DASH NO. -601 APPLICATION NEXT ASSY USED ON 965-1176 965-1186 965-1206 965-1216 TITLE SHEET INDEX SHEET NO. TITLE SHEET ——————————— 1 REVISION STATUS OF SHEETS INDEX —— 2 REVISIONS ———————————— 3 DOCUMENT ———————————— 4 This document is an unpublished work. Copyright 1999, 2000, 2002 Honeywell International Inc. All rights reserved. This document and all information and expression contained herein are the property of Honeywell International Inc.
Product Specification REVISION STATUS OF SHEETS INDEX ADDED SHEETS SHEET NUMBER REV LTR ALL D HIF-2121/R5 SHEET NUMBER REV LTR CAGE CODE: 97896 SHEET NUMBER ADDED SHEETS REV LTR SCALE: NONE SHEET NUMBER SIZE: A REV LTR SHEET NUMBER DWG NO: 965-1176-601 REV LTR SHEET NUMBER REV: D REV LTR SHEET 2
Product Specification SH ALL REV A ALL B ALL ALL C D REVISIONS DESCRIPTION Details of each section’s 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. DATE S. Wright J. Kistler APPROVED 07-JUN-00 Reason: 01 Severity: 10 Details of each section’s updates are listed in the Revision History at the beginning of each section.
Product Specification TABLE OF CONTENTS 1 INTRODUCTION..........................................................................................................................................................6 1.0 1.1 1.2 1.3 1.3.1 1.3.2 1.3.3 1.3.4 1.3.5 1.3.6 1.3.7 2 REFERENCE DOCUMENTS ........................................................................................................................................32 2.0 2.1 2.2 2.3 3 DOCUMENT OVERVIEW..........................................
Product Specification 6.2 GPWS FUNCTIONS .....................................................................................................................................................46 6.2.1 Mode 1 -- Excessive Descent Rate .....................................................................................................................47 6.2.2 Mode 2 -- Excessive Terrain Closure Rate ........................................................................................................53 6.2.
Product Specification 1 Introduction Revision History Date - Modified By 29-NOV-99 Peter Bateman 24-MAY-00 Susie Wright 06-JUN-00 – Susie Wright 01-DEC-00 – Susie Wright 11-JUN-01 – P. Bateman 11-JUN-01 – P. Bateman 02-JUL-01 – S. Wright 02-JUL-01 – S. Wright Description of the Updates Initial Release and Entry into PVCS SCR 4795: Added Envelope Modulation to EM6/8. Added commercial Modes 1, 3, 4 and 6 curves. General Document Cleanup. Document only change – Deleted proprietary note from footer.
Product Specification 1.0 Document Overview This document is organized as follows. Section 1 Introduction, identifies this product specification, gives an overview of the EGPWS, and describes the content and organization of this document. Section 2 Referenced Documents, listed by document number, title, and source, all documents that are referenced in this specification.
Product Specification 1.2 Purpose The Product Specification describes all of the system functions and design criteria for the MKVI and MKVIII Enhanced Ground Proximity Warning System (EGPWS). 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.
Product Specification The functional areas are: • Basic Ground Proximity Warning • Altitude Awareness Callouts • Excessive Bank Angle Alert • Enhanced features, Terrain and Obstacle Awareness alerts and warnings as well as optional display of this information, “Peaks” mode, and Terrain Clearance Floor. • WS Detection and Alerting (limited application).
Product Specification 1.3.1 Ground Proximity Warning As shown in Figure 1.3.1-1, the EGPWS provides the basic Ground Proximity Warning System (GPWS) alerting in six modes. MODE 2 MODE 1 EXCESSIVE DESCENT RATE "SINKRATE" "PULL UP!" EXCESSIVE TERRAIN CLOSURE RATE "TERRAIN..TERRAIN" "PULL UP!" MODE 6 MODE 3 EXCESSIVE BANK ANGLE "BANK ANGLE!" SINK AFTER TAKEOFF "DON'T SINK!" ALTITUDE CALL-OUTS "...FIVE HUNDRED...
Product Specification 1.3.1.1 Mode 1 - Excessive Descent Rate Mode 1 provides alerts when the aircraft has excessive descent rate close to the terrain (see Figure 1.3.1.1-1 and 1.3.1.1-2). Figure 1.3.1.1-1 shows the turboprop curves, available on MKVI and MKVIII EGPWS. Figure 1.3.1.1-2 shows the turbofan curves, available on MKVIII EGPWS only and selectable at the time of installation.
Product Specification Improvements to the Mode 1 alert boundaries are as follows: • Envelope Modulation - (see paragraph 1.3.1.7) • 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.
Product Specification 2500 RADIO ALTITUDE (FEET) 2000 "TERRAIN TERRAIN" 1500 "PULL UP!" 1000 "TER 500 RAIN TER R A IN " "PULL UP!" 0 0 2000 4000 6000 8000 10000 TERRRAIN CLOSURE RATE (FEET/MIN) FIGURE 1.3.1.2-2: 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.
Product Specification RADIO ALTITUDE (FEET) 2500 "DON'T SINK" 2000 1500 1000 "DON'T SINK" 500 0 0 200 400 600 ALTITUDE LOSS (FEET) FIGURE 1.3.1.3-2: MODE 3 - ALTITUDE LOSS AFTER TAKEOFF (TURBOFAN) The altitude loss variable is based on the change of altitude (MSL) from 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 Figures 1.3.1.3-1 and 1.3.1.3-2.
MODE 4A UNSAFE TERRAIN CLEARANCE "TOO LOW TERRAIN" AIRCRAFT SLOWED TO LESS THAN 178 or 148 KTS "TOO LOW TERRAIN" MIN TERRAIN CLEARANCE (FT) Product Specification 1500 1400 UNSAFE TERRAIN CLEARANCE 1300 GEAR UP, FLAPS UP 1200 TOO LOW TERRAIN 1100 WARNING AREA 1000 900 TOO LOW GEAR 800 WARNING AREA 700 600 500 400 300 200 100 0 0 100 200 300 400 COMPUTED AIRSPEED (KTS) "TOO LOW GEAR" RUNWAY FIGURE 1.3.1.
MODE 4B UNSAFE TERRAIN CLEARANCE "TOO LOW TERRAIN" AIRCRAFT SLOWED TO LESS THAN 150 KTS GEAR DOWN "TOO LOW TERRAIN" MIN TERRAIN CLEARANCE (FT) Product Specification 1500 1400 UNSAFE TERRAIN CLEARANCE 1300 GEAR DN, FLAPS UP 1200 1100 TOO LOW TERRAIN 1000 WARNING AREA 900 800 700 600 500 TOO LOW FLAPS 400 WARNING AREA 300 200 100 0 0 100 200 300 COMPUTED AIRSPEED (KTS) 400 "TOO LOW FLAPS" RUNWAY FIGURE 1.3.1.
MODE 4C UNSAFE TERRAIN CLEARANCE "TOO LOW TERRAIN" "TOO LOW TERRAIN" MIN TERRAIN CLEARANCE (FT) Product Specification 3000 2800 2600 2400 2200 2000 1800 1600 1400 1200 1000 800 600 400 200 0 UNSAFE TERRAIN CLEARANCE GEAR UP, FLAPS UP 1500 FPM CLIMB RATE TAKE-OFF OVER FLAT TERRAIN OR WATER WARNING AREA (>200 KTS) WARNING AREA (<168 KTS) 0 400 800 1200 1600 2000 2400 2800 RADIO ALTITUDE (FT) MODE 4C UNSAFE TERRAIN CLEARANCE "TOO LOW TERRAIN" "TOO LOW TERRAIN" MIN TERRAIN CLEARANCE (FT) FIGURE 1.3.
MIN TERRAIN CLEARANCE (FT) Product Specification MODE 5 EXCESSIVE GLIDESLOPE DEVIATION GLIDESLOPE BEAM CENTER SOFT "GLIDESLOPE" HARD "GLIDESLOPE" MODE 5 BELOW GLIDESLOPE ALERT GEAR DOWN 1000 900 800 700 600 500 400 300 200 100 0 SOFT ALERT AREA HARD ALERT AREA 0 1 2 3 4 GLIDESLOPE DEVIATION (DOTS FLY UP) RUNWAY SOFT ALERT AREA HARD ALERT AREA FIGURE 1.3.1.
