintenance systems with interactive protocols when the aircraft is on the ground. Front panel PCMCIA interface for uploading software and databases. Front panel maintenance test connector, test button, and headset jack for system checkout and troubleshooting. System status LEDs located on the LRU front panel to indicate External Fault, Computer OK and Computer Fail conditions. HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 14

15 1.2.1 Ground Proximity Warning As shown in Figure , the EGPWS provides the basic Ground Proximity Warning System (GPWS) alerting in six modes. MODE 1 EXCESSIVE DESCENT RATE "SINKRATE" "PULL UP!" MODE 2 EXCESSIVE TERRAIN CLOSURE RATE "TERRAIN..TERRAIN" "PULL UP!" MODE 6 EXCESSIVE BANK ANGLE "BANK ANGLE!" ALTITUDE CALL-OUTS "...FIVE HUNDRED..." MODE 3 SINK AFTER TAKEOFF "DON'T SINK!" MODE 5 EXCESSIVE DEVIATION BELOW GLIDESLOPE "GLIDESLOPE" MODE 4 TOO CLOSE TO TERRAIN "TOO LOW - TERRAIN" "TOO LOW - GEAR" "TOO LOW - FLAPS" FIGURE : GROUND PROXIMITY WARNING MODES Modes 1 and 3 through 5 are in accordance with the requirements of TSO-C92c, TSO-C151a, DO-161A, CAA Spec 14 and ICAO Annex 6. Prior to release 218 Mode 2 met the above requirements under all operating conditions. Beginning with Release 218, Mode 2 performance is modified to reduce unwanted warnings when the Terrain Awareness function is operating in a state of high integrity. Mode 2 reverts to standard performance when the high integrity state is not met. Analysis shows that overall EGPWS performance still provides an equivalent level of safety even when Mode 2 performance is modified to non-tso levels. Mode 6 provides additional protection in the form of a selectable menu of radio altitude callouts during landing approach, and an optional alert for excessive bank angle. (It should be noted that the numbering of the modes is derived from the history of the development of GPWS, and does not imply any special hierarchy). The basic GPW modes are tailored for the application by selection of various options, which are program pin-selectable during installation of the EGPWS computer. An overview of the functioning of each of the GPW modes is given in the following paragraphs. Full details of the operation of the modes are given in section 6.2. An audio declutter feature is standard which activates the voice alert once, then not again unless the situation has degraded by 20%. This feature applies to Modes 1, 3, 4, and 5. As an option, the audio declutter feature can be disabled by program pin option. With audio declutter disabled, the alert is continuously repeated until the alerting situation is corrected. HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 15

16 Mode 1 - Excessive Descent Rate Mode 1 provides alerts when the aircraft has excessive descent rate close to the terrain (see figure ). RADIO ALTITUDE (FEET) "SINKRATE" "PULL UP!" "SINKRATE" "PULL UP!" DESCENT RATE (FEET/MINUTE) FIGURE : MODE 1 - EXCESSIVE DESCENT RATE If the aircraft penetrates the outer alert boundary, the voice aural Sinkrate is generated, and alert discretes are output by the computer for driving visual annunciators. If the aircraft penetrates the inner alert boundary, the voice aural Pull Up! is generated and visual alert discretes are also output. The alert boundaries are defined in terms of aircraft vertical speed (barometric vertical speed supplemented by inertial vertical speed when available) and radio altitude. Improvements to the mode 1 alert boundaries are as follows: Envelope Modulation - (see paragraph ) Glideslope deviation bias - The outer alert boundary ( Sinkrate ) is desensitized when the aircraft is above the glideslope beam. This prevents unwanted alerts when the aircraft is safely capturing the glideslope (or repositioning to the centerline) from above the beam. Steep approach bias - If steep approach mode is defined for a given aircraft type it desensitizes the alert boundaries to permit safe, but steeper than normal, instrument precision approaches (e.g. MLS or GPS approaches) without unwanted alerts. HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 16

17 Mode 2 - Excessive Terrain Closure Rate Mode 2 provides alerts when the aircraft is closing with the terrain at an excessive rate. It is not necessary for the aircraft to be descending in order to produce a Mode 2 alert; level flight (or even a climb) towards obstructing terrain can result in hazardous terrain closure rate. The terrain closure rate variable is computed within the EGPWS computer by combining radio altitude and vertical speed in a non-linear complementary filter. The standard Mode 2 performance is described below. Starting in Release 218 Mode 2 performance is modified to reduce unwanted warnings when the Terrain Awareness function is operating in a state of high integrity. Mode 2 reverts to standard performance when the high integrity state is not met. Additional details of Mode 2 performance is described in section Mode 2 has two sub-modes, referred to as Mode 2A and Mode 2B, the active sub-mode being determined by aircraft configuration. The Mode 2A alerting envelope is illustrated in Figure , and the Mode 2B envelope is shown in Figure RADIO ALTITUDE (FEET) "TERRAIN TERRAIN" Speed Expansion "PULL UP!" TERRRAIN CLOSURE RATE (FEET/MIN) "TERRAIN TERRAIN" "PULL UP!" FIGURE : MODE 2A - EXCESSIVE TERRAIN CLOSURE RATE Mode 2A is enabled when the conditions for enabling Mode 2B are not satisfied (see below). If the aircraft penetrates the mode 2A alerting envelope, the voice aural Terrain Terrain is generated initially, and alert discretes are output for driving visual annunciators. If the aircraft continues to penetrate the envelope, then the voice aural Pull Up! is repeated continuously until the warning envelope is exited. At this point an altitude gain function, described in section , activates. The aural reverts to Terrain, Terrain... but will only be given if the terrain clearance continues to decrease. The visual alert will remain on until either the aircraft has gained 300 feet of barometric altitude, or 45 seconds has elapsed, or the radio altimeter loses track. At that point all visual alerts stop. As shown in Figure , the upper boundary of the mode 2A alert envelope varies as a function of aircraft speed and the availability of the Terrain Awareness function. The boundary expands to provide increased alert times at higher airspeeds as airspeed increases from 220 knots to 310 knots, and is reduced when the Terrain Awareness function is available and of high integrity. HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 17

