Home

TITLE SHEET A 97896

1. cooo 10 1 2 LAMP FORMAT TYPE 1 AND 2 PA 10 13 LAMP FORMAT REVERSAL 22 10 1 4 GLIDESLOPE CANCEL DISCRETE OUTPU M 94 10 1 5 WINDSHEAR LAMP DRIVER DISCRETE OUTPUTS 26 10 1 6 TERRAIN OBSTACLE LAMP DRIVER DISCRETE OUTPUTS 10 1 7 TERRAIN DISPLAY SWITCHING AND TERRAIN DISPLAYABLE DISCRETE OUTPUTS 10 1 8 RAAS
2. BKR PNL BP MKV A EGPWS AUDIO GPWS Los AIRCRAFT ESS BUS E 2212 POWER INPUT LOW LEVEL zc UN SWITCHED 3 115 VAC 115 VA PRE AMP OUTPUT AUDIO IN PILOT 22 13 POWER RETURN 600 OHMS NOMINAL lo 13D 4 ICS 15 Lt CHASSIS GND iT 22 14 CHASSIS GROUND zin H7 M UN SWITCHED AUDIOIN COPILOT OCKPIT kd SPEAKER AIRCRAFT Lt CHASSIS GND CHASSIS SIGNAL GROUND DEDICATED i HIGH LEVEL rH Bag _ SPEAKER OUTPUT GPWS SPEAKER E 429 Channel 1 MP Epic m B OHMSINOMINAL pta ge BOHM FWATTS X HIGH Speed A mr DO NOT CONNECT SIGNAL RETURN WIRE TO ANY GROUND IRS BUS 1 B 68 33 rase re is ARINC429 Channel 9 Eoi i 364 Inertial Vertical Acceleration 137 Flap Angle 19 A LOW Speed EEA 429 Channel 2 m an HOD B DSWC BUS 2 HIGH Speed A 10000 Zes umanan paana BUS 1 B 10D B Sane f ARINC 429 Channel 10 A 9 A Speed ARINC 429Channel3 N C ATINE 8 j BU82 LOW Speed A 11 2 Og 2 Comet Ar ARDATABUST
3. cooo 15 sals 16 16 cooo 18 55 49 ss 21 wes 21
4. 7 N cooo we 11 e 12 weed sls
5. poo oo OUTPUT MP LL 2 4 CTEDD DISPLAY 120 GRN RANGE 2 EH E PLT DSPLY CTL DC XXX ON GRN 120 H M jo fr MOM TERRAIN SELECT i t p PLT SYMBOL GENERATOR 1 Ae Vee poesie C Es 9 DC XXX DATA TERR SEL OUT WX VIDEO IN 1 11 si WX VIDEO IN 1B 1 ARINC 2 DATA E 1 Figure A 2 Example Display Interface Using WXR Terrain Switching Relay CAGE CODE 97896 SCALE NONE SIZE A DWG NO PDS69000940 501 REV SHEET 35 HIF 1472R6 1 BP MP TP MKV A EGPWS PPCNF2 PPCNF3 PPCNF4 PPCNF5 PPCNFG Optional Inputs Select GPS and GPIRS Overlays PPCNF7 Dual ILS Dual or Triple LRRA Alternate Mode 4B Reversal Glideslope Cancel EGPWS Suppress QFE Select PPCNF10 Audio Declutter Disable Volume Level Control GPS Altitude Ref PPCNF11 Windshear ControliLamp Format PPCNF12 Aircraft Model Selection Altitude Callout Menu Selection SIM Reposition TAD TCF Peaks Obstacles Enable PPCNF13 Bank Angle Alternate LRRA Configuration Option 3 PPCNF14 Altemate GPS Bus Speed Configuration Options 1 amp 2 16 Audio Menu PWS Option Alternate PopUp RCD Enie ond PPCNFI5 Pin Strapping Parity PPCNFI7 Alternate Terrain Display GPS Altitude ess PPCNFI9 Pro
6. 78 7D Altitude Callouts Enable Giideslope 2 Backcourse oo INH Gnd Mode 6 Low Volume ENB Gnd EN Down Gnd EN Down Gnd Reposition oo REP Gnd Air Ground switch E In Air Gnd EGPWS Self Test O 0 1 Momentary ST Landing Gear Override 28 VDC 4 Down Gnd d Landing Flap Override VDC m Down Gnd RAAS Inhibit ma INH Gnd Spare Ground Discrete Inputs Spare 28 VDC Discrete Inputs HIF 1472R6 1 CAGE CODE 97896 SCALE NONE SIZE A DWG NO PDS69000940 501 Figure A 4 Example EGPWS Analog Inputs and Discrete Input REV SHEET 37 To Aircraft Interfaces Notes IIT HIF 1472R6 1 Generic MKV A Installation Cabling and Grounding Reference Diagram I AU PL KA 5 jieuondo 10018 1 q Power High Input___ High Input To Aircraft Power lt W Bower Return AN lt Chassis Ground Go an AN Power Return and Chassis Ground 21 Inches Long Maximum excluding Ring Terminal Shielded Wire Ground Pigtails 20 Inches long Maximum excluding Ring Terminal Connect Power Return Chassis Ground and Shield
7. SHEET 9 Related TSO Non TSO Functions SW Comment Functional Release Category Version Runway Awareness Note 1 Taxiway Takeoff Caution on ground Provides flight crew with awareness Caution Caution On Taxiway On Taxiway if excessive taxi speeds or inadvertent take off on a taxiway Distance Remaining During Rejected Takeoff Advisory on ground Provides the flight crew with awareness advisory of aircraft position relative to runway end during a Rejected Takeoff Runway End Advisory on ground Provides the flight crew with awareness advisory of aircraft position relative to runway end Approaching Runway Advisory in air Provides the flight crew with awareness advisory of which runway the aircraft is lined up with Approaching Short Runway Advisory in air Provides the flight crew with awareness advisory when runway aircraft is lined up with may be too short for landing using operator specified lengths Approaching Short Runway Caution in air Provides the flight crew with awareness Caution Caution Short Runway Short Runway when runway aircraft is lined up with may be too short for landing using operator specified lengths Distance Remaining During Landing Rollout Advisory in air on ground Provides the flight crew with awareness advisory of aircraft position relative to runway end during landing rollout Taxiway Landing Caution in air Provides the flight crew with awar
8. takeoff mode during which the Boeing algorithm shifts the alerting threshold slightly to desensitize the warning For the three missed alerts maximum computed shear was within 001 of the takeoff alert threshold The Boeing windshear algorithm will only issue an alert if the threshold is exceeded Therefore the missed alerts are consistent with the design of the algorithm TSO C117a specifies that when the equipment is subjected to an average shear intensity of 0 21 an alert must be generated within 5 seconds The EGPWS will deviate from this standard in that when the Honeywell Windshear algorithm is selected alerts will be generated within 5 5 seconds when the aircraft is in the takeoff phase of flight Honeywell has shown that the Honeywell windshear algorithm provides an equivalent level of safety to the standards of the TSO In particular the algorithm has been shown to be performing as designed during takeoff conditions The Honeywell windshear algorithm deviates from the TSO by small margins The EGPWS windshear alerting functions meet the intent of the TSO with regard to unwanted late or missed alerts 5 1 4 Environmental Qualification Per DO 160G In Lieu of DO 160B C Honeywell has received concurrence from the FAA that environmental qualification to DO 160G can be used in lieu of DO 160C called out in TSO C92c and DO 160B called out in TSO C117a The use of DO 160G will provide an equivalent level of safety 5 2 Enhancem
9. N A 0 925 2 Amp Delayed Action Circuit Breaker N A 5 Amp Delayed Action Circuit Breaker The heater blanket 6900094 1 xxx only turns on at temperatures lt 40 and turns off at temperatures gt 20 Power numbers are for input at 28 0 VDC 6 4 1 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 system response to power interrupts will be as follows Power interrupt duration System Response Maximum Delay to Normal Operation 115 VAC Powered EGPWC P Ns 69000940 xxx and 69000942 xxx T lt 200 msec No effect Not applicable T gt 200 msec Cold start 28 VDC Powered EGPWC P Ns 69000941 xxx No effect Not applicable T gt 60 msec Cold start 20 seconds Max 20 seconds Max 6 5 Mechanical 6 5 1 Packaging The EGPWC is packaged in 2 MCU ARINC 600 6 form factor chassis Refer to the outline drawing CAGE CODE referenced in section 3 The part number appearing on the front panel identification plate is 69000940 xxx MKV A EGPWS 115 VAC 6900094 1 xxx EGPWS 28 VDC 69000942 xxx MK V A EGPWS 115 VAC Alternate PN 97896 SCALE NONE SIZE A DWG NO PDS69000940 501 REV C HIF 1
10. 4110 Speed M NC Hap B BUS 2 BU NIC Ar 88 DIT ARINC 429 Channel 19 429Channel21 wc 158 A Speed e B B BUS2 A B 46D Speed 15A B NIC Bl NIC 158 UM Lit HIF 1472R6 1 CAGE CODE 97896 SCALE NONE SIZE A DWG NO PDS69000940 501 Figure A 1 Example ARINC 429 Parameter Source Inputs and Audio Output REV SHEET 34 MP A DISPLAY a 10A RANGE 1 10B J1 P 54 TERRAIN SELECT 4 POP UP i DC XXX DATA TERR SEL OUT J1 A 1C EGPWS OUTPUT 1 9 ARING 2 DATA ARNA UE 10 COPILOT INSTRUMENT PANEL E WX VIDEO IN 1A elc LM TT WX VIDEO IN 1B 1 pln MANA _____ SER TERRAIN DISPLAY A A a T OUTPUT DATA 1 T WX 453 B ARINC 453 B 3B 4 0 kont E wan m TERRAIN DISPLAY f A 3C Le OUTPUT DATA 2 EN AS t id m ARINC 453 B 30 kl 12 ANNUNCIATOR BOX sc 8 1 EE TERR DISPLAY PILOT INSTRUMENT PANEL POPUP DISCRETE 10D
11. Fs cat SHEET 1 OF 46 HIF 1472 R6 1472R6 DOT HIF 1472R6 1 Table of Contents 1 0 INTRODUCTION 2 0 SCOPE ieee 3 0 REFERENCE DRA WINGS DOCUMENTS 4 0 LIST OF ABBREVIATIONS 5 0 SYSTEM PERFORMANCE 5 1 TSO DEVIATIONS 5 1 1 MODE 2 GPWS ALERT ENVELOPE LOWER MAXIMUM ALTITUDE FROM 1250 FEET TO 950 FEET 5 1 22 MODE 1 GPWS ALERT ENVELOPE RAISE LOWER CUTOFF FROM 10 FEET TO 130 FEET 5 1 3 MODE 7 WINDSHEAR ALERTING GUST CONDITIONS AND SHEAR INTENSITY TESTS 5 1 4 ENVIRONMENTAL QUALIFICATION PER DO 160G IN LIEU OF DO 160B C 5 2 ENHANCEMENT TO GPWS 5 3 NON TSO FUNCTIONS 5 31 SMARTRUNWAY SMARTLANDING FUNCTIONS 6 0 COMPUTER DESIGN 6 1 COMPUTER INPUT OUTPUT 6 2 ENVIRONMENTAL 6 3 RELIABILITY 6 3 1 SCHEDULED MAINTENANCE 6 3 2 CALIBRATION 6 33 6 4 EGPWC POWER REQUIREMENTS 6 41 SYSTEM RESPONSE TO POWER INTERRUPTS 6 5 MECHANICAL 6 5 1 PACKAGING 6 5 2 OUTLINE M 6 5 3 REAR CONNECTORS c 6 5 4 CONNECTOR SHELLS amp CONTACTS 6 5 5 WEIGHT dass 6 5 6 AIRCRAFT MOUNTING 21 7 0 SOFTWARE DESIGN 229 8 0 INSTALLING MKV A AN AIRCRAFT PREVIOUSLY FITTED WITH EGPWS 24 8 1 RETAINING THE PIN PROGRAM STRAPPING TO DEFINE CONFIGURATION OPTIONS 24 8 2 USING THE APD OR OSS TO DEFINE CONFIGURATION OPTIONS 24 9 0 FEATURE AND OPTION SELECTION 5025 1
12. Level 2 Self Test is initiated by pressing the GPWS TEST switch to start the Level 1 Self Test 2 Once the Level 1 Self Test begins press and hold the GPWS TEST switch for less than 2 seconds This will cancel the Level 1 Self Test and start the Level 2 Self Test 3 Verify the following voice messages are annunciated e CURRENT FAULTS e NO FAULTS e PRESS TO CONTINUE NOTE If the EGPWS Computer or system faults exist the fault s will be annunciated as GPWS internal or external faults The aural message will provide a description of the fault If a fault is annunciated it should be corrected prior to proceeding with the remainder of this procedure Level 3 Self Test System Configuration NOTE The GPWS FAIL WINDSHEAR FAIL and TERRAIN FAIL amber lamps will be illuminated during the Level 3 Self Test The Level 3 Self Test provides enunciation of the system configuration NOTE X s listed below represent numbers or letters Any enunciations are acceptable where X is listed below e g the serial number maybe annunciated as SERIAL NUMBER 316 1 Press the GPWS TEST to start the Level 1 Self Test 2 Press the GPWS TEST switch to cancel the Level 1 Self Test and start the Level 2 Self Test 3 When you hear the message Press to continue press the GPWS TEST switch to start the Level 3 Self Test 4 Ensure the following messages regardless of order are annunciated e SYSTEM CONFIGURATION