Product Specification MODE 6 ALTITUDE AWARENESS CALLOUTS "MINIMUMSMINIMUMS" "FIVE HUNDRED" RUNWAY FIGURE 1.3.1.6-1: MODE 6 ALTITUDE CALLOUTS BANK ANGLE CURVE TERRAIN CLEARANCE (FEET) EXCESSIVE BANK ANGLE WARNING "BANK ANGLE BANK ANGLE"" 2500 AUTOPILOT ENGAGED BANK ANGLE CURVE 210 FT 156 FT 200 10 FT 0 0 +/-10 +/-20 +/-30 +/-40 ROLL ANGLE (+/- DEG) +/-50 FIGURE 1.3.1.
Product Specification 1.3.1.7 Envelope Modulation The Envelope Modulation feature provides improved alerting protection at some key locations throughout the world, while improving nuisance margins at others. This is made possible with the use of navigational signals from GPS. 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.
Product Specification 1.3.1.9 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.
Product Specification 1.3.2 Terrain and Obstacle Awareness A major feature of the EGPWS is the Terrain and Obstacle Awareness alerting and display functions. These 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 1.3.2-1.
Product Specification FIGURE 1.3.2-2: TERRAIN DATABASE REGIONS – AMERICAS FIGURE 1.3.
Product Specification FIGURE 1.3.2-4: TERRAIN DATABASE REGIONS – PACIFIC 1.3.2.1 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 6.7.3.
Product Specification MKVI/MKVIII EGPWC supplies a discrete pop-up signal. This can be used to switch flight deck displays between the Weather Radar and the terrain display. In addition, the MKVIII EGPWC can be display terrain on an Electronic Flight Instrument System (EFIS) display. Terrain is depicted on a display as shown in Figure 1.3.2-5. BACKGROUND TERRAIN YELLOW CAUTION AREA "CAUTION TERRAIN, CAUTION TERRAIN" RED WARNING AREA "TERRAIN TERRAIN, PULL UP!" FIGURE 1.3.
Product Specification 1.3.3 Reserved 1.3.4 Maintenance/Test Interfaces In addition to power-up and continuous BIT, user activated tests (via a discrete test switch), and/or maintenance system commands are supported. 1.3.4.1 Cockpit Self Test A cockpit mounted test switch is used to manually initiate tests and BIT annunciation anytime the aircraft is on ground. In addition, if the aircraft is above 2000 feet AGL the cockpit self test can be initiated if no alert is in progress.
Product Specification 1.3.5 System Elements 1.3.5.1 Architecture Figure 1.3.5.1-1 provides a typical block diagram of MKVI EGPWS inputs, Figure 1.3.5.1-2 for outputs. When used, the terrain display output is provided either directly to the DSU, or to display switching relays. The mode curves below are typical, other outputs are possible via configurable mode curves. The following table summarizes the type and quantity of I/O available with both versions of the EGPWC.
Product Specification MODE 1 AC ANALOG INPUTS MAGNETIC HEADING EGPWS INPUT DIAGRAM ROLL ATTITUDE PITCH ATTITUDE MODE 2 DC ANALOG INPUTS ANALOG INPUT HANDLER BAROMETRIC PRESSURE OUTSIDE AIR TEMP MAINTENANCE AND BITE RADIO ALTITUDE ARINC 552A or ALT 55 MODE 3 GLIDESLOPE DEVN ARINC 547/578-4 GLIDESLOPE AOA MODE 4 SERIAL INPUTS DISPLAY STATUS TERRAIN DISPLAY BARO ALTITUDE BARO RATE SAT CAS INPUT PROCESSING MODE 5 ADC ALTITUDE POSITION POSITION QUALITY GROUND SPEED GROUND TRACK DATE/TIME STATUS DI
Product Specification EGPWS OUTPUT DIAGRAM MODE 1 8 OHM MODE 2 AUDIO GENERATOR 600 OHM MODE 3 ARINC 429 DRIVERS MODE 4 MODE 5 LS HS UARTs DISPLAY CONTROL WARNING/CAUTION TO RECORDERS WEATHER RADAR FRONT PANEL PCMCIA SMARTCABLE INTERFACE (UPLOAD/DOWNLOAD) INPUT PROCESSING MAINTENANCE AND BITE MODE 6 & BANK ANGLE RS232 INTERFACE (TEST AND UPLOAD/DOWNLOAD) GLIDESLOPE CANCEL GPWS MONITOR TERRAIN MONITOR DISCRETE HANDLER WINDSHEAR GPWS WARNING GPWS CAUTIONS TERRAIN/OBSTACLE CAUTION TERRAIN
Product Specification 1.3.5.2 System Components Refer to section 2.1 for EGPWC outline drawings. For MKVI EGPWC, 965-1176-xxx or 965-1186-xxx and MKVIII EGPWC, 965-1206-xxx or 965-1216-xxx: Honeywell P/N 405-0383-001 TRAY Source/Vendor Bendix/King Vendor Part Number 071-04003-0002 There are two connectors that interface with the Enhanced MKVI/MKVIII computer. The 78 pin and 50 pin front panel interface connectors of the MKVI/MKVIII contain all the interfaces for signals and power.
Product Specification 1.3.5.3 Databases The EGPWS contains the following types of databases, which 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 6.3.1.2) and may also contain an Obstacle Database (see section 6.7.6). 1.3.
Product Specification 2 Reference Documents Revision History Date - Modified By 29-NOV-99 Peter Bateman 24-MAY-00 Susie Wright 06-JUN-00 – Susie Wright 11-JUN-01 – P. Bateman 02-JUL-01 – S. Wright 2.0 Description of the Updates Initial Release and entry into PVCS SCR 4942: General Document Cleanup. Document only change – Deleted proprietary note from footer. SCR 6170: General Document Cleanup. Added review comments Effectivity App. Cfg.
Product Specification ARINC 600-8 ARINC 414 ARINC 429-13 ARINC 601 ARINC 604-1 ARINC 609 ARINC 624 ARINC 424-11 ARINC 702-5 ARINC 707-5 ARINC 710-8 ARINC 727-1 ARINC 706-3 ARINC 704-2 ARINC 738 ARINC 708-6 ARINC 708-A ARINC 453 EIA 232D PCMICA V2.01 PCMICA/ ATA V1.01 PCMCIA/RE V1.00 RTCA/EUROCAE RTCA/EUROCAE RTCA /DO -200 RTCA/DO-201 RTCA/DO-208 C72-4711-01MD-11 C72-4711-02MD-11 MIL-STD-1629 MIL-STD-785B and Notices MIL-HDBK-217F MIL-STD-975 MIL-STD-882 AC25-12 AC25.
Product Specification 3 Computer Design Criteria Revision History Date - Modified By 29-NOV-99 Peter Bateman 24-MAY-00 Susie Wright 06-JUN-00 – Susie Wright 3.0 Effectivity App. Cfg. -001 -001 -003 -003 -003 -003 Description of the Updates Initial release and entry into PVCS SCR 4942: General Document Cleanup. Document only change – Deleted proprietary note from footer.
Product Specification FLUID SUSCEPTIBILITY X No test required SAND AND DUST X No test required FUNGUS RESISTANCE F No test (non-nutrient material certification) required SALT SPRAY X No test required MAGNETIC EFFECT POWER INPUT Z A Less than 0.3m Normal:22.0-30.3VDC Abnormal: (5 minutes) 20.5-32.3VDC Emergency: 18VDC interrupt for 200msec Normal Surge (30msec): 15-40VDC Abnormal Surge: 100msec @ 46.3VDC, 1 sec @ 37.8VDC VOLTAGE SPIKES A 600VDC, 10µs, 50Ω source impedance AUDIO FREQ.
Product Specification 3.3 Reliability/Maintainability 3.3.1 Scheduled Maintenance No scheduled maintenance is required for the EGPWC. 3.3.2 Reliability A MKVI/MKVIII EGPWC Failure Modes, Effects and Criticality Analysis (FMECA) has been performed and is contained in Honeywell document 070-4610-000. Included in FMECA are MKVI/MKVIII EGPWC assembly level reliability predictions.
Product Specification 3.5.2 System Response to Power Interrupts On application of power to the EGPWC, the computer will perform a power up BIT test to assure proper system performance prior to initiation of normal operation. The time delays before commencing normal operation will be as defined in the tables below. The EGPWC system response to power interrupts will be as follows: Power interrupt duration System Response Maximum Delay to Normal Operation T < 200 msec.