18 2500 RADIO ALTITUDE (FEET) "TERRAIN TERRAIN" "PULL UP!" "TERRAIN TERRAIN" "PULL UP!" TERRRAIN CLOSURE RATE (FEET/MIN) FIGURE : MODE 2B - EXCESSIVE TERRAIN CLOSURE RATE Mode 2B provides a desensitized alert envelope, permitting normal landing approach maneuvering close to the terrain without producing unwanted alerts. Mode 2B is enabled for four conditions: Whenever flaps are selected to the landing position If the aircraft is performing an ILS approach and is within ±2 dots of both localizer and glideslope centerlines If the aircraft is within 5 miles (10 miles starting in 218) and 3500 ft of the destination runway and the Terrain Awareness function is enabled and of high integrity For the first 60 seconds after takeoff If the aircraft penetrates the mode 2B envelope with either gear or flaps not in landing configuration, the voice aural Terrain, Terrain is generated initially, and alert discretes are output for driving visual annunciators. If the aircraft continues to penetrate the envelope, then the voice aural Pull Up! is repeated continuously until the warning envelope is exited. If the aircraft penetrates the mode 2B envelope with both gear and flaps in landing configuration, the voice aural Terrain... is repeated until the envelope is exited. Envelope Modulation, as described in section , is used to eliminate, wherever possible, operationally-induced unwanted warnings. HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 18

19 Mode 3 - Altitude Loss After Takeoff Mode 3 provides alerts when the aircraft loses a significant amount of altitude immediately after takeoff or during a missed approach, as shown in Figure RADIO ALTITUDE (FEET) "DON'T SINK" "DON'T SINK" ALTITUDE LOSS (FEET) FIGURE : MODE 3 - ALTITUDE LOSS AFTER TAKEOFF The altitude loss variable is based on the altitude (MSL) value from the time of the beginning of the inadvertent descent. The amount of altitude loss, which is permitted before an alert is given, is a function of the height of the aircraft above the terrain, as shown in Figure Mode 3 is enabled after takeoff or go around when landing gear or flaps are not in landing configuration, and stays enabled until the EGPWS computer detects that the aircraft has gained sufficient altitude that it is no longer in the takeoff phase of flight. If the aircraft penetrates the mode 3 boundary, the voice aural Don t Sink is generated, and alert discretes are provided for activation of visual annunciators. The visual annunciators remain active until a positive rate of climb is re-established. HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 19

20 MIN TERRAIN CLEARANCE (FT) Product Specification Mode 4 - Unsafe Terrain Clearance Mode 4 provides alerts for insufficient terrain clearance with respect to phase of flight and speed. Mode 4 exists in three forms: 4A, 4B and 4C. Mode 4A is active during cruise and approach with gear not in landing configuration. Mode 4B is also active in cruise and approach, but with gear in landing configuration. Mode 4C is active during the takeoff phase of flight with either gear or flaps not in landing configuration. As shown in Figure the standard upper boundary for mode 4A is at 500 feet radio altitude. If the aircraft penetrates this boundary with the gear still up, the voice aural will be Too Low Gear. Above 190 knots (207 knots for KC-135) the upper boundary increases linearly with airspeed to a maximum of 1000 feet radio altitude at 250 knots or more. Penetrating this boundary produces a Too Low Terrain aural. MODE 4A UNSAFE TERRAIN CLEARANCE "TOO LOW TERRAIN" "TOO LOW TERRAIN" AIRCRAFT SLOWED TO LESS THAN 190 KTS "TOO LOW GEAR" UNSAFE TERRAIN CLEARANCE GEAR UP, FLAPS UP KC-135 BOUNDARY TOO LOW GEAR ALERT AREA TOO LOW TERRAIN ALERT AREA COMPUTED AIRSPEED (KTS) RUNWAY FIGURE : MODE 4A - UNSAFE TERRAIN CLEARANCE - GEAR UP When the landing gear is lowered, the upper boundary decreases to 245 feet. This is reduced to 150 feet on those aircraft types that routinely delay full flap deployment (Turbo Prop) until the airfield is within approximately one nautical mile. Penetration below 159 knots (185 knots for KC-135 & Boeing 747-8) results in the Too Low Gear messages with gear up or the Too Low Flaps message with gear down and flaps not in landing configuration, while above 159 knots (185 knots for KC-135 & Boeing 747-8) the message is Too Low Terrain. Mode 4B is illustrated in figure HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 20