13. 29 HIF 1472R6 1 13 0 Installation Checkout 13 1 Maintenance Philosophy Installation checkout typically consists of performing a ground test ofthe EGPWS The ground test consists of performing Self Test Levels 1 2 3 and 6 to verify proper installation and function of cockpit switches and lamps The Line Maintenance Manual LMM referenced in Section 3 0 provides a resource for troubleshooting in service and new installations of EGPWS The LMM also provides details on other routine EGPWS tasks such as database loading 13 2 Ground Test A system checkout to verify correct installation should be performed A generic ground test procedure is included in Appendix B of this document This sample procedure should be tailored to the installation being tested in order to verify the aircraft specific interfaces Further examples of ground tests are available from Honeywell via the EGPWS website To obtain a copy of a sample Ground Test Procedure please visit www egpws com select the Support tab then Installation Information then Ground amp Flight Test Procedures sub page Also refer to the Line Maintenance Manual for more information on line maintenance operations and troubleshooting 13 3 Computer Status LED A COMPUTER STATUS LED is located on the front panel of the LRU During the power up sequence the LED should be ignored Once the LRU has completed its power up initialization approximately 20 seconds after application of power t
14. MONITOR DISCRETE OUTPUT 26 10 1 9 INDICATOR CONTROL FORMAT 1 1 1 26 10 1 10 INDICATOR CONTROL SUPPLIERS ener 20 1100 ELECTRICAL INTERFACE Ne 11 1 OUTPUT DISCRETE DIODE ISOLATION 11 2 TERRAIN DISPLAY INTERFACE 28 11 2 1 SWITCHING RELAYS 28 113 ANALOG INTERFACES 26 114 CABLING AND GROUNDING 20 12 0 EXTERNAL POSITION SOURCE 121 HORIZONTAL POSITION SOURCE 29 12 2 VERTICAL POSITION SOURCE E 13 0 INSTALLATION CHECKOUT 131 MAINTENANCE PHILOSOPHY 30 13 2 GROUND TEST 14 0 INSTALLATION LIMITATIONS 31 141 TSO C92C INSTALLATION NOTE 14 2 TSO C117A INSTALLATION NOTE 14 2 1 TSO C117A INCOMPLETE TSO ARTICLE D 14 2 2 BOEING WINDSHEAR CAUTION PRE ALERT 14 3 TSO C151C INSTALLATION NOTE 144 INSTALLATION NOTE P 145 GPS INSTALLATION NOTE Om 146 MODE 1 GPWS ENVELOPE RAISE LOWER FROM 10 FEET 130 FEET INSTALLATION NOTE 14 7 LOW AIRSPEED MONITOR ON 69000940 101 AND 69000942 151 INSTALLATION NOTE 32 148 TERRAIN AWARENESS CAUTION AND WARNING VISUAL ALERTS DURING SELF TEST APPENDIX A SAMPLE WIRING DIAGRAMS APPENDIX B GROUND TEST PROCEDURE an
15. Wire Ground Pigtails to the Aircraft ground plane Power High Power Return and Chassis Ground wires to be 22 AWG minimum All wires are 24 AWG unless noted otherwise Shield Wire Ground Pigtails to be 24 AWG minimum All lengths are straight line measurements This is a generic reference drawing Actual cable bundling and aircraft installation may vary as appropriate Connectors other than the MKV A Aircraft Interface Connector are shown as a reference and are not required Also cable bundling as shown is for illustrative purposes only Figure A 5 Example EGPWS Cabling and Grounding CAGE CODE 97896 SCALE NONE SIZE A DWG NO PDS69000940 501 REV SHEET 38 Appendix B Ground Test Procedure 1 0 General Accomplishment of the procedures in this section verify that the system has been properly installed It is assumed that the person s performing these tests has a working knowledge of the Honeywell MKV A EGPWS installed in the aircraft It is not necessary to follow the exact order of the test procedures as they are listed It is up to the discretion of the person s performing the tests as to what order is the most logical to perform these tests 2 0 Test Equipment PC with MKV A EGPWS BOSS software installed Ethernet cable connected between PC and EGPWC a compatible USB to Ethernet adapter may be used 6000 monophonic headphone with standard 1 4 audio plug only needed if monitoring self test audio from the EGPWC front panel h
16. aural volume NOTE GPWS FAIL TERRAIN FAIL and WINDSHEAR FAIL annunciators will illuminate during all levels of Self Test 4 2 System Self Test 4 2 1 Self Test Level 1 Long Self Test Accomplish a system Self Test per the following steps NOTE Aircraft must be in a location that has an unobstructed field of view of GPS satellites to ensure the GPS receiver can navigate The TERRAIN FAIL annunciator will be illuminated until the GPS receiver is properly tracking position The initial position fix may take up to 20 minutes to acquire CAGE CODE 97896 SCALE NONE SIZE A DWG NO PDS69000940 501 REV C SHEET 39 HIF 1472R6 1 4 2 2 Level 1 Self Test 1 Apply power to the aircraft Ensure all systems reguired by EGPWS are on and functional 2 Ensure that TERRAIN is selected for display 3 Press and hold down the GPWS TEST switch for more than 2 seconds 4 Verify the following sequence a GPWS FAIL Amber lamp turns on b WINDSHEAR FAIL Amber lamp turns on c TERRAIN FAIL Amber lamp turns on d EGPWS Amber lamps turn on e Voice GLIDESLOPE f EGPWS Amber lamps turn off g G S CANCEL Amter lamp turns on momentarily h EGPWS Red lamps turn on 1 Voice PULL UP 1 EGPWS Red lamps turn off WINDSHEAR Red lamps turn on 1 Voice Siren Windshear Windshear Windshear m WINDSHEAR Red lamps turn off n WINDSHEAR Amber lamps turn on momentarily Terrain test pattern is displayed
17. be heard Select the TERRAIN INHIBIT switch The enunciation TERRAIN OFF should be heard Deselect the TERRAIN INHIBIT switch The enunciation TERRAIN ON should be heard Select the GPWS FLAP OVRD switch The enunciation LANDING FLAPS should be heard Deselect the GPWS FLAP OVRD switch The enunciation NOT LANDING FLAPS should be heard Depress and release the Pilot s CANCEL GS switch The enunciation GLIDESLOPE CANCELLED followed by GLIDESLOPE ENABLED should be heard Depress and release the Co Pilot s CANCEL GS switch The enunciation GLIDESLOPE CANCELLED followed by GLIDESLOPE ENABLED should be heard Press the GPWS TEST switch to cancel the Level 6 Self Test 5 0 Analog Input Test The procedure listed below tests a radio altimeter input This is an example of a test for one type of analog sensor The circuit breaker nomenclature and location are examples only and will vary according to the specific aircraft installation 5 1 Radio Altimeter Interface Test 1 uet CAGE CODE HIF 1472R6 1 Make sure GPWS FAIL WINDSHEAR FAIL and TERRAIN FAIL lamps are NOT illuminated Open the 28 VDC circuit breaker labeled Rad Alt located in the R H forward overhead C B panel Verify the GPWS FAIL lamp illuminates Verify the WINDSHEAR FAIL lamp illuminates Verify the RAAS INOP lamp illuminates Verify the visual RAAS INOP message is displayed on t
18. class of aircraft to determine that the aircraft installation conditions are within the TSO standards The article may be installed only if further evaluation by the applicant documents an acceptable installation and is approved by the Administrator 14 2 1 TSO C117a Incomplete TSO Article TSO C117a provides minimum performance standards for airborne windshear warning and escape guidance systems for transport category aircraft The MKV A EGPWS provides the airborne windshear warning function but does not provide escape guidance and therefore only provides part of the functionality specified in the TSO An Airborne Windshear Warning System is defined in TSO C117a paragraph 4 1 while an Airborne Windshear Escape Guidance System is defined in paragraph a 4 iv In order to provide the complete functionality of both a windshear warning and an escape guidance system a separate guidance system must be installed in addition to the windshear warning function that is provided by the MKV A EGPWS The windshear warning function provided by the MKV A operates independently of any escape guidance function and or auto recovery system The windshear warning function is described in the Product Specification for the MKV A Enhanced Ground Proximity Warning System document no PDS69000940 000 Details of the windshear alerting function and the system performance is described in section 6 5 of the product specification document 14 2 2 Boeing Windshear
19. e PART NUMBER 69000940 10X 69000941 10X 69000942 15X e MOD STATUS XX e SERIAL NUMBER XXXXX e SOFTWARE VERSION PART NUMBER XXX e APD VERSION PART NUMBER XXX e RCD PART NUMBER XXXXXXXX XXX e TERRAIN DATABASE VERSION XXX ENVELOPE MODULATION DATABASE VERSION PART NUMBER e OSS CONFIGURATION FILE XXX e BOOT CODE PART NUMBER 69001906 XXX e AIRCRAFT TYPE XXX e AUDIO MENU X e ALTITUDE CALLOUT MENU X Note The messages listed below will only be heard if the option has been enabled or disabled from the basic configuration via program pin strapping or APD OSS programming 97896 SCALE NONE SIZE A DWG NO PDS69000940 501 REV C SHEET 41 HIF 1472R6 1 CAGE CODE 97896 HIF 1472R6 1 ALTERNATE VOLUME I SELECTED ALTERNATE VOLUME 2 SELECTED CONFIGURATION OPTION 1 SELECTED CONFIGURATION OPTION 2 SELECTED CONFIGURATION OPTION 3 SELECTED LAMP FORMAT 2 SELECTED SMART CALLOUT SELECTED VISUAL SUPPRESS SELECTED AUDIO DECLUTTER DISABLED ALTERNATE MODE 6 VOLUME SELECTED OFE SELECTED ALTERNATE GLIDESLOPE CANCEL SELECETED OPTIONAL INPUTS SELECTED SINGLE GPS SELECTED DUAL GPS SELECTED SINGLE GPIRS SELECTED DUAL GPIRS SELECTED DUAL RADIO ALTIMETER SELECTED TRIPLE RADIO ALTIMETER SELECTED WINDSHEAR DISABLED WINDSHEAR CAUTION DISABLED WINDSHEAR CAUTION WITH VOICE SELECTED WINDSHEAR INOP DISABLED TERRAIN CLEARA
20. lighted annunciation on the switch e The aircraft must be flying in a configuration with specific slats flaps gear and speed brake settings e When active an aural Standby is provided at 125 and 95 feet and an aural Flare is provided at 75 feet e Ifa Mode 1 alert is present above 130 feet and remains active as the aircraft passes through 130 feet the Mode 1 alert algorithm will remain active to 10 feet The EGPWS performs fault monitoring of the steep approach select input Please note that this Steep Approach function is different from the standard EGPWS steep approach function which is selectable for all aircraft types This specific steep approach mode is limited to specific aircraft models and is approved for the A320 family of aircrafts only Consult the aircraft configuration data tables in the ICD 5 1 3 Mode 7 Windshear Alerting Gust conditions and shear intensity tests TSO C117a specifies that when the equipment is subjected to an average shear intensity of fayx 0 105 alert must be generated within 10 seconds There are three occurrences of missed warning alerts when using CAGE CODE 97896 SCALE NONE SIZE A DWG NO PDS69000940 501 REV C SHEET 7 HIF 1472R6 1 the Boeing windshear algorithm three occurrences of missed warning alerts for the Boeing windshear algorithm occurred when in the horizontal decreasing energy orientation The significant difference is that the missed alerts happened in the