Product Specification 3.6.2 Connectors 3.6.2.1 MKVI/MKVIII EGPWC, 965-1176-xxx/965-1206-xxx Front Connector The main front connectors for the 965-1176-xxx MKVI EGPWC and 965-1206-xxx MKVIII EGPWC are listed in section 1.3.5.2. Refer to the Installation Design Guide for pin-out information. FIGURE 3.6.2.
Product Specification The configuration module is listed in section 1.3.5.2 and is installed on the connector as shown in Figure 3.6.2.1-2. FIGURE 3.6.2.1-2: CONFIGURATION MODULE (SHOWN AS INSTALLED) 3.6.2.2 Front Panel Test Connector A test connector is provided on the EGPWC front panel. This provides access for a PC test monitor and future portable data loading capabilities. Reference section 6.10.4 for pin-out and functional details.
Product Specification 3.7 Software Design Requirements The EGPWC software development process creates software, which meets the guidelines of RTCA DO-178B, Levels C and D as identified in the following table. Refer to the Software Development Plan for the EGPWC (SDP) for additional information regarding the Computer Software Configuration Items (CSCIs) listed below.
Product Specification 4 External Interface Revision History Date - Modified By 29-NOV-99 Peter Bateman 24-MAY-00 Susie Wright 06-JUN-00 – Susie Wright Description of the Updates Initial Release and Entry into PVCS SCR 4942: General Document Cleanup. Document only change – Deleted proprietary note from footer. Effectivity App. Cfg. -001 -001 -003 -003 -003 -003 Refer to the Installation Design Guide.
Product Specification 5 Functional Inputs Revision History Date - Modified By 29-NOV-99 Peter Bateman 24-MAY-00 Susie Wright 06-JUN-00 – Susie Wright Description of the Updates Initial Release and Entry into PVCS SCR 4942: General Document Cleanup. Document only change – Deleted proprietary note from footer. Effectivity App. Cfg. -001 -001 -003 -003 -003 -003 Refer to the Installation Design Guide.
Product Specification 6 System Functions Revision History Date - Modified By 29-NOV-99 Peter Bateman 24-MAY-00 Susie Wright 06-JUN-00 – Susie Wright Description of the Updates Initial Release and entry into PVCS SCR 4942: General document cleanup. Document only change – Deleted proprietary note from footer. Effectivity App. Cfg. -001 -001 -003 -003 -003 -003 6.0 Mode Control EGPWC uses mode control to enable specific features in the EGPWC modes.
Product Specification 6.0.3 MKVIII EGPWS Windshear Takeoff/Approach Mode Separate logic is utilized to control the takeoff/approach mode switching for mode 7 windshear detection. The takeoff state actually reflects takeoff or go-around. The approach state reflects final approach. The state of this latch is maintained in nonvolatile memory in order to prevent inadvertent mode switching as a result of power loss. 6.0.
Product Specification 6.1 Configuration Module Revision History Date - Modified By 29-NOV-99 Peter Bateman 24-MAY-00 Susie Wright 06-JUN-00 – Susie Wright Description of the Updates Initial Release and entry into PVCS. SCR 4942: General document cleanup. Document only change – Deleted proprietary note from footer. Effectivity App. Cfg. -001 -001 -003 -003 -003 -003 MKVI/MKVIII application uses a configuration module instead of the program pins used by MKV/MKVII EGPWS.
Product Specification 6.2 GPWS Functions Revision History Date - Modified By 29-NOV-99 Peter Bateman 08-MAR-00 M. Calhoun 24-MAY-00 Susie Wright 06-JUN-00 – Susie Wright 01-DEC-00 – Susie Wright 27-FEB-01 – M. Calhoun 07-JUL-01 – S. Wright 30-JAN-02 – N Paterson Description of the Updates Initial Release and entry into PVCS SCR 4908: Corrected Mode 1 curve in Figure 6.2.1-2. Added Figure 6.2.4.1-2A to correctly show Mode 4A type 5. SCR 4795: Add Envelope Modulation for EM6/8. General document cleanup.
Product Specification 6.2.1 Mode 1 -- Excessive Descent Rate Mode 1 provides an alert based on valid radio altitude and valid aircraft descent rate. The descent rate is computed based on barometric rate from the Air Data Computer (ADC). Two different alert envelopes are possible. Through Envelope Modulation, both envelopes can be biased to the right at certain airports to minimize nuisance alerts. Figure 6.2.1-1 illustrates Mode 1 functionality.
Product Specification 2.6 2450 FT 2.4 2.2 -5007 FPM (Thousands) 2 1.8 1.6 1.4 SINK RATE ALERT AREA 1 0.8 -1031 FPM MIN TERRAIN CLEARANCE (FT) 1.2 0.6 0.4 0.2 50 FT 0 0 -4000 -2000 -6000 ALTITUDE RATE (FPM DESCENT) FIGURE 6.2.1-2: MODE 1 OUTER CURVE (TURBOPROP) 2.6 2450 FT 2.2 -5007 FPM 2 1.8 1.6 1.4 ALERT/WARNING AREA 1.2 -964 FPM MIN TERRAIN CLEARANCE (FT) (Thousands) 2.4 1 0.8 0.6 0.4 0.2 10 FT 0 0 -2000 -6000 -4000 -8000 -10000 ALTITUDE RATE (FPM DESCENT) FIGURE 6.2.
Product Specification For some installations a steep approach bias can be optionally applied to the Mode 1 curves. If steep approach is enabled and the steep approach discrete is selected, then fixed positive biases are added to both the Sinkrate curve (500 FPM), and the Pull Up curve (200FPM). If steep approach is activated, then the cockpit self test is inhibited when the aircraft is on the ground.
Product Specification The static Mode 1 inner curve for turbofan airplanes (available on MKVIII EGPWS only) is composed of two straight lines with the equations: (lower line) RADIO ALTITUDE (FT) = -1620 (FT) - 1.1133 * ALTITUDE RATE (FPM) (upper line) RADIO ALTITUDE (FT) = -400 (FT) - 0.4 * ALTITUDE RATE (FPM) 2.6 2450 FT 2.2 -7125 FPM 1.8 1.6 1.4 1.2 1 0.8 -1710 FPM 2 -1482 FPM MIN TERRAIN CLEARANCE (FT) (Thousands) 2.4 WARNING AREA 0.6 0.4 284 FT 0.
Product Specification Figure 6.2.1-4 indicates the actual Mode 1 caution/warning curves for turboprop aircraft (Figure 6.2.1-4A for turbofan), considering filter lags and time delays, for constant descent rates initiated from 2450 feet radio altitude over water or flat terrain. Both the outer and inner curves are shown.
Product Specification 3000 WARNINGS FROM 2450 FT AGL 2800 OVER FLAT TERRAIN OR WATER 2600 SINKRATE WARNING AREA MIN TERRAIN CLEARANCE (FT) 2400 2200 2000 1800 1600 1400 1200 1000 PULL UP WARNING AREA 800 600 400 200 0 0 2000 4000 6000 8000 10000 ALTITUDE RATE (FPM DESCENT) FIGURE 6.2.
Product Specification 6.2.2 Mode 2 -- Excessive Terrain Closure Rate Mode 2 provides two types of alerts based on aircraft gear/flap configuration, radio altitude (terrain clearance), and how rapidly that radio altitude is decreasing (closure rate). Barometric altitude of the airplane is not important in initiating this warning. These two alerts are commonly referred to as Mode 2A, described in sections 6.2.2.1 and 6.2.2.2, and as Mode 2B, described in section 6.2.2.3.
Product Specification 6.2.2.1 Mode 2A Mode 2A is operational when the flaps are not in the landing position. The maximum upper envelope is at 1650 feet radio altitude for speeds below 220 knots (for fast tuboprop, 190 knots for slow turboprop). As the aircraft speed increases up to 310 knots (for fast turboprop, 280 knots for slow turboprop), the upper altitude increases linearly to a maximum value of 2450 feet radio altitude. For speeds above these values, the upper altitude limit remains at 2450 feet.