21 MIN TERRAIN CLEARANCE (FT) MIN TERRAIN CLEARANCE (FT) Product Specification MODE 4B UNSAFE TERRAIN CLEARANCE "TOO LOW TERRAIN" "TOO LOW TERRAIN" AIRCRAFT SLOWED TO LESS THAN 159 KTS GEAR DOWN "TOO LOW FLAPS" UNSAFE TERRAIN CLEARANCE GEAR DN, FLAPS UP TOO LOW TERRAIN ALERT AREA KC-135 & BOUNDARY TOO LOW FLAPS ALERT AREA COMPUTED AIRSPEED (KTS) RUNWAY FIGURE : MODE 4B - UNSAFE TERRAIN CLEARANCE - GEAR DOWN Mode 4C is based on a minimum terrain clearance, or floor, that increases with radio altitude during takeoff. A value equal to 75% of the current radio altitude is accumulated in a long term filter. Any decrease of radio altitude below the filter value with gear or flaps up will result in the voice aural Too Low Terrain. Mode 4C is illustrated in figure MODE 4C UNSAFE TERRAIN CLEARANCE "TOO LOW TERRAIN" "TOO LOW TERRAIN" UNSAFE TERRAIN CLEARANCE GEAR UP, FLAPS UP 1500 FPM CLIMB RATE TAKE-OFF OVER FLAT TERRAIN OR WATER ALERT AREA (<190 KTS) ALERT AREA (>250 KTS) RADIO ALTITUDE (FT) FIGURE : MODE 4C - UNSAFE TERRAIN CLEARANCE - AT TAKEOFF Optional variations to the mode 4 alert boundaries are available as follows: Envelope Modulation, as described in section Overflights during holding patterns, as described in section Disabling of mode 4A/B speed expansion when Terrain Clearance Floor alerting is enabled or the Terrain Awareness function is available and of high integrity. HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 21

22 MIN TERRAIN CLEARANCE (FT) Product Specification Mode 5 - Below Glideslope Mode 5 provides two levels of alerting when the aircraft flight path descends below the glideslope beam on front course ILS approaches. The first alert activation occurs whenever the aircraft is more than 1.3 dots below the beam and is called a soft glideslope alert because the volume level of the Glideslope alert is approximately one half (-6 db) that of the other alerts. A second alert boundary occurs below 300 feet radio altitude with greater than 2 dots deviation and is called loud or hard glideslope alert because the volume level is increased to that of the other alerts. Mode 5 is illustrated in figure MODE 5 EXCESSIVE GLIDESLOPE DEVIATION GLIDESLOPE BEAM CENTER SOFT "GLIDESLOPE" HARD "GLIDESLOPE" MODE 5 BELOW GLIDESLOPE ALERT GEAR DOWN HARD ALERT AREA SOFT ALERT AREA GLIDESLOPE DEVIATION (DOTS FLY UP) SOFT ALERT AREA HARD ALERT AREA RUNWAY Other variations to the mode 5 alert boundaries are as follows: FIGURE : MODE 5 - EXCESSIVE GLIDESLOPE DEVIATION Envelope Modulation, as described in section Localizer intercept, as described in section For release -236 and later Mode 5 alerting is provided on Localizer Performance and Vertical Guidance (LPV) approaches given the aircraft is configured appropriately and required data is available. HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 22

23 Mode 6 - Callouts Mode 6 provides alerts and callouts for descent below predefined altitudes, decision height (DH), minimums, approaching decision height and approaching minimums as shown in figure Alerts for excessive roll or bank angle are also provided as part of this mode as shown in figure The Excessive Bank Angle aural alerts are given twice, and then suppressed unless the roll angle increases by an additional 20%. Menus containing minimums type callouts require the availability of either a less than DH discrete input, or an ARINC 429 selected minimums input. Menus containing approaching minimums type callouts require the availability of an ARINC 429 selected DH input. In either case the input must be both available and defined in the ICD for the selected aircraft configuration. For example; a GIV operator can select a menu containing Minimums since a discrete DH input is available; however, they cannot select a menu with Approaching Minimums due to the lack of an ARINC 429 selected DH input. If they did strap for a menu with Approaching Minimums a GPWS Fail indication would be given. Alternately, a GV operator can select a menu with both Minimums and Approaching Minimums as an ARINC 429 selected minimums input is defined. A further consideration is that a few installations allow for the minimums and approaching minimums callouts to be triggered either by radio altitude DH or barometric altitude MDA. This capability requires the definition of an ARINC 429 selected DH/MDA input and is only available on a limited number of installations. Specific callouts are program pin selectable from predefined menus. Mode 6 alerts and callouts produce aural and ARINC 429 output indications, but do not produce visual indications. A Smart five hundred foot callout is available. This callout will only be issued when the system detects that a non-precision approach is being performed or that the aircraft is outside ±2 dots glideslope or localizer deviation. Note: In part number only, the Smart Callout is disabled whenever ALL of the following conditions occur: 1) Terrain Awareness and Geometric Altitude functions are active and of high integrity. 2) The aircraft is within 5 NM of the runway. 3) The aircraft is within 3500 feet of the runway elevation. In all subsequent (and previous) part numbers, the activation of the smart callout is only dependent on lack of ILS (or excessive deviation from it). Part number 208(Mod 1)-208 will no longer disable the Smart Callout for the conditions listed above, but will be dependent only on ILS and excessive ILS deviation. An optional discrete input provides the ability to force the mode 6 audio level to low volume (if it is not already defaulted to low volume). This enables operators to control the mode 6 volume level with activation of windscreen rain removal or if lower volume callouts are desired at all times. MODE 6 ALTITUDE AWARENESS CALLOUTS * "APPROACHING "MINIMUMS" MINIMUMS" "FIFTY" * A selected DH ARINC 429 input must be available and in the selected configuration as defined in the ICD for this callout to be available RUNWAY FIGURE : MODE 6 ALTITUDE CALLOUTS HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 23