21. that is the central element of the Enhanced Ground Proximity Warning System 5 e 69000940 starting with 101 e 69000941 starting with 101 e 69000942 starting with 151 2 0 SCOPE This document provides an overview of a typical EGPWS system installation including self test and override switches indicator lamps terrain displays speaker and or audio panel interfaces Generic system block diagrams including interfaces to control panels and displays and sample wiring diagrams are included Interface details for specific aircraft types are contained in the Interface Control Document for the MKV A EGPWS listed in Section 3 0 In addition to this installation manual the installer needs to have the ICD available in order to determine the details for the particular aircraft type that is being configured Maintenance aspects of the installation such as Self Test fault isolation and troubleshooting are contained in the Line Maintenance Manual for the MKV A EGPWS listed in Section 3 0 For a complete description of the system functions see the Product Specification for the MKV A EGPWS listed in Section 3 0 This document is intended to provide the information specified in TSO C151c 5 6 TSO C92c d 1 iii d 1 iv and d 1 v and TSO C117a h 1 iii h 1 iv and h 1 v 3 0 REFERENCE DRAWINGS DOCUMENTS Document Drawing Document Drawing Number Title HWS69000942 201 Outline Drawing E
22. 0 0 COCKPIT ANNUNCIATORS 25 CAGE CODE 97896 SCALE NONE SIZE A PD569000940 501 REV SHEET 2 HIF 1472R6 1 cooo 1 2 Un A
23. 472R6 1 SHEET 16 Figure 6 5 1 1 MKV A EGPWC CAGE CODE 97896 SCALE NONE SIZE A DWG NO PDS69000940 501 REV C SHEET 17 HIF 1472R6 1 6 5 2 Outline ise 8 350 11 5 14 3 56 HOLES AIR COOLING OUTLET 1 13 28 63 12 90 327 66 NUN 315 98 6 50 165 10 1 64 194 06 3 82 97 03 00 02 0 0 0 51 015 3 68 0 38 1 25 05 31 75 1 27 2 14 3 56 HOLES i AIR COOLING INLET G000000000000000000000000 Figure 6 5 2 1 MKV A Outline CAGE CODE 97896 SCALE NONE SIZE DWG NO PDS69000940 501 REV C SHEET 18 HIF 1472R6 1 6 5 3 Rear Connectors The rear connector is divided into three shells The top and middle shells contain all interface signals Power interface is in the bottom shell isolated from interface signals Connector index pin coding is orientation 08 for 115V reference figure 6 5 3 1 and orientation 10 for 28V reference figure 6 5 3 2 in accordance with ARINC 723 1 recommendations for the GPWS Part numbers for the rear connectors are listed in section 6 5 4 FACE VIEW OF ENGAGING ENDS Oo CENTER POST CENTER KEY C3 A gt OG RIGHT LEFT POST LEFT KEY POST RIGHT KEY ogo DARKENED PORTION INDICATES EXTENDED PART OF POST IN PLUG E KEY HOLE SHOWN IN RECEPTACLE PLUG RACK RECEPTACLE
24. 6 SCALE NONE SIZE A DWG NO PDS69000940 501 REV C SHEET 23 HIF 1472R6 1 8 0 Installing a MKV A in an Aircraft Previously Fitted With a MK V EGPWS The MKV A EGPWC is designed as a replacement for the MK EGPWC The MKV A EGPWC retains all previous functions of the V EGPWC while addressing issues with out of production parts and limitations with memory processor throughput and input output interfaces It also provides updated interfaces for software uploading and downloading which include Ethernet and USB memory stick data loading capability The MKV A EGPWC is a direct replacement for the previous MK V EGPWC with part numbers 965 0976 OXX XXX XXX 965 1676 XXX Airbus and 965 1690 XXX Boeing The table below shows the part numbers for the initial release of the MKV A and the MK V model that it replaces MKV A to existing MK V part number mapping New MKV A EGPWC Characteristics Replaces MK V EGPWC Characteristics Part Number Part Numbers 965 0976 003 XXX XXX 115 VAC used on multiple aircraft PAAS HS WA 965 1690 0XX 115 VAC used on B737 and B747 8 69000941 XXX 28 VDC 965 0976 040 XXX XXX 28 VDC used on multiple aircraft 69000942 XXX 115 VAC 965 1676 0XX 115 VAC used on A320 330 340 aircraft The EGPWS has a number of selectable options that are configured as part of the installation design There are two different installation methods to control the configuration options on the MKV A The first method is to c
25. ALE NONE SIZE A NO PDS69000940 501 REV C SHEET 26 HIF 1472R6 1 GPWS FAIL or GPWS INOP AMBER With other system fail indicators With other system fail TERR INOP indicators Indicates that a function in the GPWS system is inoperative Indicates that TAD and TCF functions are inoperative or not available TERR OFF or TERR OVRD or WHITE or BLUE Within reach of both pilots TERR INHIBIT GPWS P TEST Note 1 Within reach of both pilots Indicates that TAD and TCF functions have been manually turned off Lamp illuminated when TAD TCF inhibited EGPWS press to Self Test G S P CANCEL Note 2 Within reach of both pilots EGPWS BELOW G S press to Cancel Indicator Control Color Recommended Location Function Optional Indicators and Controls gt gt gt gt gt RED In Pilot Point of View Windshear warning AMBER In Pilot Point of View WINDSHEAR WINDSHEAR WINDSHEAR FAIL or WINDSHEAR INOP With other system fail AMBER indicators Windshear caution Indicates that Reactive Windshear detection is inoperative WHITE BLUE or AMBER G S CANCELED Within reach of both pilots Within reach of both pilots FLAP OVERRIDE near Flap handle WHITE On when G S alerts are manually canceled Typically only used with Alternate G S Cancel selection Inhibits GPWS Mode 4B Too Low Flaps alert pilot may manually reset GPWS INHIBIT W
26. BOX 5 LEFT CENTERIRIGHT OSITION POS LEFT CENTER RIGHT POST POST POST OSITION KEY KEY KEY 08 2 EN o 5 4 3 POLORIZATION POSITION V C Figure 6 5 3 1 Rear Connector Keying for the 115 MKV A EGPWC CAGE CODE 97896 SCALE NONE SIZE A DWG NO PDS69000940 501 REV C SHEET 19 HIF 1472R6 1 FACE VIEW ENGAGING ENDS go CN CENTER POST CENTER KEY 8 RIGHT LEFT POST LEFT KEY POST RIGHT KEY DARKENED PORTION INDICATES EXTENDED PART OF POST IN PLUG KEY HOLE SHOWN IN RECEPTACLE PLUG RACK RECEPTACLE BOX LEFT CENTERIRIGHT POSITION LEFT CENTER RIGHT POST POST POST POSITION key KEY KEY 10 4 1 EX 10 5 4 1 POLORIZATION POSITIONS amp gt Figure 6 5 3 2 Rear Connector Keying for the 28V MKV A EGPWC CAGE CODE 97896 SCALE NONE SIZE DWG NO PDS69000940 501 REV C SHEET 20 HIF 1472R6 1 6 5 4 Connector Shells amp Contacts Vendor amp Part No ITEM QTY Honeywell Cannon EGPWS 115V Rear Connector 1 440 0497 002 NIC66F11A08AA1 ARINC 600 Size 1 EGPWS 28V Rear BKAD1 125 5611 30008 20 05W2 P0008 L Connector 1 440 0497 005 NIC66F11A10AA1 0 2 ARINC 600 S
27. Caution Pre Alert The Boeing Windshear algorithm is considered an alternate implementation of the windshear function and is limited to specific aircraft types The Boeing Windshear algorithm includes both a warning function and an optional caution pre alert function The Boeing Windshear caution pre alert function is not supported and is not available in the MKV A EGPWS on any aircraft types including those that use the Boeing Windshear Warning algorithm 14 3 TSO C151c Installation Note Per TSO C151c 5 a 3 the following statement applies to installation of the equipment covered by this document This article meets the minimum performance and quality control standards required by a technical standard order TSO Installation of this article requires separate approval CAGE CODE 97896 SCALE NONE SIZE A DWG NO PDS69000940 501 REV C SHEET 31 HIF 1472R6 1 14 4 KCPB Installation Note For installations using the KCPB display interface it should be noted that e The Check Altitude function is not supported by the MKV A EGPWS e When a Vertical Situational Display VSD is provided simultaneously with the standard horizontal display the Airplane Flight Manual Supplement AFMS should contain the following statement During a terrain warning the horizontal and vertical terrain display may not show the same color for threatening terrain and the horizontal display is to be considered the primary source of terrain threat info
28. GPWS 115 VAC SYS69000940 700 Interface Control Document for the MK V A EGPWS PDS69000940 000 Product Specification for the MK V A EGPWS APD Tool User s Manual Product Description SmartRunway SmartLanding Functions of the Enhanced Ground Proximity Warning System System RAAS 060 4303 000 EGPWS Interface Methodology KCPB Display PDS69000940 201 Line Maintenance Manual for the MK V A EGPWS PDS69000940 801 Pilot s Guide CAGE CODE 97896 SCALE NONE SIZE A DWG NO PDS69000940 501 REV C SHEET 5 HIF 1472R6 1 4 0 LIST OF ABBREVIATIONS The following acronyms may be used in this document APD BIT EGPWC EGPWS FAA G S HW ICD LRU MKV A MK V N A ND OSS PC PFD RAAS RCD RTCA SW SYS TAD TAWS TBD TBC TSO VAC VDC VSD CAGE CODE 97896 HIF 1472R6 1 Aircraft Personality Database Built In Test Enhanced Ground Proximity Warning Computer Enhanced Ground Proximity Warning System Federal Aviation Administration Glideslope Hardware Interface Control Document Line Replaceable Unit Mark V A EGPWS Warning Computer Mark V EGPWS Warning Computer Not Applicable Navigation Display Option Selection Software Personal Computer Primary Flight Display Runway Awareness and Advisory System Reloadable Customer Definitions Requirements and Technical Concepts for Aviation Software System Terrain Awareness amp Display Terrain Awareness Warning System To Be Determined To Be Confi
29. HITE Within reach of both pilots Silences GPWS audio ALTITUDE CALLOUTS WHITE Within reach of both pilots Silences radio altitude callouts audio In same assembly as above Inhibit or with other system fail indicators ALTITUDE CALLOUTS AMBER Indicates Radio Altitude Callouts functions are inoperative WHITE BLUE or GREEN Within reach of both pilots near each terrain display On WX Control panel or EFIS Control panel RANGE knob N A RAAS INOP or With other system fail Indicates Terrain Display selected ON momentary press to select deselect Use one for each pilots terrain display Controls range of Terrain display Indicates Runway Awareness RAAS FAIL AMBER indicators 2 inoperative or not il R A WHITE Within reach of both pilots RM CES RAAS OVRD Note 1 Typically GPWS Press to Test is located on the red PULL UP or GPWS lamp assembly 2 Typically G S Press to Cancel is located in the amber GPWS or BELOW G S lamp assembly CAGE CODE HIF 1472R6 1 97896 SCALE NONE SIZE DWG NO PD569000940 501 REV SHEET 27 10 1 10 Indicator Control Suppliers Listed below are some sources of indicators and or control panels for the EGPWS Supplier Contact Info Korry Electronics http www esterline com controlsystems KORR Y KORR Y Home tabid 2394 Default aspx Vivisun http www vivisun com products Eaton Staco http www flamecorp
30. ICD ERE MES AE 1 E O si FI GS AMBER GS AMBER 1 To activate Peaks amp Obstacles connect PPCNF13 to MP15D 1 an ical ac I MOM GS CANCEL LL EEE MOM GSCANCED 2 Ss To enable Terrain display Pop Up on Alert select PPCNF15 for Alt pop Up Off 1 aate CR PRA Change parity as required I0 rA so uet IE WIND WIND EVI GPWS Terrain Display Type 50 SHEAR RED SHEAR RED INOP State 2 State 1 OPEN State 3 be mid lom ma Ed State4 State 5 x Stato 6 taa M 1 AVABL State ap State9 100 State 10 State 11 114 Sato 12 ams TERR OVRD AMBER r i 18 li LA INHIBIT i 7 129 428VDC ARINC 429 KCPB ARINC 429 ARINGA28 Range Range Bus Video Bus EGPWS Discretes Left Honeywell 45 31 28 NC A Terrain PN 80 5145 XXX EE 3A Display KCPB Video Honeywell MERD 833 J238 PN 80 5204 XXX 334 J29 Honeywell GNS XLs JOTNS 910104 NIC PN 17960 0203 J101 N6 101 063 Universal 640 See note 4 See note 4 See note 4 mem PN 6402 1 1 0 WRX RIT Universal EFL890R See note 4 See note 4 See note 4 meron PN 8904 35533 0x Notes 1 ARINC 429 Ran