Product Specification 2.6 9800 FPM AT 2450 FT, AIRSPEED >= 310 KTS MIN TERRAIN CLEARANCE (1000 FT) 2.4 AIRSPEED EXPANSION AREA 2.2 UPPER LIMIT BASED ON AIRSPEED UPPER LIMIT (FT) = 1650 + 8.9[AIRSPEED - 220] 2 5733 FPM AT 1650 FT, AIRSPEED <= 220 KTS 1.8 1.6 1.4 AIRSPEED EXPANDS UPPER LIMIT WHEN BETWEEN 220 AND 310 KNOTS 1220 FT 1.2 1 2038 FPM 3545 FPM 0.8 0.6 0.4 ALERT AREA 0.2 30 FT 0 0 2 4 6 8 12 10 CLOSURE RATE (1000 FPM) FIGURE 6.2.2.
Product Specification 6.2.2.2 Mode 2A Altitude Gain When the Mode 2A envelope is exited, after having been violated for more than 3 seconds, an altitude gain feature is automatically activated. Altitude (MSL) is sampled at this time to compute subsequent changes in altitude. The caution lights (warning lights if using Lamp Format 1) remain on, and if the terrain is still closing the voice message is “Terrain”.
Product Specification 2.4 MODE 2B TERRAIN CLOSURE RATE 2.2 STATIC ALERT ENVELOPE 2 1.8 1.6 1.4 3000 FPM (Thousands) 1.2 1 2038 FPM 0.8 2253 FPM MIN TERRAIN CLEARANCE (FT) 2.6 0.6 0.4 789 FT ALERT AREA FLAPS DOWN LOWER CUTOFF (200 FT, VARIES WITH ALTITUDE RATE) 0.2 FLAPS UP LOWER CUTOFF (30 FT) 0 0 2 4 6 8 10 CLOSURE RATE (1000 FPM) FIGURE 6.2.2.
Product Specification 6.2.3 Mode 3 -- Descent After Takeoff Mode 3 provides alerts for excessive altitude loss after takeoff Mode 3 is based primarily on radio altitude, barometric altitude, and barometric altitude rate. Mode 3 is shown in the block diagram of Figure 6.2.3-1.
Product Specification MODE 3 - DESCENT AFTER TAKEOFF 1000 GPWS FLAP OVERRIDE 925 RADIO ALTITUDE (FEET) 5 FT/SEC 750 700 500 "DON'T SINK" 250 50 0 0 25 75 100 125 ALTITUDE LOSS (FEET) 50 150 175 FIGURE 6.2.
Product Specification Barometric altitude rate is used in the same manner as was described for Mode 1. The Mode 3 alert envelopes are inhibited close to the ground. The descent required for an alert varies as a function of flight profile and time. Once a descent begins during the takeoff phase of flight, as determined by the polarity of the altitude rate signal and takeoff/approach mode logic, the computer will store the existing value of altitude.
Product Specification 6.2.4 Mode 4 -- Unsafe Terrain Clearance Mode 4 generates three types of voice alerts based on radio altitude, computed airspeed, and aircraft configuration, commonly referred to as Modes 4A, 4B, and 4C. Modes 4A and 4B static alert envelopes are illustrated in Figures 6.2.4.1-2 through -8. Dynamic envelopes are not included for these Modes because they do not differ significantly from the static cases. The Mode 4C static envelope is illustrated in Figure 6.2.4.2-2.
Product Specification knots (for Mode 4 Types 7,9) the upper boundary increases linearly with airspeed to a maximum of 750 feet radio altitude at 200 knots or more (170 knots for alternate airspeed range). One exception to this is for Mode 4 Type 5 where it increases to 200 knots at 1000 feet. Penetrating this boundary produces a repetitive “Too Low Terrain” message.
Product Specification MIN TERRAIN CLEARANCE (FT) 1800 1600 250 KTS 1400 1200 1000 FT 1000 800 FT LIMIT DURING OVERFLIGHT 190 KTS 800 EXPANDED ALERT AREA 500 FT 600 400 ALERT AREA 200 30 FT 0 0 100 200 300 400 COMPUTED AIRSPEED (KTS) MIN TERRAIN CLEARANCE (FT) FIGURE 6.2.4.
Product Specification 4A) or with landing gear down and flaps not in landing position (and not overridden) “Too Low Flaps”. For aircraft types that routinely delay full flap deployment (Mode 4 Types 8 and 9) these airspeeds are 148 knots and 118 knots respectively. To maintain the same airspeed expansion function up to 750 feet nominal at 200 knots the lower level “corner” is at 150 knots (Mode 4 Type 6), or 120 knots (Mode 4 Type 7) while above this airspeed the message is “Too Low Terrain”.
Product Specification MIN TERRAIN CLEARANCE (FT) (Thousands) 1.6 250 KTS 1.4 1.2 1000 FT 1 800 FT LIMIT DURING OVERFLIGHT 0.8 159 KTS 0.6 EXPANDED ALERT AREA 245 FT 0.4 0.2 30 FT ALERT AREA 0 0 100 200 300 400 COMPUTED AIRSPEED (KTS) FIGURE 6.2.4.
Product Specification 1000 MIN TERRAIN CLEARANCE (FT) 170 KTS 750 FT 800 EXPANDED ALERT AREA 600 120 KTS 400 200 170 FT ALERT AREA 30 FT 0 0 100 200 300 AIRSPEED (KTS) FIGURE 6.2.4.1-6: MODE 4B STATIC ALERT ENVELOPE (ALTERNATE AIRSPEED RANGE, MODE TYPE 7) MIN TERRAIN CLEARANCE (FT) 1000 200 KTS 750 FT 800 EXPANDED ALERT AREA 600 400 148 KTS 200 150 FT ALERT AREA 30 FT 0 0 100 200 Normal 300 400 AIRSPEED (KTS) FIGURE 6.2.4.
Product Specification MIN TERRAIN CLEARANCE (FT) 1000 170 KTS 750 FT 800 EXPANDED ALERT AREA 600 118 KTS 400 200 150 FT ALERT AREA 30 FT 0 0 100 200 300 AIRSPEED (KTS) FIGURE 6.2.4.1-8: MODE 4B STATIC ALERT ENVELOPE (ALTERNATE AIRSPEED RANGE, MODE TYPE 9) 6.2.4.2 Mode 4C Mode 4 also provides an alert based on minimum radio altitude clearance during takeoff as illustrated in Figure 6.2.4.2-1.
(Thousands) MIN TERRAIN CLEARANCE (FT) Product Specification 1 1000 FT 750 FT 0.8 (>= 200 KTS or 170 KTS) 667 FT ALERT AREA EXPANDED 0.6 500 FT (<= 178 KTS or 148 KTS) 100 FT 0.4 0.2 ALERT AREA 30 FT 0 0 0.4 0.8 1.2 1.6 RADIO ALTITUDE (FT) 2 2.4 (Thousands) 1.2 (Thousands) MIN TERRAIN CLEARANCE (FT) FIGURE 6.2.4.2-2: MODE 4C STATIC ALERT ENVELOPE (MODE 4 TYPES 6,7,8,9) 1333 FT 1000 FT 1 (>= 200 KTS) 0.8 ALERT AREA EXPANDED 667 FT 0.6 100 FT 500 FT (<= 178 KTS) 0.4 0.
Product Specification 2.6 MIN TERRAIN CLEARANCE (FT) (Thousands) 2.4 2.2 2 1.8 1.6 1333 FT 1.4 1000 FT (>= 250 KTS) EXPANDED ALERT AREA 500 FT (<= 190 KTS) 667 FT 1.2 1 100 FT 0.8 0.6 0.4 ALERT AREA 30 FT 0.2 0 0 0.4 0.8 1.2 1.6 RADIO ALTITUDE (FT) 2 2.4 (Thousands) FIGURE 6.2.4.2-3A: MODE 4C STATIC ALERT ENVELOPE (TURBOFAN – MODE 4 TYPE 1) Mode 4C is based on a minimum terrain clearance, or floor, that increases with radio altitude during takeoff.
Product Specification MIN TERRAIN CLEARANCE (FT) MODE 4C UNSAFE TERRAIN CLEARANCE GEAR UP, FLAPS UP 1600 TAKE-OFF OVER FLAT TERRAIN OR WATER 1500 FPM CLIMB RATE 1400 1200 1000 800 ALERT AREA 600 (>200 KTS or 170 KTS) 400 ALERT AREA 200 (<178 KTS or 148 KTS) 0 0 400 800 1200 1600 2000 2400 2800 RADIO ALTITUDE (FT) FIGURE 6.2.4.