24 TERRAIN CLEARANCE (FEET) Product Specification EXCESSIVE BANK ANGLE WARNING "BANK ANGLE BANK ANGLE"" 2500 AIR TRANSPORT and KC-135 BANK ANGLE CURVE BIZJET BANK ANGLE CURVE FT KC-135 BANK ANGLE CURVE 50 FT 200 FT 150 FT 0 +/-10 +/-20 +/-30 +/-40 ROLL ANGLE (+/- DEG) +/-50 FIGURE : EXCESSIVE BANK ANGLE Envelope Modulation The Envelope Modulation feature provides improved alerting protection at key locations throughout the world, while improving nuisance margins at others. This is made possible with the use of navigational signals from GPS or Flight Management Systems (FMS). All position data is cross-checked to ground based navigational aids, altimeter and heading information, and stored terrain characteristics prior to being accepted for Envelope Modulation purposes. This guards against possible navigational position errors. Modes 4, 5, and 6 are expanded at some 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. The tables that store the Envelope Modulation data are maintained in non-volatile memory. HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 24

25 Terrain Clearance Floor The Terrain Clearance Floor (TCF) function, simplified illustration in Figure , adds an additional element of protection to the standard Ground Proximity Warning modes. It creates an increasing terrain clearance envelope around the intended airport runway directly related to the distance from the runway. TCF alerts are based on current aircraft location, nearest runway center point position and radio altitude. TCF is active during takeoff, cruise and final approach. This alert mode complements existing mode 4 protection by providing an alert based on insufficient terrain clearance even when in landing configuration. Alerts for TCF illuminate EGPWS cockpit lamps and produce aural alerts. When an aircraft penetrates the TCF alert envelope the voice aural Too Low Terrain will be given. With audio declutter enabled (default), the voice aural will occur once when the initial envelope penetration occurs, and one time thereafter for each 20% degradation in radio altitude. At the same time the EGPWS warning lamps will illuminate. The lamps will remain on until the alert envelope is exited. With audio declutter disabled via the audio declutter disable program pin, the voice aural will be continuous until the alerting envelope has been exited. In the part number additional TCF features were introduced. In Release 218 the TCF curve was modified to provide improved advisories near the runway end. Refer to section for more information. "TOO LOW TERRAIN" RUNWAY 4 N M 400 AGL 1 2 N M 1 5 N M 700 AGL FIGURE : TERRAIN CLEARANCE FLOOR HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 25

26 Other Non-TSO Functions Speed Brake Alert (KC-135) Product Specification The KC-135 speed brake alert provides both aural and visual indication to the crew that the speed brakes are deployed while the aircraft is below 1000 feet AGL. The voice aural is Speed Brake (pause) Speed Brake, where the pause is 0.75 seconds of silence. The message is repeated every seven seconds until the speed brakes are retracted or the function is manually inhibited. The alert inhibit function allows the crew to prevent or stop the alert. The inhibit function has an automatic reset feature when the aircraft climbs through 2000 AGL or when the landing gear or flaps transition from down to up Runway Awareness and Advisory System The Runway Awareness and Advisory System (RAAS) is an optional feature that is activated via an RCD. It offers improved situational awareness for the flight crew in order to help lower the probability of runway incursion incidents and accidents by providing timely aural messages to the flight crew during ground taxi, takeoff (including rejected takeoffs), final approach, and landing/roll-out operations. Existing EGPWS protection and operation is unaltered by the addition of RAAS. A complete description of this feature may be found in Honeywell document, , Product Description, Flight Safety Functions of the Enhanced Ground Proximity Warning System Long Landing Monitor The Long Landing Monitor function is an optional feature that is activated via an RCD. It offers the pilot increased runway awareness and complements the RAAS Distance Remaining callouts. The function advises the crew of their position during a landing when the aircraft has not touched down in a nominal amount of time and/or distance. Existing EGPWS protection and operation is unaltered by the addition of the Long Landing. A complete description of this feature may be found in Honeywell document, , Product Description, Flight Safety Functions of the Enhanced Ground Proximity Warning System Stabilized Approach Monitor The Stabilized Approach Monitor is an optional feature that is activated via an RCD, and offers a significant safety advancement to supplement flight crew awareness of unstabilized approaches. Existing EGPWS protection and operation is unaltered by the addition of the Stabilized Approach Monitor. The Stabilized Approach Monitor specifically has the following monitoring functions: Landing Flap Monitor Issues an annunciation if the landing flaps are not set. Excessive Speed Monitor Issues an annunciation if the aircraft speed becomes excessive compared to the final approach speed (Vref or Vapp). Excessive Approach Angle Monitor Issues an annunciation if the aircraft approach angle to the runway threshold becomes too steep. Unstabilized Approach Monitor Issues an annunciation if the aircraft has not been stabilized at the 450 foot Gate. A complete description of this feature may be found in Honeywell document, , Product Description, Flight Safety Functions of the Enhanced Ground Proximity Warning System Altimeter Monitor The Altimeter Monitor is an optional feature of the EGPWS that is activated via an RCD, and provides the flight crew with awareness of problems with the pressure altitude system. Existing EGPWS protection and operation is unaltered by the addition of the Stabilized Approach Monitor. A complete description of this feature may be found in Honeywell document, , Product Description, Flight Safety Functions of the Enhanced Ground Proximity Warning System Takeoff Flap Configuration Monitor The Takeoff Flap Configuration Monitor is an optional feature of the EGPWS that is activated via an RCD and provides the flight crew with awareness of improper Flap setting when the aircraft is lined-up on a runway in advance of takeoff. With the benefit of a virtual box around the EGPWS runway data, the alert is provided well before thrust levers are advanced for runway takeoff. Existing EGPWS protection and operation is unaltered by the addition of the Takeoff Flap Configuration Monitor. A complete description of this feature may be found in Honeywell document, , Product Description, Flight Safety Functions of the Enhanced Ground Proximity Warning System. HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 26