31. IGHT SWC AOA RIGHT SWC VALIDITY LEFT SWC AOA LEFT SWC VALIDITY MP lations See MKV A ICD Optional ILS Select required by some analog ILS install Optional ILS Select required by some analog ILS installations See MKV A ICD Optional ILS Select required by some analog ILS installations See MKV A ICD 10VDC REF AOA Potentiometer 1 Vane Potentiometer 10VDC REF AOA Potentiometer 2 SafeFlight AOA AOA VALIDITY degrees c ANALOG INPUT Channel 1 28 VDC Valid ANALOG INPUT Channel 2 28 VDC Valid t Rain INPUT Channel 3 Gnd ILS Select 28V ILS Select ANALOG INPUT Channel 4 28 VDC Valid Gnd ILS Select 28V ILS Select Gnd ILS Select 28V ILS Select ANALOG INPUT Channel 4 o 28 VDC Valid INPUT Channel 2 28 VDC Valid ANALOG INPUT Channel 4 28VDC Valid 10 Volt DC Reference Out i ANALOG INPUT Channel 2 10 Volt DC Reference Out sANALOG INPUT Channel 4 u i jANALOG INPUT Channel 2 28 VDC Valid MKV A EGPWS 7D 8c 8D JA 98 9c 9D 7A 14
32. Low Temperature 55C Low Operating High Temperature 4 5 3 amp 4 5 4 Temperature 55C In Flight Loss of Cooling 4 5 5 Ground Survival High Temperature 85C High Operating Temperature 70C In Flight Loss of Cooling Equipment Tested to Category X Not Applicable Altitude 4 6 1 Equipment Tested to Category F2 55 000 ft Decompression 4 6 2 Equipment Tested to Category A2 8 000 ft to 55 000 ft in 15 Overpressure 4 6 3 seconds Equipment Tested to Category A2 Absolute pressure 170kPa 15 000 ft Temperature Variation Equipment Tested to Category A 10C minute Equipment Tested to Category A Operational Shock and Crash Equipment Tested to Category B Safety Impulse and Sustained Performed using a ridged vibration fixture without shock mounts Crash Safety Sustained performed in centrifuge using a ridged vibration fixture without shock mounts Vibration Eguipment Tested to Category R Random and Robust Random Curves C 8 C1 Performed using a ridged vibration fixture without shock mounts Explosive Atmosphere Eguipment Tested to Category E Water Proofness 10 1 Eguipment Tested to Category X Not Applicable Fluids Susceptibility Eguipment Tested to Category X Not Applicable Sand and Dust 5 Eguipment Tested to Category D Fungus Equipment Tested to Category F By Analysis Salt Fog Test Equipment Tested to Category X Not Applicable Magnetic Effect Equipment Tested to Category Z P
33. NCE FLOOR DISABLED TERRAIN AWARENESS DISABLED SIMULATOR REPOSITION SELECTED BANK ANGLE SELECTED ALTERNATE RADIO ALTIMETER 1 SELECTED ALTERNATE RADIO ALTIMETER 2 SELECTED ALTERNATE GPS BUS SPEED SELECTED PWS OPTION 1 SELECTED PWS OPTION 2 SELECTED BANK ANGLE OPTION 1 SELECTED BANK ANGLE OPTION 2 SELECTED ALTERNATE POP UP SELECTED PEAKS ENABLED GPS ALTITUDE REFERENCE WGS 64 SELECTED PITCH ALERT ENABLED MODE 6 LOW VOLUME SELECTED TERRAIN AWARENESS AND DISABLED FMS GLIDESLOPE INHIBITED GLIDESLOPE INHIBITED STEEP APPROACH ACTIVATED SCALE NONE SIZE A DWG NO PDS69000940 501 REV C SHEET 42 STEEP APPROACH ENABLED STEEP APPROACH SELECTED IRS ATTITUDE MODE SELECTED OBSTACLE AWARENESS ENABLED OBSTACLE AWARENESS DISABLED ALTERNATE MODE 4B REVERSAL SELECTED ALTERNATE DISPLAY TYPE X SELECTED e TERRAIN DISPLAY TYPE XX SELECTED RUNWAY AWARENESS ENABLED RUNWAY AWARENESS ENABLE SET RCD ENABLE SELECTED APPROACH MONITOR ENABLED APPROACH MONITOR INHIBITED FLAPS MONITOR ENABLED ALTIMETER MONITOR ENABLED e LONG LANDING ENABLED AIRSPEED LOW INHIBITED ALTIMETER MONITOR INHIBITED PRESS TO CONTINUE If the switch is not pressed self test will be terminated 4 2 5 Level 6 Self Test Discrete Input Test NOTE The GPWS FAIL WINDSHEAR FAIL and TERRAIN FAIL amber lamps will be illuminated during the Lev
34. PRODUCTION Release 31 Mar 2014 09 24 08 MST Printed on 25 Jun 2014 APPLICATION TITLE SHEET DASH NO NEXT ASSY USED ON INDEX SHEET NO 501 69000940 TITLE SHEET INCLUDES REVISION DESCRIPTION 1 69000941 TABLE OF CONTENTS 2 69000942 DOCUMENT 4 REVISIONS ALL SHEETS ARE SAME REVISION STATUS DATE Release per 0215541 27 MAR 2014 G Ma Added section 14 7 Airspeed Low issue on 69000940 101 and 69000942 See AeroPDM 151 for additional approvals Added section 14 8 Caution and Warning visual alerts during Self Test This document is an unpublished work Copyright 2014 Honeywell International Inc All rights reserved Honeywell Proprietary This document and all information and expression contained herein are the property of Honeywell International Inc are loaned in confidence and may not in whole or in part be used duplicated or disclosed for any purpose without prior written permission of Honeywell International Inc Typed signatures constitute approval Actual CAD Prepared Drawing Using MSWord Software signatures on file at Honeywell in Redmond WA Not to be manually altered CONTRACT NO PRECIOUS METAL Honeywell International Inc un INDICATOR CODE WA 98073 9701 ell A DRAWN eee SE EGPWS P N 6900094x ENGR Jim Mulkins 2013 10 14 MFG is s _ CAGE CODE DWG NO REV avo I a 97896 05690004051 c
35. ata and outputs 6 2 Environmental The environmental qualification for both the 115 VAC and the 28 VDC units are shown below Table 5 1 1 DO 160G Environmental Qualification Form for 115 VAC MKV A Nomenclature MKV A Enhanced Ground Proximity Warning System EGPWS Type Model Part Number 115 VAC MKV A PNs TSO TSO C92c C117a C151c 69000940 8 6900942 NUMBERS Manufactures Specification and or Other Applicable Specification Honeywell International Inc Address Address Revision amp Change Number of Rev New Date Tested 9 2012 thru 7 2013 DO 160G CAGE CODE 97896 SCALE NONE SIZE A DWG NO PDS69000940 501 REV C SHEET 12 HIF 1472R6 1 CONDITIONS SECTON DESCRIPTION OF TESTS CONDUCTED Temperature and Altitude Low Temperature High Temperature In Flight Loss of Cooling Altitude Decompression Overpressure 4 0 4 5 1 amp 4 5 2 4 5 3 amp 4 5 4 4 5 5 Equipment tested to Category A2 modified F2 Ground Survival Low Temperature 55C Low Operating Temperature 40C Ground Survival High Temperature 85C High Operating Temperature 70C In Flight Loss of Cooling Equipment Tested to Category X Not Applicable Equipment Tested to Category F2 55 000 ft Equipment Tested to Category A2 8 000 ft to 55 000 ft in 15 seconds Equipment Tested to Category A2 Absolute pressure 170kPa 15 000 ft Temperature Variation Equipment Tested to Category A 10C minute Humidi
36. cB 11 2 seat Li 213 Static Air Temperature TR ARINC 429 Channel 11 8A HIGH Speed ARINC 429 Channel 4 FN A f B 88 B WXR HAZ BUS LOW Speed A 12A EA 1 Label I MCP BUS B DAE TOM ARINC 429 Channel 12 9 LOW Speed eL 034 ILS Select B 80 B DAA BUS 2 LOW Speed A Lae m EFIS BUS 1 B 108 48 712 Dict worst Diay Mose Lp 278 cete Md 2 WR Ono Bes F RE Sts te ace E E 429 Channel 13 ARINC429Channel6 au 0 zz A HIGH Speed See Prov Rate 8 B IRS BUS 2 LOW Speed A 110608 331 Longitudinal Acceleration EE 23 Nama Ailton DAA BUS 1 B 11D B 12 erten E f ARINC 429 Channel 14 A 1 LOW Speed ARINC 429 Channel 7 25 Comte oped PU 212 baronett hate 1 B AIR DATA BUS 2 LOW Speed A TACHA o nase pe DSWC BUS 1 B 12D 241 siersraerArge Erie f ARINC 429 Channel 15 EE HIGH Speed ARING429Channel8 120 tale Fre Bi nen quee eae te fas LU B FMCBUS2 HIGH Speed A 13 000 GPS BUS 1 B 13BE B 196 Tn ARINC 429 Channel 16 SJ 172 Gra Spud 5 ARINC 429Channel18 Beas mr o LM f LOW Speed 22 5D B EFIS BUS 2 Speed AE I x Ren on ec Si oi ono NC B 6D g ude f ARINC 429 Channel 17
37. com Staco php Mid Continent http www mcico com TAWS CNBC1F25D2AA A4 htmI MN 9402D0065F24 Ameri King http ameri king com Northern Airborne http www northernairborne com pdfs install Ops SM53 RGT Install Ops 804 0400 pdf 11 0 Electrical Interface 11 1 Output Discrete Diode Isolation It is recommended that output discretes that are connected as program pin terminations be pulled up to at least 12 VDC or must be diode isolated See Figure A 3 for an example of the program pin diode isolation wiring 11 2 Terrain Display Interface Retrofit Terrain Display wiring must meet the Weather Radar display manufacturer s requirements including termination ARINC 429 control bus wiring must be twisted shielded pair cable ARINC 453 picture bus wiring must meet the following requirements Cable length must be 300 feet 91 4 meters or less Wire to Wire capacitance must not exceed 10 nF total Shielded twisted pair with not less than one twist per inch Impedance of 70 78 ohms 10 at I MHz Recommended sources PIC Wire PN D620224 EMTEQ PN D07802 100 11 2 1 Switching Relays In some installations a relay is used to switch the display input between the weather radar input and the EGPWS Terrain input Examples of the terrain display switching relay implementation are shown in Figure A 2 11 3 Analog Interfaces The analog ports are shown in Figure A 4 Analog ports 1 and 2 have an input impedance of 90K ohms Analog ports 3 and 4 are
38. considered high impedance ports and have a nominal input impedance of 2 41M ohms 11 4 Cabling and Grounding Wire size and lengths of power return chassis ground and shield pigtails are shown in Figure A 5 This diagram is an example Pertinent aircraft manuals and wiring diagrams should be followed CAGE CODE 97896 SCALE NONE SIZE DWG NO PDS69000940 501 REV C SHEET 28 HIF 1472R6 1 12 0 External Position Source The MKV A reguires external sources to provide horizontal position vertical position velocity and vertical rate information 12 1 Horizontal Position Source External GPS interfaced to the EGPWS must meet the performance reguirements of TSO C129a or any revision of TSO C145 TSO C146 or TSO C196 Aircraft operating under 14 121 may be configured to operate solely a non GNSS position source 12 2 Vertical Position Source Vertical position may come from a barometric source such as an altimeter or air data computer or from a geometric source such as GNSS The MKV A also reguires a radio altimeter vertical position source External vertical position sources must meet minimum performance requirements of the applicable document as listed below Barometric Altitude TSO C10b or TSO C106 Vertical Velocity TSO C8 Radio altitude TSO C87 or ETSO 2C87 or DO 155 GNSS Minimum vertical accuracy meeting DO 229D section 2 2 3 3 4 CAGE CODE 97896 SCALE NONE SIZE DWG NO PDS69000940 501 REV C SHEET