Product Specification 6.2.5 Mode 5 -- Descent Below Glideslope Mode 5 provides two levels of alert when the aircraft flight path descends below the glideslope beam on front course ILS approaches. Figure 6.2.5-1 is a functional block diagram description of Mode 5. A delay of approximately 0.8 seconds is inserted between the alert output and the enabling logic during an alert condition to help prevent nuisance alerts.
Product Specification MODE 5 EXCESSIVE GLIDESLOPE DEVIATION SOFT GLIDESLOPE ALERT ENVELOPE MIN TERRAIN CLEARANCE (FT) (Thousands) 2.6 2.4 2.2 2 1.8 1.6 1.3 DOTS 1.4 1.2 1000 FT 1 0.8 SOFT ALERT AREA 0.6 0.4 0.2 2.98 DOTS 30 FT 150 FT 0 0 1 2 3 4 GLIDESLOPE DEVIATION (DOTS FLY UP) FIGURE 6.2.5-2 MODE 5 STATIC SOFT ALERT ENVELOPE A second alert boundary (Figure 6.2.
Product Specification Both envelopes allow additional deviation below 150 feet of radio altitude to allow for normal beam variations near the threshold. This is shown in the envelope of Figure 6.2.5-2 as the sloped portion of the curve, where the equation relating radio altitude and glideslope deviation required for the soft alert is: MIN TERRAIN CLEARANCE (FT) = 243 − 71. 43 • GLIDESLOPE DEVN ( DOTS FLY UP ) and in Figure 6.2.5-3 for the hard alert: MIN TERRAIN CLEARANCE (FT) = 293 − 71.
Product Specification GLIDESLOPE VALID GLIDESLOPE INHIBIT IN APPROACH MODE LANDING FLAPS GEAR DOWN POWER SAVE LATCH STD ENABLE/RESET GLIDESLOPE CANCEL ALT ENABLE/RESET MODE 5 ENABLE FRONT COURSE TRACK/HDG SELECTED CRS/HDG WITHIN 90 DEG LOCALIZER CAPTURE RADIO ALTITUDE MODE 5 MAX ALTITUDE LOCALIZER DEVN WITHIN 2 DOTS OR RADIO ALT 500 FT BELOW MODE 5 MAX ALT FEET MODE 5 MAX MODE 5 MAX ALTITUDE RADIO ALTITUDE MODE 5 MAX MINUS 500 FT GREATER THAN MIN DESCENT RATE DESCENT RATE -500 0 DESCENT RATE (FPM
Product Specification 6.3 Terrain Clearance Floor Revision History Date - Modified By 29-NOV-99 Peter Bateman 24-MAY-00 Susie Wright 06-JUN-00 – Susie Wright Description of the Updates Initial release and entry into PVCS SCR 4942: General document. Document only change – Deleted proprietary note from footer. Effectivity App. Cfg. -001 -001 -003 -003 -003 -003 The Terrain Clearance Floor (TCF) alert function adds an additional element of protection to the standard Ground Proximity Warning System.
Product Specification 6.3.1.3 Alert Envelopes The TCF alert envelope is a circular band centered over the selected runway. Figures 6.3.1.3-1 and 6.3.1.3-2 illustrate the shape of the TCF alert envelope. FIGURE 6.3.1.3-1: TCF ALERT ENVELOPE COMPONENTS 1/2 Runway Length Envelope Bias Factor TCF Alert Envelope FIGURE 6.3.1.
Product Specification 15+k nm Minimum Terrain Clearance, ft 700 700 ft Curve expansion for Runway sides 12+k nm 4+k nm 400 400 ft 245 TCF Alert Area 30 ft *10 ft k Runway End 0.30 + k 2.45+k 4+k 12 + k 15 + k No limit 0.10 + k Distance to Destination Runway End, nm K = Position Error + Runway Data Quality (typically 0.3125 nm) FIGURE 6.3.1.3-3: TCF ALERT CURVE 245 FT CONVENTIONAL TCF RUNWAY ENVELOPE BIAS FACTOR CONVENTIONAL TCF ENVELOPE BIAS FACTOR 45° 245 FT FIG-6.3.1.
Product Specification 700' AGL 400' AGL 24 5' AG L 245' AGL 2.45NM 4NM 12NM 15NM FIG-6.3.1.3-5: TCF ALERT AREA VIEWED ALONG RUNWAY TRACK The Runway Field Clearance Floor (RFCF) alert envelope is a circular band centered over the selected runway but unlike the radio altitude based TCF envelope, the RFCF envelope only extends 5 NM past the end of the runway.
Product Specification 6.4 Advisory Alerts Revision History Date - Modified By 29-NOV-99 Peter Bateman 24-MAY-00 Susie Wright 06-JUN-00 – Susie Wright 18-AUG-00 - MJC 11-JUN-01 – P. Bateman 11-JUN-01 – P. Bateman 02-JUL-01 – S. Wright 30-JAN-02 – N Paterson Description of the Updates Initial release and entry into PVCS SCR 4942: General document cleanup. Document only change – Deleted proprietary note from footer. 6.4.
Product Specification Other maximum enabling, and reset, altitudes are used at certain airports to increase alerting range. The landing gear logic is also overridden at these airports (see Envelope Modulation section 6.8). 6.4.2 Altitude Callouts Altitude callout messages are enabled based on the menu set selected. Altitude callouts are only activated between the associated value, and a value 10 feet less than this value (20 feet when above 150 feet).
Product Specification When the roll angle exceeds these limits two “Bank Angle” voice messages are given with the standard 0.75 second delay between messages. Once the bank angle messages are given the voice is shut off until the roll angle increased by another 20% at which time another two bank angle messages will be given. If the radio altitude data is invalid (e.g., looses track at high roll attitudes) then the warning threshold is set to the maximum curve value. Figure 6.4.
Product Specification TERRAIN CLEARANCE (ft) 2450 WARNING AREA 2000 ADDITIONAL AUTOPILOT ENGAGED WARNING AREA 1600 1200 800 10 DEG 400 150 FT 30 FT 5 FT Cutoff 0 0 10 20 30 40 50 55 BANK ANGLE WARNING THRESHOLD (+/- DEG) FIGURE 6.4.4-1A: BANK ANGLE CURVE (TURBOFAN) 6.4.5 Above Field Callout A “500 ABOVE” or “500” callout is provided when the aircraft is within 5 nm’s of a runway and the aircraft is configured for the above field callout.
Product Specification 6.5 MKVIII Windshear Detection Alerts Revision History Date - Modified By 29-NOV-99 Peter Bateman 06-JUN-00 – Susie Wright 02-JUL-01 – S. Wright Effectivity App. Cfg. -001 -001 -003 -003 -008 -008 Description of the Updates Initial Release and entry into PVCS. Document only change – Deleted proprietary note from footer. SCR 4734: Added Honeywell windshear for BD-100 Windshear detection and annunciation is available for limited aircraft with the Mk VIII EGPWS installed.
Product Specification The algorithm as shown in figure 6.5.1-2 calculates a total windshear indication and does not resolve individual horizontal and vertical windshear components. The shear signal is modulated by radio altitude and roll angle in order to provide further margin against unwanted alerts that could potentially result from turning into and out of winds.
Product Specification Mode 7-Windshear Typical Alert Envelope for Airspeed = 150 Knots UPDRAFT TAKEOFF (FEET/MIN) APPROACH 2000 WINDSHEAR CAUTION 1000 DECREASING HEADWIND (KNOTS/SEC) 4 2 0 0 2 4 INCREASING HEADWIND (KNOTS/SEC) 1000 WINDSHEAR WARNING 2000 DOWNDRAFT (FEET/MIN) FIGURE 6.5.1-3: TYPICAL WINDSHEAR ALERT THRESHOLDS Logic is provided to distinguish between the takeoff and approach phases of flight.
Product Specification 6.6 Reserved Revision History Date - Modified By 29-NOV-99 Peter Bateman 06-JUN-00 – Susie Wright HIF-2121/R5 Description of the Updates Initial release and Entry into PVCS. Document only change – Deleted proprietary note from footer. CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 965-1176-601 Effectivity App. Cfg.
Product Specification 6.7 Terrain Awareness Functions Revision History Date - Modified By 29-NOV-99 Peter Bateman 24-MAY-00 Susie Wright 06-JUN-00 – Susie Wright 02-JUL-01 – S. Wright 30-JAN-02 – N Paterson Description of the Updates Initial release and entry into PVCS SCR 4942: General document cleanup. Document only change – Deleted proprietary note from footer. Added review comments SCR 6325: Para 6.7.4 revised MSL to GSL Effectivity App. Cfg.