27 Low Airspeed Monitor (737NG Only) As of the -232/055 part number, the EGPWS provides a Low Airspeed Monitor function for the 737NG. In several incidents and accidents a slow loss of airspeed was not noticed by the pilots. With the advent of glass cockpit (EFIS) displays, Boeing added a yellow flashing box around the digital airspeed number when the aircraft drops below 70% of the amber airspeed band (the amber band spans the airspeed range between Stick Shaker Speed and Minimum Operating Speed). The AIRSPEED LOW, AIRSPEED LOW aural issued by the EGPWS is designed to be coincident with that flashing. The Low Airspeed Monitor is a basic function on the 737NG. In other words, once a -232/055 (or later) EGPWS is installed the monitor will be active Terrain and Obstacle Awareness The Terrain and Obstacle Awareness alerting and display functions use aircraft geographic position, aircraft altitude and a terrain and obstacle database to predict potential conflicts between the aircraft flight path and the terrain, and to provide graphic displays of the conflicting terrain or obstacle, as illustrated by the block diagram, Figure AIRPORT POSITION DATABASE TERRAIN CLEARANCE FLOOR ALGORITHM AIRCRAFT POSITION DATA (LAT/LNG) TERRAIN/OBSTACLE ELEVATION DATABASE BAROMETRIC ALTITUDE GROUND TRACK GROUND SPEED VERTICAL SPEED ROLL ATTITUDE TERRAIN/OBSTACLE AWARENESS ALERTING ALGORITHMS TERRAIN/OBSTACLE CAUTION ALERT TERRAIN/OBSTACLE WARNING ALERT DISPLAY ALGORITHMS DISPLAY DATA FIGURE : TERRAIN & OBSTACLE AWARENESS FUNCTIONS Terrain Alerting The Terrain Awareness alerting algorithms continuously compute terrain clearance envelopes ahead of the aircraft. If the boundaries of these envelopes conflict with terrain elevation data in the terrain database, then alerts are issued. Two envelopes are computed, one corresponding to a terrain caution alert level and the other to a terrain warning alert level, as described in section The algorithms are designed to meet the following criteria: Operational compatibility - minimal unwanted alerts during normal flight operations and approach procedures Improved terrain awareness warning times - provide adequate alert times for all flight phases and conditions Robustness - tolerant of aircraft position errors, altitude signal errors and database errors The caution and warning envelopes use the Terrain Clearance Floor as a baseline, and look ahead of the aircraft in a volume which is calculated as a function of airspeed and flight path angle. Simplified diagrams of the terrain caution and warning envelopes are shown in Figures and If the aircraft penetrates the caution envelope boundary, the voice aural Caution Terrain, Caution Terrain is generated, and alert discretes are provided for activation of visual annunciators. Simultaneously, terrain areas that conflict with the caution criteria are shown in solid yellow color on the terrain display, as described in section If the aircraft penetrates the warning envelope boundary, the voice aural Terrain Terrain, Pull Up! is generated, and alert discretes are provided for activation of visual annunciators. Simultaneously, terrain areas that conflict with the warning HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 27

28 criteria are shown in solid red color on the terrain display, as described in section Terrain Display The EGPWS computer outputs a display of terrain data in weather radar format per ARINC-708/708A (ARINC 453) or per the Honeywell Picture Bus format. The terrain data can be displayed either on a dedicated weather radar indicator or, if the aircraft is equipped with an Electronic Flight Instrument System (EFIS), on the electronic Navigation Display (ND) or Multi- Function Display (MFD). When the terrain display is present, it replaces the weather radar display. The terrain display can be made available to the flight crew at any time. When the conditions for either a terrain caution or a terrain warning are detected, the EGPWS computer supplies a discrete pop-up signal that can be used to switch flight deck displays between the weather radar and the terrain display. Terrain is depicted on the display as shown in Figure BACKGROUND TERRAIN YELLOW CAUTION AREA "CAUTION TERRAIN, CAUTION TERRAIN" RED WARNING AREA "TERRAIN TERRAIN, PULL UP!" FIGURE : TERRAIN AWARENESS DISPLAY ON EFIS NAVIGATION DISPLAY (SIMULATED) Areas of terrain that satisfy the terrain caution alert criteria are shown in solid yellow, and areas of terrain that satisfy the terrain warning alert criteria are shown in solid red. Terrain which is significantly close to the aircraft, but which satisfies neither the caution or warning criteria, is shown as a green, yellow or red dot pattern whose perceived brightness is less than the yellow caution area. The density of the pattern is coarsely varied to depict terrain altitude with respect to the aircraft. Reference section for a detailed description of the display presentation Obstacle Alerting The EGPWS has the capability to detect and annunciate obstacle alerts. The same visual annunciations that are activated for terrain caution/warning are activated for obstacle caution/warning. The actual alert voices for obstacles are controlled via the selected audio menu. For the basic menu the obstacle voice is similar to the terrain alert, except that for an obstacle alert, the word Obstacle replaces the word Terrain. Obstacle alerting is activated by defining obstacle alerting as basic to the airplane configuration, or if not basic to the aircraft type via program pin (Note). Note: Obstacle alert activation via basic definition or program pin implemented in 965-XXXX-XXX HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 28