39. d indicator nomenclature is example only and may vary according to the specific aircraft installation me ee d 11 12 13 CAGE CODE HIF 1472R6 1 Verify that all instruments are turned on Turn off source s of GPS position signals Verify that the RAAS INOP amber lamp is illuminated Press the RAAS INHB INOP switch so that the INHIB white indicator is illuminated Verify the RAAS INOP amber lamp is extinguished Move the lamp test switch to the DIM position Verify all segments of the annunciator switch dim along with the rest of the instruments Move the lamp test switch to the BRIGHT position Verify all segments of the annunciator switch fully illuminate along with the rest of the instruments Press the RAAS INHB INOP switch so that the INHIB white indicator extinguishes Verify the RAAS INOP amber lamp is illuminated Return the GPS position source s back to normal Verify the RAAS INOP amber lamp is extinguished 97896 SCALE NONE SIZE DWG NO PDS69000940 501 REV C SHEET 45
40. de 2 alert algorithm In addition this envelope modification happens only if the TSO C151c Look ahead TA WS algorithms are active with high quality terrain data in the area of the aircraft and with very accurate vertical and horizontal position Therefore the aircraft is provided protection by the TAWS algorithms as well as the reduced Mode 2 alert envelope 5 1 2 Mode 1 GPWS Alert Envelope Raise lower cutoff from 10 feet to 130 feet TSO C151c requires performance to TSO C92c and RTCA DO 161A Minimum Performance Standards Airborne Ground Proximity Warning Equipment dated May 27 1976 Therefore the following deviation applies to TSO C151c as it applies to GPWS modes of operation The EGPWS will deviate from this standard in that under specific conditions the EGPWS will increase the cut off floor of the Mode 1 alert envelope from 10 feet to 130 feet The reason for this deviation is to allow aircraft to perform allowed steep approaches to specific airports For example London City airport in England is known to be a problematic location This change will allow configured aircraft to land using steep approaches without nuisance alerts Honeywell has shown to the FAA that the implementation of this change provides an equivalent level of safety In particular the implementation includes the following e The flight crew must activate a dedicated Steep Approach switch in the flight deck e When selected the switch will have a
41. e Category Version GPWS Bank Angle Callout 101 See Product Specification Customer Requested Advisory Alert This option enabled via program pin APD OSS provides an aural advisory for excessive bank angles V1 Callout VI callout option is enabled by program pin APD OSS Provides aural output based on an ARINC 429 discrete input to the EGPWS Engine Fail Callout Engine Fail callout option is enabled by program pin APD OSS Provides aural output based on an ARINC 429 discrete input to the EGPWS Autopilot Disconnect Alert Boeing The Autopilot disconnect alert is enabled by program pin APD OSS and provides an aural alert if the autopilot is unexpectedly disconnected based on an ARINC 429 discrete input to the EGPWS The aural message is Autopilot Autopilot AutoTilt This feature is an output from the EGPWC that can be used by compatible weather radars to assist in automatically calculating the optimum tilt angles for a scanning weather radar antenna 101 101 101 See Product Specification See specific aircraft interface details in ICD See Product Specification Customer Reguested Advisory Alert Customer Reguested Advisory Alert Speed Brake Alert Alerts flight crew of incorrect speedbrake position with respect to current airplane configuration Low Airspeed Monitor 737NG An Airspeed Low Airspeed Low aural alert is issued when the aircraft airspeed decreases to below 70 of
42. e basis for EGPWS certification are DO 161A DO 178B DO 200A TSO C92c TSO C117a TSO C151c AC 25 11A AC 25 12 AC 25 23 AC 25 1309 1A AC 120 40 AC 120 41 14 CFR 25 1301 and 25 1309 Table 7 1 Software Level Criticalities lists the components functions failure category and associated software level for the EGPWS Application CSCI Table 7 1 Software Level Criticalities Component EA Failure Category Software Level Shared Functions Utilities 8 Voice Data DO 178B Level C Operating System File System Current Value Table Configuration Data Non Volatile Memory Monitoring Task Monitor DO 178B Level C Functions Built In Test Self Test controller and Level 1 go no go Output Processing Ground Proximity Warning Major Advisories Mode 6 RAAS Windshear Network Based ARINC 615 Minor DO 178B Level D Data Loadin ARINC 615A Maintenance Self Test Levels 2 through 6 Minor DO 178B Level D Functions CMC CFDS Flight History Keyboard Monitor Debug Diagnostic Network Stack No Safety Effect DO 178B Level E Deos Supplied Debugger Status Monitor Telnet Server FTP Server There is a small portion of the ARINC 615 615A dataloader that responds to basic queries and the initial dataload request There is another small portion that verifies the load results These portions are DO 178B Level C with a failure category of Major Debug Diagnostic component is deactivated in revenue flight CAGE CODE 9789
43. e the 69000942 151 installed The Low Airspeed software defect is resolved in Application Software version 02 and later 14 8 Terrain Awareness Caution and Warning visual alerts during Self Test Installation Note For installations that do not have the Terrain Caution lamp configured which are currently limited to Boeing 737 aircraft types when the self test is executed the Terrain Warning and Terrain Caution 429 output bits are not being set and therefore are not being displayed on the ND This issue is specific to the Terrain Awareness Caution and Warning visual alerts during Self Test and is limited to the following Boeing aircraft types 737 600 Integrated 737 700 Integrated 737 800 Integrated 737 700IGW Integrated 737 NG Integrated and 737 800 Integrated MMA P 8A CAGE CODE HIF 1472R6 1 97896 SCALE NONE SIZE DWG NO PDS69000940 501 REV C SHEET 32 Appendix A Sample Wiring Diagrams The figures that are included in this section are examples of EGPWS interface wiring Pin connections for each specific aircraft type are listed in Appendix of the ICD CAGE CODE 97896 SCALE NONE SIZE A DWG NO PDS69000940 501 REV SHEET 33 HIF 1472R6 1
44. eadphone jack 3 0 SOFTWARE APD AND RCD VERIFICATION With PC connected launch the BOSS program and run present status PS to verify If a PC with BOSS software is not available the part numbers can also be verified through the Level 3 Self Test 1 Verify that the correct application software is loaded 2 Verify that the correct RCD is loaded if applicable 3 Verify that the correct APD is loaded if applicable 4 0 EGPWS SYSTEM SELF TEST The EGPWC Self Test is divided into 6 levels as noted below Level 1 Go No Go Test Level 2 Current Faults Level 3 EGPWS Configuration Level 4 Fault History Level 5 Warning History Level 6 Discrete Input test 4 1 Self Test Initiation Self Test is initiated by pressing the PRESS TO SELF TEST button on the LRU front panel or from a GPWS TEST switch in the cockpit as applicable In the procedure below wherever reference is made to GPWS TEST switch either the PRESS TO SELF TEST button on the LRU front panel or the GPWS TEST switch in the cockpit can be used A Short Level 1 Self Test is a Go No Go test for the system and is initiated by pressing the TEST switch for less than 2 seconds A Long Level 1Self Test combines the short Go No Go test with the enunciation of the entire EGPWS audio menu programmed for the aircraft A Long Level 1 Self Test is initiated by pressing and holding the TEST switch for more than 2 seconds NOTE The Self Test aural volume is 6 dB lower than the warning
45. ection guide is listed in the Reference Drawings Documents table in section 3 0 of this document CAGE CODE 97896 HIF 1472R6 1 SCALE NONE SIZE DWG NO PD569000940 501 REV C SHEET 11 6 0 COMPUTER DESIGN 6 1 Computer Input Output The following table summarizes the type and quantity of I O available with all versions of the EGPWC A front panel self test switch audio jack and status LEDs are also provided for maintenance and fault isolation The primary processing 15 accomplished with a PowerPC SC8378 microprocessor RS 422 inputs Multiplexed with an ARINC 429 receiver Ground activated input discretes 28VDC activated input discretes Program pin inputs used to select configuration and optional features Audio outputs 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 Rear connector Ethernet interface Front connector USB interface for dataloading Front connector Ethernet interface for ARINC 615A dataloading Discrete outputs Drivers for lamps EFIS EICAS discrete inputs or external display relay control 3 9 6 1 Front connector Ethernet interface for maintenance troubleshooting and engineering and production testing This interface allows for access and control of internal EGPWS d
46. el 6 Self Test The Level 6 Self Test provides enunciation of changes to discrete inputs 1 Press the GPWS TEST to start the Level 1 Self Test 2 Press the GPWS TEST switch to cancel the Level 1 Self Test and start the Level 2 Self Test 3 When you hear the message Press to continue press the GPWS TEST switch to start the Level 3 Self Test 4 Press the GPWS TEST switch for 5 seconds to cancel the Level 3 Self Test 5 When you hear the message Press to continue press the GPWS TEST switch to start the Level 4 Self Test 6 Press the GPWS TEST switch for 5 seconds to cancel the Level 4 Self Test 7 When you hear the message Press to continue press the GPWS TEST switch to start the Level 5 Self Test 8 Press the GPWS TEST switch for 5 seconds to cancel the Level 5 Self Test 9 When you hear the message Press to continue press the GPWS TEST switch to start the Level 6 Self Test 10 You will hear Discrete Input Test Press to Cancel repeated every 60 seconds 11 Select the RAAS INHIB switch 12 The enunciations RUNWAY AWARENESS INHIBIT and APPROACH MONITOR INHIBIT should be heard 13 Deselect the RAAS INHIBIT switch CAGE CODE 97896 SCALE NONE SIZE A DWG NO PDS69000940 501 REV C SHEET 43 HIF 1472R6 1 14 15 16 17 18 19 20 21 232 23 24 25 26 27 The enunciations RUNWAY AWARENESS NOT INHIBIT and APPROACH MONITOR NOT INHIBIT should
47. eness Caution Caution Taxiway Caution Taxiway if aircraft is not aligned with a runway just before landing These functions and features are described in Honeywell document 060 4564 001 Product Description SmartRunway SmartLanding Functions of the Enhanced Ground Proximity Warning System Approach Monitor Note 1 Landing Flaps Not Set Advisory in air Provides the flight crew with awareness advisory Flaps Flaps if landing flaps not set on approach Excessive Speed Advisory in air Provides the flight crew with awareness advisory Too Fast if aircraft speed is too fast on approach Excessive Approach Angle Advisory in air Provides the flight crew with awareness advisory Too High if aircraft approach angle is too steep Unstabilized Approach Caution in air Provides the flight crew with awareness Caution Unstable if aircraft has not been stabilized on approach These functions and features are described in Honeywell document 060 4564 001 Product Description SmartRunway SmartLanding Functions of the Enhanced Ground Proximity Warning System Takeoff Flap Monitor Note 1 Incorrect Takeoff Flap Caution on ground Provides the flight crew with awareness Caution Flaps Flaps if an improper flap setting is detected when the aircraft is lined up on a runway in advance of takeoff These functions and features are described in Honeywell document 060 4564 001 Product Description Smar