Product Specification Aircraft-dependent Inputs Aircraft Position LOCAL TERRAIN PROCESSING Aircraft Heading Local Terrain and Obstacle Data (Overlay Format) Aircraft Position SURFACE TERRAIN, OBSTACLE, AND AIRPORT DATABASES Nearest Runway Data AUDIO OUTPUT Altitude Rate Altitude (MSL) TERRAIN THREAT DETECTION AND DISPLAY PROCESSING Flight Path Angle EGPWS Input Processing and Signal Selection Ground Speed Ground Track LAMP OUTPUTS Terrain Display Data Roll Attitude Display Override and Range
Product Specification 6.7.1.3 Control Inputs Installations provide discrete terrain display select switches in the cockpit for each display. These are momentary contact switches that are processed by the EGPWS input processing and signal selection block as inputs to the Wx/TERR select logic. For some fully integrated displays this selection is provided via a display controller. In addition a Terrain Inhibit switch may also be provided to deactivate the enhanced functions of the EGPWS.
Product Specification 6.7.3.1 Terrain Caution and Warning Envelopes The basic terrain caution envelope (or yellow alert envelope) and terrain warning envelope (or red alert envelope) boundaries are illustrated in Figure 6.7-2.
Product Specification 6.7.3.1.1 Caution Altitude Floor The caution altitude floor (or terrain floor) is computed as a function of aircraft altitude with respect to nearest runway altitude and range to the nearest runway threshold position. This parameter represents a distance below the aircraft. The relationship to the nearest runway threshold location prevents undesired alerts when the aircraft is taking off or landing at an airport.
Product Specification Color Solid Red Solid Yellow High Density Red Dots High Density Yellow Dots Low Density Yellow Dots Solid Green High Density Green Dots1 Low Density Green Dots Terrain Elevation Terrain threat area – warning. Terrain threat area – caution. Terrain more than 2000 feet above aircraft altitude. Terrain between 1000 and 2000 feet above aircraft altitude. Terrain that is 500 feet (250 feet with gear down) below to 1000 feet above aircraft altitude.
Product Specification aircraft. The red and yellow dot patterns are unchanged and continue to indicate terrain that is near or above the current altitude of the aircraft. Solid yellow and red colors are also unchanged and continue to indicate caution and warning areas relative to the flight path of the aircraft. Terrain identified as water (0 feet MSL) may optionally be displayed as cyan dots if the aircraft display hardware supports the color cyan.
Product Specification High Density Red Ref Altitude + 2000 High Density Yellow Ref Altitude + 1000 Low Density Yellow Ref Altitude -250/500 (Maximum Elevation Number) Solid Green Highest Band Reference Altitude High Density Green Middle Band Lowest Band (Minimum Elevation Number) Low Density Green Black Cyan Sea Level (Maximum Elevation Number) High Density Red Ref Altitude + 2000 High Density Yellow Ref Altitude + 1000 Low Density Yellow Ref Altitude -250/500 High Density Green Ref
Product Specification SELF-TEST TERRAIN DISPLAY During self-test, if all required inputs are valid then a display test pattern will be painted for approximately 12 seconds. The test pattern, as illustrated in the Figure below, consists of 9 blocks, each filled with a different fill pattern and color. These 9 ‘styles’ reflect those that are normally used in a terrain picture on the display being used.
Product Specification 6.7.4.4 Terrain Test Display During manually initiated self-test (see 6.10.6), the terrain alert aurals are included in the GPWS audio test outputs. Additionally, a test display is output to the EGPWS display devices. This terrain test display exercises the complete set of EGPWS colors and dot patterns. 6.7.4.5 Mode Annunciation For some installations a 6 character mode annunciation display window is available to the EGPWS.
Product Specification There is no direct source of true heading, but there is a source of magnetic heading. There is no direct source of magnetic track, but there is a source of true track. 6.7.8 Geometric Altitude Geometric Altitude is a computed aircraft altitude designed to help ensure optimal operation of the EGPWS Terrain Awareness and Display functions through all phases of flight and atmospheric conditions.
Product Specification 6.7.8.2.1 Non-Standard Altitude To support the Geometric Altitude function the EGPWS computes a non-standard altitude using the hydrostatic equation relating changes in height to changes in pressure and temperature. Non-standard altitude uses static pressure derived from standard altitude (uncorrected barometric altitude), along with SAT, to continuously accumulate changes in Geometric Altitude.
Product Specification a corresponding decrease in accuracy. When using standard altitude in place of non-standard altitude, affected estimated VFOMs are adjusted resulting in the affected signals being weighted less heavily in the final blended altitude. 6.7.9 WGS-84 Correction Some GPS receivers provide GPS altitude referenced to WGS 84 instead of Mean Sea Level (MSL).
Product Specification 6.8 Envelope Modulation Revision History Date - Modified By 29-NOV-99 Peter Bateman 23-MAY-00 Susie Wright 06-JUN-00 – Susie Wright 27-FEB-01 – M. Calhoun 02-JUL-01 – Susie Wright Description of the Updates Initial release and entry into PVCS SCR 4796: Update Envelope Modulation to use Geometric Altitude when available. General document cleanup. Document only change – Deleted proprietary note from footer.
Product Specification Latitude and longitude are continuously monitored for the airport locations. Additional data processing is not required until the aircraft approaches one of the Envelope Modulation areas. Once a latitude/longitude-defined area is penetrated, the other data inputs are checked for “normal” conditions before any alert/warning envelopes are modulated. There are currently four types of Envelope Modulation required for the approaches causing problems for GPWS: 1.
Product Specification TABLE 6.
Product Specification 6.9 System Outputs Revision History Date - Modified By 29-NOV-99 Peter Bateman 24-MAY-00 Susie Wright 06-JUN-00 – Susie Wright 01-DEC-00 – Susie Wright 27-FEB-01 – M. Calhoun 11-JUN-01 – P. Bateman 02-JUL-01 – S. Wright Effectivity App. Cfg. -001 -001 -003 -003 -003 -003 -006 -006 -008 -008 -008 -008 -008 -008 Description of the Updates Initial release and entry into PVCS SCR 4738: Add lamp format 2. General document cleanup.
Product Specification RELATIVE PRIORITY WARNING CONDITION POSSIBLE MESSAGES LAMP FORMAT 1 HIGHEST Mode 7 W/S Warning Mode 1 Pull Up Mode 2 Pull Up Preface Mode 2 Pull Up Terrain Awareness Preface W/S W/S W/S W/S WARN Pull Up GP WARN Terrain Terrain GP WARN Pull Up GP WARN Terrain Terrain GP WARN Terrain Ahead GP WARN Terrain Awareness Warning Pull Up GP WARN Obstacle Awareness Preface Obstacle Obstacle GP WARN Obstacle Ahead GP WARN Obstacle Awareness Warning Pull Up GP WARN Mode 2 Terrain Terrain GP
Product Specification 6.9.3.2 Windshear Discrete (Lamp) Outputs The Mode 7 Windshear detection warning and caution functions activate separate lamp outputs. Priority logic, described in section 6.5, prevents windshear caution during a windshear warning condition and provides an inhibit which turns off the EGPWS alert and warning lamps. 6.9.3.3 Audio On Discrete The Audio On output is activated whenever the EGPWS is talking. It will stay on until the voice is completed.
Product Specification The DSP performs a rho-theta conversion of the display matrix overlays using current aircraft position and aircraft heading and synthesizes a radar-like sweep ahead of the aircraft. This sweep can feed two display outputs with independent range scale settings. 6.9.4.1.1 Output Display Buses The EGPWS provides two output buses that conform electrically to ARINC-453 and implement the ARINC-708 data formats used by weather radar.
Product Specification Installations that use a cockpit selection switch for each display may use these outputs to directly control relays that make the switch between weather and EGPWD. The EGPWS will read each connected cockpit selection switch and output the corresponding selection. The EGPWS may also be optionally configured to pop-up the terrain display when an EGPWS alert is detected thereby overriding the crew selections.
Product Specification 6.10 Maintenance Functions Revision history Date - Modified By 29-NOV-99 Peter Bateman 06-APR-00 M. Calhoun 24-MAY-00 Susie Wright 06-JUN-00 – Susie Wright 01-DEC-00 – Susie Wright 27-FEB-01 – M. Calhoun Description of the Updates Initial release and entry into PVCS SCR 4896: Added the following to the Present status example in section 6.10.12 and to the level 3 self test description in section 6.10.6.