29 1.2.3 Mode 7 - Windshear Alerting Mode 7 produces optional alerts for flight into an excessive windshear condition during takeoff or final approach in accordance with TSO-C117a. The windshear caution, or pre-alert as it is sometimes referred to, provides visual, ARINC 429 and optional aural output indications. The windshear warning also produces visual, ARINC 429 and aural output indications. Windshear detection is active between 10 and 1500 feet AGL during the initial takeoff and final approach phases of flight. Alerts are provided when the level of windshear exceeds predetermined threshold values. The actual windshear value measured represents the vector sum of inertial vs. airmass accelerations along the flight path and perpendicular to the flight path. These shears result from vertical winds and rapidly changing horizontal winds. Windshear warning alerts are given for decreasing head wind (or increasing tail wind) and severe vertical down drafts. Windshear caution alerts are given for increasing head wind (or decreasing tail wind) and severe up drafts. The windshear microburst phenomenon and windshear caution and warning levels are illustrated in figure MODE 7 EXCESSIVE WINDSHEAR DETECTION DECREASING HEADWIND (KTS PER SEC) WINDSHEAR WARNING AREA WINDSHEAR CAUTION LAMP UPDRAFT (FEET PER MIN) MICROBURST DOWNDRAFT (FEET PER MIN) CAUTION WINDSHEAR AREA INCREASING HEADWIND (KTS PER SEC) "WINDSHEAR WINDSHEAR WINDSHEAR" RUNWAY FIGURE : TYPICAL MICROBURST ENCOUNTER Maintenance/Test Interfaces In addition to power-up and continuous BIT, user activated tests, via discrete test switches, and/or maintenance system commands are supported. HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 29

30 Cockpit Self Test For all aircraft types that provide a cockpit mounted test switch, it can be used to manually initiate tests and BIT annunciation anytime the aircraft is on ground. Prior to , if above 2000 feet AGL the cockpit self test can be initiated provided that no alert is in progress. A test switch on the unit s front panel, along with a headphone jack, is also provided to give the flexibility of running tests both in the cockpit and at the LRU. For some maintenance systems the test command is input via an ARINC 429 input word. Several levels of information may be voice annunciated by pressing the self-test switch. The test sequences can be summarized as follows. 1) Go/No Go Test: This sequence indicates the systems ability to perform all of its configured functions. For this sequence, when the test switch is activated, the cockpit lamps are activated and voices are issued to indicate what functions are correctly operating. For instance, if no faults exist on an installation that uses the Terrain Awareness function in addition to basic GPWS and windshear, then the result of the self-test would typically be: Glideslope---- Pull Up-----Windshear Windshear Windshear----Terrain Terrain, Pull Up However, if no valid glideslope input was present then the sequence would be Glideslope INOP----- Pull Up-----Windshear Windshear Windshear----Terrain Terrain, Pull Up For installations that use a terrain display the interface with the display will be tested by viewing a terrain test image on the appropriate cockpit EFIS Display or separate weather radar display. During system self-test all INOP annunciators are activated. 2) Current faults: This sequence annunciates all faults, if any, that currently exist. It will distinguish between internal and external faults. If no faults exist then the message No Faults is given. 3) Configuration information: This sequence annunciates the versions of the resident hardware, software and databases versions. Also annunciated are the current program pin option selections, including voice and callouts menus selected. 4) Fault history: This sequence annunciates all system faults that were logged for the past ten flight legs. (Information on the last 64 legs is accessible via the RS-232 interface). 5) Warning history: This sequence annunciates all EGPWS alerts that were logged for the past ten flight legs. (Information on the last 64 legs is accessible via the RS-232 interface). 6) Discrete input test: This sequence annunciates discrete input transitions to aid system installation and maintenance. Reference section for detailed description of self-test functionality Maintenance System Interface The EGPWC supports ARINC 429 interactive protocols to provide maintenance information, including fault history, for aircraft installations that use an on-board central maintenance system. If date, time, flight number and aircraft ID are provided, this information can also be tagged to fault history records. In addition, maintenance system test commands can be used to initiate EGPWS self test. For other installations non-interactive maintenance data is provided on the ARINC 429 bus. This data consists of internal faults, external bus faults, input discrete status and faults, and program pin option status. Reference section for more detail Front Panel Test Interface The EGPWC provides a front panel test connector which can be connected to a VT 101 (terminal emulation device) or a portable PC to both receive and control internal data. This test interface can be used for engineering and production testing, both on the bench and at the aircraft. The LRU front panel also contains a test switch, 600-ohm headset jack, and several fault LEDs. The test switch and audio jack allow for performing the cockpit self test from the LRU. The status LEDs include External Fault, Computer OK, and Computer Fail. A PCMCIA interface is also provided at the front panel for data loading/unloading purposes. Reference section for more detail. HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 30