48. ent to GPWS The EGPWS provides ground proximity warnings in accordance with RTCA DO 161A As part of this functionality there is an enhancement that has been implemented on specific aircraft types that support a tactical mode of operation To support tactical operations on these specific aircraft types the basic Air Transport modes 1 2 3 4 and 6 can be disabled and replaced with altered modes performance curves to prevent nuisance alerts during tactical operations The use of Tactical Modes performance curves can only be performed on specific aircraft types and while a dedicated input discrete configured as part of the aircraft type is selected by the pilot If an aircraft type is selected that includes Tactical Modes ensure that these modes are appropriate for the aircraft operations and that appropriate airworthiness approval is granted CAGE CODE HIF 1472R6 1 97896 SCALE NONE SIZE DWG NO PDS69000940 501 REV C SHEET 8 5 3 Non TSO Functions The MKV A EGPWS includes functions that are not covered by a TSO approved minimum performance standard These functions are considered as non TSO functions These added non TSO functions do not affect or interfere with any required minimum performance standard of the MKV A and do not violate any of its limitations The following chart lists the non TSO functions that are integrated in the MKV A EGPWS Related TSO Non TSO Functions SW Comment Functional Releas
49. ge bus shield return is TRA 45a chassis ground pin 22 J1 3 is 75 ohm terminated return J1 2 is an un terminated return 2 ARINC429 Range bus shield retum is MFRD chassis ground pin J1 2 42 9 is a 75 ohm terminated retum 12 3915 an un terminated retum 7 428VDC ARINC429 Range bus shield retum is GNS XLs chassis ground pin J101 X4 JI01 G6 is a 5 ohm terminated retum 2101 0515 an un lerminated retum ac 4 The ARINC429 Range bus and KCPB Video Bus for Universal 640 and EFL890R KCPB Video EN are program selectable See the applicable Universal Insalaton Manual for detail 30 EST Terrain Display sc HI E sp 11 ARINC 429 Range Figure A 3 Example EGPWS Outputs to Display Indicator Alert Lamps and Inhibit Switches CAGE CODE 97896 HIF 1472R6 1 SCALE NONE SIZE A DWG NO PDS69000940 501 REV C SHEET 36 Clockwise CW Increasing ACA 10 0 REF Signal out H Signal out ARINC 552 or ALT 50 Radio Altimeterf1 1 VALIDITY ARINC 552 or ALT 50 Radio Altimeterf2 VALIDITY E 5 Glideslopest1 GS 1 VALIDITY ILS SELECT 1 547 Glideslope 2 _ GS 2 VALIDITY i ILS SELECT 2 547 Glideslope 1 ILS SELECT 1 GS 1 VALIDITY ARINC 547 Localizer 41 LOC 1 VALIDITY R
50. gram Pin Common PPCom GS Cancel Lamp DOUTLI GPWC Alert Lamp DOUTL2 GPWC Waring Lamp DOUTL3 Windshear Caution Lamp DOUTL4 Windshear Warning Lamp 000115 Audio On Discrete 00015 Terrain Displayable 1 DOUTLT Terrain Display Discrete 1 DOUTLB Terrain Display Discrete 2 000119 Terrain Displayable 2 DOUTL10 GPWS Self Test DINPLB Glideslope Cancel DINPLI1 Terrain Select 1 DINPL15 Terrain Select 2 DINPLIG Temein amp TCFImhibit pineL13 GPWSNS Monitor DMON1 Terrain Not Available DMON2 A Left ARINC 429 Range Bus Left KCPB Terrain Display Right KCPB Terrain Display Right ARINC 429 Range Bus BP 4D 14D 8 8B 5A 15c 15A 15B 15D 3D 7B 9D 148 10 108 1c 1D PROGRAM PIN CONFIGURATIONS Aircraft Type PILOT s PANEL CoPILOT s PANEL Altitude Callout Menu Laana j se e Audio Menu LAS Terrain Display Type 50 1 x 108 Peaks Mode Enabled 1 EET pe Say ME Obstacles Awareness Enabled me 07 00 a PULLUP RED puLtup RED m i 2 pound MOM GPWS ST EU MOM GPWSSD 24 Ne NIA see
51. gram pins that select the aircraft type must be strapped to the appropriate connections These three program pins are TP 10A PPCNF1 TP 10B PPCNF2 and TP 10C PPCNF3 MP 4D PPCNF4 is currently a spare but this pin must be strapped to chassis ground to ensure that a program pin open wire fault is not reported See ICD Appendix D 1 for the program pin strapping AII existing wires that are connected to MP 3A must be disconnected and re connected to chassis ground In the legacy MK V installation MP 3A provides the Program Pin Common connection which was connected to aircraft ground In the MKV A MP 3A is used as a discrete monitor output when an APD or OSS is used CAGE CODE 97896 SCALE NONE SIZE A DWG NO PDS69000940 501 REV C SHEET 24 HIF 1472R6 1 9 0 Feature and Option Selection The MKV A EGPWS provides a set of default features that are defined by Aircraft Type The functionality of many ofthese features may be tailored to suit customer preferences by appropriate program pin strapping or by defining the option selection via the APD Refer to the Product Specification for the MKV A EGPWS for more information on the functionality features and options Refer to the Interface Control Document for the MKV A EGPWS for configuration details of each aircraft type 10 0 Cockpit Annunciators 10 1 1 Lamp Drivers The EGPWC supports two types of Ground Open discrete outputs used to signal various discrete conditions Monitor Discre
52. he Alternate Glideslope Cancel feature requires that there be a cockpit annunciation that the cancel is in effect This can be done using the Glideslope Cancel Discrete Output of the EGPWC The Glideslope Cancel Discrete Output activates when the Mode 5 Glideslope message has been cancelled by cockpit switch 10 1 5 Windshear Lamp Driver Discrete Outputs The Mode 7 Reactive Windshear detection warning red caution amber and INOP Lamp Driver discrete outputs are defined by the Interface Control Document Aircraft Type Output Discrete Definitions table 10 1 6 Terrain Obstacle Lamp Driver Discrete Outputs The Terrain Obstacle warning red caution amber inhibit override and INOP Not Available Lamp Driver discrete outputs are defined by the Interface Control Document Aircraft Type Output Discrete Definitions table 10 1 7 Terrain Display Switching and Terrain Displayable Discrete Outputs The EGPWC produces two discrete outputs for controlling the terrain display They can be used either to control picture bus switching relay s or connected directly to the symbol generators For some installations the EGPWC produces two Terrain Displayable discrete outputs for controlling the display of the Terrain Mode annunciation lamps One discrete is used for the Captain s terrain display mode annunciation and one for the F O s terrain display mode annunciation For each pilots side if the EFIS is in a mode which will support Terrain d
53. he LED will remain illuminated and the status will be indicated by the LED color as described in the table below More information on the LRU Status LEDs can be found in the Line Maintenance Manual COMPUTER STATUS LED COLOR INDICATION Not illuminated Not powered Green Powered No faults Red Powered Internal fault CAGE CODE 97896 SCALE NONE SIZE A DWG NO PDS69000940 501 REV C SHEET 30 HIF 1472R6 1 14 0 Installation Limitations 14 1 TSO C92c Installation Note TSO C92c e reguires the manufacturer to provide the following note to each person receiving for use one or more articles manufactured under this TSO The conditions and tests required for TSO approval of this article are minimum performance standards It is the responsibility of those desiring to install this article on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards The article may be installed only if installation of the article is approved by the Administrator 14 2 TSO C117a Installation Note TSO C117a i requires the manufacturer to provide the following note to each person receiving for use one or more articles manufactured under this TSO The conditions and tests required for TSO approval of this article are minimum performance standards It is the responsibility of those desiring to install this article either on or within a specific type of
54. he terrain display Start the Level 2 Self Test by pressing the GPWS TEST switch to start the Level 1 Self Test Once the Level 1 Self Test begins press and hold the GPWS TEST switch for less than 2 seconds This will cancel the Level 1 Self Test and start the Level 2 Self Test Verify the following voice messages are enunciated e CURRENT FAULTS e GPWS COMPUTER OK e EXTERNAL FAULTS e RADIO ALTIMETER 1 WIRING FAULT MODE 1 INOP MODE 2 INOP MODE 3 INOP MODE 4 INOP MODE 5 INOP MODE 6 INOP 97896 SCALE NONE SIZE A DWG NO PDS69000940 501 REV C SHEET 44 10 11 12 13 14 15 WINDSHEAR INOP e TERRAIN CLEARANCE FLOOR INOP e GPW e PRESS TO CONTINUE Close the 28 VDC circuit breaker labeled Rad Alt located in the R H forward overhead C B panel Verify the GPWS FAIL WINDSHEAR FAIL and RAAS INOP lamps are off Verify the visual RAAS INOP message is removed from the terrain display Start the Level 2 Self Test by pressing the GPWS TEST switch to start the Level 1 Self Test Once the Level 1 Self Test begins press and hold the GPWS TEST switch for less than 2 seconds This will cancel the Level 1 Self Test and start the Level 2 Self Test Verify the following voice messages are enunciated e CURRENT FAULTS e NO FAULTS PRESS TO CONTINUE 6 0 RAAS Inhibit Test This test section should be accomplished if RAAS is enabled in this installation The switch an
55. ing Induced Transient Susceptibility Lightning Direct Effects 23 0 Icing 24 0 Equipment Tested to Category A3J3L3 A3 Pin Injection Transient Susceptibility WF3 600V 24A WF 4 300V 60A J3 Cable Bundle Single and Multiple Stroke Transient Susceptibility WF1 300V 600A first stroke and 150V 150A Subsequent strokes WF3 600V 120A first stroke and 300V 60A Subsequent strokes L3 Cable Bundle Multiple Burst Transient Susceptibility WF3 360V 6A 1 MHz and 10 MHz Equipment Tested to Category X Not Applicable Equipment Tested to Category X Not Applicable Electrostatic Discharge 25 0 Equipment Tested to Category A Fire Flammability 26 0 Equipment Tested to Category C By Analysis CAGE CODE 97896 SCALE NONE SIZE DWG NO PDS69000940 501 REV C SHEET HIF 1472R6 1 Table 5 1 2 DO 160G Environmental Qualification Form for 28 VDC MKV A Nomenclature MKV A Enhanced Ground Proximity Warning System EGPWS Type Model Part Number 28 VDC MKV A PN TSO TSO C92c C117a C151c 69000941 NUMBERS Manufactures Specification and or Other Applicable Specification Manufacturer Honeywell International Inc Address Revision 8 Change Number of Rev New Date Tested 9 2012 thru 7 2013 DO 160G CONDITIONS SECTON DESCRIPTION OF TESTS CONDUCTED Temperature and Altitude 4 0 Equipment tested to Category F2 F2 Low Temperature 4 5 1 amp 4 5 2 Ground Survival