Product Specification 6.10.2.2 Current Faults Faults and failures in the system are divided into two main categories, internal faults and external faults. These main two categories are used to distinguish faults for different processing requirements. (For example recording faults into fault history.
Product Specification 6.10.2.3.2 Windshear Monitor (MKVIII EGPWS) The Windshear monitor is activated by failures that affect the Windshear function. Both analog and digital versions of the monitor are provided. The configured discrete output is biased on with loss of system power. 6.10.2.3.3 Terrain Awareness Monitor The Terrain Awareness monitor is encoded on an ARINC 429 label and is supplied by the Terrain Awareness function. 6.10.2.3.
Product Specification 6.10.3.2.1 Activity Cumulative Counters For each of the items listed in the table below a cumulative counter will be maintained in non-volatile memory. These counters are never cleared after the time of manufacture. Cumulative Fault Counters Glideslope Cancels Number of Flights GPW INOP Time TA&D INOP Time TA&D Not Available Time Terrain Inhibit Time Flight Time Operating Time TABLE 6.10.3.2.1.T10: 6.10.3.2.
Product Specification GPWS Alert Cumulative Counters Mode 1 Sinkrate Caution Mode 1 Pull Up Warning Mode 2 Pull Up Warning Mode 2 Terrain Caution Mode 3 Don’t Sink Caution Mode 4 Too Low Terrain (Approach) Caution Mode 4 Too Low Gear Warning Mode 4 Too Low Flaps Warning Mode 4 Too Low Terrain (Takeoff) Caution Mode 5 Glideslope Alert Mode 6 Bank Angle Callout Mode 7 Windshear Caution Mode 7 Windshear Warning Terrain Clearance Floor Warning Terrain Ahead Caution Terrain Ahead Warning Envelope Modulation Enga
Product Specification 6.10.3.3.3 Alert History User Interface The alert history data is accessible via the front panel test connector using a PC, or annunciated during the Flight history audio readout. When the alert history is requested alert history records are scanned and formatted for enunciation or display. 6.10.3.4 Ground History Ground history consists of Ground History Records stored by the EGPWS on the ground for the purpose of maintenance and troubleshooting.
Product Specification External Fault Computer OK Computer Fail Condition Recommended Maintenance Action OFF OFF OFF EGPWC Power off Turn EGPWC power ON.
Product Specification EGPWC FRONT PANEL PLUG Connection Source 3 (Receive) 4 (Transmit) 1 (Ground) PC, DB-9 Termination 3 (Transmit) 2 (Receive) 5 (Ground) PC, DB-25 Alternate Termination 2 (Transmit) 3 (Receive) 7 (Ground) TABLE 6.10.4-3: EGPWC FRONT PANEL RS-232 CONNECTIONS 6.10.5 Smart Cable (PCMCIA Interface) The EGPWC Smart Cable is a removable PCMCIA interface (part number 951-0386-001). The Smart Cable is compatible with any ATA style cards. Table 6.10.
Product Specification Color Label Green O Power Yellow O IN PROG Yellow O CARD CHNG Green O XFER COMP Red O XFER FAIL FIGURE 6.10.
Product Specification 6.10.6 Self-Test The EGPWC provides self-test capability on the ground. This provides an indication of the ability of the EGPWC to perform its intended function. The EGPWC self-test is initiated by momentarily pressing the cockpit self-test button. The self-test results are annunciated, at 6db lower than the normal audio level selected for the aircraft, via the same audio system as the EGPWS alerts.
Product Specification 6.10.6.1 Level 1 self-test Level 1 self-test is divided into three functions - the preamble, short level 1 self-test and long level 1 self-test. During level 1 self-test, a Short Cancel terminates the self-test level and “CURRENT FAULTS” is annunciated to indicate activation of level 2 self-test. During level 1 self-test, a Long Cancel terminates the entire self-test sequence. 6.10.6.1.
Product Specification 6.10.6.1.2 Short Level 1 Self-Test The short level 1 self-test is a subset of the long level 1 self-test. Short level 1 self-test is intended to provide a confidence, Go / No Go, test to show that the EGPWS is fully operational. It indicates which modes of the EGPWC are currently operational and which functions are not available. Short level 1 self-test is initiated immediately following the successful completion of the self-test preamble. The results are described in Figure 6.10.6-2.
Product Specification 6.10.6.1.3 Long Level 1 Self-Test The long level 1 self-test is initiated by pressing and holding the cockpit self-test button until self-test voices start. The long level 1 self-test annunciates all configured and activated alert voices, including warning voices, caution voices and altitude callout voices. If activated, the long level 1 self-test is initiated immediately following the short level 1 self-test. The results are described in Figure 6.10.6-3.
Product Specification 6.10.6.2 Level 2 Self-Test - Current Faults Level 2 self-test provides enunciation of all faults existing at the time of the request. Level 2 self-test is initiated by pressing the cockpit self-test button within 3 seconds of the end of level 1 self-test. The results are described in Figure 6.10.6-4. During level 2 self-test, a Short Cancel or Long Cancel terminates the self-test level and “PRESS TO CONTINUE” is annunciated for proceeding to level 3 self-test.
Product Specification 6.10.6.3 Level 3 Self-Test - System Configuration Level 3 self-test provides enunciation of the system configuration present at the time of the request. Level 3 self-test is initiated by pressing the cockpit self-test button within 3 seconds of the end of level 2 self-test. The process is described in Figure 6.10.6-5 and includes the information as described in table 6.10.6-1. During level 3 self-test, a Short Cancel bumps the enunciation to the next level 3 item (e.g.
Product Specification 6.10.6.4 Level 4 Self-Test - Fault History Level 4 self-test provides enunciation of the faults recorded over the last 10 flight legs. Level 4 self-test is initiated by pressing the cockpit self-test button within 3 seconds of the end of level 3 self-test. The process is described in Figure 6.10.66. If any faults were recorded in the last ten legs then voice sequence as described in Table 6.10.6-2 will be annunciated. Otherwise the message “NO FAULTS” will be annunciated.
Product Specification 6.10.6.5 Level 5 Self-Test - Warning History Level 5 self-test provides enunciation of the alerts (cautions and warnings) recorded over the last 10 flight legs. Level 5 selftest is initiated by pressing the cockpit self-test button within 3 seconds of the end of level 4 self-test. The process is described in Figure 6.10.6-7. If any alerts were recorded in the last ten legs then voice sequence as described in Table 6.10.6-3 will be annunciated.
Product Specification 6.10.6.6 Level 6 Self-Test - Discrete Input Test Level 6 self-test provides enunciation of any changes in the state of discrete inputs for the defined configuration. Changes in the state of the actual self-test discrete are not annunciated as it is directly tested in its use to control the test sequences. This feature is provided for production aircraft testing of discrete input.
Product Specification 6.10.7 ATP The Acceptance Test Procedure (ATP) for the EGPWC will be functional in nature, not designed to characterize the box. There is no requirement to produce a data sheet showing input thresholds or accuracy of internal processing. The ATP is not required to test any of the software or databases, other than to verify that they are present and operating.
Product Specification Input Signal Monitoring: All input signals will be monitored and any failed signals, busses, or LRU’s will by identified. Watchdog Monitor: The Watchdog Timer resets the processor when the software fails to complete its execution cycles in the specified amount of time. Aircraft configuration database Monitor: The configuration database is monitored for database integrity.
Product Specification Command “^Z“ “^Y” “HELP“ “?“ “PS” “CFG” “CMR” “CMW ” “CUW ” “FHF” “FHI” “FHG” “FHW” “FHS” “FHC” “FHE” “GPS” “ST” “ST 1” “ST L” “ST “ “ST C” “VOI” “BI” Description This command Starts (or re-starts after a “^Y”) each session. Upon receiving the “^Z” command the EGPWC provides a “>“ prompt indicating that the communication link has been established and the EGPWC is ready to accept other commands.
Product Specification The RS-232 port will default to the following characteristics: 19,200 baud, 8 bits, no parity, and 1 stop bit. The other potential baud rate settings is 38400. The baud rate 38400 will be used for file/database loading only. See section 6.10.4 for a description of the EGPWC front panel test plug connections required to support RS-232 communications. 6.10.10 Data Loading Interface The EGPWC has the capability of having software, or databases, updated by using a PCMCIA card.