31 1.2.5 System Elements Architecture Figure contains a block diagram of typical EGPWS inputs. Figure contains a block diagram of typical EGPWS outputs. Note that this describes only one possible interface as in some installations combined data is made available via Data Acquisition Units (DAU), Integrated Avionics Computers (IAC), or Input/Output Concentrators (IOC) in lieu of directly from the source system. Also note that this figure does not represent a MKVII EGPWC type of interface. As can be seen in the figures, single, and dual and in some cases triple input redundancy is accommodated. When used, the terrain display output is either provided directly to symbol generators, or to display switching relays. The following table summarizes the type and quantity of I/O available with both versions of the EGPWC. Input/Output Type Note: is the MKV EGPWC, is the MKVII EGPWC. Quantity Quantity ARINC 429 inputs The inputs can be software programmed for either high or low speed operation for -06x 8 7 for -06x RS-422 inputs 1 1 Multiplexed with an ARINC 429 receiver. ARINC 429 output channels -06x LRUs add 2 ARINC 429 GPS output channels 2 4 for -06x 1 3 for -06x Picture Bus (ARINC 453/708) output channels 2 2 RS-422 outputs wire AC analog input channels wire AC/DC analog input channels 4, DC only 29 3 wire DC ratio analog input channels, (ARINC 595) DC barometric altitude rate 0 1 Ground activated input discretes VDC activated input discretes 8 23 Program pin inputs used to select configuration and optional features (-208+) Discrete outputs Drivers for lamps, EFIS/EICAS discrete inputs or external display relay control. Audio outputs 2 2 An 8-ohm speaker output and a 600-ohm interphone output that is also available at the LRU front panel. The audio volume levels are software controlled. Precision reference output For excitation of external sources, such as AOA vane mounted potentiometers. 10 VDC 5 VDC Phantom power output 0 1 For excitation of remote ADC or BIAX accelerometers. Rear connector RS-232 interface 1 1 For the -06x LRUs the rear RS-232 pins are used for an ARINC 429 GPS output channel Front connector RS-232 interface Provided to aid in maintenance troubleshooting and engineering and production testing. This interface allows for access and control of internal EGPWS data and outputs. 0 for -06x 0 for -06x 1 1 A front panel self test switch, audio jack, and status LEDs are also provided for maintenance and fault isolation. The primary processing is accomplished with a 486DX2 microprocessor. HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 31

32 System Components Refer to section 2.1 for EGPWC outline drawings. For MKV EGPWC, xx-xxx-xxx, x-xxx-xxx with internal PXpress GPS, and x-xxx-xxx with internal Mercury AT GNSS: 28 V MKV Rear Connector: MOUNTING TRAY-SHORT BASIC ARINC 600 Source/Vendor Vendor Part Number Honeywell Barry Controls T600-2-S-R-A-xxxx Item Qty Vendor & Part No. EGPWC Rear Connector (ARINC 600 Size 1): Honeywell AMP Cannon Souriau NIC66F11A10AA1 BK AD S611-MG F0 05W2-P0010-L Lower Plug Power Pins Lower Plug Ground Pin Top and Middle Plug I/O Pins GPS Coax Connector RF Socket Size for RG 142 Type N/A N/A 115 VAC MKV Rear Connector: Item Qty Vendor & Part No. EGPWC Rear Connector (ARINC 600 Size 1): Honeywell AMP Cannon Souriau NIC66F11A08AA1 BK AD S611-MG F0 05W2-P0008-L Lower Plug Power Pins Lower Plug Ground Pin Top and Middle Plug I/O Pins GPS Coax Connector RF Socket Size N/A for RG 142 Type N/A N/A HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 32

33 For MKVII EGPWC, xx-xxx-xxx: 1) The following tray part numbers are the same part numbers previously supplied for the non-enhanced MK-VII. These part numbers can be used when installing an ENHANCED MK-VII P/N XX WITHOUT internal GPS receiver. TRAY-SHORT BASIC Honeywell P/N Source/Vendor Vendor Part Number Honeywell Barry Control Hollingsead International N/A Electrical & Mechanical Technologies (EMTEQ) MT4-2005S TRAY-LONG BASIC Honeywell P/N Source/Vendor Vendor Part Number Honeywell N/A Barry Control N/A Hollingsead International N/A Electrical & Mechanical Technologies (EMTEQ) MT4-2008S 2) The following tray part numbers can be used when installing an ENHANCED MK-VII P/N XX WITH internal GPS receiver. TRAYS WITH GPS ANTENNA CONNECTOR MOUNTING HOLE Vendor/Supplier Short Tray P/N Long Tray P/N Honeywell Electrical & Mechanical Technologies (EMTEQ) MT4-2017S MT4-2023S 3) The following tray part numbers are recommended for improved cooling. TRAYS with Cooling Cavity and with GPS ANTENNA CONNECTOR MOUNTING HOLE Vendor/Supplier Short Tray P/N Long Tray P/N Honeywell Electrical & Mechanical Technologies (EMTEQ) MT4-2014S MT4-2020S There are two tray connectors that interface with the Enhanced MK-VII computer. These two connectors are the same as previously used by the MK-VII GPWS. The upper connector (J2) is an ARINC 600 connector (150 contact style) and the lower connector (J1) is an ARINC 404A (Section A-40 Contacts/Section B-40 contacts). NOTE: When retrofitting a MK-VII with an Enhanced MK-VII new wiring and some re-terminations are required; replacement of the existing connectors is NOT necessary (unless damaged). For Enhanced MK-VII 115VAC, upper connector (J2) MUST be keyed (polarized) to ARINC position 10. For Enhanced MK-VII 28VDC, upper connector (J2) MUST be keyed (polarized) to ARINC position 10, and the lower connector (J1) MUST be keyed (polarized) to ARINC position 88. HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 33