56. ing below the transition altitude SW Comment Release Version These functions and features are described in Honeywell document 060 4564 001 Product Description SmartRunway SmartLanding Functions of the Enhanced Ground Proximity Warning System 1 These functions are sold under the sales package name of SmartRunway and or SmartLanding but are referred to in cockpit switches and annunciations as RAAS Runway Awareness and Advisory System 2 During some high speed approaches some Long Landing Distance Remaining callouts may be omitted For a full explanation of this functionality refer to the Product Description SmartRunway SmartLanding Functions of the Enhanced Ground Proximity Warning System 5 3 1 SmartRunway SmartLanding Functions The SmartRunway and SmartLanding packages are a group of functions collectively known as the Runway Awareness amp Advisory System RAAS These functions provide alerts for taxiway takeoff and landing short runway takeoff and landing takeoff with incorrect flap configuration unstabilized approach long landing and mis set altimeter These functions have configurable values that can be selected by the operator The selected values are controlled by a configuration file that is loaded into the EGPWC The definition and creation of this configuration file is described in the RCD Selection Guide for the EGPWS Runway Awareness and Advisory System RAAS The RCD sel
57. isplay the Terrain display function is valid and the Terrain display has been selected either via manual selection or auto pop up when applicable then the discrete will be set active so that the Terrain Mode annunciation lamp is illuminated For some installations the EGPWC produces two Displayable discrete outputs for controlling display mode annunciation lamps One discrete is used for the Captain s display mode annunciation and one for the F O s display mode annunciation Each output is routed through the picture bus switching relay to drive either TERR mode annunciation if terrain is displayed or WXR mode annunciation if the WXR R T is on displayed or not 10 1 8 RAAS Monitor Discrete Output For some installations a dedicated discrete output is provided as a RAAS monitor which is activated when RAAS is inoperative 10 1 9 Indicator Control Format Table Recommended indicator nomenclature color and location 1s listed in the table below Indicator Control Color Recommended Location Function Required Indicators and Controls gt gt gt gt gt Lamp Format Type Lamp Format is defined by the Aircraft Type Configuration Data table 2 GPWS or PULL UP warning alerts PULL UP HED In Pilot Primary Field of View including Terrain amp Obstacle warnings BELOW BELOW G S or GPWS RAAS G S AMBER In Pilot Primary Field of View caution alerts including Terrain amp Obstacle cautions CAGE CODE 97896 SC
58. ize 1 Lower Plug Power Pins 404 4127 002 208270 2 031 1303 000 8660 249 Insertion Extraction Tool 91066 3 Crimp Tool M22520 1 01 with positioned M22520 1 02 AMP Coaxicon Lower Plug Ground Pin 404 4127 003 208273 2 031 1308 000 8660 250 Insertion Extraction Tool 445147 1 Crimp Tool M22520 1 01 with positioned M22520 1 11 AMP Coaxicon 2 Middle Plug VO 120 404 4127 004 208262 3 030 2259 000 8660 202 Insertion Extraction Tool Pe 91066 1 mom Crimp Tool M22520 2 01 with positioned M22520 2 23 AMP Coaxicon 6 5 5 Weight The weight of the EGPWC tray and connector is listed in the table below Weight 6 00 Ibs 6 25 Ibs 6 00 Ibs 0 85 Ibs 0 45 Ibs 6 5 6 Aircraft Mounting Aircraft mounting is per ARINC 600 6 Vibration isolation or shock mounting is not required The mounting tray can be ordered from Honeywell or other suppliers The table below lists supplier information Supplier Part No Contact Info Honeywell 600 4697 001 http www honeywell com sites aero Avionics Servicesl htm AEI http www aeisinc com ARINC Standard Mounting Trays Barry Controls http www barrycontrols com products product cfm cid 13 Carlisle http www carlisleit com product arinc 600 trays EMTEQ http www emteq com equipment mounting trays php Cooling shall be per ARINC 600 6 and ARINC 404A convection cooling No forced air cooling is required for specified system performance over the envi
59. ndshear will activate the warning lamp output red For Lamp Format Type 2 configurations only messages containing the word Pull Up will activate the warning lamp output red All other messages except Windshear will activate the alert lamp output amber Note the Mode 6 does not activate any lamp outputs only voices 10 1 3 Lamp Format Reversal For those Aircraft Types defined as using Lamp Format Type 1 in the Interface Control Document Configuration Data table dedicated Below Glideslope annunciation the Lamp Format Type 2 can be optionally selected via PPCNF12 Lamp Format Reversal This option changes the Below Glideslope annunciation both the Lamp Driver Discrete Output and the ARINC 429 label 274 bit 12 to be activated for all non Pull Up annunciations and the warning Discrete Output both the Lamp Driver Discrete Output and the ARINC 429 label 274 bit 13 to be activated for Pull Up annunciations only CAGE CODE 97896 SCALE NONE SIZE A DWG NO PDS69000940 501 REV SHEET 25 HIF 1472R6 1 In addition if the Terrain or Obstacle caution discrete outputs are defined in the Aircraft Type of the Interface Control Document to activate the GPWC warning lamp this option will move those annunciations to the GPWC alert lamp discrete output Lamp Format 2 Selected will be reported during the Level 3 Self Test and in the Present Status output 10 1 4 Glideslope Cancel Discrete Output Use of t
60. nen 1 0 GENERAL CAGE CODE 97896 SCALE NONE SIZE DWG NO PDS69000940 501 REV SHEET 3 HIF 1472R6 1 000000000000000000000000000000000000000000000000000 26 o00000000000000000000 26 o000000000000000000000 28 o00000000000000000000 30 o00000000000000000000 3 1 o000000000000000000 3 1 o000000000000000000 3 1 o00000000000000000000 32 o00000000000000000000 39 2 0 3 0 4 0 4 1 4 2 4 2 1 4 2 2 4 2 3 4 2 4 4 2 5 5 0 5 1 6 0 CAGE CODE SOFTWARE APD AND RCD VERIFICATION EGPWS SYSTEM SELF TEST SELF TEST INITIATION G SELF TEST LEVEL 1 LONG SELF TEST 39 LEVEL 1 SELF TEST LEVEL 2 SELF TEST CURRENT FAULTS LEVEL 3 SELF TEST SYSTEM CONFIGURATION LEVEL 6 SELF TEST DISCRETE INPUT TEST 43 RADIO ALTIMETER INTERFACE TEST 44 RAAS INHIBIT TEST M 49 e000000000000000000000 40 o00000000000000000 41 97896 SCALE NONE SIZE DWG NO PDS69000940 501 REV C SHEET 4 HIF 1472R6 1 1 0 INTRODUCTION The purpose of this document 15 to provide guidance information and instructions to assist the installer with the design of the installation for the MKV A EGPWC Enhanced Ground Proximity Warning Computer The MKV A EGPWC with one of the part numbers listed below is the computer
61. ontrol the configuration options through program pin strapping The second method for controlling the configuration options is through the use of an Aircraft Personality Database APD or Option Selection Software OSS For details on selection of the aircraft type and program pin wiring refer to Appendix D in the ICD document no SYS69000940 700 8 1 Retaining the Pin Program Strapping to Define Configuration Options Ifa MKV A EGPWS is being installed as a replacement for EGPWS and there are no changes that are being made to any of the configuration option selections then the MK V A can be installed with no wiring changes The MK V can be removed and the MKV A simply plugged into the existing installation 8 2 Using the APD or OSS to Define Configuration Options The Aircraft Personality Database APD and Option Selection Software OSS are configuration files that are loaded into the unit to control the selection and activation of the selectable options Four program pins are used to define the aircraft type while the APD OSS controls the selectable options The APD definition is contained in Appendix B 1 in the ICD The OSS definition is contained in Appendix B 2 in the ICD A User s Manual for the APD generation tool exists and is referenced in Section 3 0 Wiring changes to an existing MK V installation are required if an APD or OSS is used When using an APD or OSS all existing program pin wires must be disconnected The pro
62. ower Input Equipment Tested to Category ZXI Z DC Powered Equipment X DC Current Ripple Test Not Applicable DC Inrush Current Test Voltage Spike Equipment Tested to Category A Equipment Tested to Category Z Equipment Tested to Category CC Radio Frequency Susceptibility 20 0 Equipment Tested to Category R Radio Frequency Emission 21 0 Equipment Tested to Category M CAGE CODE 97896 SCALE NONE SIZE DWG NO PDS69000940 501 REV C SHEET HIF 1472R6 1 CONDITIONS SECTON DESCRIPTION OF TESTS CONDUCTED Lightning Induced Transient 22 0 Eguipment Tested to Category A3J3L3 Susceptibility Pin Injection Transient Susceptibility WF3 600V 24A WF4 300V 60A 3 Cable Bundle Single and Multiple Stroke Transient Susceptibility WF1 300V 600A first stroke and 150V 150A Subseguent strokes WF3 600V 120A first stroke and 300V 60A Subsequent strokes L3 z Cable Bundle Multiple Burst Transient Susceptibility WF3 9 360V 6A 1 MHz and 10 MHz Lightning Direct Effects 23 0 Equipment Tested to Category X Not Applicable Icing 24 0 Equipment Tested to Category X Not Applicable Electrostatic Discharge 25 0 Equipment Tested to Category A Fire Flammability 26 0 Equipment Tested to Category C By Analysis 6 3 Reliability 6 3 1 Scheduled Maintenance No scheduled maintenance is required 6 3 2 Calibration No calibration is required 6 3 3 MTBF MTBUR MIL HDBK 217 Pl
63. rmation An example of a KCPB display interface capable of VSD is the Honeywell Enhanced GNS XLS More details of the KCPB display interface are provided in the EGPWS Interface Methodology document 14 5 GPS Installation Note Honeywell does not recommend activation of the Altimeter Monitor Below Transition Altitude function in EGPWS connected to Honeywell PXpress based GPS engines KLN 94 GNS XES GNS XLS due to observed prolonged instances of altitude aiding The Altimeter Monitor Below Transition Altitude is inoperative when the GPS source is in altitude aiding mode during which time the crew will observe activation of an installed RAAS INOP annunciation 14 6 Mode 1 GPWS Alert Envelope Raise lower cutoff from 10 feet to 130 feet Installation Note The Mode 1 steep approach mode described in TSO deviations section 5 1 2 has been approved for the A320 family of aircrafts only 14 7 Low Airspeed Monitor on 69000940 101 and 69000942 151 Installation Note A software defect exists in the Low Airspeed alerting logic in the 69000940 101 and 69000942 151 In the case when the Low Airspeed Alert Threshold is ramping upward and moves above Computed Airspeed the Low Airspeed alert is missed The Low Airspeed Monitor should never be activated on the 69000942 151 The MKV A 69000940 1xx is part of the standard production installation for Boeing 737 Aircraft The Low Airspeed Monitor is only enabled on Boeing 737 aircraft which should not hav