Product Specification J2 connector J3 connector 4 3 28 RS232 TX GPS RECEIVER SERIAL CHANNEL SMC1 RS232 RX GND GND SERIAL CHANNEL SMC2 MUX ENABLE INTERNAL GPS PORT 11 RS232 RX/ RS422 RX A 45 RS232 TX/ RS422TX A 12 RS422 RX B 46 RS422 TX B GSE Present 2 Smart Cable Present 6 Smart Cable Power (5V) AIC SERIAL CHANNEL #1 10 RS232 RX/ RS422 RX A 27 RS232 TX/ RS422TX A 11 1 Smart Cable Ground RS422 RX B 44 RS422 TX B 16 Audio Clock Smart Cable Clock 7 Audio MOSI 9 29 Groun
Product Specification If an error occurs during data loading (i.e. there is a failed load), the EGPWC will NOT attempt to start the application software but will wait for a new dataload to commence and successfully complete. Once the dataload is complete, the load request is cleared. If GSE is not present then the EGPWS will be rebooted. If GSE is present then the EGPWS will run the software previously present in RAM, without resetting the EGPWS or rebooting. 6.10.10.
Product Specification • • • Configuration database. Voice Waveform database Image DSP programs In self-test level 3 and RS-232 present status, the application software will report the versions of the application software (which includes the configuration database), terrain database, Envelope Modulation database, and boot code. In addition, the application software will report the EGPWC part number, modification status, and serial number.
Product Specification In addition, the EGPWC ATP performs a “final” check to ensure that the internal CCAs and software are correct for the indicated EGPWC part number. 6.10.11.4 Production Configuration Management The application software, Envelope Modulation database and terrain database will be loaded into the EGPWC at the 965 production level. The loading will be done via PCMCIA card(s). The PCMCIA card(s) will contain the upload list and appropriate “canner” output.
Product Specification An example of a present status output is shown below: EGPWC CONFIGURATION PART NUMBER: MOD STATUS: SERIAL NUMBER: APPLICATION S/W VERSION: TERRAIN DATABASE VERSION: ENVELOPE MOD DATABASE VERSION: BOOT CODE VERSION: CURRENT FAULTS GPWS COMPUTER OK GPWS EXTERNAL FAULTS: GPS BUS FAULT CONFIGURATION: AIRCRAFT TYPE =X AIR DATA TYPE =X RADIO ALTITUDE TYPE =X N
Product Specification 6.10.13 Flight History Output Formats When requested via the RS-232 commands (see section 6.10.9) the EGPWS will output the recorded flight history to the terminal screen. The format of the history outputs is described in the following sections. The standard requirements of RS232 output (i.e. page breaks, etc.) still apply to these formats. For all history displays except fault history, an is displayed for each event.
Product Specification 6.10.13.1 Fault History Output Format Fault history recording is described in detail in section 6.10.3. When requested, the EGPWS will output fault history information in the following order and format: “FAULT HISTORY:” “FLIGHT LEG” “GPWS COMPUTER FAULTS:” (if any exist), Internal Fault 1 Internal Fault 2 (etc.) “GPWS EXTERNAL FAULTS:” (if any exist), External Fault 1 External Fault 2 (etc.
Product Specification 6.10.13.2 INOP History Output Format INOP history is described in detail in section 6.10.3.2.2 When requested, the EGPWS will output INOP history information in the following order and format: “INOP HISTORY:” “FLIGHT LEG” “GPWS COMPUTER FAULTS:” (if any exist), Internal Fault 1 Internal Fault 2 (etc.) “GPWS EXTERNAL FAULTS:” (if any exist), External Fault 1 External Fault 2 (etc.
Product Specification 6.10.13.3 Ground History Output Format Ground history is described in section 6.10.3.4. When requested, the EGPWS will output ground history information in the following order and format: “GROUND HISTORY:” “GPWS COMPUTER FAULTS:” (if any exist), Internal Fault 1 Internal Fault 2 (etc.) “GPWS EXTERNAL FAULTS:” (if any exist), External Fault 1 External Fault 2 (etc.
Product Specification 6.10.13.5 Status History Output Format Status history is described in detail in section 6.10.3.5. When requested, the EGPWS will output the status history information in the following order and format: “STATUS HISTORY:” “ENVELOPE MOD IN PROGRESS:” “FLIGHT LEG” < Operating Time > “FLIGHT LEG” < Operating Time > etc.
Product Specification 6.10.13.6 Cumulative Counters Output Format The cumulative counters are described in detail in section 6.10.3.2.1 and section 6.10.3.3.1. When requested, the EGPWS will output the EGPWS cumulative counter information in the following order and format: “WARNING COUNTERS:” In this table ‘Voice’ refers to the actual warning voice given by the EGPWS (i.e. “Pull Up”).
Product Specification 6.10.14 Internal GPS Status Format The EGPWS will be capable of displaying the status for up to eight visible satellites being tracked on the eight channels of the receiver. Note that if the receiver is tracking less than eight satellites, the unused satellite ID’s will be set to zero. The data will be collected from the receiver and when requested this data will be output to the user.
Product Specification 6.10.15 Configuration Module Programming via RS-232 The application code is capable of loading the configuration module with new data. This programming is achieved using the keyboard monitor. The ‘^Z’ command from the keyboard is used to activate the keyboard command and allow the EGPWS to accept valid commands. To prevent inadvertent access to the configuration module’s EEPROM the keyboard monitor is set up with a tiered menu.
Product Specification String Format Version String Format Version (1 byte) Data Block Number of Categories (1 byte) Category 1 (1 byte) Category 2 (1 byte) Category 3 (1 byte) . . . Last Category (1 byte) CRC String CRC String (4 bytes) TABLE 6.10.15.1.1-1 STRING FORMAT VERSION ZERO FOR CMW COMMAND String Format Version String Format Version (1 byte) Data Block Number of Categories (1 byte) Category 1 (1 byte) Category 2 (1 byte) Category 3 (1 byte) . . . Last Category (1 byte) TABLE 6.10.15.1.
Product Specification After being written to EEPROM, the configuration module data will be read back. If this data fails the 32-bit CRC it will be taken to indicate the data write to the EEPROM failed, and the write process shall be restarted for up to four attempts. After programming the memory locations, the EEPROM will be read per section 6.10.15.2 to confirm a successful data transfer to the configuration module occurred.
Product Specification Appendices Appendix A: Definitions The following acronyms are used in this document: HIF-2121/R5 Acronym Interpretation AAAS ADC ADS AGL AHRS MSL ATA ATP BCD BIST BIT BITE BNR BOSS C/O CAA CFIT CFM COTS CP CRS CW DAA DADC DAU DC DDM DEVN DH DITS DME DO DSP DSU DSWC EEPROM EFCP EFIS EGPWC EGPWD EGPWS EICAS EMI ENB EPROM F/T F/W FAA FCC FDR FIAS FMC FMS Alternate Audio Alert Select Air Data Computer Air Data System Above Ground Level Attitude Heading Reference System Mean Sea Level
Product Specification HIF-2121/R5 Acronym Interpretation FPM FSEU FWC G/S GMT GPS GPW GPWS GT H/W HDG HDOP HSID I/O IAC ILS INOP IOC ISO IVS KT KTS LED LRRA LRU LSB LT MCP MDA MFD MKII MKVI MKVIII MLS MSB N/A NCD ND NVM OMS P/N PAR PC PCMCIA PFD PMAT PP PVM PWS QFE QNH RA RAM RDOP ROM RTCA RTS RWY S/T Feet per Minute Flaps/Slats Electronic Unit Fault Warning Computer Glideslope Greenwich Mean Time Global Position System Ground Proximity Warning Ground Proximity Warning System Greater Than Hardware Head
Product Specification HIF-2121/R5 Acronym Interpretation S/W SDI SDRD SIG SPC SRD SSM ST SWC TACAN TAD TA&D TBD TCAS TCF TERPS TK TLB TSO TTL UART USM UTC UUT VDC VDOP VHF VLSI VOR W/S WC Software Source/Destination Identifier Software Design Requirements Document Significant Stall Protection Computer System Requirements Document Sign Status Matrix Self Test Stall Warning Computer Tactical Air Navigation Terrain Awareness Display Terrain Awareness & Display To Be Determined Traffic Collision Avoidance