34 MK-VII UPPER CONNECTOR (J2) (both 115VAC and 28VDC) Without Contacts (pins) With Contacts (pins) UPPER Honeywell P/N Honeywell P/N CONNECTOR J2 ITT-Cannon P/N SGA3D150P1510FO ITT-Cannon P/N SGA3D150P1510 CONTACTS (PINS) FOR UPPER CONNECTOR J2 Contacts (pins) Size 2222 Honeywell P/N Amp P/N ITT-Cannon P/N Framatome P/N Tri-Star P/N Boeing P/N BACC47EF1 LOWER CONNECTOR J1 MK-VII LOWER CONNECTOR (J1) FOR 115VAC UNIT Connector P/N with Contacts (sockets) Contacts Size 2020HD (sockets) Honeywell P/N Mil-Spec M39029/ ITT-Cannon P/N DPX2MA-40S-40S-33B-0315 ITT-Cannon P/N Tri-Star P/N MK-VII LOWER CONNECTOR (J1) FOR 28VDC UNIT ( & ) Connector without Contacts (sockets) With Contacts (sockets) LOWER Honeywell P/N Honeywell P/N CONNECTOR J1 ITT-Cannon P/N ITT-Cannon P/N CONTACTS (PINS) FOR LOWER CONNECTOR J1 DPX2MA-40S-40S-33B-0388-FO DPX2MA-40S-40S-33B-0388 Contacts (sockets) Size 2020HD Mil-Spec Tri-Star P/N M39029/ ITT-Cannon P/N The GPS Antenna connector is ONLY required for Enhanced MK-VII units with internal GPS receiver. GPS Connector J3 MK-VII GPS ANTENNA CONNECTOR (J3) No GPS With Internal GPS N/A Huber & Suhner P/N 14BMA50-3-3C Databases The EGPWS contains the following databases that can be loaded via the EGPWC front panel PCMCIA interface independent of the system software. Updates to each database will be made available. Envelope Modulation database (see section 6.8) Terrain database (see section 6.7.5), which also contains the runway database (see section ) and may also contain an obstacle database (see section 6.7.6). HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 34

35 ARINC 429 INPUTS MODE 1 RADIO ALTITUDE LRRA ALTITUDE COMPUTED AIRSPEED CORRECTED ALTITUDE ALTITUDE RATE TRUE AIRSPEED STATIC AIR TEMP AIR DATA ACCELERATIONS ATTITUDE ALTITUDE VERTICAL SPEED POSITION MAG HDG/TK TRUE HDG/TK GROUNDSPEED IRS/AHRS GLIDESLOPE DEVN LOCALIZER DEVN SELECTED RWY CRS ILS/MLS DATA SELECTED DH SELECTED RANGE EFIS DATA POSITION MAGNETIC TRACK CORRECTED ALT FMS DATA POSITION POSITION QUALITY ALTITUDE GROUNDSPEED GROUND TRACK DATE/TIME STATUS GPS DATA DITS INPUT HANDLER EGPWS INPUT DIAGRAM MAINTENANCE AND BITE MODE 2 MODE 3 MODE 4 MODE 5 MODE 6 & BANK ANGLE AOA FLAP ANGLE SWC/AOA DATA WINDSHEAR TEST COMMAND FAULT TAGS MAINTENANCE SYSTEM DC ANALOG INPUTS TERRAIN CLEARANCE FLOOR RADIO ALTITUDE ANALOG LRRA GLIDESLOPE DEVN AOA ANALOG AOA DATA ANALOG INPUT HANDLER INPUT PROCESSING TERRAIN/OBSTACLE AWARENESS ARINC 547 GLIDESLOPE DISCRETE INPUTS SELF TEST INITIATE DH TRANSITIONED AUDIO INHIBIT LANDING GEAR AND/OR O'RIDE LANDING FLAPS AND/OR O'RIDE GLIDESLOPE INHIBIT GLIDESLOPE CANCEL ILS/MLS SELECT ILS SELECTED (TUNED) MODE 6 ENABLE MODE 6 VOLUME MOMENTARY AUDIO SUPPRESS DISCRETE FLAP POSITION Additional Optional Inhibits (RAAS/Approach Monitor) DISCRETE INPUT HANDLER CONFIGURATION RAAS (OPTIONAL) 3 4 L 3 4 R LONG LDG (OPTIONAL) ALTIMETER MONITOR (OPTIONAL) TAKEOFF FLAP (OPTIONAL) APPROACH MONITOR (OPTIONAL) R L TERRAIN DISP SELECT DISCRETES FRONT PANEL TEST SWITCH PROGRAM PINS (17) PROGRAM PIN INPUTS FIGURE : EGPWS INPUT BLOCK DIAGRAM HIF-2121/R5 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: AC SHEET 35