64. rmed Terrain Clearance Floor Technical Standard Order Volts Alternating Current Volts Direct Current Vertical Situation Display SCALE NONE SIZE DWG NO PD569000940 501 REV C SHEET 6 5 0 System Performance The EGPWS operational performance will meet as a minimum the reguirements of TSO C92c TSO C117a and TSO C151c Class A The actual performance is defined in the EGPWS Product Specification 5 1 TSO Deviations 5 1 1 Mode 2 GPWS Alert Envelope Lower maximum altitude from 1250 feet to 950 feet TSO C151c requires performance to TSO C92c and RTCA DO 161A Minimum Performance Standards Airborne Ground Proximity Warning Equipment dated May 27 1976 Therefore the following deviation applies to TSO C151c as it applies to GPWS modes of operation The EGPWS will deviate from this standard in that under specific conditions the EGPWS will lower the Mode 2 alert envelope maximum altitude from 1250 feet to 950 The reason for this deviation is that aircraft are being allowed to fly with minimum radar vector altitudes that place the aircraft within 1000 feet AGL of terrain on approach This causes Mode 2 nuisance alerts since the top of the Mode 2 alert envelope is set to 1250 feet Thus this deviation will reduce these nuisance alerts Honeywell has shown to the FAA that the implementation of this change provides an equivalent level of safety In particular the lowering of the Mode 2 alert envelope does not turn off the Mo
65. ronmental conditions specified in section 6 2 of this document If cooling is provided then 2 0 CFM is preferred Per ARINC 600 6 the resultant pressure differential would be 5 3 mm of H20 CAGE CODE 97896 SCALE NONE SIZE DWG NO PDS69000940 501 REV C SHEET 21 HIF 1472R6 1 0 22 HOLE IN MOUNTING FOR 8 32 SCREW ux 2 50 CLEARANCE HOLE A 12 40 EE 9000 3 00 7 5 A IDENT La 2 PL Figure 6 5 6 1 Mounting Tray Outline CAGE CODE HIF 1472R6 1 97896 SCALE NONE SIZE A DWG NO PDS69000940 501 REV C SHEET 22 7 0 Software Design The software criticality has been determined based on the overall functional hazard classification as indicated in the Functional Hazard Assessment FHA for the MKV A Enhanced Ground Proximity Warning System EGPWS SSA69000940 100 Based on the functional hazard assessment the most severe failure category 1s classified as Major In support of the most severe system failure category the CSCIs for the EGPWS are being developed to DO 178B Level C and D standards Maintenance functions like CFDS CMC Flight History and the Keyboard interface will be DO 178B Level D A DO 178B Level E network stack debugger status monitor telnet server and FTP server will be included to support debugging diagnostics and test but these components will be deactivated in revenue flight Th
66. tRunway SmartLanding Functions of the Enhanced Ground Proximity Warning System Long Landing Monitor Note 1 CAGE CODE HIF 1472R6 1 97896 Long Landing Caution in air note 2 Provides the flight crew with awareness Caution of either Long Landing or Deep Landing The message is aircraft configurable This function gives the crew awareness of their position during a landing when the aircraft has not touched down in a nominal distance past the approach threshold or before the runway end Long Landing Distance Remaining Advisory in air note 2 Provides the flight crew with awareness advisory of the current distance from aircraft to runway end SCALE NONE SIZE DWG NO These functions and features are described in Honeywell document 060 4564 001 Product Description SmartRunway SmartLanding Functions of the Enhanced Ground Proximity Warning System PD569000940 501 REV SHEET 10 Related TSO Functional Category Altimeter Monitor Note 1 Notes Non TSO Functions Above Transition Altitude Monitor in air Provides the flight crew with awareness advisory Altimeter Setting if an improper corrected altitude setting is observed while operating above the transition altitude Below Transition Altitude Monitor in air Provides the flight crew with awareness advisory Altimeter Setting if an improper corrected altitude setting is observed while operat
67. te outputs are used to signal failure conditions for the computer or the system Other Lamp Driver outputs are used to signal the warning or mode control status of the EGPW system Short term current limiting protection is provided on all drivers for output shorting conditions The Monitor Discretes are biased ON via lamp power when the EGPWC is not powered while installed Lamp Driver and Monitor Discrete Output Characteristics Max Open Circuit Voltage Potential across Closed switch VDC Max The ground going discrete may be wired together with diode isolation to produce the OR function for the active low state of these signals These outputs can also be used as discrete drivers for other devices alert warning lamp outputs are normally a steady state switch to ground The lamps can be individually programmed to flash as a function of Aircraft Type only see Interface Control Document The flashing outputs operate at a nominal 70 cycles per minute and 50 duty cycle 10 1 2 Lamp Format 1 and 2 Two Lamp Formats are defined as a function of the aircraft type and are modifiable The Lamp Format Type is defined in the Configuration Data table and referenced in the Output Discrete Definitions table of each aircraft type in the Interface Control Document For Lamp Format Type 1 configurations only Mode 5 Below Glideslope message will activate the alert lamp output amber All other messages except Wi
68. the amber band on the PFD speed tape 101 101 See Product Specification See Product Specification Runway Awareness Note 1 Approaching Runway Advisory on ground Provides flight crew with awareness advisory of a proximate runway edge being approached by aircraft during taxi On Runway Advisory on ground Provides flight crew with awareness advisory of which runway aircraft is lined up with Insufficient Runway Length Advisory on ground Provides flight crew with awareness advisory when runway aircraft is lined up with may be insufficient length for takeoff using operator specified lengths Insufficient Runway Length Caution on ground Provides flight crew with awareness Caution Caution Short Runway Short Runway during takeoff roll when runway aircraft is using for takeoff may be insufficient length using operator specified lengths Extended Holding on Runway Advisory on ground Provides flight crew with awareness advisory of extended holding on runway Taxiway Takeoff Advisory on ground Provides flight crew with awareness advisory of excessive taxi speeds or inadvertent take off on a taxiway 101 These functions and features are described in Honeywell document 060 4564 001 Product Description SmartRunway SmartLanding Functions of the Enhanced Ground Proximity Warning System CAGE CODE HIF 1472R6 1 97896 SCALE NONE SIZE DWG NO PD569000940 501 REV
69. the Display EGPWS Red lamps turn on q Voice TERRAIN TERRAIN PULL UP r EGPWS Red lamps turn off EGPWS Amber lamps turn on momentarily t Voice RUNWAY AWARENESS OK FEET or METERS if activated u RAAS FAIL Amber lamp turns on momentarily Voice SINKRATE W Voice PULL UP Voice TERRAIN y Voice PULL UP 7 Voice DON T SINK DON T SINK aa Voice TOO LOW TERRAIN bb Voice TOO LOW GEAR Voice TOO LOW FLAPS dd Voice TOO LOW TERRAIN ee Voice GLIDESLOPE ff Voice BANK ANGLE BANK ANGLE gg Voice MINIMUMS hh Voice TWO HUNDRED voices will depend on configured altitude callout menu ii Voice ONE HUNDRED jj Voice FIVE HUNDRED kk Voice TOO LOW TERRAIN 11 Voice CAUTION TERRAIN long pause CAUTION TERRAIN mm Voice TERRAIN TERRAIN PULL UP CAGE CODE 97896 SCALE NONE SIZE A DWG NO PDS69000940 501 REV C SHEET 40 HIF 1472R6 1 4 2 3 4 2 4 CAGE CODE nn Voice CAUTION OBSTACLE long pause CAUTION OBSTACLE 00 Voice OBSTACLE OBSTACLE PULL UP GPWS WINDSHEAR and TERRAIN FAIL Amber lamps turns off Level 2 Self Test Current Faults NOTE The GPWS FAIL WINDSHEAR FAIL and TERRAIN FAIL amber lamps will be illuminated during the Level 2 Self Test The Level 2 Self Test provides enunciation of all faults existing at the time of the test request 1
70. ty Equipment Tested to Category A Operational Shock and Crash Safety Impulse and Sustained Vibration Equipment Tested to Category B Performed using a ridged vibration fixture without shock mounts Crash Safety Sustained performed in centrifuge using a ridged vibration fixture without shock mounts Equipment Tested to Category R Random and Robust Random Curves C amp C1 Performed using a ridged vibration fixture without shock mounts Explosive Atmosphere Equipment Tested to Category E Water Proofness Equipment Tested to Category X Not Applicable Fluids Susceptibility Equipment Tested to Category X Not Applicable Sand and Dust Fungus 13 0 Salt Fog Test Equipment Tested to Category D Equipment Tested to Category F By Analysis Equipment Tested to Category X Not Applicable Magnetic Effect Equipment Tested to Category Z Power Input Equipment Tested to Category A WF XLPI A WF AC wide frequency 360 Hz to 800 Hz X Ac Harmonic Test Not Applicable L AC Current Modulation Tests P AC Power Factor Test Inrush Current Test Voltage Spike Eguipment Tested to Category A Audio Freguency Susceptibility Induced Signal Susceptibilit 19 0 Radio Freguency Susceptibilit 20 0 Radio Freguency Emission Equipment Tested to Category R WF Equipment Tested to Category CW Equipment Tested to Category R Equipment Tested to Category M Lightn
71. us was used to estimate EGPWC MTBF and MTBUR values for the MKV A beginning three years from the Initial Production Delivery IPD date MTBUR operating IPD Comments operating hours hours MKV A EGPWS 25 000 21 250 2014 Estimates completed prior to 6900094x xxx initial product delivery The EGPWC Failure Modes and Effects Analysis FMEA was developed using SAE ARP5580 Recommended Failure Modes and Effects Analysis FMEA Practices for Non Automobile Applications and in some cases MIL STD 1629 as guidelines The Honeywell part number for the EGPWC FMEA document is shown below The FMEA employs failure estimates based on MIL HDBK 217 Plus UNIT DOCUMENT COMMENTS MKV A EGPWS SSA69000940 301 69000940 xxx 115 VAC Unit 6900094x xxx 69000941 xxx 28 VDC Unit 69000942 xxx 115 VAC Unit CAGE CODE 97896 SCALE NONE SIZE A DWG NO PDS69000940 501 REV C SHEET 15 HIF 1472R6 1 6 4 EGPWC Power Reguirements Input power requirements for both 115 VAC and 28 VDC versions of the MKV EGPWC are provided in the table below End Item Part Number 69000940 xxx 69000942 xxx 6900094 1 xxx EGPWC Input Power Type EGPWC Input Power Requirement With no warning With warning over 8 speaker With heater blanket on Power Maximum Power Factor Recommended EGPWC Power Control Device 115 VAC 400 Hz 21 Watts 24 Watts 28 VDC 20 Watts 23 Watts NA 78 5 Watts max 25 95 VA

TITLE SHEET A 97896

Contents

Download Pdf Manuals

Related Search

Related Contents